DE29501148U1 - Centrifugal separation device - Google Patents

Description

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Device for separating substances by means of centrifugal force

Centrifugal separators with at least one vortex chamber are used to separate and separate solid and/or liquid particles from gaseous or liquid media using centrifugal force. The flow separation process using vortices is very efficient and achieves high separation performance comparable to fabric and electrostatic filters. In addition, there are advantages resulting from the simple structure of the corresponding systems, which result from the assembly of multi-vortex chamber systems from series components. A preferred area of application for such vortex chambers is the separation of the finest dust from gaseous media.

A corresponding vortex chamber can be found in DE 25 38 664 C2. This shows a device for separating the specifically lighter part from a flow of a medium loaded with suspended substances, in which the flow is diverted in a curved channel and partially introduced into a vortex chamber that is tangent to the main flow and is in direct contact with it in the inner curved area of the channel, whereby a centrifugal force field is generated in the vortex chamber, from which the specifically lighter part is sucked out together with the clean gas through two immersion pipes that extend coaxially into the vortex chamber and are mirror images of their center plane into the central area of the vortex chamber, with a further suction pipe being inserted concentrically into each of the immersion pipes in such a way that an annular space is created between the pipes.

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This vortex chamber with coaxially mirror-imaged, short paired immersion tubes acts as a clean gas generator, whereby the clean gas freed of dust is taken from the interior of the vortex chamber through the immersion tubes. The raw gas volume flow to be dedusted is driven with a flat rectangular flow cross-section, curved over a free flow boundary past the vortex in the circular cylindrical vortex housing and partially sucked into the vortex chamber to be converted into clean gas. The other part flows further in a residual raw gas channel and reaches a downstream vortex chamber, where it is concentrated with the dust fraction separated in the first stage. A larger series of vortex chambers connected in series thus produces clean gas step by step, whereas the smaller, highly concentrated residual raw gas volume flow remaining at the end of the row of vortex chambers is fed to a small separator of known design as a direct separator. The cross-sectional shape of the driving volume flow is determined by the shape of the flow inlet, hereinafter referred to as the inlet. In the case of the aforementioned vortex chamber, this inlet has a flat rectangular cross-section and extends over the entire length of the vortex chamber housing.

In addition to the vortex flow and the sink flow caused by the immersion tubes, a so-called secondary flow forms in areas close to the wall, which is directed from the axial center of the vortex chamber wall to the vortex chamber bottoms, then to the immersion tube roots and finally to the immersion tube mouths.

The curvature of the raw gas channel corresponds approximately to that of the vortex cylinder shell. The contact zone between the raw gas and vortex flow extends over a portion of the vortex cylinder circumference and its height with a developed rectangular shape.

Thus, the tangentially arriving flow impulse from the curved raw gas channel area is transferred axially symmetrically with integral driving effect into the vortex by the secondary flow near the wall. The double flow impulse transport begins its meridian path, diverging axially at the raw gas channel outer wall and leads over the vortex chamber floors to the

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Roots of the immersion tubes. From here it drives an axially converging quasi-screw flow closely around the immersion tubes up to their suction openings, where the highest centripetal accelerations develop.

This is the separation zone for the finest particles from the multiphase flow. With each revolution of the screw flow, the specifically heavier particles of the aerodispersion are moved radially further outwards. In the fine separation zone, the raw gas is converted into clean gas, which is then sucked out through the dip tubes. The separated particles are moved radially further outwards through the vortex flow field and thus finally reach the residual raw gas flow by concentrating it. Coarser particles remain in the raw gas volume flow and flow past the vortex chamber, because the curved raw gas channel acts as a coarse separation zone, whereby the centrifugal forces acting on a particle create particle paths that do not follow the secondary flow into the vortex chamber.

The separation process of the vortex chamber takes place in the fine separation zone twice over the length of the immersion pipes in a multi-circuit screw flow. The symmetrical division of the secondary flow, which transports dust and at the same time transports angular momentum radially inwards, into two partial flows reduces their dust load and thus the angular momentum losses caused by concentration. This and the symmetrical formation of the flow in general result in higher rotation speeds and thus greater separation efficiencies in the vortex chamber. The principle applied here, that a screw flow with multiple flow revolutions is used to generate a fluid-physical particle separation force mechanism for high separation performance, will certainly also be a component of future generations of vortex separators. While the continuous phase of the multi-phase flow follows the screw-shaped streamlines to the clean gas extraction openings of the immersion pipes, a particle of the disperse phase is separated with each revolution by the effect of the full centrifugal force from the centripetal acceleration of the

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Screw flow is shifted further radially outwards and finally transported out of the screw flow zone. This cleans the screw flow zone and converts the suction volume flow into clean gas.

The separation principle of the vortex chamber with the screw flow zone means that the separation process is already complete when the flow of the medium to be cleaned passes into the vortex sink flow. In contrast, the prevention of separation of fine and very fine particles observed in cyclones is caused precisely by the fact that these particles cannot be kept away from the sink flow and therefore inevitably end up in the clean gas flow. This is caused by the fact that the drag forces acting on the particles and directed into the sink outweigh the centrifugal forces.

The vortex sink flow that also occurs in the vortex chamber is not used for vortex separation but takes on other functions, namely, on the one hand, it drives the vortex against the drail-consuming internal flow friction and the wall friction through a constant supply of fresh angular momentum from the raw gas flow that peripherally contacts the vortex, and on the other hand, it guides the finest particles to be separated into effective separation zones of the flow field immediately around the immersion tubes. This particle and angular momentum transport also occurs in the cyclone with a certain amount of support from the secondary flow, but in the vortex chamber it is exclusively through this. Due to the special housing shape of the vortex chamber and the favorable use of flow symmetry, a separation-effective quasi-screw flow is generated in the fine separation zone inside the vortex via the secondary flow. This screw flow causes the particle drag force from the sink flow superimposed on the vortex to be rotated by 90° in the axial direction compared to the cyclone, so that centrifugal force and drag force are perpendicular to each other. In the vortex chamber, the full centrifugal force is used for radial particle displacement and separation. The advantage of the symmetrical division of the fine separation zone into two axially mirror-image halves also has an effect: The ring layer thickness of the particles created by the

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The zone filled with screw flow is also halved. This halves the maximum displacement path for particles required to produce clean gas. The particles can be pushed out of the fine separation zone more quickly until clean gas is produced. This improves the separation performance of the vortex chamber.

Because the immersion tubes are arranged in pairs in the vortex chamber, the pressure loss load, which is mainly caused by the rotary flow, is halved. This means that the vortex chamber principle is superior to known centrifugal separation processes, such as the cyclone, from the outset due to lower energy consumption.

In contrast to the vortex chamber separators described above, which always have a residual raw gas flow and are referred to here as vortex separators of the first type, separator solutions have also become known which, based on the vortex chamber described above, convert the entire incoming raw gas volume flow into clean gas. These direct separating devices are referred to here as vortex chamber separators of the second type. In this case, the residual raw gas channel is omitted and is replaced by a dust discharge. A direct separator of this type is known, for example, from DE 28 32 097 C2. This vortex chamber again has a raw gas inlet and a pair of immersion tubes. However, the residual raw gas channel is not present. Instead, the circular cylindrical wall contour of the vortex chamber housing is led to the raw gas inlet. Ring-shaped dust discharge openings are arranged symmetrically to the center plane of the vortex chamber and are located in the rotationally symmetrical flow corners of the vortex chamber. This means that the separated particles are discharged at locations where, in addition to the centripetal accelerations of the vortex field, superimposed centripetal accelerations from the doubly curved secondary flow near the wall occur, which promotes dust discharge. For this purpose, annular gaps are left at the rotationally symmetrical flow corners of the vortex chamber between the circular axial boundaries of the cylinder jacket and the two vortex chamber floors, so that the dust can be discharged axially and rotationally symmetrically through two cross-sections that are as large as possible. On the other hand, excessively large

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Angular gap cross-sections result in angular momentum losses, which lead to reductions in the rotational speeds at the immersion tubes and thus to lower separation performance. Angular momentum losses are caused by the discharge openings at the free flow boundaries that result there, because here, through induction, flow energy is released from the vortex, in this case from its secondary flow close to the wall, to the originally static gas volume of the outside space. As a result, a lower angular momentum is transported further radially inwards to the immersion tubes in the secondary flow that continues from the discharge gaps over the vortex chamber floors.

The separated dust is discharged into two external spaces via the two discharge slots and is thus separated. To facilitate dust discharge, the vortex chamber is preferably arranged with a horizontal axis. The two external spaces are then located horizontally next to the vortex chamber floors. The dust collection bunker is arranged vertically below the external spaces and open to them. The external spaces form the dust transport spaces between the discharge slots and the bunker. The dust is transported by gravity sedimentation.

The theoretical potential vortex is based on the assumption of frictionless flow with constant angular momentum. The distribution of the rotational speed v _ro t over the radius r satisfies the relationship v _ro t * r = const . According to this distribution law of the angular momentum theorem, flow velocities that are too high for smaller radii up to the immersion tube are obtained, which are not achievable in real practice. Real rotational speed distributions ^v rot( ^r ) ' ⁿ cyclones as well as in the vortex chamber can be approximated by the relationship v _ro t * r ^m = const. The exponent m takes into account the reduction in rotational speed due to flow losses.

These angular momentum losses, known as m-losses in vortices used in separation technology, are caused by internal friction of the continuum flow and by its housing wall friction, but also by complex interactions between the flowing continuous and disperse phases. With increasing dust concentration, the value of m decreases more and with it the rotational speed. This does not necessarily mean that the

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The separation efficiency of a centrifugal separator is impaired because as the dust concentration increases, the particles fly closer together. This reduces their flow resistance and the particles are moved collectively more quickly, which promotes the separation process. In addition to being of different sizes, the particles can have different shapes, they can rotate, have different densities, collide with one another and cause wall impacts, which slows down the secondary flow. Such interaction cannot currently be theoretically determined. Such influences on the m value can only be determined empirically. The m value is also an aerodynamic quality measure for the type of housing used to generate a technical vortex and guide its secondary flow. The exponent m is always less than 1. The more m approaches 1 without the influence of dust concentration, the higher the aerodynamic and thus also the separation quality of the flow separator. Vortex chambers with symmetrical guidance of the secondary flow already have high m-values.

Technical vortices with a rotational speed that increases radially inwards according to the distribution v _ro i· * r ^m = const only arise if the flow impulse introduced tangentially at the periphery is transported radially inwards as angular momentum. This means that the respective gas mass to which the impulse adheres must be guided radially inwards, up to the radius r at which the highest rotational speed v _ro t of the separation vortex is intended. This is only possible via suction inside the vortex, in the case of the vortex chamber through the dip tube openings in the central area. If the suction openings were moved axially further outwards towards the vortex chamber floors, this would shorten the screw flow zone and thus reduce the separation performance. In the vortex chamber, the highest rotational speed occurs, as intended, near the outer and inner dip tube walls, strictly speaking near the inner dip tube wall, because this is where the radial angular momentum transport takes place. However, due to their small radial distance from one another and the m-losses that continue to grow radially inwards, the outer and inner rotational speeds on the immersion tube wall are approximately the same. The main part of the immersion tube volume flow moves from the immersion tube openings in a thin ring layer through the immersion tubes due to the strong centrifugal effect.

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A well-integrated rotationally symmetrical suction system on the vortex axis requires the vortex to be superimposed with a sink flow. This is the only way to achieve the accelerated rotation speeds required for separation. If the suction system is switched off in a vortex chamber of the first type, i.e. in a residual raw gas vortex chamber, a rotation speed distribution v _ro t; * r^ = const is formed. The exponent m is equal to m = -1. The flow then rotates like a solid body with a rotation speed that decreases linearly towards the center of rotation to \/ _δγ χ = 0 and cannot be used for separation.

Rotating flow housings for the effective separation of multiphase flows must have certain larger dimensions of the vortex volume relative to the size of the flow inlet. In these housings, the centrally extracted volume flow is supplied exclusively by the secondary flow flowing along the housing walls. Every real friction-affected housing-guided curved flow generates a secondary flow that is determined by the wall friction. The secondary flow determines the separation flow process of the vortex chamber. Without the secondary flow, i.e. without flow friction, the vortex chamber would not function. The paired screw flow on the immersion tubes is a part of the secondary flow field as a separation zone. But the secondary flow also transports the angular momentum required for high separation performance into the interior of the vortex. This angular momentum is therefore transported close to the wall and is thus exposed to increased friction effects, as well as the stronger concentration influence of the dust transported in the relatively thin secondary flow layer. A favourable guidance of the secondary flow is therefore of great importance.

Until vortex chambers with paired immersion tubes and the targeted integration of secondary flow became known, the field of material separation by centrifugal force was dominated by cyclones, which had reached their technical performance limits despite all other advantages. In the specialist literature on cyclone development there are even tips on combating the secondary flow that hinders the cyclone separation process.

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The integration of the secondary flow into the vortex separation process results in an improvement in the separation performance of corresponding vortex chamber separators. A comparison of the separation performance of vortex chamber separators of the first and second type shows that the latter do not yet come close to the performance level of the residual raw gas vortex chambers. High separation performance is achieved in the residual raw gas vortex chamber when the extraction ratio is not chosen to be too high. The extraction ratio is the quotient of the clean gas volume flow divided by the raw gas volume flow of a vortex chamber. This determines the slope of the screw flow line of the quasi-screw flow on the immersion tube and thus the particle residence time in the fine separation zone. Smaller slopes therefore lead to higher separation performance. The transfer of these flow-based relationships to the direct separation vortex chamber leads to a certain geometry requirement on the raw gas inlet gap for high separation performance. The ratio of the inlet gap width b _e to the vortex chamber diameter d must not be too large.

Reference systems with second type of vortex chambers for hot gas dedusting coal-fired boilers in large gardening operations achieved dust removal performance that was well below the clean gas dust concentrations required in the legal requirements of the Technical Instructions for Air Quality Control (TALuft). Hot gas dedusting is particularly problematic because the higher viscosities of the carrier gases (continuous phase) delay the movement of the particles. The vortex chambers achieved the development goals and also proved themselves in rough intermittent operation of these dust removal systems through robust operating behavior. Frequent undershoots of the dew point during heating operation did not affect the function of the vortex chambers. .

During the development of these systems, a problem arose due to the deagglomeration of fly ash particles: the combustion process produces fly ash particles with low strength structures. Depending on the type of combustion design and the type of fuels burned, these strength structures change in a complex way. Due to their brittle structure, fly ash particles are further broken down by flow forces

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and thus the separation process is made more difficult. Despite this deagglomeration effect, the vortex chambers achieved sufficient separation performance.

The deagglomeration effect and its effect on the separation process in vortex chambers can be described as follows: For dust types with no tendency to deagglomerate, a vortex chamber creates a separation characteristic field in which the clean gas concentration c _re j _n decreases approximately hyperbolically _above the inlet velocity v _e and tends towards zero (0) as v e increases. This makes it possible to achieve extremely high separation performance. For dusts with deagglomeration properties, c _re j _n decreases with a weaker hyperbolic character and reaches a minimum, after which c _re j _n increases slightly again as v _e increases further. For such dusts, vortex chambers are optimally designed for an operating point close to the c _re j _n minimum.

A typical sign of a deagglomeration effect in a vortex chamber characteristic map c _re j _n (ve) is the concentration minimum c _re j _n . The flow-physical causes of the deagglomeration effect can be explained by the raw gas inlet of the second type of vortex chamber: In order to achieve a comparable high separation performance with that of the first type of vortex chamber separator, i.e. the residual raw gas vortex chamber, the volume flow load of the immersion tubes must not be too high. This means small relative inlet gap widths b _e /d. A very sharply pronounced radial distribution of the inlet velocity v _e (r) with high velocity gradients dv _e /dr then forms above the inlet gap width b _e . This leads to high shear stresses and thus to the comminution of friable fly ash particles that enter the vortex chamber with a high average velocity v _e . The disadvantageous consequence of this comminution is a reduction in the high separation performance potential of the vortex chambers for dusts consisting of such friable particles.

One solution to keep the shear stress small and the deagglomeration effect within limits could be to set the entry velocity v _e in the vicinity of the c _re j _n minimum. However, this would mean that such vortex chambers would only

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for reduced flow velocities, which would limit the advantageous size reduction with increasing volume flow load of the vortex chambers. The deagglomeration effect in vortex chambers of the second type changes with the type of dust. The characteristic curves c _re j _n (ve) run differently with different and differently pronounced ■ minima c _re j _n . The deagglomeration effect is also influenced by the vortex chamber diameter d as a characteristic measure of the size. As d increases, the inlet deagglomeration decreases, but so does the separation performance, because such high centripetal accelerations cannot be achieved in larger vortex chambers.

The invention is therefore based on the object of avoiding this aforementioned unsatisfactory behavior, in particular of direct-separating vortex chambers, and of designing a vortex chamber of this type in such a way that the performance-inhibiting influence of adverse dust properties such as the deagglomeration effect is limited by special flow control despite the use of usual flow speeds, so that the performance of the vortex chamber is extended into new areas and the vortex chamber is further simplified in such a way that advantages are achieved in its manufacture and in its integration into multi-vortex chamber systems.

This object is achieved in a generic device by the features of claim 1.

Advantageous further developments of the invention are specified in the subclaims.

The essential features of the invention consist of a fluidically improved vortex chamber inlet, which interacts with improved vortex spaces and discharge gaps, whereby these features can be combined with the known liquid injection measure for the purpose of treating particularly problematic dusts. First, the steps and findings leading to the invention are explained.

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The separation flow process of the vortex chamber begins at the inlet. Here, the raw gas volume flow portion of a single vortex chamber of the multi-vortex chamber system selected in the rule is introduced into the vortex chamber. The flow introduction of the multi-phase flow determines its entry impulse, which is introduced tangentially at the vortex periphery. This entry angular momentum is transferred into the symmetrical secondary flow and passed on with it along the housing walls into the screw flow zones around the paired immersion tubes. The highest rotational speed of the vortex flow field reached there determines the separation performance of the vortex chamber, as does the meridian speed of the screw flow as a characteristic size of the volume flow with which the vortex chamber is subjected at a constant entry speed. Too high a volume flow rate V of a single vortex chamber in relation to the average inlet velocity v _e increases the gradient of the quasi-screw flow to such an extent that it makes too few revolutions to the dip tube orifices and therefore fewer particles are pushed out of the fine separation zone. The separation performance then decreases. The rotational and meridional speed of the screw flow zone must work together in a favorable manner in order to achieve the highest possible separation performance. To achieve this, the specific volume flow V/v _e must be optimally selected.

The increase in rotational speed with decreasing radius due to radial angular momentum transport towards the interior of the vortex occurs in real frictional flows approximately according to the relationship v _ro t * r ^m = const with m < 1. The real increase in rotational speed leads to rotational speeds v _{Γ γγδ/δ} at the immersion tube, which decrease as the m value continues to decrease. The m value takes into account all losses caused by the frictional nature of the real flow due to the angular momentum transport on its way radially inwards. Transport losses of angular momentum arise during flow transformations and through the casing-dependent guidance of the layered flow close to the wall, which is subject to the angular momentum to be passed on.

The vortex chamber inlet determines the tangential entry impulse l _e of the flow of the clean gas. In previous vortex chamber separators of the second type, i.e. the direct separating ones, the flow inlet consists of a

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flat rectangular gap with the axial vortex chamber length h as the long side, whereby the relevant gap width b _e is very narrow. These narrow inlet gap widths result from the requirement of smaller specific volume flows V/v _e for higher separation performance of these direct-separating vortex chambers. The incoming multiphase flow, which is more heavily laden with dust, must therefore pass through very narrow gap widths be. Streamlines with strongly changing flow velocities lie very close to one another, because the flow velocity is zero (O) at the radially inner and outer fixed gap boundaries. In the radial direction r, normal to the walls of the flow inlet, the flow must therefore build up with very strong velocity gradients dv _e /dr over a short distance up to the maximum inlet velocity v _emax in the middle of the gap.

This very sharp entry velocity profile v _e (r) leads to high internal friction and wall friction in the entry flow in these vortex chambers. After the entry gap, the flow enters the vortex cylinder as a one-sided, flat rectangular wall jet. Due to the curvature of the wall, high centripeal accelerations act on the jet flow immediately downstream of the gap entry with a radially compressing effect. As a result, the sharp radial velocity profile is still maintained here. But in this wall flow zone of the one-sided free jet downstream of the entry gap, the driving jet flow is quickly slowed down over a short circumferential arc length by the high internal friction and wall friction in the jet flow. Thus, the entry jet is forced to suffer higher angular momentum losses shortly after the entry gap due to friction on the outer wall of the vortex cylinder before this driving flow of the vortex reaches the vortex chamber floors. These are losses in momentum transfer at a constant radius. The amount of the tangentially introduced flow impulse l _e is already reduced to a greater extent at the outer wall of the vortex cylinder to the value of the angular momentum Im < l _e . Here, l _m is the angular momentum of the secondary wall layer flow on the cylinder jacket of the vortex housing. These impulse introduction losses already mean a loss of separation performance.

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The introduction losses for the angular momentum at a constant radius are increased by the influence of the disperse phase on the continuous phase: If one imagines the continuum flow through the narrow inlet gap as being composed of many thin flow layers corresponding to the gas molecules, a particle from the dispersed group of particles flies in several continuum layers with different flow speeds due to its finite size. However, the particle can only fly at one speed and thereby slows down the flow in neighboring layers to lower speeds. This means momentum losses in the drive flow with the further consequence of losses in separation performance. This applies when the particle trajectories and the streamlines of the continuum coincide. However, particles can also move perpendicular to the streamlines, caused by centrifugal force effects when the particle trajectory is curved, by collisions or by wall impacts of particles. If a particle hits the housing wall, its flight speed is slowed down there. If the slowed-down particle then bounces back into flow layers further away from the wall as a result of the impact, the slowed-down particle has a decelerating effect on the continuum flow there. Decelerating influences on the flow are also caused by particle collisions, inertial effects and rotation of particles. These influences of the disperse phase on the continuous phase, which reduce the momentum and separation performance, have a particularly strong effect with narrow inlet gap widths. The particle paths to the wall are very short and all the particles fly there in a densely packed manner.

These angular momentum reducing influences in the multiphase flow close to the wall can also be explained with the theoretical model of an apparent viscosity. For small volume concentrations c _v of particles, the relative viscosity increase (μ ₅ - μ)�Iμ is proportional to c _v . The estimate applies to pure shear flow, ms is the apparent viscosity of the aerodispersion and m is the viscosity of the pure continuous phase. Since the momentum reduction Delta I is proportional to the wall shear stress τ and τ in turn is proportional to μ ₅ , Delta I is proportional to {1 + kc _v ) μ with the proportionality factor k. Thus, an increasing volume concentration of particles has an approximately increasing effect on the momentum loss. It must be clear that these relationships are significantly different.

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become more complex in curved flows, when the particle paths do not coincide with the streamlines, at higher dust concentrations with particle collectives of different grain sizes and different grain shapes as well as particle collisions with each other and with the wall and with different rotations of the particles. Laser measurements on cyclones show that the maximum rotational flow velocity v _ro t,max is greatly affected by the influence of increasing dust concentration: When the dust concentration increases from 0.5 to 60 g/rri3, v _ro t _/rnax is delayed by more than 30% compared to the speed value of the low concentration.

Another effect of the narrow inlet gaps in the vortex chambers that reduces the separation efficiency is caused, as already mentioned, by the high shear stresses on the particles in the inlet flow. Due to the strong velocity gradients of the sharp

The inlet velocity profile causes a jet mill effect which shifts the grain distribution of the raw gas dust into finer grain areas due to _the deagglomeration effect. These disadvantageous grain distribution transformations within the vortex chamber for certain dusts with weaker strength properties result in an effect which reduces the separation performance and which even leads to an increase in the clean gas concentration c _re j _n when the speed of _{v e} increases beyond a certain average critical inlet velocity v e > V 6 ^Jt. In the velocity range v _e > V ₆ ^Jt the jet mill effect outweighs the separation effect due to the excessive refining effect on the grain distribution. The vortex chambers can therefore only be used in the velocity range v _e < v _e/ k _r rt and are designed for v _e approximately equal to v _e/ i< _r jt because the clean gas concentration reaches its minimum there. But even in the subcritical operating range of the vortex chambers, the jet mill effect already exists, increasing from very low inlet speeds with weaker shear stresses up to v^^. Without the jet mill effect, the vortex chamber would already achieve higher separation performance even at lower inlet speeds. This limitation of the operating range of previous vortex chambers also disadvantageously limits their desired

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Reduction in size due to higher volume flow rates in the individual vortex chambers. This means that manufacturing costs cannot be reduced any further at present.

These findings have now led to new types of inlets which are characterised by significantly lower losses and, in conjunction with new types of vortex spaces and discharge gaps, result in a new third type of vortex chamber. These inlets influence the inlet flow they guide in such a way that the flow only has a very low shear load and continues to exert a stronger driving effect on the separation flow. The approach to this therefore begins with the desired radial and axial jet velocity profiles. Gentle velocity profiles with weak velocity gradients must be created in the inlets. This leads to a deviation from the flat rectangular inlet jet. However, in the high-performance separation flow field, a certain upper limit for the specific volume flow loading V / v _e with (V/v _e ) _max must be observed so that the screw flow around the immersion tubes is not adversely affected with regard to the separation performance. This requires a maximum permissible inlet cross-section A _emax depending on the vortex chamber size. For A _e less than or equal to A _emax, the vortex chamber achieves high separation performance. These development conditions lead to thicker entry jets with entry cross-sections ranging from circular to oval to rectangular, whereby the ovals or rectangles must have smaller axial ratios than the extremely flat rectangular entry cross-section of the vortex chambers of the previous type.

In the new rectangular or rectangular-like inlet cross-sections, the long side or the longer side boundary no longer extends over the entire vortex chamber length I as in the previous vortex chambers of the first and second type. In the new inlet with a circular cross-section, its diameter d _e is smaller than I, and in the case of an elliptical inlet cross-section, the long ellipse axis is kept smaller than the vortex chamber length. In principle, in the case of deviations from the circular or regularly polygonal inlet cross-section, the longer cross-sectional extension in one direction is smaller than the

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The vortex chamber length h is maintained. This brings manufacturing advantages with a reduction in manufacturing costs. The new vortex chamber types based on this can be manufactured in a simplified manner from tubes, i.e. semi-finished products. The vortex chamber shells no longer need to be rolled or stamped individually, which increases manufacturing costs but also leads to manufacturing inaccuracies with further cost-increasing adjustment work. Furthermore, the more complicated and therefore more expensive joining work on shells and inlet parts of previous vortex chambers is no longer necessary: In the original inlet types, which extend over the entire vortex chamber length h, the rolled vortex chamber shell is not a continuous circular cylinder shell. As a manufactured part, it is open over a certain circumferential arc for inlet parts to be installed later. As a result, this non-closed cylinder shell has insufficient inherent rigidity. The assembly with the inlet parts requires additional adjustment and straightening work using construction devices. The advantageous new vortex chamber shells are closed circular cylinder or barrel shells with multiple central openings for easy-to-insert inlets and therefore have sufficient inherent rigidity to maintain roundness. Further manufacturing and installation advantages of the new vortex chamber types are discussed in the description of the various designs of the inlets.

In addition to these important economic advantages for reducing manufacturing costs, there are the benefits of improving flow and separation performance with the new inlets. All inlet types have in common thicker jet flows with fuller, gentler

Velocity distributions in the radial and axial direction of the inlet cross-sections. Fullness means larger areas with constant or almost constant velocity distribution, which is only slowed down to zero (0) at the next distance from the wall. Smoothness of the velocity profiles means the weak velocity gradients that predominate in the distributions.

The entry velocity distributions with distinctive rectangular profiles directly at the flow inlet are achieved by short inlet nozzles located in front of the egg inlet cross-section. Important here are the short acceleration distances for the inlet flow up to the narrowest

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Nozzle cross-section, the inlet cross-section. The larger radial jet thickness leads to deeper penetration of the inlet jets along the vortex chamber shell into the vortex housing and thus to an improved driving effect on the separating flow. The deeper penetration of the inlet flow or its greater range can be explained on the one hand by the jet theory and on the other hand by the lower braking effect of the flow walls on the velocity field of the inlet flow. All new inlets generate wall jets in the vortex chamber that are on one side and spread out doubly symmetrically in the axial direction on the concave wall of the vortex housing from the axial vortex chamber center. In doing so, they adapt better to the natural secondary flow so that the inlet flow can be transferred to the secondary flow with less loss. During this transfer, the inlet flow already has contact with the vortex flow radially inwards, which advantageously improves its drive. This optimal integration of inlet flow, secondary flow and vortex flow further improves the high-performance separation flow. The vortex housing can have a cylindrical to barrel-shaped shape with mixed forms in between, such as a double-cone shape.

The inlet cross-sectional shapes, which are concentrated more towards the axial center plane than the axial plane of symmetry of the vortex chamber, result in a central jet entry. The resulting thicker incoming jet has a greater range than the original flat-rectangular inlet jet, whose range is not great due to the very narrow radial jet width. According to jet theory, the range of the jet is the length of the jet core. The jet core is the zone in which the maximum nozzle exit velocity is maintained over a certain distance x _o with flow cross-sections decreasing in the direction of flow. In a simple round free jet that exits into still ambient air, the jet core is a cone, and the jet propagation with the so-called mixing zone also takes place in the shape of a cone, but which widens in the direction of flow. The core length X ₀ of this round jet grows proportionally to the jet diameter d _e , which in this case is the diameter of a circular inlet cross-section. In the old V rbel chambers with flat rectangular entry cross-sections of radially aligned width b _e, quasi-plane beams were used. In the case of plane

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In the case of free jets, the length of the wedge-shaped core increases proportionally b _e . However, in the case of vortex chambers, there are wall jets that are attached to one side. Their ranges X ₀ are doubled compared to free jets. The increase in X ₀ for round and flat jets, which is proportional to the jet diameter d _e or the jet width b _{e ,} is maintained.

For the same inlet cross-sectional areas in vortex chambers with round and flat jets, d _e assumes values that are approximately 10 times larger than b _e . This means that the jet penetration depth of the round jet is approximately 10 times greater than that of the flat jet. This applies in accordance with the free jet theory mentioned above. However, this mainly only comes into play when the vortex chambers are started up, when the separating flow field is built up. After this unsteady start-up process, the stationary operating state of the separating flow sets in. The inlet flow then enters the fully built-up vortex flow field. From the inlet cross-section, the inlet flow continuing from there to the vortex housing wall must continue to overcome the angular momentum-reducing braking effect caused by wall friction, which also depends on the particle concentration. Radially towards the vortex axis, however, instead of initially encountering predominantly static gas, the inlet flow encounters a vortex flow whose speeds at the free interface to the inlet flow are only imperceptibly lower than the speeds acting there. This is the characteristic of an intentional drag effect of the inlet flow on the vortex flow, which is, however, still driven by the screw flow zone around the immersion tubes. The angular momentum introduced with the inlet flow is transported there via the secondary flow and, reduced by the transport losses, comes into effect as a vortex-driving flow force. The drive mechanism of the vortex chamber flow can be interpreted as a flow between two concentric rotating cylinders. This is a well-known viscous flow form. Here, however, there are no solid differently rotating cylinder walls. The cylinder walls are replaced by differently rotating layer flows of the secondary flow on the vortex chamber shell and around the immersion tubes.

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The new vortex chambers with central flow inlets in relation to their length therefore have thicker inlet jet flows. Since the braking effect due to wall friction can only affect a very thin flow layer in the immediate vicinity of the wall and, on the other hand, with a pronounced stationary vortex flow form, there are only very small speed differences between the inlet flow and the boundary vortex field radially inwards, significantly larger volume areas with maximum speeds remain in the inlet flow zone than was the case with the thin, flat-rectangular inlet flows of the known older vortex chamber designs. The inlet flows with central jet entry therefore influence significantly larger volume areas of the vortex field with higher energy content. The gradual jet flow conversion from thick-flat from the more round to the flat-rectangular cross-sectional shape of the layer flow on the vortex housing shell takes place over larger shell areas compared to the flat-rectangular inlet jets of older designs. This explains the better driving effect through central inlet flows and the higher separation performance that can be achieved.

Further flow and separation advantages of the central, thicker inlet flows result from their better integration into the secondary flow. The thick jets follow the predominantly tangential flow direction they received there after leaving the leading inlet housing due to inertia. They hit the concavely curved vortex housing wall at an angle with a greater jet thickness. This means flow deflections: Tangential streamlines of the inlet flow close to the wall hit the concave wall more quickly and therefore experience weaker deflections when the components are deflected in circular orbits concentric to the circumference of the vortex housing than inlet streamlines further away from the wall, which hit the housing wall later. The size of these deflection angles also increases the additional axial streamline deflection in directions parallel to the vortex axis. As a result, the originally tangential inlet streamlines near the wall and further away from the wall are brought closer together again after their double-curved radial and axial deflections. This deflection process therefore has a beneficial accelerating effect on the free inlet flow. Another

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The advantageous acceleration effect downstream of the inlet cross-section is achieved solely by the curvature of the tangential inlet flow in radial planes. The flow is pressed against the vortex casing wall in a radial direction by centrifugal action and is thus accelerated by free jet contraction. These acceleration effects when the tangential inlet flow is transferred into the vortex casing secondary flow generate advantageous driving effects of the vortex through the rotating outer layer flow.

The radial and axial multiple curvatures of the tangential and centrally entering inlet flow produce streamlines that are favorably adapted to the natural secondary flow of the jacket. This advantage in turn increases the separation performance by improving the vortex drive. Such favorable streamline adaptation of the inlet flow to the secondary flow of the vortex cylinder jacket is not present in the previous vortex chambers with a flat rectangular inlet jet flowing in over the entire length of the vortex chamber: the natural secondary flow on the cylinder jacket has increasing axial velocity components with increasing axial distance from the flow symmetry plane of the vortex chamber. In superposition with its circumferential velocity components, this results in streamlines of the secondary flow that run obliquely to the vortex axis. In contrast, the flat rectangular inlet flow of the older type occurs as a parallel flow in the circumferential direction, i.e. perpendicular to the vortex axis. This means that the streamlines of the inlet flow cross with those of the secondary flow, particularly from the secondary flow area, which comes from upstream of the inlet and, after passing the inlet cross-section, lies radially inwards over the inlet flow. The streamlines crossing obliquely in this flow contact zone cause drive impulse losses and generate turbulence, which is transported with the secondary flow into the screw flow zone around the immersion tubes and reduces the fine separation there. Furthermore, the crossing of streamlines in the area of the inlet cross-section generates high shear stresses on the incoming particles, which have a negative effect on the separation performance. The new inlet flows prevent all of these disadvantages of unfavorable inlet adjustments to the vortex and secondary flow field.

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The improved drive effects of the new vortex chamber inlets described here with lower inlet impulse conversion losses and angular momentum transport losses lead to improved m-values of the rotary flow v _rot * r ^m = const . This means that the new vortex chambers can be supplied with higher specific volume flows V / v _e . This has a beneficial effect on the size of the system and the manufacturing costs.

The common flow and separation advantages described for all new inlet types are supplemented by the favorable velocity profiles with low shear stresses on the particles that are also created with these inlet flows. This advantageously extends the operating range of the vortex chambers to higher inlet velocities. This enables even higher separation performance and even further reductions in size and manufacturing costs.

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The invention is illustrated by means of drawings and explained in more detail below. They show

Fig. 1 a circular cylindrical vortex chamber, with an inlet of partially axial length,

Fig. 2 shows in perspective the flow conditions of the vortex chamber according to Fig. 1,

Fig. 3 the vortex chamber according to Fig. 2 schematically in longitudinal section,

Fig. 4 perspective view of the inlet according to Fig. 1,

Fig. 5 a cross section through the vortex chamber according to Fig. 1,

Fig. 6 an inlet with rounded rectangular cross-section,

Fig. 7 a cross-section through a vortex chamber with an inlet according to Fig. 6,

Fig. 8 shows a schematic view of a pipe inlet, Fig. 9 shows another design of a pipe inlet, Fig. 10 shows another design of a pipe inlet,

Fig. 11 a cross-section through a vortex chamber with inlet according to Figs. 8 to 10,

Fig. 12 a vortex chamber with several pipe inlets, Fig. 13 a pipe inlet according to Fig. 12 as a single part, Fig. 14 the pipe inlets according to Fig. 12 in a parallel arrangement,

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Fig. 15 the pipe inlets according to Fig. 12 in divergent arrangement,

Fig. 16 a cross-section through a vortex chamber with pipe inlets distributed around the circumference,

Fig. 17 a pipe inlet with integrated flow guide bed,

Fig. 18 a view of the pipe inlet according to Fig. 17 with the swirl chamber casing unrolled,

Fig. 19 different inlet cross-sections according to Fig. 18, Fig. 20 a cross-sectional structure according to Fig. 18 with overflow,

Fig. 21 a cross-section through a vortex chamber with a pipe inlet having an acceleration section,

Fig. 22 a pipe inlet in the form of a flat nozzle, Fig. 23 the pipe inlet according to Fig. 22 in a draft representation, Fig. 24 the pipe inlet according to Fig. 22 in an adapted form,

Fig. 25 a part of a vortex chamber jacket with the pipe inlet according to Fig. 24,

Fig. 26 the vortex chamber shell according to Fig. 25 with a cutout,

Fig. 27 perspective view of a developed vortex chamber shell with an additional pipe inlet,

Fig. 28 shows the pipe inlet according to Fig. 27 in a perspective view in a curved form, Fig. 29 shows the pipe inlet according to Fig. 28 in the inserted state,

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Fig. 30 perspective view of a pipe inlet with guided acceleration,

Fig. 31 a cross-section through a vortex chamber with the pipe inlet according to Fig. 30,

Fig. 32 the pipe inlet according to Fig. 30 with streamlines,

Fig. 33 a pipe inlet with straight inlet guide,

Fig. 34 the pipe inlet according to Fig. 33 in draft representation,

Fig. 35 the pipe inlet according to Fig. 33 with a vortex chamber membrane!,

Fig. 36 an inlet nozzle,

Fig. 37 a retracted inlet,

Fig. 38 the inlet according to Fig. 37 in design representation with streamlines,

Fig. 39 an embodiment of the inlet according to Fig. 37,

Fig. 40 a retracted inlet formed from a semicircular profile,

Fig. 41 a retracted inlet formed from a U-profile,

Fig. 42 a cross-section through a vortex chamber with inlets according to Figs. 40 and 41,

Fig. 43 a retracted inlet with a pentagonal tongue,

Fig. 44 the inlet according to Fig. 43 with streamlines,

Fig. 45 an embodiment of the inlet according to Fig. 43,

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Fig. 46 another retracted inlet with a tongue, Fig. 47 a design of the inlet according to Fig. 46,

Fig. 48 shows a perspective design representation of an inlet according to Figs. 46 and 47 with streamlines,

Fig. 49 a side view of the inlet according to Fig. 48 with streamlines,

Fig. 50 a further embodiment of a retracted inlet with a tongue,

Fig. 51 a development of the inlet according to Fig. 50, Fig. 52 a vortex chamber with an inlet according to Figure 50,

Fig. 53 an embodiment of the inlet according to Fig. 50 with a split support,

Fig. 53a a developed section for a retracted inlet,

Fig. 54 a retracted inlet, based on the section according to Fig. 53a in draft representation,

Fig. 55 is a sectional view of the inlet according to Fig. 54,

Fig. 56 a retracted inlet with a wedge-shaped inlet bed with a curved bottom surface,

Fig. 57 a cross section through the inlet according to Fig. 56,

Fig. 58 a partial cross-section of a vortex chamber with an inlet according to Fig. 56,

Fig. 59 a section for the production of the inlet according to Fig. 56,

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Fig. 60 a retracted inlet with a wedge-shaped inlet bed and a straight bottom surface,

Fig. 61 a cross section through the inlet according to Fig. 60,

Fig. 62 a partial cross-section of a vortex chamber with an inlet according to Fig. 60,

Fig. 63 a cutout for a retracted inlet with two tongue halves,

Fig. 64 a retracted inlet with two tongue halves, based on the section according to Fig. 63,

Fig. 65 a cross section through the inlet according to Fig. 64,

Fig. 66 an embodiment of the inlet according to Fig. 64 with a folded gap support,

Fig. 67 the gap support according to Fig. 66 as a single part, Fig. 68 a cross section through the inlet according to Fig. 66,

Fig. 69 a retracted inlet with an inlet bed for generating lateral step vortices,

Fig. 70 a step with a vortex,

Fig. 71 the inlet bed of the inlet according to Fig. 69,

Fig. 72 a design of a step with a trailing edge,

Fig. 73 a further embodiment of a step with a trailing edge,

Fig. 74 a design of a step with a leading edge,

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Fig. 75 a design of the inlet according to Fig. 69 with a curved bottom surface,

Fig. 76 a retracted wedge-shaped curved step vortex inlet, Fig. 77 schematically the inlet according to Fig. 76 with streamlines,

Fig. 78 a cross-section through a vortex chamber with an inlet according to Fig. 76,

Fig. 79 a vortex chamber with a circumferential inlet in the form of a spiral casing,

Fig. 80 a central cross-section through the vortex chamber according to Fig. 79, Fig. 81 a further development of an inlet with two partial spirals, Fig. 82 a further development of an inlet with four partial spirals,

Fig. 83 a further development of an inlet with four partial spirals and an outer spiral,

Fig. 84 a further development of an inlet with four partial spirals and a rotationally symmetrical outer casing,

Fig. 85 a further development of an inlet with a rotationally symmetrical outer housing and a multiple arrangement of retracted inlets,

Fig. 86 a longitudinal section through a vortex chamber with an inlet arrangement according to Fig. 85,

Fig. 87 a vortex chamber with a rotationally symmetrical outer casing and an inner cylinder shell,

Fig. 88 a central cross-section through the vortex chamber according to Fig. 87,

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Fig. 89 a further development of the vortex chamber according to Fig. 87 with an annular support plate,

Fig. 90 a further development of the vortex chamber according to Fig. 89 with two symmetrical individual housings,

Fig. 91 a cross-section through a vortex chamber with a rotating spiral casing of circular cross-section,

Fig. 92 is a side view of the spiral casing according to Fig. 91,

Fig. 93 a cross section through a circumferential ring housing of U-shaped cross section,

Fig. 94 a cross section through another circumferential ring housing of U-shaped cross section,

Fig. 95 a vortex chamber with a straight paring slot, Fig. 96 a rear view of the vortex chamber according to Fig. 95, Fig. 97 a side view of the vortex chamber according to Fig. 95,

Fig. 98 perspective view of a vortex chamber with a V-shaped paring slot,

Fig. 99 a rear view of the vortex chamber according to Fig. 98,

Fig. 100 a cross section through a vortex chamber with a peeling slot according to Fig. 98,

Fig. 101 a corner area of the peeling slot according to Fig. 98 in an enlarged view,

Fig. 102 a longitudinal section through a barrel-shaped vortex chamber, ·": :**: :"* :*': ··' ·: : .··.

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Fig. 103 is a side view of the vortex chamber according to Fig. 102,

Fig. 104 a design of the vortex chamber according to Fig. 103 with a flange arranged at the inlet,

Fig. 105 a plan view of a vortex chamber module,

Fig. 106 a main view of a multi-vortex chamber system,

Fig. 107 a side view of the multi-vortex chamber system according to Fig. 106,

Fig. 108 a barrel-shaped vortex chamber with a paring slot,

Fig. 109 a side view of the vortex chamber according to Fig. 108,

Fig. 110 is a main view of a multi-vortex chamber system with vortex chambers according to Fig. 108,

Fig. 111 a horizontal section through the multi-vortex chamber system according to Fig. 110,

Fig. 112 a plan view of a quadruple module formed from barrel-shaped vortex chambers with paring slots,

Fig. 113 a plan view of a quadruple module formed from cylindrical vortex chambers with paring slots,

Fig. 114 a vortex chamber block formed from modules according to Fig. 113,

Fig. 115 the vortex chamber block according to Fig. 114 with a central raw gas line,

Fig. 116 a plan view of a quadruple module formed from cylindrical vortex chambers with axial discharge gaps,

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Fig. 117 a swirl chamber with an injection nozzle, Fig. 118 an enlarged view of the injection nozzle according to Fig. 117 and

Fig. 119 a swirl chamber block with a system of injection nozzles, made up of modules according to Fig. 113.

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In the figures Ftg.1 to 3, a circular cylindrical vortex chamber with a central inlet with a rectangular inlet cross-section is shown in various overall views. Fig. 1 shows the circular cylindrical vortex chamber 1 in a perspective overall view with the circular cylindrical vortex housing 2 broken open. The immersion pipes 3, which are arranged in pairs concentrically to the vortex chamber axis, penetrate the vortex chamber bottoms 4, which are also arranged concentrically, and their cleaning suction openings are axially symmetrical far into the axial center of the vortex chamber. The vortex chamber bottoms have smaller diameters than the vortex housing and thus form annular discharge gaps 6 with the vortex housing. The dust-laden raw gas volume flow enters through the inlet 7 with a rectangular inlet cross-section 8, which is arranged centrally in relation to the longitudinal extension of the vortex chamber. An equal volume flow of clean gas exits through the two outer dip tube ends 9, cleaned of dust in equal volume flow proportions. The dust separated in the vortex chamber by centrifugation is separated on both sides through the two discharge gaps. For this reason, the vortex chamber is preferably installed lying down with a horizontal axis in vortex chamber systems. Lateral dust transport spaces for transporting the separated dust to the bunker are not shown here.

The inlet 7 has a simple design with rectangular flow cross-sections that form a flow guide bed 10 that is open towards the vortex housing to improve the vortex drive, but represents a component that lies outside the circular cylindrical vortex housing boundary. The rectangular flow cross-sections have decreasing radial heights and increasing axial widths in the flow direction. The increase in width is adapted to the local curvature of the natural secondary flow lines in order to improve the driving effect of the inlet flow.

The advantageous separation flow-improving effect of the inlet according to Fig. is illustrated in Fig. 2. The raw gas inlet flow 11 spreads out axially symmetrically through the flow guide bed 10 towards the vortex chamber bottoms 4, whereby the streamline field of the inlet flow corresponds to the natural secondary flow field of the vortex (not shown here).

is largely congruent in order to avoid losses of angular momentum as far as possible. The inlet flow thus forms with the secondary flow on the jacket of the vortex housing a largely rotationally symmetrical driven jacket ring layer flow 12 with a screw flow character, the screw flow lines of which lead axially symmetrically to the two vortex chamber bottoms. There, the jacket ring layer flow is diverted via rotationally symmetrical flow corners 13, here at right angles, and transferred into the two identical driven bottom layer flows 14 with a spiral flow character. At the rotationally symmetrical flow corners 13, the dust discharge of the separated dust transported in the jacket ring layer flow 12 also takes place through the ring-shaped discharge gaps 6 with the support of additional centrifugal effects through the corner flow. In the approximately flat bottom layer flows 14, the deformation impulse from the shroud ring layer flow 12 is transported further on spirally radially inward flow lines to the immersion tube roots 15. There, the bottom layer flows 14 are fed into the two driven

Immersion tube ring layer flows 16 with screw flow characteristics around the immersion tubes. From the immersion tube roots, the immersion tube screw flows lead axially symmetrically to the

Clean gas extraction openings 5 of the immersion tubes 3 near the center of the vortex chamber. Between the driven shroud ring layer flow 12 and the double-symmetric driven immersion tube ring layer flows 16, the quasi-flat vortex flow field 17 driven thereby is formed. In addition to the advantageous, highly separating rotational speed distribution of the vortex flow field 17, a weaker rotational speed distribution with lower speeds is shown to illustrate how a disadvantageous inlet of older vortex chamber types has a weakening effect on the separation flow and thus on the separation performance, in which the flat rectangular inlet gap extended over the entire axial vortex chamber length with a very small gap width. The screw streamline fields of the driven

Immersion tube ring layer flows 16 simultaneously form the two axially symmetric fine separation zones 18. Up to this point in the

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The predominantly fine-grained dust transported by wall layer flows is separated in the fine separation zones. This produces clean gas, which is extracted through the clean gas extraction openings 5 of the immersion pipes 3.

In Fig. 3, the double particle separation process is illustrated in detail in an axial sectional view of the same vortex chamber with the inlet 7 according to Fig. 1,2. The wall layer flow 12, shown here with meridional velocity components, forms the coarse separation zone in addition to its task of transporting angular momentum. Coarser particles that enter with the raw gas flow are transported by the screw flow of the coarse separation zone to the discharge gaps 6 and discharged there without reaching the fine separation zones 18. One side of the fine separation zone is shown here in a simplified manner by a screw flow line, while on the immersion tube opposite, the meridional flow leading to its clean gas extraction opening is shown in connection with the meridional flow in the entire vortex chamber in order to show the path along which the raw gas volume flow in the wall layer flows is guided through the vortex chamber and converted into clean gas. The screw flow of the fine separation zone 18 leads to the advantageous particle separation force mechanism acting on a particle, consisting of two mutually perpendicular forces Fz and Fs. This enables the high-performance separation explained above. The particle centrifugal force Fz displaces the particles in a radial direction. In the axial direction, the particles are displaced by the axially directed particle drag force Fs of the sink flow superimposed on the vortex in the fine separation zone, more strongly in the immediate vicinity of the dip tube and more weakly radially further outwards, because the speed of the sink flow axially directed on the dip tube outside the dip tube boundary layer initially decreases sharply with increasing radius and then asymptotically approaches zero (0). Furthermore, the particle centrifugal force decreases with increasing radius because the centripetal acceleration v increases. _Γ0 {2 /r proportional to r -(2m +1) decreases when the rotational speed v _ro t of the vortex field satisfies the distribution v _ro t * r ^m = const. This is how the complex displacement path of the particles during the separation process is created, which is shown here in the picture for a co-rotating coordinate system approximately up to the radial center of the vortex field. The particles in the fine separation zone 18 up to the finest

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Particles separated by different grain sizes are displaced back into the shroud ring layer flow 12 via such displacement paths and are more likely to be discharged during this second pass, or they must complete several passes before they are discharged because, for example, they are led past the discharge gaps more frequently by complex impact processes at higher dust concentrations in the wall layer flow.

Figs. 4 and 5 show a simple inlet 19 similar to Figs. 1 to 3. In Fig. 4, the inlet is shown in a developed and perspective view to better illustrate its simple design principle: Like the inlet 7 in Figs. 1 to 3, this inlet 19 has the same central rectangular inlet 8 and an external flow guide bed 20 open towards the vortex housing with rectangular

Flow cross-sections 21, and its axially symmetrical lateral boundary walls 22 are curved, as in Fig. 1 to 3, in accordance with the adjacent streamlines of the natural secondary flow. The flow guide bed 20 is, however, modified compared to Fig. 1 to 3 in that the axial spread of the inlet flow in rectangular flow cross-sections 21 does not take place over a partial area of the vortex chamber length, but over the full vortex chamber length up to the vortex chamber floors. In a modification, Fig. 4 also shows that the external flow guide bed 20, after reaching the full vortex chamber length, can be continued over a partial circumferential area with a constant height equal to the vortex chamber length with a radial rectangular width decreasing in the direction of flow.

This creates a variety of design features for favorable inlet integration into the special vortex chamber flow in order to improve its separation performance. Variation options arise, for example, by keeping the areas of the rectangular flow cross-sections 21 constant in the flow direction until the full axial vortex chamber length is reached. In this circumferential area, the inlet flow is then advantageously guided with approximately constant circumferential speed components. A further

A possible variation is to allow the areas of the flow cross sections 21 to decrease in the flow direction in order to

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Inlet flow in the flow guide bed 20 can be conveniently controlled to accelerate in special cases, for example when there are very high dust concentrations and their braking effect on the walls would cause a premature deceleration of the driving inlet flow, reducing the separation efficiency. Variation options also include limiting the radial widths of the rectangular flow cross-sections 21 according to the outer radial boundary 23 of a logarithmic spiral, a spiral of another curve function or a simple spiral approximation using circular arcs. It is advantageous to let the spiral curves or their approximation curves run tangentially into the circumferential circle of the vortex housing. Fig. 5 shows a radial view of the vortex chamber with this new type of inlet 19. The outer radial boundary 23 illustrates the spiral inlet character of these new types of inlets 19 according to Figs. and 5. The illustration of the spiral inlet according to Fig. 5 also applies to the new inlet 7 according to Fig. 1 to 3. Spiral inlet flows have a beneficial effect on the formation of rotational symmetry of the vortices driven by them. This increases the separation performance.

In Figs. 6 and 7, further modifications of the inlets 7 and 19 according to Figs. 1 to 3 and Figs. 4 and 5 are shown. Fig. 6 shows a developed perspective view of a new type of inlet 24 with an inlet cross-section 25 that is formed by a rectangle with rounded corners. With rounded corners, corner flow losses are largely avoided, as they occur, for example, with rectangular flow cross-sections. These flow losses mean losses of angular momentum and ultimately reduce the separation performance. Another special feature of the inlet 24 is that its inlet cross-section 25 is approximately halfway recessed radially inwards into the circular cylindrical vortex housing used here, as is particularly illustrated in Fig. 7 in the radial view. Other radial inlet depths can also be used. By allowing the inlet cross-section 25 two advantageous

Flow guide beds 26 and 27 are formed. The downstream flow guide bed 26 is again designed like a spiral housing and with its axial height spread of the flow cross sections 28 in the flow direction of the natural secondary flow of the driven

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Vortex is favorably adapted as with the flow inlets according to Fig. 1 to The advantageous acceleration control of the inlet flow by changing the flow cross-sections of the flow guide bed 26, in this case the half cross-sections, in the direction of flow is also used here. For the flow-favorable inlet of the flow guide bed 26 at the tangential transition of the inlet spiral curve into the circumferential circle of the vortex housing, the corner roundings, which are circular in the inlet cross-section, are bent more and more flatly in the downstream course of the corner stream, deviating from the circular shape, until they turn into a straight line at the inlet trailing edge 29. The flow guide bed 27 arranged upstream of the inlet cross-section 25 promotes the inlet flow there from the outside by collecting with little loss from the outside and bringing it together in a flow-optimized manner and leading it to the inlet cross-section 25. The flow guide bed 27 shown here as a half-bed is an inlet bed that is let in radially inwards into the circular-cylindrical vortex housing 2, as shown in Fig. 7. The distribution of the radial inlet widths again follows a spiral curve in a flow-optimized manner or, more simply, a spirally set approximate curve as a circular arc. This inner inlet half-bed is also adapted to the natural secondary flow, especially the incoming secondary flow, in a flow-optimized manner. On the other hand, a flow-optimized adaptation to the collection process in the outside is also required in order to optimally design the entire inlet flow of this advantageous partially let in inlet 24 to increase separation performance.

In the series of new inlets with central flow inlets, pipe inlets are among the structurally simplest forms, especially those inlets that can be manufactured from pipes with circular cross-sections as the simplest semi-finished products, whereby inlets with non-circular pipe cross-sections can also be considered with regard to optimal flow conditions. The following Figs. 8 to 16 show various designs of pipe inlets as single inlets and multiple inlets in connection with simple circular cylindrical heat exchanger housings. Fig. 8 shows in a simplified developed perspective representation various parametrically variable design options for a pipe inlet. The pipe inlet 30 has a circular semi-

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recessed inlet cross-section 31 and therefore two flow guide beds. The upstream inner flow guide bed is simply designed as a cut-off pipe section that is cut flush with the vortex housing surface. For the downstream outer flow guide bed 33, all advantageous design options for spiral housing-like design apply, up to the optimal secondary flow adjustment with downstream axial expansion of the flow guide bed, as already described for the previous inlets according to Fig. 1 to 7, with the difference that the flow guide bed here, starting from a semi-circular cross-section, automatically transitions through the strak with circularly rounded flow corners into the straight inlet trailing edge 34 as the surface line of the vortex housing. In order for the corner roundings here in the strak to remain simple circles, the strak end points must coincide with the end points of the inlet trailing edge 34. In this simplified developed representation according to Fig. 8, the strak lines are straight lines. In the real circularly curved cylinder shell of the vortex housing, the straight strak lines turn into curves.

Fig. 9 shows a modification of a pipe inlet 35 with a half-recessed inlet cross-section compared to the pipe inlet 30 according to Fig. 8, again in a simplified developed representation. The downstream flow guide bed 36 is also designed as a cut-off pipe section here to further simplify the construction of the pipe inlet. Due to the spatial simplification of the drawing in Fig. 9, the pipe jacket line 37 drawn there converges at the inlet trailing edge point 38 at an apparently unfavorable angle other than zero (0) with the tangent to the circumference of the vortex housing. This is not the case in the real representation; in Fig. 10 a simple inlet 38 according to Fig. 9 is shown in a real radial view. The inlet 38 is modified in that, instead of an upstream flow guide bed cut flush with the vortex housing surface, it has a pipe section pulled out of the circular cylindrical vortex housing as a pipe guide bed. The outer pipe jacket line 39 runs tangentially into the circumference of the vortex housing at the tangent contact point 40, so that the downstream flow guide bed 41 is integrated as a pipe guide bed in a flow-optimized manner. The short upstream

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Flow guide bed 42 can also be omitted. This creates the structurally simplest pipe inlet 43 according to Fig. 10. This consists of a straight pipe section 45 pulled out tangentially from the vortex housing, which is cut off at the penetration 44 of the vortex housing flush with its inner curved surface.

This extremely simple inlet 43 introduces the raw gas tangentially in a round jet into the simple circular cylindrical vortex housing used here, as is additionally illustrated in the simplified spatial representation in Fig. 11. Without a downstream flow guide bed, the inlet nevertheless achieves an inlet flow field that is advantageously integrated into the vortex field with its natural secondary flow close to the wall through favorable free secondary flow adjustment: This is achieved by the round jet being deflected by the convex inner wall curvature after it enters the vortex housing in such a way that the centrifugal forces in the inlet flow caused by this are directed radially outwards against the vortex housing wall. As a result, the inlet jet is pressed against the vortex housing wall and flattened. However, since it tends to lose its shape imposed by the strict housing guidance in the inlet cross-section due to inertia, the inlet jet is forced into the inlet cross-section by the inlet cross-section.

In order to maintain the flow velocity further into the vortex housing, the jet flow can only react to the flattening by symmetrically deviating to the sides in an axial direction for reasons of continuity. This creates the advantageous multiple streamline curvature in the inlet flow field, which can be adapted to the natural secondary flow in the vortex housing in a largely congruent manner.

The inlet 46 in Fig. 10, which is also structurally very simple, is a modification of the inlet 43. Instead of being made from a straight piece of pipe, this inlet 46 is made from a prefabricated pipe bend. This allows the area enclosed by the penetration curve to be advantageously increased; because in this area close to the inlet, the jet flow is hardly slowed down by wall friction, and this results in larger contact areas of the still energetic fresh inlet flow with the vortex field to be driven. The

· · 9 1

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Flow curvature also offers another advantage, which is particularly effective with thicker entry jets: With a curved entry jet, the incoming vortex flow that meets the jet is not deflected as strongly locally by its displacement effect as with a thicker entry jet. The curved entry jet therefore achieves a better vortex drive.

Using the example of simple straight pipe inlets, advantageous multiple arrangements of inlets on a single vortex chamber are described below, which apply to all possible types of inlets. When influencing the boundary layer on aircraft wings, flow control distributed over many impulse transfer points produces more favorable driving effects on the flow than influencing it from a single point. The aerodynamic quality of the flow control depends on the local arrangements and distance distributions of the influencing points and generally increases with their number and the area of the influencing zone. However, the multiple distribution of flow influencing points leads to increased construction costs. The same applies to the aerodynamic quality of the rotary flow drive of a vortex chamber with multiple arrangements of inlets. The selected simplicity of the individual inlets limits the construction costs. The multiple inlet arrangements are shown in Figs. 12 to 16 shown.

In Fig. 12, a simple inlet group 47 is shown in a parallel triple arrangement of straight pipe inlets. As a structurally very simple individual part of this inlet group, the pipe inlet is shown in perspective in Fig. 13; it is identical to the single inlet 43 shown in radial view in Fig. 10. The inlet flow field 48 in Fig. 12 shows the desired free secondary flow adjustment with the symmetrical axial spreading of the streamlines in the direction of flow. With such group arrangements, even higher m values in the rotational speed distribution v _ro t * r ^m = const can be achieved compared to single inlets and thus even higher rotational flow velocities in the fine separation zone on the immersion pipes. Fig. 14 shows an inlet group 49 with parallel directed outlet jets. In Fig. 15, the same triple arrangement 50 is shown with axially symmetrically spreading

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Main exit directions of the exit jets are shown. By varying the inclination of the jet exit directions of the individual pipe inlets of an inlet group, further improvements in the free secondary flow adjustment can be achieved. Fig. 16 shows that both individual inlets and inlet groups can be arranged distributed over the circumference of the vortex housing with any number of individual inlets to improve the drive and separation performance.

In Figs. 17 to 20, a pipe inlet 51 with a flow guide bed 52 is shown. In Fig. 17, the pipe inlet 51 with the flow guide bed 52 integrated downstream for optimal drive effect is shown in perspective as a single component. For better understanding, the integration of the pipe inlet 51 into the vortex housing shell is only illustrated by drawing the shell circumferential circle 53 in the axial center plane. Fig. 18 shows the pipe inlet 51 with the flow guide bed 52 in a developed view together with part of the vortex housing shell 54, whereby the cross-sectional shape of the guide bed 52 results from folded cross sections, one of which is designated as 56 by way of example. The picture shows: Where it is compatible with the optimal flow guidance through the flow guide bed 52, its lateral boundary contours 55 of the flow cross sections that widen axially symmetrically downstream and flatten radially are guided straight in the development. This results in design and manufacturing advantages. Otherwise, the boundary contours, including the inlet surface lines running between them, are curved twice in the axial and radial directions. The middle surface line 57 is shown in Fig. 17. It lies in the axial plane of symmetry and is therefore only curved once radially. At its inlet point 58 in the surface circumference circle 53, it must preferably run tangentially in a flow-optimized manner. Fig. 19 shows the advantageous cross-sectional distribution in the flow direction from the developed representation according to Fig. 18: The constructive geometrically flow-optimized inlet development begins from a circular cross-section 59. The cross-sectional distribution passes over a semi-circular cross-section 60 without corner roundings 61 into further downstream guide bed cross-sections 62,63 with streamlined roundings 64,65 to the adjacent vortex housing shell. The inlet trailing edge 66

I · · C · ·
» * * · ·
· *

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-see also Fig. 17 -must coincide with a surface line of the vortex housing for the favorable alignment of the inlet housing: Here the inlet trailing edge is shown as a straight line because a simple circular cylinder is chosen for the vortex housing. The cross-sectional distribution shows how the individual guide bed cross-sections widen axially symmetrically in the direction of flow with simple geometric cross-sectional shapes and flatten in the radial direction. Fig. 20 shows a downstream guide bed cross-section 64 in individual representation: In order to simplify its construction, all curves 67,68 are made of circles.

The aerodynamic pipe inlet 51 with integrated flow guide bed 52, developed from a circular cross-section, consists exclusively of cross-sectional shapes with curved cross-sectional contours that are favorably matched to one another. This brings aerodynamic advantages for low-loss cross-sectional conversions of the inlet flow, which in this case begins with a circular cross-section and is radially flattened and axially symmetrically widened downstream. The flow guide bed 52 is designed in such a way that it acts in the sense of a combined guided and free secondary flow adjustment. The inlet flow is guided in the core in the flow guide bed 52 in order to maintain the high core speeds downstream as far as possible. On the sides of the downstream guide bed cross-sections 62,63, the strong circular fillets 64,65 cause a gentle, axially symmetrical, low-loss overflow of the inlet flow onto the vortex housing shell. With this measure, the integral propulsion effect of the aerodynamic inlet can be further improved by increasing the contact area with the vortex.

In Figs. 21 to 26 a simple pipe inlet with guided acceleration control is shown. For cross-section conversions with guided flows in the flow direction, as is the case here with the inlets, it is advantageous to accelerate the inlet flow in the housing-guided inlet part in order to minimize the flow losses due to cross-section conversion. Fig. 21 shows an accelerated pipe inlet 69 in a radial overall view with a

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circular cylindrical vortex housing. This structurally simple pipe inlet is advantageously manufactured simply from a semi-finished product 70 according to Fig. 22, consisting of a circular pipe section that is flattened evenly on one side over its pipe length so that straight surface lines are created. Fig. 23 shows the straight surface lines 71 of the deformed pipe section. The outlet cross-section 72 is smaller in area than the circular inlet cross-section 73 due to the sheet metal forming by means of flattening. The outlet cross-section 72 is also flattened so that a rectangular cross-section with rounded corners is created, which is advantageous in terms of flow technology and can be flattened to different extents in order to set any acceleration conditions for the inlet flow. In the further simple production process, according to Fig. 24, a lost section is separated from the semi-finished product 70 according to the penetration curve 74 with the circular-cylindrical vortex housing in such a way that, according to Fig. 21, a fluidically advantageous tangential run-in of the outer inlet surface line 75 into the circumference 76 of the vortex housing is maintained. According to Fig. 25, this creates an inner initial guide bed 77 for the inlet flow, which is advantageous for the vortex drive and which then spreads out over free secondary flow adjustment to promote drive and separation performance, as has already been described for the simple pipe inlets 43 according to Fig. 10, 11. Fig. 26 shows a casing part 78 of the vortex housing according to Fig. 25 without the associated inlet part in order to illustrate its easy manufacturing insertion into the vortex housing with the simple recess 79.

The pipe inlet according to Fig. 21 to 26 can also be made from prefabricated semi-finished products that have cross-sections other than circular in the prefabrication stage. In Figs. 27 to 29, this is shown for a new type of inlet that is simple to manufacture and that is designed as a tubular closed molded part in the semi-finished product, for example with rectangular cross-sections of constant height and with circular corner roundings with a constant radius that remain constant in the direction of flow. Fig. 27 shows, in a simplified spatial development, the simple design of the tubular semi-finished product 80 in terms of flow and manufacture, whose cross-sections 81 are equally rounded at the corners with

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radially constant width have an axial height distribution, which leads to axisymmetrical side wall curvatures 82 of the inlet 83. This enables advantageous secondary flow adjustment. In accordance with the radial width distribution 84 in the direction of flow, a lost section is separated from the tubular semi-finished product 80, so that a final stage 85 of the inlet according to Fig. 28 is created. In Fig. 29, the inlet joined to the vortex housing shell is shown in perspective.

Fig. 30 to 32 show a new type of aerodynamic pipe inlet with guided acceleration control, which is developed from a circular cross-section via cross-section conversions into rectangles with circularly rounded corners. According to Fig. 30, the flow cross-sections already decrease from the circular cross-section outside the vortex housing, so that the inlet flow is accelerated in a guided manner up to approximately the penetration opening 85. Viewed in the direction of flow, the flow cross-section 86 is already rectangular with rounded flow corners at the beginning of the penetration opening 85. The guided acceleration advantageously takes place in a pipe bend, which flattens radially as the flow bends. This is particularly illustrated in the radial overall view of the vortex chamber according to Fig. 31. This advantageously results in the lowest flow bend losses. The radial flattening of the originally circular flow cross-section also has a beneficial effect on the secondary flow adjustment. The important radial round jet flattening and axially symmetrical jet spread while keeping the flow speed constant over as large a space as possible in core flow areas is already initiated in the closed bend area of the inlet. These flow processes are illustrated in the top view in Fig. Here, the optimal integration of the inlet flow 87 (black flow arrows) into the natural secondary flow 88 to be driven (white flow arrows) is illustrated by the favorable combined guided to free secondary flow adjustment through largely congruent flow fields. The aerodynamic inlet goes downstream after its closed accelerated bend guide section 89 for the flow into the radially inward open and axially symmetrically spreading

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Flow guide bed 90. The flow cross sections in the open flow guide bed are only partial cross sections 91 of the entire inlet flow, so that this flow guide bed increasingly takes on the task of partially guiding the inlet flow downstream. Since the inlet flow is designed with the requirement of keeping the flow speeds constant, the flow continuity in the partial cross sections 91 takes effect in such a way that in the open flow guide bed, flow medium flows in over its entire advantageously large contact area radially inwards to the vortex, largely evenly distributed, with fresh, constant angular momentum from the inlet. The equalization of the secondary flow-adapted introduction into the outer vortex ring layer to be driven is advantageously supported according to Fig. 30 by the outer radial inlet housing limitation 92 in the form of a spiral curve such as a logarithmic spiral or other spirals. According to Fig. 30, 32, this aerodynamic pipe inlet uses another flow-related advantage: the penetration opening 85 is further contracted at its upstream beginning 93, so that in the plan view according to Fig. 32, parts of the inlet are still covered by solid flow walls, decreasing further downstream. This improves the flow guidance properties of the inlet similar to those of an advantageous pipe-like, closed, stricter flow guidance, although the flow cross-sections in this area already partially create open contact surfaces for vortex propulsion. With this advantageous aerodynamic inlet, a gentle start to the introduction of angular momentum into the vortex is achieved while at the same time gently introducing axially symmetrical flow fanning. The entire inlet becomes a largely optimal aerodynamic inlet for high drive performance and separation performance of the vortex chamber due to the integral effect of all the special design measures described here.

While largely preserving the advantageous properties of the aerodynamic pipe inlet according to Fig. 30 to 32, Figs. 33 to 36 show an advantageously simplified design of the related high-performance inlet in terms of manufacturing technology. The simplifications are achieved by using a simpler closed

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accelerated straight inlet guide section 94 was selected according to the radial view in Fig. 33. This is preferably prefabricated as a semi-finished product from a truncated cone of pipe, which is pressed flat on one side according to Fig. 34, here advantageously to a cross-section of zero (0), so that straight surface lines are created. This complete flattening simplifies the manufacturing process in that the lateral roundings decrease linearly with the rounding radius up to the inlet rear edge to zero (0). In the final manufacturing stage, a lost section 95 according to Fig. 33 is then cut off from the semi-finished product in accordance with the radius of curvature of the circular cylindrical vortex housing used here. The use of a truncated cone has the advantage that when flattening, a stronger axially symmetrical cross-sectional spread is achieved in the sense of a favorable secondary flow adjustment than is possible with a straight piece of pipe as the starting molded part. The rear inlet part 96, which was created in this way for low production costs, is shown in Fig. 35 in a top view together with a nozzle-like inlet front part 97 attached to it. The separate representation of this inlet nozzle is shown in Fig. 36 as a non-rotationally symmetrical molded part 97. This design was chosen here for demonstrative purposes to illustrate that a flow-optimized adjustment between the front and rear inlet parts also requires a rotationally asymmetrical front inlet part due to the rotational asymmetry of the rear inlet part, since the transition tangents of both molded parts must then match. In applied flow technology, manufacturing simplifications can often only be carried out by accepting certain flow losses. The design of the inlet front part 97, which is also possible here, as a rotationally symmetrical inlet nozzle, which is simpler to manufacture, leads to partially moderate wall contour kinks for the flow guidance in two opposite side areas of the circular joining point of the two components.

If several vortex chambers in a multi-vortex chamber system are connected in parallel in terms of flow, it is advantageous for flow and manufacturing reasons to distribute the total volume flow of the system via a settling chamber to a large number of similarly designed vortex chambers. In terms of flow, very even volume flow distributions to the individual vortex chambers can be achieved in this way.

· t

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and in terms of construction, a significant cost-saving advantage is created by considerably simplifying the system structure, as the distribution and branching channels for volume flow distribution are eliminated. In these multi-vortex chamber systems with volume flow distribution via calming chambers, each individual vortex chamber draws in its inlet volume flow in an approximately rotationally symmetrical manner from a spatial area of a hemisphere, the more the cross-sectional shape of the intake opening adapts to a shape with a rotationally symmetrical character. This condition is optimally met by a circular cross-section. According to this definition, a square inlet cross-section can also be assigned to spatial intake flow fields with a more rotationally symmetrical character, as can rectangular cross-sections with a smaller aspect ratio, but not the flat rectangular inlet cross-sections of the older vortex chamber generations with aspect ratios of around 40:1 to 60:1. These high aspect ratios lead to quasi-flat intake flow fields upstream of the outer inlet opening, which have an unfavorable effect on the uniform volume flow distribution via settling chambers. In contrast, the spatial intake fields described above have considerable advantages for the uniformization of the volume flow distribution via settling chambers in multi-vortex chamber arrangements.

For the free distribution of volume flow to multi-vortex chamber arrangements connected in parallel via calming chambers without distribution and branching channels, it is advantageous to guide the flow in the calming chambers at a lower speed for loss and distribution reasons and to accelerate it only in the area of the intake flow fields of the same individual vortex chambers. The housing-guided acceleration must advantageously take place over short distances in order to generate the full velocity distributions of almost rectangular shape in the narrowest inlet cross-section, which are advantageous in terms of drive and separation technology, described above. The short acceleration distances of the nozzles required for this at the start of the inlet also have a beneficial effect on the desired laminarization of the inlet flow by reducing turbulence. For these reasons, all new types of vortex chamber inlets can also be equipped with flow-controlled

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upstream inlet nozzles. The upstream nozzles can have different contraction ratios to suit different separation and dust removal tasks and are adapted to the specific design features of the inlet for favorable spatial suction in more or less rotationally symmetrical designs. One embodiment of such a upstream nozzle is shown in Fig. 35 and 36 as already described. Furthermore, these upstream nozzles can be designed in such a way that pipes or flow channels with different cross-sectional shapes can be connected upstream to them. The nozzles can also be adapted to the pipes or channels using special transition pieces. Finally, the pipe or channel connections can also be designed without upstream nozzles at the inlets.

So-called retracted inlets are described below. The complete retraction of the inlet into the vortex housing of the vortex chamber brings significant structural simplifications of the individual vortex chambers and simplifications in assembly as well as easier maintenance.

Multi-vortex chamber systems; because the individual vortex chambers can be easily locked in parallel in perforated walls with narrow multiple hole arrangements made of circular holes for small system construction volumes. The parallel arrangement is preferably carried out in two perforated walls with special fastening devices that can be quickly and easily removed. The vortex chambers can be individually mounted or dismantled at any point on the perforated plates. With retracted inlets integrated into the vortex housing, there is a greater range of variation in different design features, each with special flow and manufacturing advantages, which often lead to compromise solutions for inlet configurations.

In Figs. 37 to 39, a retracted aerodynamic inlet is shown, which has an advantageous combination of several favorable aerodynamic design features. Fig. 37 shows a retracted aerodynamic inlet 98 in a perspective overall view, integrated into a circular cylindrical vortex housing selected here. In Fig. 38, this inlet 98 is shown in skeleton form with excellent intersecting surface lines in order to ensure its shape and integration into the vortex housing for optimal

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drive and separation performance-related flow. Therefore, surface lines in the central flow direction are shown as longitudinal surface lines 99 and surface lines transverse to this are shown as transverse surface lines 100. Fig. 39 shows a slightly modified design of an inlet with a curved inlet trailing edge 101, enlarged for better illustration. The outlet inlet according to Fig. 37, 38 has a straight inlet trailing edge. The special aerodynamic design features are described along the outer flow paths starting in the calming chamber for the single vortex chamber, in compatibility with the simultaneously required favorable internal flow guidance of the vortex chamber with external and internal streamline guides: The secondary flow branching axially symmetrically in the center plane of the vortex chamber in its interior requires an inner bow shape 103 according to Fig. 39 that is favorably adapted to this secondary flow branching for low-loss axial flow division. The incoming secondary flow is also partially pushed radially towards the inside of the vortex. For this reason, the inlet expansion must not be too far radially inwards, as otherwise the advantageous rotational symmetry of the vortex flow will be disturbed too much. The inlet is therefore flattened from the inside while maintaining a rectangular shape.

Inlet cross-section 104 with a smaller aspect ratio, which in turn is required for a thicker inlet jet for better vortex drive and higher separation performance. The inlet jet thickness is advantageously increased by the curved inlet trailing edge 101, so that the inlet jet can penetrate deeply into the vortex in the circumferential direction and can also fan out axially. With these features, the shape of the inlet can be designed in accordance with the requirements for a favorable internal flow. But this also results in favorable design features for the design of the external shape of the retracted inlet: The rectangular inlet cross-section 104 has S-shaped

The lateral boundaries 105 continue upstream in the transverse shell lines 100 with gradual flattening up to the inlet leading edge point 106. The longitudinal shell lines 99 are also slightly curved in an S-shape. In the favorable shell line section with the more evenly curved inlet leading edge 107, this results in an advantageous outer inlet bed 108 for streamlined spatial suction of the inlet flow. The S-shaped curved shell lines have an effect

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also has a loss-reducing effect on the internal flow of the vortex chamber. The spatial suction takes place with little loss via the approximately semicircularly curved inlet leading edge 107 with a subsequent gently rounded transition into the outer inlet bed 108. The circular circumferential lines of the vortex housing help to support the guide. The entire inlet is designed in such a way that the inlet volume flow is taken predominantly from a thicker curved layer directly above the vortex housing shell and guided to the inlet cross-section 104. In this shell-parallel layer guidance of the inlet flow, the inlet trailing edge 101 according to Fig. 39 and 102 according to Fig. 38 can advantageously be designed simply as a sharp flow dividing edge due to the flow-parallel alignment of the wall tangents there. Another advantageous effect of this aerodynamic inlet concept is the guided, favorable secondary flow adjustment that begins in the inlet bed 108, so that the inlet flow immediately after the flow inlet 104 is already approximately congruent with the natural secondary flow of the vortex. This is illustrated by the streamline image in Fig. 38.

Figs. 40 to 42 show variants of drawn-in inlets that have been greatly simplified in terms of production technology. In terms of the evaluation of the flow quality, such simplifications must represent a fluidic compromise solution. Fig. 40 shows a drawn-in inlet that is manufactured in the simplest way from the semi-finished product of a semi-circular profile 109. Other profile cross-sectional shapes can also be used that can develop suitable collection properties in the intake area as well as more favorable flow guidance properties in the inlet bed 110. Fig. 41 shows another example of this: Here, a flatter U-profile 111 is selected as a semi-finished product in the prefabrication stage. The drawn-in profile inlets according to Figs. 40, 41 have special features that are favorable in terms of flow technology: Both inlets are provided with undercut guide bed rear edges 112 and 113. These undercuts bring several fluidic advantages: Firstly, the guide bed lengths are advantageously shortened and the flow-retarding wall friction surfaces are reduced, but the desired minimization of the surface area of the profile guide bed also brings the advantage of reducing special profile-form-related loss zones in which

I · * · ft &diams;&diams;* ft * *»·

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special flow losses can occur, such as corner flow losses due to the U-profile 111 according to Fig. 41. The profile guide bed is advantageously reduced in size so that it just meets the flow-related requirements of the favorable flow collection and the subsequent special flow guidance. Furthermore, the undercut design offers the advantage of a shock-free flow onto the inlet trailing edge 114 according to Fig. 40, 41. With a shock-free flow, the inlet trailing edge is flowed tangentially, in relation to the circumferential circle of the vortex housing. Then no shock losses arise due to flow separation bubbles in the interior of the vortex housing shortly behind the inlet trailing edge. The separation bubbles would generate additional turbulence, which penetrates the vortex flow field with its separation zones with the inlet flow and reduces the separation performance through turbulent diffusion. The inlet trailing edge can advantageously be made sharp simply with a shock-free flow. The advantageous undercut design is most easily described using the overall radial view of the inlet with vortex chamber according to Fig. 42: The flow in the inlet bed 110 is aligned approximately parallel to its lower boundary 115. In Fig. 40, the lower boundary is identical to the lower surface line 116, while the lower boundary in Fig. 41 is formed by the lower boundary plane 117. According to Fig. 42, the projection line 118 of the undercut is now inclined until the circle tangent through its intersection point 119 with the circumferential circle of the vortex housing runs parallel to the lower boundary 115 of the inlet bed. Then, to a good approximation, there is largely shock-free flow at the inlet trailing edge 114.

The following describes recessed inlets in which design features for high aerodynamic quality are combined with features for simple production. However, aerodynamic and production-related features cannot be combined in any way or number. The compatibility of aerodynamic and production-related feature combinations therefore leads to a group of differently designed recessed inlets with higher aerodynamic quality for economical production methods at the same time.

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A corresponding inlet with aerodynamic and manufacturing features combined is shown in Fig. 43 to 45. According to Fig. 43, the main part of the inlet is formed from a pentagonal axially symmetrical tongue 120 , which is simply and more strongly curved radially inwards than the vortex chamber jacket curved in the same direction. The tongue 120 is axially symmetrical to its curved center line 121, which in the picture illustrates the simple tongue curvature and begins at the inlet leading edge 122 with the same tangent as at the vortex housing jacket. For reasons of axial flow symmetry, the inlet leading edge 122 runs parallel to the vortex housing axis and, in the case of the circular cylindrical vortex housing selected here, parallel to its surface lines. In Fig. 44, the inlet is shown without the vortex housing jacket! and the inlet flow is shown by flow arrows on one side to the flow symmetry plane as the axial center plane of the vortex housing. The two upstream side boundaries 123 of the tongue are symmetrically curved through the vortex chamber floors in the sense of a symmetrical pre-fanning of the inlet flow for favorable secondary flow adjustment to the two lateral axial vortex chamber boundaries. The tongue 120 is arranged in a roughly similarly shaped and slightly larger recess 124 in the vortex housing shell according to Fig. Bending the tongue downwards relative to the vortex chamber shell creates the V-shaped, retracted inlet gap 125 radially inwards below the V-shaped inlet trailing edge 126. If the inlet trailing edge 126 has a weaker V-shape, the inlet gap 125 has an almost constant gap width. If the V-shape is more pronounced, the larger gap widths form symmetrically to the axial center plane of the vortex housing. The gap width distribution of the inlet can be advantageously adjusted via the V-shape of the inlet trailing edge 126, but also by different V-shapes of the inlet trailing edge 126 relative to the corresponding V-shaped part 127 of the tongue 120. With these simple manufacturing adjustments of the inlet gap geometry, aerodynamic advantages can be achieved with the favorable secondary flow adjustment of the inlet flow. By bending the tongue 120 downwards relative to the swirl chamber shell, wedge-shaped lateral gaps were also created between the side boundaries 123 and the corresponding side boundaries of the recess 124. These gaps are here

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closed by two axially symmetrically inserted, double-curved wedge-shaped round parts 128, so that according to Fig. 44 an advantageous low-loss overflow of the round parts 128 is made possible with the simultaneous symmetrical flow collection and pre-fanning upstream in front of the inlet gap 125. In Fig. 45 a slightly modified form of the drawn-in inlet according to Fig. 43 is shown: The inlet trailing edge 129 was moved further downstream according to the flow-optimized undercut principle already explained earlier. Its rounded corners 130 serve to advantageously reduce corner losses of the gap flow. The inlet trailing edge moved back by undercutting enables its simple manufacturing design as a sharp leading edge 129 for the flow-optimized peeling off of the gap flow, which is advantageously distributed as a parallel flow in the radial direction.

In Figs. 46 to 49, an extremely simple production-technically drawn-in inlet from the inlet group with aerodynamic and production-technical combination features is shown for high aerodynamic quality of the inlet flow. This inlet is advantageously integrated with the circular-cylindrical vortex housing casing selected here as a one-piece. According to Fig. 46, a recess 131 is cut out of the vortex housing casing, which is designed as a piece of pipe, and is axially symmetrical to the center plane of the vortex housing, approximately in a sickle shape. This forms the tongue 132, which, as already described, is curved radially inwards more strongly than the vortex housing casing, simply and in line with the flow. This creates the approximately sickle-shaped inlet gap 133 for aerodynamically favorable secondary flow adjustment of the inlet flow. The distribution of the radial gap width, which decreases slightly axially outwards and is axially symmetrical to the center plane, can in turn be influenced in a flow-favorable manner by the undercut design of the sharp inlet rear edge 134 with flow-favorable corner roundings 135. Towards the axial center plane, the inlet rear edge 134 and the corresponding tongue rear edge 136 are V-shaped for manufacturing reasons. Fig. 47 to 49 show a modification of the inlet according to Fig. 46, which according to Fig. 47 essentially consists in the fact that the recess 137 has narrow incisions 138 running upstream on the sides, which are approximately parallel to the flow!

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local inlet flow. Through these incisions 138, the tongue is advantageously extended in the direction of flow so that it can be gently and easily bent into the vortex housing. This advantageous tongue curvature is illustrated in Fig. 48 with the skeleton line representation of the inlet. Open wedge-shaped gaps 139 are created at the incisions 138 by bending the tongue downwards. These gaps 139 are left open here for reasons of simplifying production. Fig. 48 shows that the open gaps 139 are advantageously aligned with low losses due to their alignment parallel to the flow: The inner flow 140 in the vortex chamber, shown with a white flow arrow, and the adjacent outer flow 141 in the inlet bed 142, shown with black flow arrows, advantageously run largely parallel to one another in their contact area, so that there is a free flow boundary between them with largely equal flow velocities on both sides of the boundary. These advantageous flow conditions, shown in perspective according to Fig. 48, are illustrated in Fig. 49 in a radial section. Here, in particular, the advantageous effect of the undercut of the tongue on the formation of a shock-free flow onto the sharp inlet trailing edge 134 is illustrated in a streamlined manner.

Figs. 50 to 53 show further manufacturing modifications of the drawn-in sickle-shaped inlet according to Figs. 46 to 49. The modified inlet according to Fig. 50 differs from the initial inlet according to Fig. essentially by a double curvature of the tongue 143. This is illustrated by the skeleton line representations in both images. The double tongue curvature has an advantageous effect on the formation of a largely constant gap width distribution 144 well into the axial lateral corner zones of the inlet bed 145. Furthermore, the formation of a constant gap width distribution is advantageously supported by the undercut 146 of the tongue rear edge 147 compared to the inlet rear edge 148. Fig. 51 shows the simple formation of the inlet sickle in a developed representation, limited by the tongue rear edge 147 and the inlet rear edge 148. Fig. 52 shows the advantageous integration of the retracted sickle-shaped inlet into the entire vortex chamber. The vortex chamber 149 is limited to the outside exclusively in a circular cylinder because the inlet is retracted.

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This makes it easy to lock the vortex chamber in perforated walls, particularly in multi-vortex chamber systems with multiple arrangements of identical series vortex chambers. A modification of the inlet according to Fig. 50 is shown in Fig. 53: Here, a gap support 150 is arranged in the axial inlet center of the inlet gap, which advantageously serves to precisely adjust the gap width. Several gap supports can also be arranged in the inlet gap.

In Figs. 53a to 55, further additional manufacturing modifications of the drawn-in sickle-shaped inlet according to Figs. 46 to 49 are shown. According to the developed representation in Fig. 53a, the special manufacturing features of this sickle inlet consist of two symmetrically arranged narrow incisions 152 extending upstream from the tongue rear edge 151, which, for reasons of minimal flow losses, are advantageously arranged approximately parallel to the local flow near the wall in the inlet bed and can be cut straight or curved. The incisions 152 begin at points 153 which are offset by a certain distance in the axial direction inwards towards the vortex chamber center plane compared to the outer limiting points 154 of the unrolled inlet sickle 155. The directional orientation of the incisions 152 is advantageously such that the symmetrical arrangement of the incisions 152 spreads out in the direction of flow in order to initiate the flow-favorable fanning effect already in the inlet bed 156. The incisions 152 end in two front limiting points 157, the connecting line of which represents the inlet leading edge, from which the tongue is bent into the vortex housing with an advantageous simple curvature in order to form the retracted inlet with the inlet bed 156. The perspective representation of this is illustrated in Fig. 54 with additional skeleton line representation. The connecting lines of the front boundary points 157 with the outer boundary points 154 form the lateral boundaries 159 of the inlet bed 156, which can be straight or curved. From these lateral boundaries 159, the curved side walls 160 are bent into the inlet bed 156. This creates narrow gaps 161 as shown in Fig. 55, which are advantageously aligned in the direction of the local external and internal flows at the inlet, so that only minimal flow losses occur at the free flow boundaries at the gaps 161.

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Figs. 56 to 68 show further additional manufacturing modifications of the drawn-in sickle-shaped inlet according to Figs. 46 to 58. Fig. 56 shows a drawn-in sickle-shaped inlet with a wedge-shaped inlet bed 162 that spreads out in the direction of flow, the side walls 163 of which are advantageously formed from slightly doubly curved conical shell partial surfaces. The base surface 164 is also designed as a doubly curved conical shell partial surface. Fig. 57 illustrates this simple inlet bed construction in axial section with alternating inverted circular arcs as the cross-sectional contour, and Fig. 58 shows the simplicity of the inlet in a radial view. Fig. 59 shows a developed representation of the inlet in a prefabrication stage with the base surface 164 omitted in order to illustrate the advantageously simple manufacturability. The lateral boundaries 165 of the wedge-shaped inlet bed 162 can be designed to be straight or curved in the development. The inlet rear edge 166 is again advantageously designed to be undercut.

Figs. 60 to 62 show a further simplified modification of the inlet according to Figs. 56 to 59, in which the inlet bed according to Fig. 61 is designed with a bottom surface 167 that is straight in axial section. In the actual perspective view according to Fig. 60, the bottom surface is advantageously simply curved, as Fig. 62 also illustrates in radial view. These inlets according to Figs. 56 and 60 in turn enable the already described advantageous low-loss flow over the wedge-shaped lateral boundaries 165. Likewise, the wedge-shaped design of the inlet bed 162 achieves a streamlined pre-fanning of the inlet flow.

Figs. 63 to 65 show a further simplified modification of the inlet according to Figs. 56 to 59. The special manufacturing feature consists, according to the developed representation in Fig. 63, of a narrow straight incision 168 arranged in the axial vortex chamber center plane, through which two axially symmetrical and wedge-shaped lateral boundaries 169 of the inlet bed are created, which run straight or curved in the developed view in order to enable advantageous low-loss overflow. Between the incision 168 and the

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Between the limits 169 there are two tongue halves 170, the trailing edges of which run straight in the direction of the mantle lines of the circular-cylindrical vortex housing. The two straight tongue trailing edges 171 can also be arranged symmetrically in a V shape in order to increase the undercut effect towards the axial vortex chamber center plane. Furthermore, the tongue trailing edges can be designed to be symmetrically curved in order to adapt the inlet flow to the fanning out that continues in the vortex housing in the simplest way possible by undercutting. The tongue halves 170 are bent into the vortex housing in such a way that gently curved flow transitions begin at the lateral inlet limits 169. Further towards the axial center of the vortex chamber, the tongue halves 170 are advantageously simply left flat, as shown in Fig. 64 in perspective view and Fig. 65 in axial section: Bending the tongue halves 170 into the vortex housing creates a wedge-shaped gap 172 between the tongue halves, which is left open in the inlet variant according to Figs. 63 to 65 for reasons of simplicity, since the flow losses caused by this are small. The gap 172 can also be closed with a sheet metal wedge.

Fig. 66 shows a further inlet variant in which the wedge-shaped gap 172 according to Fig. 64 is covered by a simply folded sheet metal support 173, which simultaneously touches the undercut inlet rear edge 174 and thus advantageously serves to adjust the inlet cross-section. Fig. 68 shows an axial section with the inlet cross-section supported by the sheet metal support 173. Fig. 67 shows a perspective individual view of the simple sheet metal support 173.

In Figs. 69 to 78, a special group of drawn-in aerodynamic inlets with wedge-shaped inlet beds is described, in which a symmetrical pair of counter-rotating step vortices is generated at the lateral boundaries of the inlet bed, which have a positive influence on the inlet flow in several respects. This advantageous influence on the inlet flow by step vortices achieves a largely constant surface inlet velocity distribution over the inlet cross-section. This

Velocity distribution favors the main vortex drive in the

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Vortex housing and leads to high volume flow rates through retracted inlets relative to their size. On the other hand, the inlet flow control by step vortices promotes the desired favorable pre-fanning of the flow in the inlet bed and the subsequent axial fanning of the inlet flow in the vortex housing for the favorable secondary flow-integrated main vortex drive. The step vortices are mounted in the inlet bed in such a way that the flow arriving upstream of the inlet bed peripherally touches the step vortices above (seen radially outwards from the vortex chamber axis) and is deflected by the step vortices and led into the inlet bed. A partial volume flow of the inlet flow is drawn by the step vortices on their underside (seen radially inwards from the vortex chamber axis) and fanned out in the desired favorable manner due to the step vortex flow directed axially symmetrically towards the two vortex chamber floors. The partial flow between the two step vortices in the inlet bed senses stable, wedge-shaped free flow boundaries that widen in the direction of flow from the fixed step vortices and is thus also fanned out in a favorable and low-loss manner.

Figs. 69 to 71 show a new type of drawn-in step vortex inlet of the simplest design with rectangular cross-sectional profiles. Fig. 69 shows the overall perspective view of the drawn-in step vortex inlet with the symmetrical step vortices and the inlet flow influenced by them. With the step vortex inlets, according to Fig. 70, there is always an advantageous vortex-influenced overflow of the step-like lateral inlet boundaries 175. The inlet flow 176 close to the wall is guided in a streamlined manner down the step and into the inlet bed by the step vortex 177 located immediately behind the step. Fig. 71 shows the inlet bed 178 in a separate view. The lateral inlet boundaries 175 are designed here as walls with a simple S-shaped curvature that widen in the main flow direction in a wedge-shaped manner.

Figs. 72 to 74 show modifications of the step design for the retracted step vortex inlet according to Figs. 69 to 71. In Fig. 72, the simple rectangular step 179 is replaced by a tangential to the upper step wall

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running outflow plate 180 with a sharpened outflow edge 181. This provides better local stabilization of the step vortex. The sharpening serves to advantageously avoid outflow edge turbulence. Any turbulence introduced into the vortex chamber would have a reducing effect on separation performance. In Fig. 73, the angular space below the outflow edge 181 as shown in Fig. 72 is replaced by a semicircular step vortex bed 182. This avoids corner flow losses of the step vortex guide, which in turn would also generate turbulence. Fig. 74 finally shows the addition of the step vortex bed 182 by a flow-optimized inflow nose 183 with an inflow edge 184, which can be rounded to sharp. The inflow nose is advantageously profiled in such a way that it expands the partially circular stepped vortex bed 182 and, on the other hand, redirects the inlet flow deflected by the stepped vortex with gentle corner rounding 185 in a direction parallel to the bottom surface 186. Fig. 74 therefore represents the lowest-loss design of a stepped vortex guide.

While the drawn-in step vortex inlets with their variants according to Fig. 69 to 74 all use rectangular to rectangular-like main flow cross-sections with simply curved bottom surfaces, which appear as straight lines in the axial section, Fig. 75 shows an additional inlet variant to Fig. 74, the bottom surface 187 of which is bulged radially inwards towards the vortex chamber axis in the axial section, so that this bottom surface 187 is doubly curved overall. Bulged bottom surfaces lead to advantageously larger inlet flow cross-sections with thicker inlet jets.

Figs. 76 to 78 show a drawn-in step vortex inlet with simple rectangular flow cross-sections, in which the two corners facing the vortex chamber axis are circularly rounded for optimal flow. Furthermore, the inlet is advantageously designed with an undercut inlet bed rear edge and also an undercut inlet rear edge as well as with wing-like outflow plates, the outflow edges of which are only curved to one side and increasingly more in the main flow direction. Likewise, the inlet bed widens in the main flow direction in a wedge shape with progressively increasing wall curvatures of the

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axial side boundaries of the inlet bed. This results in a small-volume inlet with high aerodynamic quality that is simple to manufacture. Fig. 76 shows the drawn-in, wedge-shaped, curved step vortex inlet in a perspective overall view. The inlet trailing edge 188 is advantageously undercut in a sickle shape towards the rear downstream and merges with rounded side boundaries 189 into the trailing edges 190 on the wing-like outflow plates 191, which are progressively increasingly curved in the main flow direction. The inlet bed trailing edge 192 is undercut in a sickle shape towards the front upstream. This advantageously reduces the wall surface of the inlet bed to a minimum, so that its favorable guiding properties for the inlet flow are just about retained. Fig. 77 shows a perspective, skeletal representation of the drawn-in step vortex inlet with the symmetrical step vortex pair 194, through whose flow-influencing support the inlet flow 195 is advantageously introduced into the inlet bed 193 in the manner described and is fanned out in such a way that the inlet flow adapts favorably to the edge zones of the natural secondary flow 196 in the vortex housing. This flow-favorable inlet integration into the vortex housing is additionally supported by the two corners 197 of the rectangular inlet flow cross-sections 198 that are rounded radially inwards. Fig. 78 shows this drawn-in step vortex inlet in a radial view. It is shown how the step vortex inlet handles large inlet volume flows with a relatively small size thanks to its advantageously large suction capacity.

The following describes a group of new aerodynamic inlets that run peripherally around the vortex housing, through which the vortex flow is advantageously driven evenly over the entire vortex housing circumference, axially symmetrically, centrally to eccentrically, with favorable integral secondary flow adjustment. This type of continuously rotating vortex drive has a beneficial effect on the rotational symmetry of the driven vortex separation flow and its separation performance.

In Figs. 79 to 84, a new type of rotating aerodynamic inlet of the simplest design is shown with variants. Fig. 79 shows the inlet in axial view and Fig. 80 in radial view. The

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Inlet from a rotating spiral casing 199 with flow inlet 200. The spiral casing has rectangular flow cross-sections, the corners of which can also be advantageously rounded. The rectangular flow cross-sections 201 are open radially inwards to the vortex in the vortex casing 202 with a free flow boundary. Radially between the rotating spiral casing 199 and the vortex casing 202 there is a rotationally symmetrical distribution chamber 203 which has advantageously profiled curved side wall boundaries 204, via which the inlet flow advantageously merges integrally into the local natural secondary flow in a rotationally and axially symmetrical manner, approximately congruent with it. The free flow boundary between the spiral casing 199 with distribution chamber 203 and the vortex casing 202 also forms an advantageously large drive surface for the vortex with the transfer of angular momentum. The rotating spiral housing can also be divided circumferentially into advantageously identical partial spiral housings, each with its own associated flow inlets. Fig. 81 shows a rotationally symmetrical distribution chamber 203 with a double arrangement of identical partial spiral housings 204 and Fig. 82 a corresponding quadruple arrangement. Fig. 83 shows that an additional outer spiral housing 205 can be placed around these partial spiral housing arrangements if, for example, a single external flow inlet is required. In Fig. 84, this outer spiral housing 205 according to Fig. 83 is advantageously replaced by a largely rotationally symmetrical ring housing 206 with a tangential flow inlet 207, which is easier to manufacture and which supports the even distribution of the inlet volume flow to the partial spiral housings 204 due to its advantageous function as a calming chamber with circulating flow.

The rotationally symmetrical ring-shaped calming chamber with a simple tangential flow inlet can, according to the radial representation in Fig. 85, also be used as a volume flow distribution chamber for rotationally symmetrical multiple arrangements of any of the inlets described above, advantageously of the same design. Fig. 86 shows such a rotationally symmetrical multiple arrangement of the same inlets in an axial sectional representation. The multiple partial volume flow fanning out in the vortex housing achieves an advantageous vortex drive effect.

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Figs. 87 to 94 show modifications of vortex chambers with new types of inlets made of rotating spiral casings according to Figs. 79 and 80 or rotationally symmetrical ring casings according to Figs. 84 to 86.

Fig. 87 shows a new type of inlet with a rotationally symmetrical ring housing 208 in an axial section and Fig. 88 shows the corresponding radial section with the simple tangential flow inlet 209 to the ring housing. The ring housing 208 has flow-optimized corner roundings and is covered radially inward by an axially wider cylinder jacket 210 of smaller diameter than the vortex housing cylinder jacket! so that paired symmetrical ring-shaped nozzles 211 are produced with ring-shaped outlet gaps 212 for axially symmetrical flow outlet into the wall layer flow of the natural secondary flow in the vortex housing. The tangential flow inlet 209 according to Fig. 88 provides the necessary swirl introduction into the ring housing 208, from whose two symmetrical ring-shaped outlet gaps the inlet flow then exits with axially symmetrical and circumferential speed components, congruently adapted to the natural secondary flow and driving it. In addition to Figs. 87 and 88, Fig. 89 shows the arrangement of an annular support plate 213 in the axial center plane of the vortex chamber, by which the cylinder jacket 210 is supported and the inlet flow is divided into two symmetrical halves. The resulting connected symmetrical partial housings 214 can also be designed as two symmetrical individual housings 215, which are axially further apart, as shown in Fig. 90. This creates two drive parts for the separating vortex, which can be advantageously arranged at locations that are relevant to the flow.

In Fig. 91 and 92, a new type of inlet with a rotating spiral casing 216 with circular cross sections 217 is shown in axial and radial sections. The spiral casing 216 is circularly delimited on its radial inner side and there merges over the entire circumference into an axially narrower rotationally symmetrical ring casing, which advantageously acts as a flow compensation casing 218 and into which the inlet flow from the spiral casing 216 enters rotationally symmetrically over the entire circumference with the same radial and circumferential speed components. The transitions

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between the spiral casing 216 and the flow compensation casing 218 are rounded for optimal flow, as are the rotationally symmetrical transitions between the flow compensation casing 218 and the circular-cylindrical vortex casing 219. The tangential flow inlet 220 introduces the required swirl and thus generates the circumferential velocity components in the inlet flow in the spiral casing 216, while the spiral wall boundaries of the spiral casing 216 generate the radial velocity components. These radial velocity components are distributed in the

Flow compensation housing 218 continues into its transition area into the vortex housing, because the guiding effect of the flow compensation housing 218 with its continuity influence on the radial velocity components extends to this point. This radial continuity influence decreases to zero (0) at the end of the rounded profiled transition area between the flow compensation housing and vortex housing. In this way, the radially oriented meridian flow from the flow compensation housing 218 is increasingly converted into an axially oriented meridian flow, with the circumferential velocity components increasing advantageously up to this point due to the decreasing radii. Since the vortex housing extends axially symmetrically on two sides from the central flow compensation housing, the radial-axial conversion takes place with the meridian flow being divided into two axially symmetrical partial volume flows. In this way, the advantageous rotationally and axially symmetrical flow adjustment of the inlet flow is congruent with the local natural secondary flow and with an advantageous integral driving effect on the separation vortex.

Figs. 93 and 94 show modifications to the inlet according to Figs. 91 and 92 that are simpler to manufacture, in which the rotating spiral housing is replaced by rotating, rotationally symmetrical ring housings with simple tangential flow inlets (not shown here). Fig. 93 shows a U-shaped ring housing 221 with rounded radial outer corners, which is connected to two identically designed, here circular-cylindrical, vortex housing halves 222 in such a way that a rotationally symmetrical inlet gap to the vortex housing is created between the vortex housing halves for the inlet flow. The required

·

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The flow-optimized roundings on the inlet gap are created by simple one-sided sheet metal forming on the vortex housing halves 222. As a result, the two-sided roughly circularly rounded inlet gap area also acts advantageously as a flow compensation chamber. In a further manufacturing variant according to Fig. 94, the two vortex housing halves 223 are deformed on one side by sheet metal forming so that U-shaped ends with rounded U-bottoms are created at the ends of the vortex housing halves in axial section. The U-shaped ring housing is then placed on the short U-legs. This creates an advantageous ring housing with a flow compensation chamber that is simple to manufacture.

The vortex chambers with new types of inlets described above are all designed with two rotationally and axially symmetrical axial discharge slots for discharging the separated dust between the previously circular cylindrical vortex chamber shell and the two vortex chamber bottoms as axial boundary walls of the vortex housing. The two discharge slots divide a vortex chamber into three component groups. The following, in Figs. 95 to 101, vortex chambers with new types of discharge slots in the form of peeling slots in the vortex housing shell are shown. These arrangements of peeling slots in the vortex housing shell offer advantageous manufacturing simplifications in the manufacture of vortex chamber systems. Vortex chambers with axial discharge slots consist of three manufacturing units: These are the vortex housing shell with the inlet arranged on it and the two identically manufactured circular vortex chamber bottoms with the identical immersion tubes arranged concentrically in them. These three production units have previously had to be held concentrically to one another in separate holders in vortex chamber systems. In contrast, the vortex chamber with peeling slots in the vortex housing shell is simply held as a single production unit. This means considerable advantages in simplifying the vortex chamber system structure, particularly in multi-vortex chamber systems, as well as advantages in system assembly and maintenance due to the simple exchangeability of identical series vortex chambers. In principle, all vortex chambers with peeling slots in the vortex housing shell can be advantageously designed with all of the new inlets described above. For the following

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For reasons of simplicity, vortex chambers with new types of scraper gates are designed as a standardized representation with new types of simple curved pipe inlets with attachment nozzles for free, evenly distributed, accelerated suction from settling chambers in multi-vortex chamber systems.

Fig. 95 shows such a vortex chamber with a new type of straight paring slot 224 parallel to the vortex chamber axis in an axially broken-open overall view. The two vortex chamber bottoms 226 and the dip tubes 227 are connected to the circular-cylindrical vortex housing shell 225 in an advantageous integral design by streamlined roundings 228 at all flow corners for the secondary flow. Fig. 96 shows this vortex chamber with a straight paring slot in an axial rear view from the outside and Fig. 97 in a radial view. The paring slot 224 is advantageously simply bent outwards tangentially to the cylinder circumference in the cylindrical area of the vortex housing shell between the bottom corner roundings as a component integrated with the circular cylinder shell. This creates two axial lateral slots, which are covered here by wedge-shaped paring slot side walls 229.

In Fig. 98, a modification of this vortex chamber with a new type of V-shaped peeling slot 230 is shown in a perspective overall view and in Fig. 99 in a rear axial view. The V-shaped peeling slot can also be designed as a curve and, in addition to manufacturing advantages, offers an advantageous separation flow-favorable adaptation option to the axially symmetrical secondary flow on the cylinder jacket of the vortex housing. According to the radial view in Fig. 100, the V-shaped peeling slot 230 is advantageously shown simply without axial peeling slot side walls. The wedge-shaped open side slots advantageously increase the length of the peeling slot laterally and thus improve dust discharge. The vortex chamber can also be designed with peeling slot side walls. In advantageous multi-vortex chamber arrangements in perforated plates, the lateral slots are advantageously simply covered by the perforated plates, whereby the lateral legs 231 according to Fig. 99 and 100 are advantageously simply used for the axial and radial locking of the vortex chamber in the perforated plates not shown here. According to Fig. 100, the

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The peeling gate in the upstream area is advantageously bent tangentially out of the vortex housing casing as a component integrally connected to the cylindrical vortex housing casing, until the required peeling slot width is reached, as indicated by the course of the lateral legs 231. From this point, the V-shaped area 232 of the peeling slot plate is curved concentrically to the vortex chamber axis, so that an advantageous peeling slot of constant peeling slot width is created in the V-shaped area. Fig. 101 shows an enlarged detailed view of this advantageous simple peeling gate design according to Fig. 98 on one of the two axially symmetrical lateral peeling slot areas. This construction can in turn be used as a simple axial and radial locking aid when assembling the vortex chamber of multi-vortex chamber arrangements in perforated plates.

For all of the vortex chambers shown up to now, only circular cylindrical vortex housing shells were chosen. All vortex chambers with different new inlets as well as axial two-sided discharge slots or simple peeling slots can also be designed with new barrel-shaped to double-cone-shaped vortex housing shell designs that are advantageous in terms of flow technology. The barrel-shaped curved or, for simplified production, double-cone-shaped design of the vortex housing shell offers particular flow technology advantages for the vortex drive: With barrel-shaped to double-cone-shaped vortex housing shells, the tangential angular momentum is introduced radially further outwards. This produces higher rotational speeds in the fine separation zone around the dip tubes and thus higher separation performance while the immersion tube geometry remains the same. The vortex housing volume remains advantageously smaller with barrel-shaped to double-cone-shaped housing designs than with circular cylindrical vortex housing designs for the same maximum diameter in the center plane. In this comparison, a smaller vortex volume is therefore to be driven in the barrel- to double-cone-shaped vortex housings. This leads to lower losses in these vortex chambers due to internal flow friction and, due to the smaller housing surface, also to lower wall friction, so that higher m values for the rotational speed distribution v _ro t * r ^m = const result and, in turn, higher separation performance. In addition,

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The barrel-shaped to double-cone-shaped jacket design results in larger entry jet ranges in the circumferential direction and thus an improved tangential momentum conversion into angular momentum for the vortex, because the jet is fanned out over a larger circumferential area. This results in even higher separation performance.

The axial section in Fig. 102 shows a vortex chamber with a new type of barrel-shaped vortex housing shell 233, which is designed here, for example, with a new type of inlet as a simple pipe inlet. The pipe inlet is supplemented by an attachment nozzle for free, evenly distributed, accelerated suction from settling chambers in multi-vortex chamber systems. Any of the other new types of inlets described above can also be used. The vortex chamber is designed here with axial two-sided discharge slots. However, it can also be designed with paring slots in the vortex housing shell or with combinations of paring slots and axial discharge slots. Fig. 103 shows this vortex chamber in a radial external overall view.

In Fig. 104 , a modification of this new barrel-shaped vortex chamber with a single pipe inlet is shown in a radial view, in which the pipe inlet is designed with a flange 234 for the lateral connection of the vortex chamber to a distribution channel for multiple, similar vortex chamber connections. The flange merges into the pipe inlet with streamlined corner roundings 235 for low-loss flow introduction. In the area of the inflow corners 236, the flange merges into the pipe inlet with advantageously smaller roundings, because this area is to be designed as a low-loss flow division area. With streamlined corner roundings that vary in this way over the inner flange circumference, an advantageously low-turbulence flow distribution from the distribution channel is ensured and the separation performance of the connected vortex chambers is thus not impaired.

For multi-vortex chamber systems, it is advantageous for reasons of rational series production and system assembly in a simple system structure to combine similar vortex chambers in groups with the same number of vortex chambers into similarly designed modules. Fig. 105 shows a top view

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a new type of vortex chamber module with barrel-shaped vortex chambers with axial two-sided discharge gaps. Several vortex chambers are connected to a distribution channel 237 for raw gas on two sides, symmetrically, parallel in terms of flow and statically supporting. The distribution channel 237 carries the vortex housings of the vortex chamber group and is advantageously designed with a rectangular flow cross-section so that it serves as the static main support of the vortex chamber module. Therefore, the distribution channel extends in the axial direction of the vortex chambers so far that the two identical rectangular clean gas collection channels 238 of the module can advantageously be statically connected to the supporting distribution channel in such a way that two axially symmetrical dust transport spaces are left free between the two vortex chamber floors and the base plates 239 of the clean gas collection channels 238. The two base plates 239 each carry all the immersion tubes with the associated vortex chamber floors of an axial vortex chamber side. The base plates are advantageously designed as static support elements and are extended compared to the long cross-sectional sides of the clean gas collection channels so that they can be used as flange-like connecting elements between several vortex chamber modules. The vortex chamber assemblies, vortex housing with inlet and, in a double version, immersion tube with vortex chamber base, are therefore advantageously connected in a force-locking manner via the static path of distribution channel-clean gas collection channels in the vortex chamber module. Because these static connecting elements are box-shaped with relatively larger supporting cross-sections, a high module rigidity is achieved with an advantageously low module construction weight.

Fig. 106 shows the side view of a vortex chamber module according to Fig. 105 in parallel connection of 2 modules in a vortex chamber system. A vortex chamber module here consists of a group of a total of 6 vortex chambers, which are advantageously connected in a space-saving manner on two sides symmetrically in 3 levels in a cluster-like manner to the vertical distribution channels 237. The distribution channels 237 are connected in parallel flow to the horizontal raw gas main channel 241, which is advantageously arranged above the vortex chamber modules in order to provide sufficient free space below them for the transport of the dust separated from the vortex chambers into the dust collection funnels 242.

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To reduce the height of the system, it is advantageous to arrange several dust collecting funnels 242 next to one another. For reasons of simplicity, no dust collecting containers have been drawn under the collecting funnels in the system illustration. Fig. 107 shows the front view of this vortex chamber system with the two clean gas main channels 243 arranged on both sides next to the raw gas main channel 241 in a space-saving manner, which in turn connect the individual vertical clean gas collection channels 238 in a horizontal arrangement, each from one vortex chamber module side, in parallel flow. The two dust transport spaces 240 are also shown to the side of the vortex chambers, which open into the dust collecting funnels 242 at the bottom.

Fig. 108 shows a new type of barrel-shaped vortex chamber with a paring slot, which is shown as a straight line in the lateral projection, as the radial view in Fig. 109 indicates. This brings advantages in terms of manufacturing technology. The barrel-shaped vortex chamber is designed here with an inlet as a simple straight pipe inlet with an attachment nozzle for free, evenly distributed, accelerated suction from settling chambers in multi-vortex chamber systems. The design of the vortex chambers with paring slots leads to an advantageously simple and space-saving construction of multi-vortex chamber systems. Fig. 110 shows such a new type of multi-vortex chamber system in a main side view and Fig. 111 in a sectional view with a view from below. In this type of vortex chamber with a paring slot, the individual vortex chamber is advantageously considered a module. Because the peeling slots and inlets are advantageously arranged opposite one another in the vortex housing casing, the raw gas distribution chambers 244 as calming chambers and the dust transport chambers 245 in the multi-vortex chamber system are advantageously arranged alternately next to one another between two perforated plates 246. The gas-tight separation of the raw gas distribution chambers 244 and the dust transport chambers 245 is advantageously achieved simply by means of series separating elements 247 and 248 between the vertically arranged groups of vortex chambers. Overall, this leads to a simpler system structure and smaller system sizes. The raw gas supply is advantageously carried out from below in a space-saving manner between the dust collection containers (not shown) in separate raw gas inlets 249 and 250 to the

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individual raw gas distribution chambers 244. The clean gas from the individual vortex chambers is collected in two larger clean gas collection chambers 251 arranged axially symmetrically to the vortex chambers as calming chambers and is discharged through two clean gas outlets 252.

In Fig. 112, a vortex chamber module with a four-sided symmetrical arrangement of barrel-shaped vortex chambers with peeling slots is shown in plan view. The vortex chambers have inlets for free, evenly distributed, accelerated suction from calming chambers in multi-vortex chamber systems, which here consist of simple straight pipe inlets with nozzles. The vortex chambers can also be designed with circular cylindrical vortex housings. In the vortex chamber module according to Fig. 112, all vortex chambers are arranged in a cross-like manner so that their inlets point towards the intersection center and thus advantageously open into a single raw gas distribution space 253 as a calming chamber. The cross-like vortex chamber arrangement results in four cross corners in which four identical clean gas collection channels 254 are arranged. In this modular design, the peeling slots are located on the sides of the vortex housing opposite the inlets at the outer crossing ends of the vortex chamber arrangement and open into four identical dust transport spaces 255. Overall, this results in an extremely space-saving, compact, simple modular design, which in multiple arrangements in multi-vortex chamber systems leads to advantageously small system sizes, which in turn have an advantageously low manufacturing cost.

Fig. 113 shows a modification of the vortex chamber module according to Fig. 112 with an inverted cross-like vortex chamber arrangement. Here, all the peeling slots of the vortex housings, which were chosen to be circularly cylindrical for demonstration purposes, open into a single central dust transport chamber 256 in the intersection center. Therefore, four identical raw gas distribution chambers 257 are arranged as calming chambers at the outer intersection ends.

Fig. 114 shows the cross-shaped vortex chamber module according to Fig. 113 in side view as a single module in a multi-vortex chamber system. This module consists of 20 vortex chambers in a grape-shaped tiered and cross-shaped vortex chamber arrangement with 5 vortex chamber tiers. The

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Raw gas is advantageously supplied to the four external raw gas distribution chambers 257 as settling chambers from below via an annular raw gas distribution channel 258 with a raw gas inlet 259. The four clean gas collection channels 254 therefore open into a clean gas collection chamber 260 arranged at the top with a clean gas outlet 261. The gas-tight separation of raw gas distribution chambers 257 and dust transport chamber 256 takes place between the vortex chamber levels by series separating elements 262 and 263. The central dust transport chamber 256 opens into the dust collection funnel 264 at the bottom. The dust collection container to be connected to this has not been drawn in for reasons of simplicity.

Fig. 115 shows a modification of the multi-vortex chamber system with a cross-shaped vortex chamber module according to Fig. 114. Here, a raw gas line 265 is guided concentrically within the dust transport chamber 256 with the flow coming from above, which opens into the ring-shaped raw gas distribution channel 267 at its lower end with pipe branches 266. This raw gas routing through the dust transport chamber in the center of the multi-vortex chamber system has an advantageous space-saving effect on the system with pipe connections and, particularly for hot gas dedusting tasks, has the advantage of a favorable, more uniform preheating of the dedusting system, which has an advantageous effect on the robust system operation for intermittent operation with the risk of falling below the dew point.

Fig. 116 shows a top view of how advantageous new cross-shaped vortex chamber modules can also be designed with vortex chambers with axial two-sided discharge gaps. The vortex chambers are flanged here via inlets as simple straight pipe inlets with flow-optimized inlet roundings to the central distribution channel 268 for raw gas in the intersection center of the vortex chamber arrangement, as shown in Fig. 117 for the radial view of a vortex chamber in detail. According to Fig. 116, the four clean gas collection channels 269 are arranged in the cross corners in such a way that gaps are left between the lateral vortex chamber floors with the axial discharge gaps as dust transport spaces 270. This cross-shaped vortex chamber arrangement again results in an advantageously simple, space-saving module construction.

The vortex chamber according to Fig. 117 is additionally equipped with an injection nozzle 271 on an injection pipe 272 for atomizing liquid. The atomization of liquids, for example as water drops, takes place advantageously in the inlet of the vortex chamber. This creates an advantageous new type of wet-separating vortex chamber, which leads to even higher separation performance compared to the dry separation of dust. The increase in separation performance is based on the physical effect that dust particles combine with the liquid droplets due to particle impacts, thereby creating heavier particles that can be separated more easily with less rotary flow energy. This effect of increasing separation performance can be used particularly advantageously for the separation and deposition of very fine particles. The dust particles that are combined with the liquid droplets before they enter the vortex chamber are displaced in the vortex chamber by the vortex separation flow from the inside of the vortex through the flow process described above to the vortex housing shell and there they combine to form a thin liquid film with the dust particles suspended in it. This suspension film on the housing wall is moved by the natural secondary flow of the vortex to the two axial discharge slots or, in the case of peeling slot vortex chambers, to the peeling slot and is discharged and separated there.

In principle, all types of vortex chambers with different inlets can be advantageously equipped with injection devices for liquid atomization. In single vortex chambers, in vortex chamber modules for multi-vortex chamber systems and in other multi-vortex chamber systems, the atomization can take place not only in the separate inlets but also advantageously upstream of these in distribution housings such as settling chambers and other pipes and pipe systems. The injection nozzles can spray the atomizing liquid conically in the direction of gas flow or also advantageously in countercurrent against the local gas flow direction. One or more injection nozzles connected in parallel in terms of flow can also be used in

Gas flow cross-sections can be arranged, which are advantageously fed centrally by corresponding pipelines or distribution piping systems.

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These wet vortex chambers and wet vortex chamber systems with single vortex chambers or multi-vortex chamber systems can be used advantageously for various new process engineering applications:

Firstly, there is high-performance dust separation for special types of dust with the finest grain spectra that are extremely difficult to separate.

On the other hand, wet separation vortex chambers can be used to separate odors and harmful gases. The harmful gases are bound by the liquid droplets.

In the wet vortex chambers, special liquids can also be sprayed in droplet form, which lead to intended chemical reactions with dust particles of a certain chemical consistency and, after the reaction, are separated and separated in the vortex chamber or are then subjected to further process engineering treatment within a process engineering process.

Furthermore, the wet vortex chambers can be used advantageously for new technical applications in air conditioning and ventilation systems: By spraying water in droplet form, the air to be treated for air conditioning or ventilation purposes can be cleaned of fine dust and conditioned in a single device unit of the vortex chamber or the multi-vortex chamber system. The conditioning can consist on the one hand of regulating the humidity of the air through the wet vortex chambers and on the other hand of regulating the air temperature via the temperature of the sprayed water.

The wet vortex chambers can also be used advantageously for environmentally friendly exhaust gas aftertreatment of combustion engines in vehicles. For example, for exhaust gas recirculation in diesel engines, vortex chamber designs from the first development generation with residual raw gas channels or vortex chambers with peeling slots can be used advantageously, by spraying diesel fuel in droplets into the inlets of the vortex chambers. These fuel droplets bind harmful diesel particles

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from the diesel exhaust, and the separated

The fuel-diesel particle suspension is then fed via return lines to a further afterburning process, for example in the engine cylinders or to a separate afterburning process.

Fig. 118 shows an enlarged radial detail of an inlet with injection nozzle and injection pipe of the new wet vortex chamber according to Fig. 117. The liquid is atomized in the direction of the inlet flow in a conical manner. The liquid particle paths are curved by the drag forces from the lateral gas flow. The injection nozzle is advantageously arranged so that the entire inlet cross section of the inlet is covered by the spray flow.

Fig. 119 shows a new type of wet vortex chamber system, here formed from a single cross-shaped vortex chamber module with vortex chambers with axial two-sided discharge gaps according to Fig. 116. This wet vortex chamber system consists of three vortex chamber levels with a total of 12 vortex chambers and a raw gas inlet at the top as well as an annular clean gas collection channel with a clean gas outlet. In the central raw gas distribution channel 268 in the intersection center of the vortex chamber arrangement, the four-fold axially symmetrical and three-level distribution pipe system 273 with the injection nozzles 271 is arranged concentrically. The liquid separated as a dust suspension collects in the collecting container 274 below the vortex chambers. The central distribution channel! 268 for raw gas is extended downwards into the collecting container 274 to below the liquid level 275 and can therefore be left open at the bottom with an opening 276 over the entire pipe cross-section to the collecting container 274, because the gas seal is advantageously achieved by the effect of communicating vessels. The opening 276 has the advantage that suspension drops that were not diverted into the inlets of the swirl chambers in the upper distribution channel due to their weight sediment downwards into the liquid of the collecting container 274. The dust particles that have thus reached this point can then continue to sediment in the liquid of the collecting container 274 within the downwardly open distribution channel 268 located therein to near the bottom of the collecting container 274 and then with

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the common liquid can be pumped out as a suspension via the liquid outlet 277. In this way, the distribution channel 268, which is open at the bottom, acts advantageously as an integrated pre-separator in a single common collecting container for suspension liquid.

The devices shown and described can also have peeling slots for discharging the particles instead of the annular gaps. It is also conceivable that the inlets according to the invention are combined with such vortex chambers, with a residual raw gas channel being provided.

Claims (1)

Device for separating substances by centrifugal force Protection claims 1. Device for separating the specifically lighter and heavier components from a flow of a medium loaded with suspended substances by means of centrifugal forces, in which the raw gas flow is diverted by a guide and introduced into a vortex chamber, from which the specifically lighter component is sucked out together with the clean gas through two immersion tubes that protrude into the central area of the vortex chamber coaxially and mirror-image to their center plane, so that a vortex rotating around the immersion tubes with a centrifugal force field is generated within the vortex chamber, and the housing of the vortex chamber consists of a circumferential jacket with vortex chamber floors arranged at the axial ends, which form annular gaps with the jacket on their circumference, through which the specifically heavier component is discharged, characterized in that the casing has a closed, rotationally symmetrical basic shape and the guide consists of at least one flow inlet with an inlet cross-section whose extension running parallel to the vortex chamber axis extends only over a part of the vortex chamber length, and the inlet penetrates the vortex chamber housing. 2. Device according to claim 1, characterized in that the inlet has at least one flow guide bed. 3. Device according to claim 2, characterized in that the flow guide bed is arranged behind the inlet cross-section. 4. Device according to claim 2, characterized in that the flow guide bed is arranged in front of the inlet cross-section. 5. Device according to claim 1 or 2, characterized in that the inlet has a rectangular flow cross-section. 6. Device according to claim 1 or 2, characterized in that the inlet has a rectangular flow cross-section with rounded corners. 7. Device according to claim 1 or 2, characterized in that the inlet has an oval flow cross-section. 8. Device according to one of claims 1 to 7, characterized in that the inlet is designed as a pipe inlet. 9. Device according to claim 8, characterized in that the pipe inlet has an acceleration section. 10. Device according to claim 8, characterized in that the pipe inlet has a flow-guiding acceleration section. 11. Device according to claim 8, characterized in that the pipe inlet has the shape of a flat nozzle. 12. Device according to claim 8, characterized in that the pipe inlet has an adapted shape. 13. Device according to claim 8, characterized in that the pipe inlet is designed as a straight inlet guide. T Device according to claim 8, characterized in that the pipe inlet is designed as a curved inlet guide. . Device according to claim 1, characterized in that the inlet has a retracted shape. . Device according to claim 14, characterized in that the inlet is formed from a semicircular profile! . Device according to claim 14, characterized in that the inlet is formed from a U-profile. Yf. Device according to claim 14, characterized in that the inlet has a tongue. f. Device according to claim 17, characterized in that the inlet has a gap support. ytf. Device according to claim 14, characterized in that the inlet has a wedge-shaped E'fil bed.
c \ iff. Device according to claim 14, characterized in that _the inlet has a curved bottom surface. ^: ··: "*.: : *: *: :.:. I*\ ,2T. Device according to claim 14, characterized in that the inlet has a straight bottom surface. «22. Device according to claim 1, characterized in that the vortex chamber is provided with a circumferential inlet in the form of a spiral housing. 28. Device according to claim 22, characterized in that the inlet is formed from several partial spirals. . Device according to claim 1, characterized in that the vortex chamber has a rotationally symmetrical outer housing and a multiple arrangement of retracted inlets. . Device according to claim 1, characterized in that the vortex chamber housing has an inner cylinder jacket. . Device according to claim 1, characterized in that the vortex chamber has two symmetrical inlet housings. . Device according to claim 1, characterized in that the vortex chamber has a rotating spiral casing of circular cross-section. 28. Device according to claim 1, characterized in that the rotating spiral housing has a U-shaped cross section. 2SYl Device according to one of claims 1 to 28, d characterized in that the vortex chamber has a straight paring slot. &bull; · &diams;· &bgr;&. Device according to one of claims 1 to 29, characterized in that the vortex chamber has a V-shaped peeling slot. &Pgr;
( Device according to one of claims 1 to 30, characterized in that the vortex chamber is barrel-shaped or double-cone-shaped or double-cone-shaped with a cylindrical central part. Device according to one of claims 1 to 31, characterized in that the inlet is provided with a flange. Vf
33". Device according to one of claims 1 to 32, characterized in that it can be integrated into multi-chamber modules. Device according to one of claims 1 to 33, characterized in that the vortex chamber housing has several inlets arranged in parallel. Device according to one of claims 1 to 34, characterized in that the vortex chamber housing has several divergently arranged inlets. JJ&euro;f. Device according to one of claims 1 to 35, characterized in that the vortex chamber housing has a residual raw gas channel. Device according to one of claims 1 to 36, characterized in that the inlet has an inlet nozzle. Device according to one of claims 1 to 37, characterized in that it has at least one injection nozzle. Establishment according to ^: e ^: iflim*ii.er JArjsprjjche.fl. J3f§ 38, characterized in that one or more *ELri5prLudijsin*3n . *..: "*. are arranged in one or more distribution channels upstream of the device.