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EP3198199A1 - Tête de brûleur et turbine à gaz pourvue d'un tel brûleur - Google Patents

Tête de brûleur et turbine à gaz pourvue d'un tel brûleur

Info

Publication number
EP3198199A1
EP3198199A1 EP15766402.0A EP15766402A EP3198199A1 EP 3198199 A1 EP3198199 A1 EP 3198199A1 EP 15766402 A EP15766402 A EP 15766402A EP 3198199 A1 EP3198199 A1 EP 3198199A1
Authority
EP
European Patent Office
Prior art keywords
fuel
channel
burner
oxidant
longitudinal axis
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Withdrawn
Application number
EP15766402.0A
Other languages
German (de)
English (en)
Inventor
Thomas Baumann
Axel Widenhorn
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Duerr Systems AG
Original Assignee
Duerr Systems AG
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Priority claimed from PCT/EP2014/002604 external-priority patent/WO2015043749A1/fr
Application filed by Duerr Systems AG filed Critical Duerr Systems AG
Publication of EP3198199A1 publication Critical patent/EP3198199A1/fr
Withdrawn legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D14/00—Burners for combustion of a gas, e.g. of a gas stored under pressure as a liquid
    • F23D14/46—Details
    • F23D14/62—Mixing devices; Mixing tubes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/283—Attaching or cooling of fuel injecting means including supports for fuel injectors, stems, or lances
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/34—Feeding into different combustion zones
    • F23R3/343—Pilot flames, i.e. fuel nozzles or injectors using only a very small proportion of the total fuel to insure continuous combustion
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2900/00—Special features of, or arrangements for burners using fluid fuels or solid fuels suspended in a carrier gas
    • F23D2900/00008—Burner assemblies with diffusion and premix modes, i.e. dual mode burners
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/00002—Gas turbine combustors adapted for fuels having low heating value [LHV]

Definitions

  • the invention relates to a burner head of a burner of the type specified in the preamble of claim 1 and a gas turbine with a burner having such a burner head.
  • micro gas turbines are gas turbines of the lower power class, ie up to about 500 kW nominal power.
  • Combined heat and power systems of this type include in a known design in addition to the internal combustion engine itself nor a drivable by the internal combustion engine power converter, in particular in the form of an electric generator and a waste heat for the use of waste heat contained in the exhaust gas of the internal combustion engine.
  • the gas turbines mentioned have a burner between the compressor and the turbine, in which fuel is oxidized or burned with an oxidizing agent, as a rule with air.
  • the required mixing of fuel and oxidant takes place in a burner head.
  • This is typically attached to a burner flange, through which the fuel supply lines are also routed.
  • a combustion chamber is connected downstream.
  • the burner head extends along a burner longitudinal axis and usually comprises a plurality of arranged at a radial distance from the burner longitudinal axis in a body oxidant channels.
  • oxidant channels each opens a fuel nozzle, which is formed according to the prior art as a nozzle lance.
  • nozzle lance is preferably coaxial in each case an oxidant channel.
  • the nozzle lances are usually kept at Burner flange, where they are aligned and stored by a constructive paragraph in the axial direction.
  • the fixation of the burner nozzles is usually done by means of plates, which are bolted to the burner flange.
  • the nozzle lances are introduced into the combustion chamber via the individual oxidant passages located in the burner flange and designed as passage bores.
  • the fuel is supplied via individual hoses, which are fed via an upstream external distributor ring or also have a fuel supply channel in the burner flange.
  • the fuel nozzles are made of solid material.
  • the invention has the object of developing a generic burner head such that with a simplified structure increased reliability is achieved. This object is achieved by a burner head with the features of claim 1.
  • the invention is further based on the object of specifying a turbine, in particular a gas turbine or a micro gas turbine with an improved burner. This object is achieved by a turbine having the features of claim 15.
  • At least one supply channel for fuel supply of at least one fuel nozzle is formed in the main body of the burner head.
  • a plurality of arranged around the burner longitudinal axis in the main body oxidant channels with at least one each opening into an oxidant fuel nozzle, the fuel nozzles are at least partially and in particular all connected to the at least one supply channel for supplying fuel.
  • a fuel channel body is guided into the oxidant channel, wherein the at least one fuel nozzle is formed on the fuel channel body and in particular is arranged at least approximately on the channel longitudinal axis.
  • the fuel channel body protrudes into an opening cross-section of the oxidant channel, this at least partially interspersed, passes through or divides into partial cross-sections, and / or that the fuel channel body in
  • Oxidant channel is arranged and / or provided. Again, a simple design waiving the usual prior art nozzle lances given. The named design leads to a positioning of the fuel nozzle on the channel longitudinal axis or at least sufficiently close thereto. In any case, an at least substantially central fuel injection can be achieved, which can promote a clean mixture formation.
  • the fuel channel body has a supply bore for supplying one in the fuel channel body provided and connected to the supply bore nozzle bore with fuel from the supply channel. However, it may be provided that the nozzle bore is formed so that it can be supplied directly from the supply channel with fuel.
  • the fuel channel body can be made in one piece with the main body of the burner head or connected to this.
  • the fuel channel body can be designed or designed as an insertion and / or press-in component for application in the oxidant channel.
  • the fuel channel body does not yet have a supply bore prior to its placement in the oxidant channel. This is first generated after its application in the oxidant channel by a drilling introduced from the supply channel ago.
  • a drilling operation is understood in particular to mean any method for producing or providing a bore-like or channel-like recess in a solid material.
  • EDM and / or laser processing may also be considered.
  • the nozzle bore is already formed in the fuel channel body before application, it is drilled with the boring processing in such a way that the nozzle bore can be supplied with fuel from the supply duct. Alternatively, it can also be provided that the nozzle bore is produced only together with or after the drilling operation for the supply bore.
  • the fuel channel bodies act as baffles in the air supply of a burner, in particular a FLOX ® burner (FLOX ® stands for the flameless oxidation of a fuel). Due to this bluff body, a vortex road is initiated downstream.
  • the fuel is introduced via the fuel channel body provided channel, in particular the supply and / or nozzle bore in the oxidant channel and mixes with the flowing there
  • the vortex street causes an advantageously increased Mixing of fuel with the oxidizing agent due to the additional turbulence.
  • the characteristic periodic separations of wake vortices downstream of the fuel channel body additionally advantageously enhance the turbulence of the flow.
  • the turbulence intensity and frequency may be influenced by the dimension and / or shape of the introduced fuel channel body.
  • fuel channel bodies with circular, oval, teardrop-shaped, polygonal, trapezoidal, dragon-shaped or similar cross sections along a transverse direction to the channel longitudinal axis (with or without rounded edges) may be advantageous.
  • the fuel channel body in the flow direction of the oxidant on symmetrical side surfaces wherein the symmetry may be preferably formed as a simple rotation, point and / or mirror symmetry.
  • the side surfaces may also be asymmetrical.
  • At given flow conditions determine, in addition to the formation and axial extent of the side surfaces in the flow direction, an inflow geometry, z. B. flow angle and / or inflow surface / plateau, the upstream part of the fuel channel body, and / or a Abströmgeometrie, z. B. Ablierewinkel and / or outlet geometry, the downstream part of the fuel channel body on the formation and properties of the vortex street.
  • the fuel channel body is preferably arranged in the oxidant channel such that a neutral fiber of the oxidant flow, in particular a channel longitudinal axis of the oxidant channel, extends through the fuel channel body. This arrangement is also referred to below as a centric arrangement of the fuel channel body.
  • the vortex street may, under certain circumstances or operating conditions, introduce instabilities into the combustion chamber, or fan or amplify it. These can influence the combustion characteristics in the burner.
  • Another possibility to influence the effects of the bluff body is to dispose the fuel channel body asymmetrically in the oxidant channel and / or to form the fuel channel body asymmetrically.
  • the turbulence of the flow is increased by the fuel channel body thus arranged and / or formed. As a result, an improvement of the flameless oxidation is possible even with less pronounced vortex street.
  • a second bluff body or other bluff bodies upstream of the fuel channel body lies in the arrangement of a second bluff body or other bluff bodies upstream of the fuel channel body.
  • these bluff bodies can be designed as analogous fuel channel bodies for injecting the fuel or as pure bluff bodies.
  • the bluff bodies or fuel channel bodies in the respective oxidant channel may have different geometries, in particular a deviating cross section and / or a different symmetry of the side surfaces and / or a different topology of the side surfaces, which advantageously suppresses the formation of a dominant frequency in the combustion chamber.
  • a plurality of channels in particular oxidant channels, takes place via the fuel injection into the combustion chamber, the formation of the bluff bodies or fuel Kanal Equity with different geometry, the formation of vortex streets of different amplitude, frequency and / or detachment can be effected.
  • This can have the advantage that the formation of a dominant frequency in the combustion chamber is suppressed, which can increase the stability of the flameless oxidation. This makes it possible to stabilize the combustion process.
  • This effect can also be brought about with only one oxidant channel with fuel injection, in which at least two baffles and / or fuel channel bodies differing in their geometry, in particular in cross section and / or the symmetry of the side surfaces and / or the topology of the side surfaces
  • Oxidant channel be arranged or provided.
  • a fuel channel section and a gas channel section are formed in the fuel channel body, wherein the fuel channel section and the gas channel section open together into the at least one fuel nozzle.
  • the gas passage section conveys a gas, preferably an oxidizing gas such as combustion air, while providing fuel through the fuel passage section. Fuel and gas enter together through the fuel nozzle as a fuel-gas mixture in the oxidant channel, wherein the gas portion of said mixture favors atomization of the fuel.
  • the oxidant channels and the associated fuel nozzles, in particular fuel channels are divided at least into a first burner stage and into a second burner stage, wherein separate and independent fuel supplies, in particular fuel supply channels, are provided for the various burner stages.
  • the burner head in this case has a central pilot stage and a, preferably concentrically arranged around the pilot stage main stage, wherein the main stage is formed by the at least two different burner stages.
  • the central pilot stage stabilizes the combustion and ensures a safe function in transient control processes. In the pilot stage but only a small part of the total fuel flow is implemented. By far the largest share of fuel and power is provided by the two-stage main stage.
  • the two-stage or multi-stage design makes it possible to adapt to changes in power demand such that one or more stages of the main stage are shut down while one or more remaining stages of the main stage operate at their optimum operating point.
  • the invention described in greater detail above and in more detail below finds its preferred use in a gas turbine, which in turn is preferably part of a cogeneration system.
  • a gas turbine which in turn is preferably part of a cogeneration system.
  • the burner head according to the invention can also be used equally advantageously in other burners, for example for heating systems, boilers, exhaust air purification systems, furnaces or the like.
  • FIG. 1 is a schematic block diagram of a gas turbine with a burner according to the invention, In a longitudinal sectional view of the burner according to the invention of FIG. 1 with a burner head and a downstream combustion chamber to illustrate the gas guide, in a longitudinal sectional view of a burner head in the form of a burner flange according to the prior art for a burner of FIG. 2 with nozzle nozzles designed as fuel nozzles, in a longitudinal sectional view of a first embodiment of a burner head according to the invention with a formed in the body, annular supply channel for fuel in the form of a sealed, formed in the peripheral surface annular groove, and leading from the supply channel to the respective oxidant channel, the fuel nozzle forming fuel channels, a variant of the arrangement of FIG.
  • Oxidant channel, Fig. 13b is a partial enlargement of the magnification range after
  • 15a to 15h are sectional views in section plane XV-XV of various
  • FIG. 17 shows a further exemplary arrangement of a fuel channel body in the oxidant channel
  • Fig. 18 shows an arrangement of a plurality of fuel channel bodies in
  • Fig. 19 shows a further arrangement of a plurality of fuel channel bodies in
  • Oxidant channel Fig. 20 is a schematic view of a burner head with different fuel channel bodies in different
  • Fig. 21 is a schematic view of a burner head with a
  • Fuel channel body, in the fuel channel portion and a gas channel portion are formed, which together in a
  • the gas turbine 30 includes a compressor 32, a turbine 33 and a burner 35, the compressor 32 being driven by the turbine 33 by means of a shaft 34.
  • the shaft 34 also drives a schematically indicated generator 31 or other engine.
  • the compressor 32 air or another oxidizing agent is sucked in, compressed, and supplied to the burner 35, which is also indicated only schematically, as the oxidant stream or combustion air stream 37.
  • the burner 35 is also supplied fuel, which is oxidized or burned in the burner 35 together with the oxidant stream 37. This results in a high-energy exhaust stream 38, which is derived by the turbine 33 and thereby relaxed, as a result, the turbine 33 and from this, the compressor 32 and the generator 31 is driven.
  • FIG. 2 shows in a longitudinal sectional view of an embodiment of the invention burner 35 of the gas turbine 30 of FIG. 1.
  • the burner 35 and its burner head 36 can also be used for other purposes, for example in heating systems, boilers, kilns, in an exhaust air purification or the like come.
  • the burner 35 comprises at least one combustion chamber 39, at the one end of which a burner head 36 is arranged.
  • the burner head 36 extends along a burner longitudinal axis 1 or concentrically around it, with the burner longitudinal axis extending through the combustion chamber 39 or concentrically therethrough.
  • combustion chambers 39 may also be advantageous.
  • the burner head 36 comprises a basic body 2 which is preferably designed in one piece and in which at least one oxidant channel 3 arranged at a radial distance from the burner longitudinal axis 1 is formed.
  • a plurality of concentrically arranged around the burner longitudinal axis 1 in the base body 2 oxidant channels is provided.
  • the oxidizing agent channels 3 of the preferred example of FIG. 4 are in uniform
  • the oxidizing agent channels 3 have a uniform radial distance from the burner longitudinal axis 1. Furthermore, the oxidant channels 3 in the example according to FIG. 4 have a uniform, circular cross-sectional contour with almost identical channel diameters, as best seen in FIG. 10. However, it can also be advantageous if adjacent oxidant channels 3 have varying angular distances on the circumferential line around the burner longitudinal axis 1 and / or varying radial distances from the burner longitudinal axis 1 and / or deviating channel cross sections, in particular cross-sectional contours and / or diameters.
  • a preferred embodiment may also comprise two, three or more groups of oxidant channels 3, which differ in groups in terms of their angular spacing and / or their radial distance and / or their channel cross-section.
  • the base body 2 according to FIG. 4 still bears centrally on the longitudinal axis of the burner 1 a pilot fuel nozzle 19 whose function will be described in more detail below.
  • the combustion chamber 39 and its outer wall is enclosed by a jacket 40, whereby an annular space is formed.
  • the burner head 36 remote from the end of this annular space of the oxidant stream or the combustion air stream 37 is introduced and led to the opposite side of the burner head 36.
  • an oxidizing agent or combustion air plenum 23 which surrounds the burner longitudinal axis 1 is formed, in which the oxidizing agent collects, deflected in accordance with an arrow 41 and fed into the at least one or into the plurality of oxidant channels 3 on the side opposite the combustion chamber 39 becomes.
  • a flow restrictor element 24 for the oxidant stream 37 which is shown only schematically and not shown in detail, can optionally be arranged, with which the flow rate of the oxidant can be adjusted, controlled or regulated if necessary.
  • the illustrated construction of the burner 35 is only a preferred embodiment.
  • the burner head 36 according to the invention which is described in more detail below, can also be advantageously used in other types of burners 35.
  • FIG. 3 shows a longitudinal section of a burner head 36 'in the form of a burner flange according to the prior art.
  • the main body 2 ' carries centrally beyond a pilot fuel nozzle 19' to form a pilot stage 1 ⁇ .
  • a fuel nozzle 4' which are formed according to the prior art as a nozzle lance, and which are concentric with the respective channel longitudinal axes 20 '. Trained as a nozzle lance fuel nozzles 4 'are not shown in detail, but above described manner attached to the flange body 2, sealed against this and fed via separate fuel distributor with hoses or pipes or the like with fuel.
  • oxidation channels 3 ' By means of the fuel nozzles 4 'designed as nozzle lances, fuel is introduced into the oxidant flow through the oxidant channels 3' in the same direction and coaxially, thereby producing an oxidation or combustible mixture.
  • FIG. 4 shows a longitudinal section of a first exemplary embodiment of a burner head 36 according to the invention, which in its configuration resembles the burner head 36 according to FIG.
  • Identical features are provided here with the same reference numerals, wherein individual features have already been described above in connection with FIG.
  • the supply channel 13 is supplied with fuel in particular by a single fuel supply 9, wherein the fuel supply 9 may have a flow-limiting element 22, not shown here but shown in FIGS. 1 and 9.
  • the supply channel 13 is designed as an at least partially circumferential annular groove 15 in the base body 2, wherein the annular groove 15 is sealed on its open side.
  • the as a rotation body to The burner longitudinal axis 1 encircling base body 2 has a radially outer peripheral surface 17, in which the annular groove 15 is incorporated from the outside and radially outside closed.
  • the burner head 36 has at least one, in this case exactly one fuel nozzle 4, for each oxidant channel 3. From the additional illustration according to FIG. 10, it is apparent that eight oxidant channels 3 each having a fuel nozzle 4 are provided here by way of example. But it can also be a different number appropriate.
  • the fuel nozzles 4 are at least partially, here all formed by incorporated into the base body 2 fuel channels 5, wherein the fuel channels 5 are connected on its input side to the supply channel 13 and open on its output side in the respective oxidant channel 3.
  • the fuel nozzles 4 and the fuel channels 5 are at least partially and here all connected to the supply channel 13 for the supply of fuel.
  • the fuel channels 5 have nozzle axes 6, which is a radial direction component to the longitudinal axis of the channel 20 of the oxidant channel 3 and / or to
  • the channel longitudinal axes 20 are parallel to the axis of the burner longitudinal axis 1, so that said radial direction components apply equally relative to the channel longitudinal axis 20 and the burner longitudinal axis 1.
  • said axis parallelism does not have to be given so that the radial directional component applies at least with respect to one of the two axes.
  • the longitudinal section shown leads to a sectional plane which is spanned by the burner longitudinal axis 1 and a radial direction 26 thereto.
  • a further cutting plane is spanned by the channel longitudinal axis 20 and a radial direction 27 for this purpose.
  • the nozzle axis 6 lies at a first inclination angle ⁇ relative to the channel longitudinal axis 20 and in a second one
  • the said first and second inclination angles ⁇ , ⁇ are advantageously in a range of> 0 ° to 90 ° inclusive and preferably in a range of from 60 ° to 90 ° inclusive. In the exemplary embodiment shown, both inclination angles ⁇ are at least approximately 90 °. Further details of the burner head 36 according to FIGS. 2 and 4 and in particular further details of the angular position of the nozzle axes 6 are still shown in FIGS. 9, 10 and described in more detail below in their context.
  • FIG. 5 shows a variant of the arrangement according to FIG. 4, wherein the supply channel 13 designed as an annular groove 15 is not formed in the circumferential surface 17 (FIG. 4) but in an end face 18 perpendicular to the longitudinal axis of the burner 1.
  • the fuel channels 5 do not lead from the outside to the inside with a radial direction component, but from the inside to the outside from the supply channel 13 with the radial direction component Oxidant channels 3.
  • the embodiment of FIG. 5 is consistent with that of FIG.
  • FIG. 6 shows a longitudinal section of a further variant of the burner head 36 according to FIG. 4 or 5.
  • the oxidant channels 3 and the associated fuel nozzles 4 or fuel channels 5 are at least in this case a first one
  • the at least two, here exactly two burner stages 7, 8 together form the main stage 12.
  • the burner head 36 has a central pilot stage 1 1 with the associated pilot fuel nozzle 19.
  • Oxidant channels 3 and fuel channels 5 are arranged concentrically around the pilot stage 11.
  • separate and independent fuel feeds 9, 10 are provided, which can be provided as shown in FIGS. 1 and 9 with independent flow limiting elements 22.
  • the two fuel feeds 9, 10 lead into two separate supply channels 13, 14, which are both formed in the peripheral surface 17 of the base body 2 as an annular groove 15, 16 with mutual axial displacement.
  • Both annular grooves 15, 16 with the associated fuel channels 5 are executed according to the annular groove 15 of FIG. 4.
  • the fuel channels 5 of the upper supply channel 13 open into at least one, preferably into a first group of several oxidant channels 3, while the fuel channels 5 open into at least one other, preferably into a second group of several oxidant channels 3. This can be done in the
  • individual oxidant channels 3 or individual groups thereof are switched off or operated with different operating parameters than a respective different oxidant channel 3 or another group thereof.
  • the two burner stages 7, 8 of the main stage 12 can be operated independently of each other and, if necessary, switched off individually.
  • FIG. 7 shows a modification of the burner head 36 according to FIG. 6, in which the two separate supply channels 13, 14 are formed in the end face of the burner head 36 or its basic body 2.
  • This is comparable to the embodiment of FIG. 5 to two in the end face 18 of the body 2 incorporated annular grooves 15, 16, which are arranged in the preferred embodiment shown in the axial direction one above the other and separated by a separating plate.
  • the first fuel supply 9 opens directly into the upper annular groove 15, while the second fuel supply 10 is passed from above through the upper annular groove 15 and below it opens into the annular groove 16.
  • the two supply channels 13, 14 and the two annular grooves 15, 16 may be radially offset from each other, for example, a supply channel 13 may be radially inwardly of the Oxidationsffenkanäle 3 and the other supply channel 14 may be positioned radially outwardly thereof.
  • the supply channels 13, 14 or the associated annular grooves 15, 16 coincide with the supply channel 13 or the annular groove 15 of the embodiment according to FIG. 8 shows in a schematic detail representation a single oxidant channel 3 according to FIGS. 4 to 7 with an optional annular channel 21 which surrounds the oxidant channel 3 in an annular manner.
  • the annular channel 21 is connected to one of the two supply channels 13 described above in a manner not shown.
  • the annular channel 21 runs at least partially, in this case completely closed around the oxidant channel 3. In the illustrated embodiment, it is designed as an annular groove which is closed at the top by a cover 25 and by a cover plate. From the annular channel 21, at least one fuel channel 5, in this case a plurality of fuel channels 5 with associated nozzle axes 6, leads into the oxidant channel 3.
  • FIGS. 2 and 4 to 8 in their other features, reference numerals and optional design options coincide with each other, whereby a combination of such features as for example the combination of an end supply channel 13 with a peripheral supply channel 14 comes into consideration.
  • 9 shows in a perspective longitudinal section illustration the burner head 36 according to FIGS. 2 and 4 for illustrating different angles of the nozzle axis 6.
  • the nozzle axes 6 have first and second angles of inclination ⁇ , ⁇ which are smaller than 90 ° are.
  • Fig. 10 shows a schematic cross-sectional view of the burner head according to FIGS. 2, 4 and 9 for illustrating further optional angular positions of the nozzle axes 6.
  • the cross-sectional plane shown here is perpendicular both to the burner longitudinal axis 1 and to the respective channel longitudinal axis 20. If the channel longitudinal axes 20th deviate from the illustration of FIG.
  • the nozzle axis 6 of the fuel channel 5 in the perpendicular to the burner longitudinal axis 1 measured cross-sectional plane exactly radially to the burner longitudinal axis 1, ie in the radial direction 26.
  • the nozzle axis 6 passes through the burner longitudinal axis 1.
  • the nozzle axis 6 of the fuel channel. 5 in the plane perpendicular to the channel longitudinal axis 20 cross-sectional plane exactly radially to the channel longitudinal axis 20, so runs exactly to the channel longitudinal axis 20.
  • the nozzle axis 6 'of the fuel nozzle 5' in the cross-sectional plane perpendicular to the burner longitudinal axis 1 is measured at a side angle ⁇ to the burner longitudinal axis 1, so that the nozzle axis 6 'does not pass through the burner longitudinal axis 1. But well, the nozzle axis 6 'passes through the associated channel longitudinal axis 20'. From the burner longitudinal axis 1, a radial direction 26 'extends through the assigned channel longitudinal axis 20', the lateral angle ⁇ between the radial direction 26 'and the nozzle axis 6' being measured.
  • a fuel channel 5 "with a nozzle axis 6" is shown.
  • the nozzle axis 6 "of the fuel channel 5" in the direction perpendicular to the channel longitudinal axis 20 "lying cross-sectional plane measured in From the channel longitudinal axis 20 “extends to the mouth of the fuel channel 5" a radial direction 27 ", wherein the helix angle ⁇ between the radial direction 27" and the nozzle axis 6 "is measured.
  • the nozzle axis 6 of the fuel channel 5 has neither a side angle ⁇ , nor a helix angle ⁇ . In other words, the amounts of the side angle ⁇ and the helix angle ⁇ are 0.
  • ß can be a Ver. to achieve turbulent fuel introduction into the respective oxidant channel 20 corresponding to a spiral line 28 of FIG. 9 for good mixing of the fuel with the oxidant.
  • a fuel channel body 42 is provided which in the associated oxidant channel. 3 is guided into it.
  • the fuel channel body 42 is shown in Figures 1 1 and 12 in a total of four different exemplary embodiments, wherein in practice preferably more fuel channel body 42 of the same design are used. Of course, it is also possible to provide mixed designs within a burner head 36.
  • the various fuel channel body 42 is the formation of at least one fuel nozzle 4 at each of a fuel channel body 42 and the optional, preferred positioning of the fuel nozzle 4 at least approximately wise on the channel longitudinal axis 20. In all cases is located within the Preferably, but not necessarily, the fuel channel section 43 is fed from an associated supply channel 13, 14, as described above in connection with FIGS. 4 to 7, 9 and 10 is.
  • the respective fuel channel body 42 may protrude beyond the associated oxidant channel 3 on only one side in a cantilever manner. In the preferred embodiments shown, it is guided into the respective oxidant channel 3 in such a way that it passes completely through it transversely to its channel longitudinal axis 20 and in this case on both sides against the opposite walls of the respective one
  • Oxidant channel 3 is supported.
  • the fuel channel bodies 42 have a circular cross-section, wherein they are formed here overall cylindrical. But there are also deviating cross-sectional shapes, in particular for reducing the flow resistance into consideration, such as elliptical, teardrop-shaped or otherwise streamlined cross-sectional shapes.
  • the fuel channel section 43 is formed as a through-hole, which completely passes through the fuel channel section 43 in its longitudinal direction, ie perpendicular to the longitudinal channel axis 20.
  • a shortened, designed as a blind bore fuel channel section 43 may be provided which extends only to the fuel nozzle 4 according to the right half of FIG.
  • a channel section branches off, which forms the fuel nozzle 4, the associated nozzle axis 6 being congruent with the channel longitudinal axis 20.
  • it can also be an axis parallelism with a distance between the nozzle axis 6 and the channel longitudinal axis 20 appropriate.
  • FIG. 12 Another variant is shown in the right half of FIG. 12, wherein instead of a single fuel nozzle 4 more, here two fuel nozzles 4, for example a fuel channel body 42 are formed, which are spaced from the channel walls of the associated oxidant channel 5 and in particular in the vicinity of the associated channel longitudinal axis 20.
  • the plurality of fuel nozzles 4 are advantageously fed from a common fuel channel section 43.
  • a shortened fuel channel section 43 analogous to the right-hand half of FIG. 11 may also be expedient.
  • the fuel nozzles 4 are aligned in the flow direction of the oxidant channel 3, wherein an at least approximately central injection of the fuel into the respective oxidant channel 3 takes place.
  • FIG. 12 shows yet another variant with a fuel channel section 43 guided obliquely through the fuel channel body 42.
  • the fuel channel section 43 directly forms at its outlet end the fuel nozzle 4 whose nozzle axis 6 is equal to the fuel channel axis.
  • the nozzle axis 6 thus has both an axial and a radial direction component with respect to the plane of the burner longitudinal section shown here.
  • the nozzle axis 6 is based on the direction of the longitudinal axis of the burner 1 or the longitudinal axis of the channel 20, as well as with respect to the direction of the respective associated radial direction 26, 27 in a deviating from 0 ° and 90 °
  • the various exemplary embodiments of the fuel channel body 42 in their other features and reference numerals which also applies to the comparison of the burner heads 36 according to FIGS. 11 and 12 with the burner head 36 according to FIG. 4.
  • the fuel channel bodies 42 according to the invention can also be used in any other burner heads, in particular in burner heads 36 in accordance with the further exemplary embodiments described here in their entirety.
  • FIG. 13 a repeats the view on the exemplary embodiment of FIG. 11 already described above, wherein with the dashed box a magnification range is selected, which is shown enlarged in FIG. 13 b.
  • vortex streets 50.1, 50.2 indicated in each of the two oxidant channels 3 shown by way of example are symbolically indicated, wherein in the sectional views of FIGS. 13a and 13b the vortex symbols for a better illustration are compared with the true expression of Karman vortexes on a Discharge body are drawn rotated by 90 ° about the channel longitudinal axis 20.
  • the different characteristics of the representations of the vortex streets 50.1, 50.2 are intended here to indicate the variability and variance of the vortex formation, which has already been described in the introduction, as a function of the geometries of the fuel channel bodies 42 as bluff bodies in the oxidant flow.
  • FIG. 13b shows the region around a fuel channel body 42 of the burner head 36 with three sectional planes XIV-XIV, XV-XV and XVI-XVI through the fuel channel body 42, which are taken up in FIGS. 14, 15 and 16 described below.
  • FIGS. 14a to 14h show various exemplary variants of the body cross-section, in particular at the height of the channel longitudinal axis 20 of the oxidant channel 3, of the fuel channel body 42. Circular or oval cross sections (FIGS. 14a to 14c) and polygonal cross sections (FIGS. 14d to 14h) are thereby produced. shown explicitly. The embodiment of a polygonal cross-section with rounded corners or edges shown in FIG.
  • FIGS. 14a to 14h additionally has an effect on the vortex formation in FIG the vortex street 50.
  • the feature of the corner or edge rounding can be applied analogously to the other polygonal embodiments shown with similar effect on the vortex formation.
  • the vortex symbols are now shown in FIGS. 14a to 14h in the correct rotational position about the channel longitudinal axis.
  • the fuel channel bodies 42 of FIGS. 14a to 14d and 14f to 14h shown in detail each have a fuel nozzle 4 directed into the oxidant channel 3 in the form of a nozzle bore, which is preferably aligned parallel to the flow direction of the oxidizer along the channel longitudinal axis 20.
  • the fuel nozzle 4 is also oriented substantially perpendicular to a downstream oriented, preferably perpendicular to the channel longitudinal axis 20 oriented, an outlet geometry 44 of the respective fuel channel body forming outlet surface 45 oriented.
  • the fuel is injected substantially tangentially to the forming vortex street 50 in the vortex, preferably directly into the wake.
  • An analogous injection is in the examples of Figures 14a to 14c by the channel axis 20 in
  • Substantially parallel alignment of the fuel nozzle 4 in the fuel channel body 42 achieved.
  • more than one fuel nozzle 4 is provided in the fuel channel body 42, which may in particular also have different orientations to the outlet surface 45 or to the channel longitudinal axis 20 (see, for example, FIG.
  • FIG. 14 e shows an example with an alternative outlet geometry 44 in the form of an outlet wedge with two outlet surfaces 45 oriented at an outlet angle.
  • a fuel nozzle 4 is provided, which supplies the fuel at least with a radial pulse component into the outlet
  • Oxidizing agent can inject or inject.
  • the radial pulse component can be adjusted over the outlet angle and / or orientation of the fuel nozzle 4 to the outlet surface 45.
  • the fuel nozzles 4 are substantially perpendicular to the outlet surface. However, provision may also be made for at least one of the fuel nozzles 4 to be tilted at a nozzle angle against a surface normal on the outlet surface 45.
  • Figures 15a to 15h show various exemplary variants of the cross section of a fuel channel body 42 in the section plane XV-XV of Figure 13b, i. with distance to the channel longitudinal axis 20 but parallel to this.
  • the off-axis cross sections shown here of the body cross sections according to FIGS. 14a to 14h are intended to show some further degrees of freedom of the skilled person in the design of the fuel channel body 42 for the specific application or the operating map for oxidant flow and fuel injection to be covered by the burner head design. Again, the vortex symbols are shown in the correct rotational position about the channel longitudinal axis.
  • a diameter of the circular cross-section of the fuel channel body 42 is reduced compared to the cross section in the sectional plane XIV-XIV.
  • This diameter reduction can be provided continuously in stages or preferably at least in sections. It may be different
  • the cross section can also be designed to be sloping or rising on the plane opposite the sectional plane XV-XV viewed from the channel longitudinal axis 20.
  • Fuel channel body 42 is formed by a supply channel 13, 15 facing the end to the opposite end in diameter decreasing. Furthermore, FIG. 15 a shows the fuel channel section 43 running in the fuel channel body 42, which in this example is designed as a preferred round bore. Analogously to the example according to FIG. 15a, in the example according to FIG. 15b, the external dimensions of the cross section in the sectional plane XV -XV are reduced compared to the characteristic in the sectional plane XIV-XIV of FIG. 14b. It may be advantageous if, in addition, as shown in Fig. 15b, the oval cross-section as a whole slimmer, ie an eccentricity of the oval with increasing from the channel longitudinal axis 20 distance is increasingly formed. Analogous to the example according to FIG. 15 a, the fuel channel section 43 is designed as a preferred round bore.
  • the cross section in the sectional plane XV-XV of the exemplary fuel channel body 42 is substantially identical to the cross section in the plane XIV-XIV (see FIG. 14c), preferably substantially constant over a transverse extent of the fuel channel body 42 carried out the oxidant channel 3.
  • the fuel channel section 43 is quadrangular, wherein other polygonal or convex cross sections may also be provided. These channel cross sections can be produced, for example, by introducing the channel as a groove into the fuel channel body, which is closed again in a second step toward the lateral surface of the fuel channel body 42.
  • FIGS. 15d-15h take the variations shown in the previous examples and apply them to the respective cross-sectional geometries, without adding any essential aspects.
  • FIGS. 16 a to 16 d show a cross section through exemplary embodiments of a fuel channel body 42 in the sectional plane XVI-XVI, that is to say, FIG. H. shown at the height of the fuel channel section 43 along the channel longitudinal axis.
  • the transverse cross section (sectional plane XVI-XVI) of the fuel channel body 42 is substantially rectangular, in particular the two are contour lines 46 separating oxidant channel 3 are aligned parallel to one another.
  • the side surfaces which produce the contour lines 46 in the projection of the section plane XVI-XVI are also aligned parallel to each other, resulting in a cross section similar to the example of FIGS. 14g and 15g.
  • the side surfaces may also be aligned at an angle to each other, so that in section plane XIV-XIV and XV-XV a cross section similar to the
  • FIGS. 14d to 14f or 14g Examples according to FIGS. 14d to 14f or 14g would result.
  • the examples according to FIGS. 14a to 14c and 15a to 15c also have the potential to be combined with a transverse cross section according to FIG. 16a.
  • FIGS. 16b to 16c now show alternative cross sections of the fuel channel body 42 in the sectional plane XVI-XVI with convex and / or concave contour lines 46.
  • the contour lines 46 can be made constant or variable along the channel longitudinal axis 20 extending into the drawing planes in that the respective corresponding side surfaces of the fuel channel body can be designed to run parallel or otherwise to one another.
  • the specific training depends on the turbulence properties of the flow channel body 42 to be achieved and can not be represented conclusively at this point.
  • the vortex street 50 may, under certain circumstances, introduce instabilities into the combustion chamber, or fan it or act on it in a reinforcing manner. This is In particular, the case that induced by the congestion effect of the fuel channel body 42 vortex and / or vortex separation solutions have a frequency in the vicinity of a resonant frequency of the hot gas in the combustion chamber.
  • FIG. 17 shows an exemplary embodiment in which the flow channel body 42 is arranged at a distance from the channel longitudinal axis 20 in the oxidant channel 3.
  • the flow channel body 42 is preferably radially offset by a certain distance from the neutral fiber of the oxidant flow.
  • Fig. 18 shows a further alternative or additional possibility, as the effects of the vortex formation on the fuel channel body 42 on which the
  • Burner head 35 subsequent combustion chamber, the flame tube and the running therein flameless oxidation can be reduced.
  • at least one further bluff body 42 ' is arranged upstream of the fuel channel body 42, which is arranged to inject fuel into the oxidant.
  • this may alternatively be a further fuel channel body 42 '.
  • the vortex upstream of the jam 42 'vortex of a first vortex characteristic (frequency, amplitude, etc.) are generated, which at least partially broken at the second barrage of the fuel channel body 42 and converted into vortices of another vortex characteristic, preferably with lower amplitude.
  • a first vortex characteristic frequency, amplitude, etc.
  • FIG. 19 shows a further alternative or supplementary embodiment of the invention for suppressing instabilities, resonance phenomena or other conditions which have a negative effect on the burning behavior, in particular the stability of the flameless oxidation. If a plurality of fuel channel bodies 42 of different geometry are used in the oxidant channel, in particular arranged in the oxidant channel 3, each of the fuel channel bodies 42 generates its own vortex street 50 with a specific vortex characteristic, the vortex characteristics of at least the fuel channel bodies 42 being different
  • Geometry differ from each other.
  • three fuel channel bodies 42 are provided in an oxidant channel.
  • the fuel channel body 42 are arranged along the channel longitudinal axis 20 at the same axial height, parallel to each other.
  • Each fuel channel body 42 has one of his
  • FIG. 21 is another schematic view of an oxidant channel 3 into which a fuel channel body 42 has been inserted. More specifically, the fuel channel body 42 passes completely through the oxidant channel 3, thus leading from one channel wall to the opposite channel wall, where it acts as a bluff body with the formation of an indicated vortex street 50. For the sake of better illustration, in FIG. 21 the vortex symbols are in turn rotated by 90 ° to the longitudinal axis of the channel.
  • the fuel channel body 42 is provided with at least one, here by way of example with exactly one fuel nozzle 4.
  • a fuel channel section 43 and a gas channel section 47 are formed in the fuel channel body 42, which open into the at least one fuel nozzle 4 together in a manner described in greater detail below.
  • a gas preferably an oxidative or oxygen-containing gas such as air
  • a liquid fuel is passed through the fuel passage section 43 and through a connection opening 48 in the gas passage section 47, wherein the connection opening 48 is advantageously in close proximity to the fuel nozzle 4.
  • a fuel-gas mixture 49 which is here a fuel-air mixture, and which enters through the fuel nozzle 4 into the oxidant channel 3.
  • the fuel-gas mixture 49 relaxes, resulting in atomization of the fuel in the combustion air stream 37.
  • the mode of operation of the atomization is shown here by way of example on only one oxidant channel 3 with only one fuel channel body 42.
  • several fuel channel sections 43 advantageously comprise a common fuel reservoir, for example one of the annular supply channels 13, 14 according to FIGS 13a, 13b can be fed, and then analogous to several gas channel sections 47 can be fed from a common gas reservoir, for example in the form of such annular grooves or annular spaces.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Gas Burners (AREA)
  • Pre-Mixing And Non-Premixing Gas Burner (AREA)

Abstract

L'invention concerne une tête de brûleur (36) destinée à un brûleur (35) et une turbine à gaz (30) pourvue d'un brûleur (35) comportant une telle tête de brûleur (36). La tête de brûleur (36) s'étend le long d'un axe longitudinal (1) et comprend au moins un conduit d'agent d'oxydation (3), qui est disposé dans un corps de base (2) à une distance radiale de l'axe longitudinal de brûleur (1) et qui comporte un axe longitudinal (20), et au moins une buse à combustible (4) qui débouche dans l'au moins un conduit d'agent de oxydation (3). Un corps de conduit de combustible (42) est guidé jusque dans le conduit d'agent d'oxydation (3); au moins une buse à combustible (4) est formée sur le corps de conduit de combustible (42), et est disposée, notamment au moins approximativement, sur l'axe longitudinal (20). Dans la turbine à gaz (30), la tête de brûleur (36) comporte un étage pilote central (11) et un étage principal (12) disposé de manière concentrique autour de l'étage pilote (11); l'étage principal (12) est formé par l'au moins un étage de brûleur (7, 8). Pour chaque étage de brûleur (7, 8), un conduit d'alimentation indépendant (13, 14), qui se présente sous la forme d'une gorge annulaire (15, 16) fermée et s'étendant au moins en partie sur la périphérie, est formé dans le corps de base (2) pour former des arrivées de combustible (9, 10) distinctes qui sont indépendantes les unes des autres et qui sont destinées aux étages de brûleur (7, 8); la turbine à gaz (30) est entraînée au moins partiellement par un flux de gaz d'échappement (38) du brûleur (35).
EP15766402.0A 2014-09-25 2015-09-19 Tête de brûleur et turbine à gaz pourvue d'un tel brûleur Withdrawn EP3198199A1 (fr)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
PCT/EP2014/002604 WO2015043749A1 (fr) 2013-09-28 2014-09-25 Tête de brûleur et turbine à gaz équipée d'un tel brûleur
DE102015003920.2A DE102015003920A1 (de) 2014-09-25 2015-03-27 Brennerkopf eines Brenners und Gasturbine mit einem solchen Brenner
PCT/EP2015/001864 WO2016045779A1 (fr) 2014-09-25 2015-09-19 Tête de brûleur et turbine à gaz pourvue d'un tel brûleur

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EP (1) EP3198199A1 (fr)
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KR102469577B1 (ko) * 2020-12-31 2022-11-21 두산에너빌리티 주식회사 마이크로 믹서 및 이를 포함하는 연소기
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EP4426974A2 (fr) * 2021-11-03 2024-09-11 Power Systems Mfg., LLC Injection pilote multitube dans des tourbillons piégés dans un moteur à turbine à gaz
KR102667812B1 (ko) * 2022-02-07 2024-05-20 두산에너빌리티 주식회사 연소기용 노즐 및 이를 포함하는 가스 터빈
JP2023148761A (ja) * 2022-03-30 2023-10-13 三菱重工業株式会社 燃焼器及びガスタービン
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US20170198914A1 (en) 2017-07-13
US10712009B2 (en) 2020-07-14
DE102015003920A1 (de) 2016-03-31

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