RU2276272C2 - Antenna setting up and taking up winch drive air turbine - Google Patents

Abstract

FIELD: aircraft engineering.

SUBSTANCE: invention relates to turbomachines designed for driving auxiliary power plants, particularly, to air turbines using for operation air velocity head at flight. Proposed winch drive air turbine contains inlet diffuser formed by central fairing and shell, turbine stage and turbine outlet arranged in neck of branch pipe made to de Laval nozzle type and enclosing turbine housing from outside. Ring projection with smooth outlines is made on central fairing of inlet diffuser before nozzle assembly of turbine stage. Widening outlet part of branch pipe made to de Laval nozzle type consists of separate elements in form of leaf diffuser. Leaves of diffuser are installed so that solid opening angle of outlet diffuser part of branch pipe is 40°-60°.

EFFECT: increased efficiency of drive - air turbine owing to higher efficiency of through inlet and inlet and outlet channels.

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Description

The invention relates to turbomachines designed to drive auxiliary power plants, and in particular to air turbines using high-speed pressure of air flow during flight.

The operation mode of some aviation auxiliary power plants when using thermal turbomachines can lead to significant fuel consumption, intended mainly for mid-flight engines. Such an auxiliary power unit is a winch drive designed to release and retract long cables used as antennas.

For radio communication of the aircraft with the submarine in the fully submerged state, it is necessary to use the long wavelength range, since only such electromagnetic waves pass through the water column. Seawater strongly absorbs radio waves, but nevertheless, the longer the wavelength, the less absorption. This circumstance imposes its conditions on the device of the transmitting antenna - it should be a cable cable several kilometers long.

A device for discharging and retracting such a long antenna may have an air turbine as a drive.

The oncoming air stream flowing around the aircraft has sufficient kinetic energy, which can be used in an air turbine designed to drive a winch. This turbine, together with the gearbox and the winch, is located in one aerodynamic nacelle attached on a pylon to the wing of the aircraft.

The invention solves the problem of increasing the efficiency of the flow channels of an air turbine in order to increase the efficiency of the drive - an air turbine.

An air turbine includes an inlet diffuser, a nozzle apparatus, an impeller of the turbine with blades fixed to the shaft, and an outlet duct.

An analogous device for an air turbine can be selected conventional jet engine. It is known that aircraft jet engines mounted on aircraft flying at subsonic speeds have an inlet subsonic diffuser. The efficiency of a subsonic diffuser depends on the ratio of flight speed to speed in its inlet.

In the course of gas dynamics (see Applied gas dynamics, Abramovich GN. Third edition, revised. Publishing House "Nauka", M., 1969, p. 405) it is shown that the best condition for the operation of the input device for flying at subsonic speed is mode:

where W _e is the speed in the inlet of the diffuser;

W _n - the speed of the aircraft.

From the condition of continuity, the air flow through the inlet of the diffuser is equal to the air flow through the annular channel in front of the air turbine:

where ρ _e is the air density in the inlet of the diffuser, the same as in the distance in front of the inlet of the diffuser, in accordance with the flight altitude of the aircraft (since the change in density within the diffuser can be neglected, we take ρ _e = ρ _d );

W _e is the air velocity in the inlet of the diffuser;

F _e is the area of the diffuser inlet in front of the turbine stage;

W _d - air velocity at the end of the diffuser, in front of the turbine stage;

F _d - the area of the annular channel at the end of the diffuser, in front of the turbine stage.

The inlet diffuser is designed to provide a uniform velocity field in front of the air turbine stage. To do this, the flow along the path of the inlet diffuser must be continuous, irrotational, and the flow rate when flowing onto the blades should be reduced.

In the expanding channel, the static pressure along the diffuser increases

and if we neglect the change in density in the diffuser, then the ratio of speeds is inversely proportional to the ratio of areas as

. Наличие потерь нарушает это равенство, и полное давление в конце диффузора

всегда ниже, чем в начале:It is known that if there were no losses in the diffuser, the air in any of its cross sections would have the same total pressure equal to (at subsonic flight speeds) the total pressure in the incident air stream

. The presence of losses violates this equality, and the total pressure at the end of the diffuser

always lower than at the beginning:

An important characteristic of the diffuser is the dependence of the losses on the opening angle of the diffuser. The dependence established as a result of the statistical processing of numerous experiments shows (see Applied Gas Dynamics, Abramovich GN, Third Edition, revised. Publishing House "Nauka", Moscow, 1969, p. 406) that the opening angle of the continuous diffuser should not exceed values

In this case, the coefficient representing the ratio of the change in the total pressure of the diffuser to the change in the total pressure in the channel during sudden expansion:

At these values of ψ (as indicated in the book by G.N. Abramovich), there is no visible separation of the jets from the diffuser wall.

Restrictions (6) and (7) for the device of the inlet diffuser must be observed in all cases, regardless of the size of the air turbine and high-speed pressure during subsonic flight of the aircraft.

To determine the size of the inlet diffuser, a turbine is calculated by setting:

- turbine diameter D _cp ;

- the required turbine power N _t = G _in L _t ,

- работа расширения воздуха в турбине;where G _in = ρ _d W _d F _d - air flow through the annular channel in front of the air turbine and through the turbine;

- the work of expanding the air in the turbine;

k = 1.44, R = 287.3 J / kg · K — physical constants for air;

- температура торможения воздуха перед ступенью турбины на высоте полета;

- полное давление воздуха перед ступенью турбины; р₂ - статическое давление воздуха за ступенью турбины, величина которого соответствует давлению воздуха на высоте полета;

- air braking temperature in front of the turbine stage at flight altitude;

- total air pressure in front of the turbine stage; p ₂ - static air pressure behind the turbine stage, the value of which corresponds to the air pressure at the height of flight;

- rotational speed n;

- the angle of exit of the stream from the nozzle apparatus α ₁ ;

- other operational, geometric and statistical parameters, and as a result of calculating the stage of the air turbine, the height of the blades is determined, and then, taking into account conditions (6) and (7), the necessary geometric parameters of the input diffuser are obtained.

It should be noted that when developing an inlet diffuser for an air turbine, taking into account only the above restrictions (α = 6 ° ... 10 °, ψ = 0.15 ... 0.20) does not guarantee high efficiency of the air turbine, since the operation of the diffuser must be considered together with the turbine stage connected to it.

An analogue of the proposed device of an air turbine can be selected device free turbine used as a drive (power) at gas pumping stations and gas turbine engines. The inlet nozzles of such turbines, made in the form of an annular diffuser, have the same geometric ratios as the input device of the jet engine. These drive (power) turbines have diameters greater than the diameters of the gas generator turbines, since the rotations of the power turbine are much less than the revolutions of the gas generator turbines.

The ratios of the geometric and operational parameters of the adapter pipes between these turbines are equivalent to the subsonic inlet diffusers of aircraft gas turbine engines, since they have the general purpose of providing the necessary parameter field at the entrance to the stage. It is generally accepted that this field should be uniform.

The uniform parameter field at the entrance to the stage does not guarantee high efficiency of the stage, because at small values of D _cp / l ₂ <4 (here D _cp is the average diameter of the blades of the turbine impeller; l ₂ is the length of the pen of the turbine blades) and the degree of reactivity (ρ _article = 0.2 ... 0.4), characteristic for the stage under consideration, significant negative reactivity appears at the base of the blades (see, for example, V.I. Lokai, M.K. Maksutova, V.A. Strunkin Gas turbines of aircraft engines. Theory, design and calculation: Textbook for university students specialty "Aircraft engines and power plants" - 4th ed., revised and additional - M: Mashinostroit of, 1991. p.149). This means that in the root zone of the turbine, instead of expansion, a compression process is going on, that is, the operation of the turbine in the root zone is inappropriate.

A device is known for an air turbine designed to drive an electric generator, in which the output channel is formed of several Laval nozzles, made in such a way that a significant vacuum is created at the exit of the turbine impeller (see M. Egorov's publication in the journal Inventor and Rationalizer No. 9, 2000 the city of "UNEXCESSIBLE SOURCE OF ENERGY", Pat. No. 2124142). In this device, the free flow acts as a jet pump and, due to the ejection effect, creates a vacuum at the bottom section of the installation.

An energy converter comprising an air turbine, which is mechanically connected by a shaft to an electric generator located inside the nacelle, and the turbine outlet channel ends in the throat of a nozzle made as a Laval nozzle and enclosing the turbine from the outside. This nozzle together with the gondola forms a channel that ends in the throat of another nozzle, also made as a Laval nozzle and covering the turbine and the first nozzle from the outside.

The wind flow of air enters the inlet of the air turbine, where it converts wind energy into rotational motion of a generator that generates electricity. The pressure drop, which determines the magnitude of the air expansion work in the turbine stage, is measured from the braking pressure of the air flow in the air turbine inlet to the static pressure in the outlet channel. This pressure can be significantly lower than the static pressure of the surrounding air because in the throat of nozzles made as a Laval nozzle, the flow rate will increase significantly, and the pressure will drop by the corresponding amount and will be P ₂ <P _2H , where P ₂ is the static pressure on exit from the stage; P _2H - static pressure in the atmosphere.

The device of the air turbine is integrated into the installation, which is a stationary source of energy intended for use anywhere in the world, including places with increased wind speed, where traditional wind turbines no longer work. Such installations are an alternative solution to any other sources - thermal, electric and nuclear. However, the dimensions of the installation can be commensurate with or significantly exceed the transverse dimensions of the fuselage of a wide-body transport aircraft.

The prototype of the present invention is a device for an expanding outlet part of a nozzle made as a Laval nozzle made of separate elements in the form of a petal diffuser, with the possibility of changing the solid angle of the opening of the outlet diffuser part of the nozzle (see US 4919364, IPC 7 B 64 D 27/20, 1990)

The technical result, the solution of which the invention is directed, consists in increasing the efficiency of an air turbine and increasing the work of expanding the air in the stage and increasing the power of the turbine.

The technical result is achieved in that in the device of the air turbine of the winch drive for dissolving and selecting an antenna containing an input diffuser formed by a central fairing and a shell, a turbine stage and a turbine output channel located in the neck of a nozzle made by the type of a Laval nozzle and covering the turbine body from the outside , on the sleeve part of the central fairing of the inlet diffuser in front of the nozzle apparatus of the turbine stage, an annular protrusion with smooth contours is made, and the expanding output part of the nozzle, forming a channel by the type of Laval nozzle, made of individual elements in the form of a petal diffuser, the petals of which are moving.

What is new is that the diffuser petals are installed so that the solid opening angle of the outlet diffuser part of the pipe makes an angle α = 40 ° ... 60 °.

The essence of the proposed device is as follows. A protrusion with smooth contours is made in the inlet diffuser in front of the nozzle apparatus of the turbine stage on the sleeve part, which displaces the flow from the sleeve and root zones of the nozzle device, where the conditions for the expansion of the working fluid (air) in the stage are ineffective and as a result of such axial redistribution along the radius in the direction of the periphery into the region of effective conditions for expanding the working fluid, and the entire turbine is externally covered by a nozzle so that an annular gas-dynamic path is formed between the turbine housing and the nozzle , consisting of a tapering part, a throat located above the exhaust channel of the air turbine, and the expanding part of the nozzle next to the throat is made in the form of a petal diffuser, the petals of which have a solid opening angle of the diffuser part of the nozzle α = 40 ° ... 60 °.

As a result of this placement of the throat above the exhaust channel of the air turbine, the exhaust occurs at a reduced static pressure compared to atmospheric pressure, and an annular tearing region is formed in the lobed diffuser at an opening angle α = 40 ° ... 60 °, which contributes to a further decrease in static pressure and thereby increasing the difference between the braking pressure at the turbine inlet and the static pressure behind the stage of the air turbine, which makes it possible to obtain an increase in power on this turbine or the required power by teach the turbine is significantly smaller diameter.

, где F₁ - площадь входа, F₂ - площадь выхода из диффузора, значительное воздействие на эффективность турбинной ступени оказывает форма проточной части канала входного диффузора. Экспериментально показано, что плавно очерченный выступ, выполненный на втулочной части кольцевого диффузора перед сопловым аппаратом ступени турбины, приводит к увеличению эффективного КПД ступени, по сравнению с кольцевым диффузором, имеющим гладкие стенки.Specially undertaken studies on the influence of the shape of the contours of the input diffusers on the efficiency of the turbine stage, conducted at KSTU named after A.N. Tupolev, (see the work of R.S. Agachev, A.I. Arkhipov, M.U. Zakirov, A.G. Vavilov. The effect of transition pipes on turbine efficiency and specific parameters of gas turbine engines. // Workflows in cooled turbomachines of gas turbine engines. Kazan: KAI, 1989. S.80-84), showed that with the same value of the ratio of areas

where F ₁ is the inlet area, F ₂ is the exit area of the diffuser, the shape of the flow part of the channel of the inlet diffuser has a significant effect on the efficiency of the turbine stage. It is experimentally shown that a smoothly defined protrusion made on the sleeve part of the annular diffuser in front of the nozzle apparatus of the turbine stage leads to an increase in the effective efficiency of the stage, compared with an annular diffuser having smooth walls.

The effective efficiency of a turbine stage with an inlet diffuser having smooth walls is obtained equal to:

- эффективный КПД тяговой турбины, учитывающий механические потери η_м, уровень выходных потерь ξ_вых; (η_i)_Глад=0,760 - внутренний КПД ступени).(here

- effective efficiency of the traction turbine, taking into account mechanical losses η _m , the level of output losses ξ _o ; (η _i ) _Glad = 0.760 - internal stage efficiency).

For a turbine stage with an inlet diffuser having a protrusion on the sleeve wall, the effective efficiency in the same studies was obtained equal to:

(here (η _i ) _Projection = 0.775 is the internal efficiency of the stage).

Thus, the implementation of the protrusion on the sleeve part of the diffuser in front of the turbine stage allows to increase the effective efficiency by more than 1%.

The obvious influence of the device of the inlet diffuser nozzle with a protrusion on the sleeve part directly in front of the stage indicates that low-speed stages having inefficient conditions in the root zone for expanding the working fluid (air) in the stage do not require a uniform velocity field at the entrance to the stage, to which usually seek in the design of input devices.

The squeezing of the flow by a protrusion with smooth contours from the basal zone in front of the stage made it possible to reduce the effect of negative reactivity in the basal zone in the stage.

The oncoming air flow entering the channel-gap between the turbine body and the nozzle made as a Laval nozzle is accelerated in the confluent, tapering part of the channel, while the static pressure in the channel decreases to the smallest value in the nozzle throat located in the region where the output channels of the turbine are located . This decrease in static pressure leads to an increase in the differential across the turbine stages, and consequently to an increase in the work of gas expansion in the stage. Diffuser - the expanding part of the pipe of the second circuit after the throat consists of separate sections - petals. When moving (opening) the petals in the direction of increasing the solid angle, the petals create behind the throat, in the area of the windows of the output channels, conditions for a further decrease in static pressure. This decrease in static pressure occurs both as a result of separation of the flow of oncoming air flowing around the pipe from the outside, and as a result of creating flow conditions in the lobe diffuser as with a sudden expansion.

For an air turbine as a winch drive, it is necessary to know the operating conditions (flight speed and altitude) and for a specific winch the required turbine power:

where the air flow through the inlet diffuser and through the turbine is defined as:

and the work of expanding the air in the turbine stage is defined as:

- температура торможения воздуха перед ступенью турбины на высоте полета;

- полное давление воздуха перед ступенью турбины; р₂ - статическое давление воздуха за ступенью турбины, величина которого соответствует давлению воздуха на высоте полета.Included in equation (12): k = 1.44, R = 287.3 J / kg · K — physical constants for air;

- air braking temperature in front of the turbine stage at flight altitude;

- total air pressure in front of the turbine stage; p ₂ is the static air pressure behind the turbine stage, the value of which corresponds to the air pressure at altitude.

In flight at an altitude of 8000 meters at a speed of about 700 km / h, the air braking temperature in front of the turbine stage is set equal to

the total air pressure in front of the turbine stage is set equal to

Static pressure according to the international standard atmosphere (ISA) at an altitude of 8000 meters is

p _{2 (H = 8000)} = 35650 Pa.

Then the work of air expansion in the turbine stage will be equal to:

The proposed device nozzle, covering the turbine housing from the outside and forming an annular confuser channel in the form of a Laval nozzle, the throat of which is located above the turbine output channel, allows to lower the static pressure below (MCA).

Let conditions W _eII ≈0.5 W _n be created at the entrance to the annular channel between the nozzle and the turbine body (second circuit), as well as at the entrance to the inlet diffuser of the air turbine (1). The ratio of the cross-sectional area of the entrance to this annular channel of the second circuit F _eII to the cross-sectional area in the throat of the same annular channel F _{gII is assumed} to be equal to:

According to relation (4), the air velocity in the throat will be equal to

W _gII = 3W _eII ≈1.5W _H = 1.5 × 185.5 = 278.25 m / s.

Density of air at an altitude of 8,000 meters (ISA) is

ρ _{(H = 8000)} = 0.526 kg / m ³ .

, тогда статическое давление в горле равно:The braking pressure in the throat of the annular channel in flight with a speed of W _H = 185.5 m / s at a height of H = 8000 m is assumed to be equal

, then the static pressure in the throat is:

If we take this static pressure for the outlet channel behind the turbine, then the work of air expansion in the turbine stage will be equal to:

If we take the flow rate through the turbine unchanged and equal to G _in = 20 kg / s, without an external nozzle the power of the turbine will be

N _t = G _in L _{ep2 (MCA)} = 20 × 17193 = 343.860 kW

If there is an external pipe, the turbine power will be

N _tII = G _in L _{e pgII} = 20 × 52244 = 1044.780 kW.

Thus, a three-fold increase in turbine power was obtained.

тогда согласно (4) W_д=0,6 W_e. Параметры полета предлагаемой турбины с наружным патрубком оставим прежними, т.е. в полете со скоростью W_н=185,5 м/с на высоте Н=8000 м, давление торможения в горле патрубка примем равным

, статическое давление в горле наружного патрубка равно р_г=20362 Па, работа расширения в турбине L_e(ргII)=52244 Дж/кг. Тогда для таких условий будем иметь:Another problem that can be solved by this invention is to reduce the diameter of the turbine while maintaining the required power. So, if the required power of the antenna winch power plant should be N _t = 320 kW, and the average diameter of the turbine according to the technical specifications should be equal to D _cp = 0.65 meters. We set according to relation (1) the velocity at the inlet to the diffuser W _e = 0.5 W _n , we take

then according to (4) W _d = 0.6 W _e . The flight parameters of the proposed turbine with an external nozzle will remain the same, i.e. in flight with a speed of W _n = 185.5 m / s at a height of H = 8000 m, the braking pressure in the throat of the nozzle is assumed to be equal

, The static pressure in the throat of the outer nozzle equal to p _g = 20362 Pa, expansion work in the turbine L _{e (WGII)} = 52244 J / kg. Then for such conditions we will have:

- air flow through the turbine G _in = N _tII / L _ergII = 320,000 / 52244≈6 kg / s;

- the area of the annular channel for locating the turbine blade grids F1 = F _d = G _in / (ρ _{(Н = 8000)} · W _d ) = 6 / (0.526 · 0.6 · 0.5 · 185.5) ≈0.063 m ² ;

- the height of the blades L1 = F1 / (π · D _cp ) = 0.063 / (3.14159 · 0.65) = 0.102 m.

- the ratio D _cp / L1 = 0.65 / 0.102 = 6.4 means that in the root zone of the turbine (see, for example, V.I. Lokai, M.K. Maksutova, V.A. Strunkin Gas turbines of aircraft engines Theory, design and calculation: A textbook for university students with a degree in “Aircraft engines and power plants” - 4th ed., revised and supplemented - M .: Mashinostroenie, 1991. P.149) with values of degree of reactivity ( ρ _article = 0.2 ... 0.3) of the stage, the harmful effect of negative reactivity will take place. However, squeezing the flow in the diffuser with a protrusion with smooth contours from the basal zone in front of the stage, as shown by experimental studies, has reduced the effect of negative reactivity in the basal zone in the stage.

Thus, an air turbine for an aircraft auxiliary installation, inserted into the nozzle in the form of a Laval nozzle, which allows reducing the static pressure at the exit of the turbine stage, can have more favorable weight characteristics and better aerodynamic quality.

These calculations are approximate and are given only to confirm the beneficial effect of the device of the second circuit of the air turbine.

Under real conditions, the air entering the outlet channel after the turbine averages the static pressure in the throat. However, the ejection property of the second circuit can be increased if a petal-shaped diffuser with variable geometry attached to the confuser section of the nozzle behind the throat is installed at a solid opening angle α _{d II} = 40 ° ... 60 °, this will cause the boundary layer to tear off on the outer surface and significantly reduce the static pressure in the turbine region.

According to the schedule given in the book of Abramovich G.N. - Applied gas dynamics, third edition, revised. Ed. "Science", M., 1969, on p. 406, for diffusers, opened at an angle

the coefficient, which is the ratio of the change in the total pressure of the diffuser to the change in the total pressure in the channel during sudden expansion, takes values

This means that in such a diffuser, as well as in a channel with a sudden expansion, the static pressure in the initial section of the diffuser is much lower than in the output section.

Thus, an air bypass turbine device has an inlet diffuser of the first circuit, a protrusion with smooth contours is made on the sleeve part of the central fairing in front of the turbine stage nozzle apparatus, and the pipe forming the second circuit is made in the form of a Laval nozzle, consisting of a confuser in the inlet part, of a throat in the middle part and a diffuser in the output part, the throat of which is located above the output channel of the primary circuit, and the expanding output part of the pipe following the throat is made in the form of a petal diffus the gap, the petals of which move and change the solid angle of the opening of the outlet diffuser part of the nozzle, allows to reduce the diametric dimension of the turbine while maintaining the required power and increase the efficiency of the turbine.

Figure 1 shows a diagram of an air turbine with an inlet diffuser having an annular protrusion on the sleeve part of the central fairing in front of the nozzle apparatus and a nozzle made by the type of a Laval nozzle, covering the turbine housing from the outside and having a petal diffuser of variable geometry.

Figure 2 shows a diagram of a control device petal diffuser variable geometry. In figure 2, a pipe is shown separately, on which the flap diffuser is installed in the position of minimum drag for a long-distance flight. Figure 2, b shows the pipe, on which the flap diffuser is installed in a position that provides reduced static pressure behind the turbine.

Figure 3 shows a diagram of an aerodynamic nacelle with an air turbine, gearbox and winch for the dissolution and selection of the antenna cable.

Figure 4 shows examples of the placement of the pylon of the nacelle of an air turbine on a transport aircraft.

Figure 5 shows the approximate position of the antenna cable during radio communication with a submarine.

Here: 1 - inlet diffuser of an air turbine; 2 - shell of the input diffuser; 3 - internal fairing; 4 - an annular protrusion on the sleeve part of the internal fairing of the input diffuser; 5 - nozzle lattice of the turbine stage; 6 - the impeller of the turbine stage; 7 - output channel of an air power turbine; 8 - input confuser of the external pipe; 9 - a shell of the inlet confuser of the outer pipe; 10 - annular confuser channel between the turbine housing and the outer pipe; 11 - the throat of the channel between the turbine housing and the outer pipe; 12 - an expanding part of the annular channel between the turbine housing and the outer pipe, made in the form of a diffuser with variable geometry; 13 - petals of a diffuser with variable geometry, when opened, the magnitude of the solid angle of the diffuser changes; 14 - hinged nodes of rotation of the petals for expanding or folding the petals of the exhaust diffuser; 15 - thrust (pneumatic, hydraulic or electric) to change the geometry of the exhaust diffuser; 16 - an aerodynamic nacelle with an air power turbine and an antenna winch, mounted with a pylon on the wing of an airplane; 17 - pylon mounting device on the wing of the aircraft; 18 - wing of the plane; 19 - a shaft connecting the turbine to the gearbox; 20 - gear; 21 - winch; 22 - cable antenna; 23 - flight altitude; 24 - lower level sagging antenna, the distance to the surface of the aquatic environment; 25 - surface of the aquatic environment.

Air turbine winch drive for dissolution and selection of the antenna operates as follows. In the flight of an airplane-radio station, the oncoming air flow entering the inlet 1 of the air turbine diffuser flows through the annular diffuser channel, between the casing 2 of the inlet diffuser and the central internal fairing 3, flows around the protrusion 4, enters the nozzle apparatus 5 and the impeller 6 of the turbine stage , in which, having expanded from the braking pressure in front of the turbine to the static pressure behind the turbine, it performs work by rotating the shaft 19 of the winch gear drive. The protrusion 4 in front of the nozzle apparatus 5 squeezes the air flow from the basal region to the periphery to reduce the impact of negative reactivity in the basal zone of the stage.

Counter air that enters the inlet confuser 8 of the outer pipe 9 through the clearance channel 10 between the turbine housing 2 and the pipe 9 is accelerated in the tapering part of the channel 10, while the static pressure in the channel decreases to the lowest value in the throat 11 located in the area of windows 7 the output channels of the turbine 5, 6. This decrease in static pressure leads to an increase in the differential across the turbine stages, and consequently to an increase in the work of gas expansion in stages 5, 6 and to an increase in turbine power.

To achieve a further decrease in the static pressure at the turbine outlet, the pipe 9 ends with a diffuser 12 made of individual elements of the petals 13 in the form of a diffuser with an opening angle α = 8 ° ... 10 °, the petals of which, turning on separate hinges 14, change the solid angle the opening of the outlet diffuser part of the pipe to the values of the opening angle α = 40 ° ... 60 °. With such values of the opening angle, the flow in the diffuser is equivalent to the flow in the channel with a sudden expansion, when the static pressure sharply decreases. Thus, in the proposed device of the air turbine, a significantly larger work of expanding the incoming air flow in flight and, accordingly, the power of the turbine can be obtained. This means that the required power can be realized on a smaller diameter turbine.

The rotation of the petals 13 of the diffuser 12 in the hinges 14 can be carried out using rods 15 (having pneumatic or hydraulic, or electric drive). The torque from the turbine is transmitted through the shaft 19, the gearbox 20 to the winch 21, on which the antenna cable is wound 22. The gearbox 20 and the winch 21 are located inside the aerodynamic nacelle 16, on which the proposed air turbine device is mounted. And an aerodynamic nacelle with an air turbine, a gearbox and an antenna - a winch is fixed with the help of a pylon 17 on the wing of an airplane 18 in a row with the marching turbine engine. To communicate with a submarine in a completely submerged state, the aircraft at a height of flight 23 switches to a circular flight, so that the lower level of the sagging antenna, at the required distance 24 and on a small surface area of the aquatic environment 25. The proposed device of the air turbine allows repeatedly dissolve and select the antenna for radio broadcasts, including making false transmissions, and thereby not detect the true location of the hidden submarine.

Claims (1)

An air turbine of a winch drive for dissolving and selecting an antenna, comprising an inlet diffuser formed by a central cowl and a shell, a turbine stage and a turbine outlet channel located in the throat of a nozzle made as a Laval nozzle and covering the turbine body from the outside, on the central cowl of the inlet diffuser in front of the nozzle the apparatus of the turbine stage has an annular protrusion with smooth contours, and the expanding outlet of the nozzle, made as a Laval nozzle, is made of individual elements in the form daisy diffuser, wherein the diffuser pitch set so that the solid angle of the output opening side diffuser tube was α = 40 ... 60 °.

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