CN117662325A - ATR detonation rocket combined power engine - Google Patents

Abstract

The application relates to the technical field of rocket engines, and particularly discloses an ATR detonation rocket combined power engine. The engine comprises an outer cylinder, an inner cylinder, an outer cylinder air inlet switch, an inner cylinder air inlet switch, a gas compressor, a connecting shaft, a turbine, a precombustion container, a core cylinder, a first gas mixing pipe, an expansion shrinkage hood, a boosting rocket, a first fuel supply pipe, a second fuel supply pipe, a first oxidant supply pipe and a second oxidant supply pipe. The connecting shaft is connected with the compressor and the turbine. The precombustion container is sleeved outside the connecting shaft. The first fuel supply pipe and the first oxidant supply pipe are communicated with the precombustion vessel. The core barrel wraps the precombustion vessel and the turbine. The core barrel is wrapped by the expansion shrinkage cover. The first air mixing pipe guides the core barrel to the outside of the expansion shrinkage cover. The boosting rocket is arranged in the expansion shrinkage cover. The second fuel supply pipe and the second oxidant supply pipe are communicated with the boosting rocket. The engine enables air flow and rich gas flow to be mixed in a cross mode, mixing efficiency is improved, detonation combustion is adopted to improve combustion efficiency, and the installed booster rocket improves Mach number.

Description

ATR detonation rocket combined power engine

Technical Field

The application relates to the technical field of rocket engines, in particular to an ATR detonation rocket combined power engine.

Background

An ATR (Air Turbo rock) engine organically blends Rocket engines and aero turbine engines, the core assembly comprising: a compressor, a gas generator, a turbine, a lobe mixer, a combustor, and a tail nozzle. The ATR engine uses the gas output from the gas generator to drive the turbine to rotate, the compressor rotates synchronously through the linkage shaft connected with the turbine, so that air is sucked in, and the sucked air passes through the compressor and is mixed with the gas passing through the turbine in parallel through a lobe mixer (a blending device with a petal-shaped section), and is combusted in a combustion chamber, and then the gas is ejected from a tail nozzle, so that the reverse thrust is generated. The ATR engine has the advantages of large thrust-weight ratio, high specific impulse of low speed section and the like, but is limited by the component parameter matching of the ATR engine and the adjusting capability of a gas generator, the working mach number of the ATR engine is lower, the combustion efficiency is lower by adopting the mixing mode of the lobe mixer, and the residence time of fuel and oxidant in a combustion chamber needs to be prolonged to improve the combustion efficiency, so the combustion chamber of the ATR engine is longer, generally about 1.5 meters, and the weight of the ATR engine is larger.

Disclosure of Invention

In view of the situation that the ATR engine adopts the parallel blending mode of the lobe mixer, the combustion efficiency is lower, the combustion chamber is longer, so that the ATR engine has a larger weight, the application adopts another fuel and air mixing mode, the lobe mixer is removed, the blending efficiency and the combustion efficiency are improved through structural optimization, so that the knocking combustion is formed to generate driving force, and the combustion chamber can be designed to be shorter.

An ATR detonation rocket combined power engine comprises an outer cylinder, an inner cylinder, an outer cylinder air inlet switch, an inner cylinder air inlet switch, a gas compressor, a connecting shaft, a turbine, a precombustion container, a core cylinder, a first gas mixing pipe, an expanding and contracting cover, a boosting rocket, a first fuel supply pipe, a second fuel supply pipe, a first oxidant supply pipe and a second oxidant supply pipe.

The outer cylinder is sleeved outside the inner cylinder, so that an outer duct is formed between the outer cylinder and the inner cylinder. The outer cylinder air inlet switch is arranged in the outer duct. The inner cylinder air inlet switch is arranged at the air inlet end of the inner cylinder.

The compressor and the turbine are connected through the connecting shaft. The outer edge of the compressor is adjacent to the inner wall of the inner cylinder. The precombustor is looped over the connecting shaft, and the precombustor has an outlet that opens into the turbine. The first fuel supply pipe and the first oxidant supply pipe are respectively communicated with the precombustion container.

The core barrel encloses the precombustor and the turbine. The expansion shrinkage cover is wrapped outside the core barrel. The inner end of the first gas mixing pipe is communicated with the core barrel, and the outer end of the first gas mixing pipe penetrates through the side wall of the expansion shrinkage cover.

The boosting rocket is arranged in the expansion and contraction cover. The expanding and contracting cover is provided with an opening or an openable seal relative to the tail end of the boosting rocket.

The second fuel supply pipe and the second oxidant supply pipe are communicated with the boosting rocket. The air outlet end of the outer duct and the air outlet end of the boosting rocket are converged.

Through adopting above-mentioned technical scheme, first fuel supply pipe with first oxidant supply pipe can introduce fuel and oxidant respectively and get into the precombustion container carries out oxidation, produces high temperature rich gas, and high temperature rich gas passes through the turbine, drive turbine is rotatory, and the turbine passes through the connecting axle and drives the compressor rotation, and the compressor is inhaled air and is conveyed to the low reaches, and axial air flow and lateral rich gas flow mix outside the expansion shrink cover, and the cross mixing mode is compared in the parallel mode of mixing that adopts the lobe blender, mixes efficiently, therefore has also improved combustion efficiency, and the length of combustion chamber (being equivalent to the length of expansion shrink cover) can be designed shorter, can be 0.3~0.5m. The narrow flow passage and the wide flow passage formed between the expanding and contracting cover and the inner cylinder accelerate the combustion air flow, and the combustion air flow is ignited to generate detonation wave after being mixed with the oxidant and the fuel, so that power is generated.

Besides the combustion mode, air can enter from an outer duct between the outer cylinder and the inner cylinder through switching of the outer cylinder air inlet switch and the inner cylinder air inlet switch, fuel and oxidant can be injected into the boosting rocket through switching of the first fuel supply pipe, the second fuel supply pipe, the first oxidant supply pipe and the second oxidant supply pipe, mixed air flow after the reaction of the fuel and the oxidant can be sprayed out from the tail end of the boosting rocket and is mixed with air from the outer duct in a cross mode, the driving force is generated through combustion, the Mach number of the ATR detonation rocket combined power engine is improved, and the speed can be improved from 4Ma to 6Ma.

As an improvement of the ATR detonation rocket combined power engine, the expansion and contraction cover has an expansion portion expanding in the radial direction and a contraction portion gradually contracting in the radial direction in the gas flowing direction in this order.

By adopting the technical scheme, the expansion part and the inner cylinder of the expansion shrinkage cover generate narrow channels, so that air flow can be accelerated, the expansion channels are generated by the shrinkage part and the inner cylinder, and the detonation space is improved for combustion air flow.

As an improvement of the ATR detonation rocket combined power engine, the outer end of the first gas mixing pipe penetrates through the expansion part.

Through adopting above-mentioned technical scheme, from the pre-combustion air current of expanding portion discharge, the velocity of flow of here air current is fast, is difficult for backward flow and improves mixing efficiency, promotes factor of safety, promotes detonation combustion efficiency.

As an improvement of the ATR detonation rocket combined power engine, the ATR detonation rocket combined power engine further comprises a second gas mixing pipe. The pipe diameter of the second gas mixing pipe is 10-20% of the pipe diameter of the first gas mixing pipe. The inner end of the second gas mixing pipe is communicated with the pipe body of the first gas mixing pipe, and the outer end penetrates through the side wall of the expansion shrinkage cover. The outer end of the second gas mixing pipe faces the upstream of the gas flow relative to the outer end of the first gas mixing pipe along the gas flowing direction.

The air flow speed of the first air mixing pipe is high, the mixing distance is short, insufficient mixing can be possibly caused, by adopting the technical scheme, the pipe diameter of the second air mixing pipe is 10-20% of the pipe diameter of the first air mixing pipe, the air flow of the second air mixing pipe and air are premixed, the mixing efficiency is improved, and meanwhile, the higher safety coefficient is maintained.

The downstream refers to a position farther from the start of the flowing air stream, and the upstream refers to a position closer to the start of the flowing air stream.

As an improvement of the ATR detonation rocket combination power engine, the ATR detonation rocket combination power engine further comprises a fuel source and an oxidant source. The fuel source is connected to the first fuel supply pipe and the second fuel supply pipe, respectively. The oxidant source is connected to the first oxidant supply pipe and the second oxidant supply pipe, respectively.

By adopting the technical scheme, the first fuel supply pipe or the second fuel supply pipe can be selected to supply fuel, and the first oxidant supply pipe or the second oxidant supply pipe can be selected to supply oxidant so as to use an ATR detonation engine or a booster rocket to provide power.

As an improvement of the ATR detonation rocket combined power engine, the second fuel supply pipe and the second oxidant supply pipe penetrate through the expansion and contraction cover from the upstream of the expansion part in the gas flowing direction so as to be communicated with the booster rocket.

By adopting the technical scheme, the second fuel supply pipe and the second oxidant supply pipe can not interfere the operation of detonation waves at the downstream of the expansion part, so that the detonation wave energy loss is less, and higher power can be provided.

As an improvement of the ATR detonation rocket combined power engine, the expansion and contraction cover comprises a main cover and a tail cover which are connected in a sealing way. And an initiating explosive device is arranged between the main cover and the tail cover.

By adopting the technical scheme, when the Mach number is increased by switching the boosting rocket, only an initiating explosive device is triggered by one initiating explosive device igniter, the tail cover is burst off, then the spray pipe of the boosting rocket is opened, the rocket is started, and after fuel and oxidant are injected through the second fuel supply pipe and the second oxidant supply pipe, the rocket engine starts to work to generate boosting effect.

As an improvement of the ATR detonation rocket combined power engine, the ATR detonation rocket combined power engine further comprises a rectifying cone. The cone is mounted upstream of the compressor in the direction of gas flow. The ATR detonation rocket combined power engine comprises a plurality of inner cylinder air inlet switches. Each inner cylinder air inlet switch comprises a first cover plate and a first telescopic device. One end of the first cover plate is hinged to the inner wall of the inner cylinder. The first cover plate is provided with a convex surface part protruding towards the rectifying cone. One end of the first telescopic device is connected to the inner wall of the inner cylinder, and the other end of the first telescopic device is hinged to the inner wall of the convex surface portion. The plurality of first cover plates can be enclosed into a cone shape after being mutually close.

By adopting the technical scheme, the rectifying cone can guide air flow to the effective air guiding area of the air compressor, so that the air flow rate is improved. The first cover plates are close to each other and can be enclosed into a cone shape, namely, the air inlet channel of the inner cylinder is closed, air can be introduced from the outer duct, and the necessary condition for air flow switching is provided.

As an improvement of the ATR detonation rocket combined power engine, the ATR detonation rocket combined power engine comprises a plurality of outer cylinder air inlet switches. Each outer cylinder air inlet switch comprises a second cover plate and a second telescopic device. One end of the second cover plate is hinged to the inner wall of the outer cylinder. One end of the second telescopic device is connected to the inner wall of the inner cylinder, and the other end of the second telescopic device is hinged to the second cover plate. And the second cover plates can be enclosed into a curved ring shape which is matched with the outer duct after rotating inwards.

By adopting the technical scheme, the plurality of second cover plates can seal the outer duct so as to realize the switching of the air inlet channel by air inlet from the inner cylinder.

As an improvement of the ATR detonation rocket combined power engine, a plurality of air outlets are formed between the tail part of the outer cylinder and the tail part of the inner cylinder. The ATR detonation rocket combined power engine further comprises a plurality of tail pneumatic switches which are arranged at the air outlets one by one. Each tail pneumatic switch is hinged to the tail end of the inner cylinder and can cover the air outlet under the pushing of air flow in the inner cylinder or open the air outlet under the pushing of air flow in the outer cylinder.

By adopting the technical scheme, the tail part of the outer cylinder is contracted inwards, so that the airflow laterally flows to the tail end of the boosting rocket to form a cross mixing effect, and the mixing efficiency is improved. The tail pneumatic switch is driven by air flow in the inner cylinder or air flow in the outer duct to close or open the outer duct, other power driving parts are not needed, and the tail pneumatic switch can be made of heat-resistant silicon carbide or carbon fiber and the like and can adapt to the high-temperature environment of the tail.

In summary, the ATR detonation rocket combined power engine of the present application has the following beneficial effects:

the cross mixing mode of the axial air flow in the inner cylinder and the fuel-rich gas flow laterally discharged by the core cylinder and the expansion shrinkage cover is higher in mixing efficiency compared with the parallel mixing mode adopting a lobe mixer, so that the combustion efficiency is improved, and the length of the combustion chamber (equivalent to the length of the expansion shrinkage cover) can be designed to be shorter.

The narrow flow passage and the wide flow passage formed between the expansion and contraction cover and the inner cylinder accelerate the combustion air flow at high pressure, the combustion air flow is burnt rapidly and expanded to generate sonic detonation wave, and then the expansion is performed to generate supersonic detonation wave, so that power is generated.

Through the switching of the first fuel supply pipe, the second fuel supply pipe, the first oxidant supply pipe and the second oxidant supply pipe, the fuel injection and the oxidant injection can be switched to the injection of the fuel and the oxidant to the boosting rocket, the tail end of the boosting rocket can spray the mixed airflow after the reaction of the fuel and the oxidant, the mixed airflow is mixed with the air from the outer duct in a cross manner, the combustion generates the driving force, and the Mach number of the ATR detonation rocket combined power engine is improved.

Drawings

FIG. 1 is a schematic diagram of the internal structure of an ATR detonation rocket combination power engine.

FIG. 2 is another state diagram of the ATR detonation rocket combination power engine of FIG. 1.

FIG. 3 is a schematic top view of a plurality of inner barrel inlet switches enclosed adjacent to one another in a cone shape.

Fig. 4 is a schematic plan view and a schematic front view of the plurality of outer cylinder air inlet switches which are close to each other and are enclosed into a curved ring shape.

Fig. 5 is a schematic top view of a plurality of trailing air switches.

Fig. 6 is a schematic front view of the plurality of tail pneumatic switches of fig. 5.

Reference numerals: the outer cylinder 1, the inner cylinder 2, the outer cylinder air inlet switch 3, the inner cylinder air inlet switch 4, the compressor 5, the connecting shaft 6, the turbine 7, the precombustion vessel 8, the core barrel 9, the first gas mixing pipe 10, the expanding and contracting cover 11, the boosting rocket 12, the first fuel supply pipe 13, the second fuel supply pipe 14, the first oxidant supply pipe 15, the second oxidant supply pipe 16, the outer culvert 101, the expanding part 111, the contracting part 112, the second gas mixing pipe 17, the fuel source 18, the oxidant source 19, the main cover 113, the tail cover 114, the initiating explosive device 115, the cone 20, the first cover plate 401, the first telescopic device 402, the convex part 4011, the second cover plate 301, the second telescopic device 302, the gas outlet 102, the tail gas switch 21 and the expanding cover 22.

Detailed Description

The ATR detonation rocket combination power engine of the present application is specifically described below with reference to the accompanying drawings.

Referring to fig. 1 and 2, an ATR detonation rocket combined power engine comprises an outer cylinder 1, an inner cylinder 2, an outer cylinder air inlet switch 3, an inner cylinder air inlet switch 4, a gas compressor 5, a connecting shaft 6, a turbine 7, a precombustion vessel 8, a core cylinder 9, a first gas mixing pipe 10, an expansion and contraction cover 11 and a boosting rocket 12, and further comprises a first fuel supply pipe 13, a second fuel supply pipe 14, a first oxidant supply pipe 15 and a second oxidant supply pipe 16.

Arrows in fig. 1 and 2 indicate the direction of the air flow. Fig. 1 is a state diagram in which the outer cylinder air intake switch 3 is closed and the inner cylinder air intake switch 4 is opened. Fig. 2 is a state diagram in which the outer cylinder air intake switch 3 is opened and the inner cylinder air intake switch 4 is closed.

The outer cylinder 1 is sleeved outside the inner cylinder 2, so that an outer duct 101 is formed between the outer cylinder 1 and the inner cylinder 2. The outer cylinder air inlet switch 3 is arranged in the outer duct 101 and controls the air flow on-off of the air inlet end of the outer duct 101. The inner cylinder air inlet switch 4 is arranged at the air inlet end of the inner cylinder 2 and controls the on-off of air flow at the air inlet end of the inner cylinder 2.

The compressor 5 and the turbine 7 are fixedly connected through a connecting shaft 6. The outer edge of the compressor 5 is adjacent to the inner wall of the inner barrel 2 to draw in sufficient air.

The precombustor 8 is sleeved outside the connecting shaft 6, and the precombustor 8 is provided with an outlet which is communicated with the turbine 7 so as to ventilate the turbine 7 and drive the turbine 7 to rotate.

The first fuel supply pipe 13 and the first oxidant supply pipe 15 are respectively communicated with the precombustion vessel 8, more fuel and less oxidant are oxidized in the precombustion vessel 8 to generate precombustion effect, and at the moment, a lot of fuel is not fully combusted after being cracked at high temperature, and the precombustion gas acts on fully combusted raw materials.

The core barrel 9 encloses the precombustor 8 and the turbine 7. An expanding and contracting cover 11 is wrapped outside the tail end of the core barrel 9. The inner end of the first gas mixing pipe 10 is communicated with the core barrel 9, and the outer end penetrates through the side wall of the expansion shrinkage cover 11 so as to lead the pre-combustion gas in the core barrel 9 to the cavity of the inner barrel 2 and mix and burn with the air flow.

The boosting rocket 12 is arranged in the expansion and contraction cover 11, and the boosting rocket 12 can provide boosting force and improve Mach number of the combined power engine.

The expanding and contracting cover 11 has an opening or openable seal at the end opposite to the booster rocket 12 to provide an air injection passage for the booster rocket 12.

The second fuel supply pipe 14 and the second oxidant supply pipe 16 are in communication with the booster rocket 12 so that the apparatus can be switched to supply the booster rocket 12.

The air outlet end of the outer duct 101 and the air outlet end of the booster rocket 12 are converged, and the air discharged from the outer duct 101 can assist in burning the fuel gas of the booster rocket 12 so as to generate driving force.

By integrating the above structure, the first fuel supply pipe 13 and the first oxidant supply pipe 15 can respectively introduce fuel and oxidant into the precombustion container 8 for oxidation reaction, high-temperature rich gas is generated, the high-temperature rich gas passes through the turbine 7, the turbine 7 is driven to rotate, the turbine 7 drives the compressor 5 to rotate through the connecting shaft 6, the air sucked by the compressor 5 is conveyed downstream, axial air flow and lateral rich gas flow are mixed in a cross way outside the expansion shrinkage cover 11, the mixing efficiency is high compared with a parallel mixing way adopting a lobe mixer, the combustion efficiency is improved, the length of the combustion chamber (which is equivalent to the length of the expansion shrinkage cover 11) can be designed to be shorter, and the length of the combustion chamber can be 0.3-0.5 m. The narrow flow passage and the wide flow passage formed between the expansion and contraction cover 11 and the inner cylinder 2 accelerate the combustion air flow, and the combustion air flow is ignited to generate detonation waves after being mixed with the oxidant and the fuel, so that power is generated.

Besides the combustion mode, air can enter from the outer duct 101 between the outer cylinder 1 and the inner cylinder 2 through the switching of the outer cylinder air inlet switch 3 and the inner cylinder air inlet switch 4, fuel and oxidant can be injected into the boosting rocket 12 through the switching of the first fuel supply pipe 13, the second fuel supply pipe 14, the first oxidant supply pipe 15 and the second oxidant supply pipe 16, mixed air flow after the reaction of the fuel and the oxidant can be sprayed out from the tail end of the boosting rocket 12, the mixed air flow and the air out of the outer duct 101 are mixed in a cross mode, the driving force is generated through combustion, the Mach number of the ATR detonation rocket combined power engine is improved, and the speed of the ATR detonation rocket combined power engine can be improved from 4Ma to 6Ma.

The expansion and contraction cover 11 may be configured such that the expansion and contraction cover 11 has an expansion portion 111 that expands in the radial direction and a contraction portion 112 that gradually contracts in the radial direction in this order along the gas flow direction. A narrow passage is formed between the expansion part 111 of the expansion and contraction cover 11 and the inner cylinder 2, so that air flow passing through the expansion and contraction cover can be accelerated, and sufficient fresh raw materials are provided for the detonation wave. An expanding channel is created between the constriction 112 and the inner barrel 2 to increase the detonation space for the combustion air flow.

The position can be the expansion portion 111 of expansion shrink cover 11 to the pre-combustion air current is discharged from expansion portion 111, and the velocity of flow of here air current is fast, is difficult for the backward flow and improves mixing efficiency, promotes factor of safety, promotes detonation combustion efficiency.

The ATR detonation rocket combination power engine may also include a second gas mixing tube 17. The pipe diameter of the second gas mixing pipe 17 is 10-20% of the pipe diameter of the first gas mixing pipe 10. The inner end of the second gas mixing pipe 17 is communicated with the pipe body of the first gas mixing pipe 10, and the outer end penetrates through the side wall of the expansion and contraction cover 11. The outer end of the second gas-mixing duct 17 is directed upstream of the gas flow with respect to the outer end of the first gas-mixing duct 10 in the direction of gas flow. The airflow velocity of the first air mixing pipe 10 exhaust is fast, the mixing distance is short, insufficient mixing can be possibly caused, the pipe diameter of the second air mixing pipe 17 is 10-20% of the pipe diameter of the first air mixing pipe 10, the second air mixing pipe 17 exhaust airflow and air are premixed, mixing efficiency is improved, and meanwhile, a high safety coefficient is maintained.

In the present embodiment, downstream refers to a position farther from the start of the flowing air stream, and upstream refers to a position closer to the start of the flowing air stream.

The ATR detonation rocket combination power engine may also include a fuel source 18 and an oxidant source 19. The fuel may be unsymmetrical dimethylhydrazine, anhydrous hydrazine or coal oil, and the oxidant may be liquid oxygen. A fuel source 18 is connected to the first fuel supply pipe 13 and the second fuel supply pipe 14, respectively. The oxidant source 19 is connected to the first oxidant supply pipe 15 and the second oxidant supply pipe 16, respectively. The present solution may select the first fuel supply pipe 13 or the second fuel supply pipe 14 to supply fuel, and may select the first oxidant supply pipe 15 or the second oxidant supply pipe 16 to supply oxidant to power the rocket 12 using ATR detonation engine or booster.

In the gas flow direction, the second fuel supply pipe 14 and the second oxidant supply pipe 16 preferably penetrate the expansion and contraction cover 11 from the upstream of the expansion portion 111 and then communicate with the booster rocket 12, so that the second fuel supply pipe 14 and the second oxidant supply pipe 16 do not interfere with the operation of the detonation wave downstream of the expansion portion 111, the detonation wave energy loss is small, and high power can be provided.

The expanding and contracting cover 11 may comprise a main cover 113 and a tail cover 114 in airtight connection. An initiating explosive device 115 is installed between the main cover 113 and the tail cover 114. The tail cap 114 may be made of a high temperature resistant and lightweight material such as silicon carbide, carbon fiber, etc. When the booster rocket 12 is switched to increase the Mach number, only one initiating explosive 115 needs to be started to trigger the initiating explosive 115 to burst off the tail cover 114, then the nozzle of the booster rocket 12 is opened, the rocket is started, and after fuel and oxidant are injected through the second fuel supply pipe 14 and the second oxidant supply pipe 16, the rocket engine starts to work to generate boosting action.

When the booster rocket 12 does not work, the outer cylinder air inlet switch 3 is closed to close the outer duct 101, the inner cylinder air inlet switch 4 is opened to open the air inlet end of the inner cylinder 2, and air flow enters the inner cylinder 2.

When the booster rocket 12 works, the outer cylinder air inlet switch 3 is opened to open the outer duct 101, the inner cylinder air inlet switch 4 is closed to close the air inlet end of the inner cylinder 2, and air flow enters the outer duct 101 between the inner cylinder 2 and the outer cylinder 1.

The combined power engine is arranged in an aircraft, and when flying, the air flow speed is high, the air inlet end cannot be completely closed, but the air inlet channel can be switched by utilizing the outer cylinder air inlet switch 3 and the inner cylinder air inlet switch 4 of the design, so that the operation difficulty is reduced.

As in fig. 3, the atr detonation rocket combination power engine may also include a cone 20. The cone 20 is installed upstream of the compressor 5 in the direction of gas flow. The ATR detonation rocket combination power engine comprises a plurality of inner cylinder air inlet switches 4. Each inner barrel air inlet switch 4 includes a first cover 401 and a first retractor 402. One end of the first cover plate 401 is hinged to the inner wall of the inner cylinder 2. The first cover 401 has a convex portion 4011 protruding toward the cone 20. One end of the first telescopic device 402 is connected to the inner wall of the inner tube 2, and the other end is hinged to the inner wall of the convex portion 4011. The plurality of first cover plates 401 can be enclosed into a cone shape after being close to each other. The cone 20 guides the air flow to the effective air guiding area of the compressor 5 to increase the air flow rate. The first cover plates 401 are close to each other and can be enclosed into a cone shape, namely, the air inlet channel of the inner cylinder 2 is closed, air can be introduced from the outer duct 101, and the necessary condition for air flow switching is provided.

Referring to fig. 2 and 4, the atr detonation rocket combination power engine may include a plurality of outer barrel air intake switches 3. Each outer cylinder air intake switch 3 includes a second cover plate 301 and a second telescopic member 302. One end of the second cover plate 301 is hinged to the inner wall of the outer cylinder 1. One end of the second telescopic device 302 is connected to the inner wall of the inner cylinder 2, and the other end is hinged to the second cover plate 301. The plurality of second cover plates 301 can be enclosed into a curved ring shape adapting to the outer duct 101 after rotating inwards, so that the plurality of second cover plates 301 can seal the outer duct 101 to enter air from the inner cylinder 2, and switching of air inlet channels is realized. The upper half of fig. 4 is a top view of a curved ring shape of the fitting outer duct 101 after the plurality of second cover plates 301 are rotated inward, and the lower half is a front view of the curved ring shape.

Referring to fig. 2, alternatively, a plurality of air outlets 102, for example four, are formed between the tail portion of the outer tub 1 and the tail portion of the inner tub 2, with the tail portion of the outer tub 1 being inwardly constricted. The ATR detonation rocket combination power engine further includes a plurality of tail gas-operated switches 21, for example, four, which are installed one by one at the plurality of gas outlets 102, referring to fig. 5, and referring to fig. 6, the tail gas-operated switches 21 may be in a shape of a curved ring sheet, for example, an arc shape in a plan view of fig. 5, and a square shape in a front view of fig. 6. Each tail pneumatic switch 21 is hinged at the tail end of the inner barrel 2 and can cover the air outlet 102 under the pushing of the air flow in the inner barrel 2 or open the air outlet 102 under the pushing of the air flow in the outer barrel 1. The tail part of the outer cylinder 1 is contracted inwards, so that the airflow laterally flows to the tail end of the boosting rocket 12 to form a cross mixing effect, and the mixing efficiency is improved. The tail pneumatic switch 21 is driven by the air flow in the inner cylinder 2 or the air flow in the outer duct 101 to close or open the outer duct 101, and other power driving parts are not needed, and the tail pneumatic switch 21 can be made of heat-resistant silicon carbide or carbon fiber and the like and can adapt to the high-temperature environment of the tail.

Optionally, the ATR detonation rocket combined power engine further comprises a flared expansion cover 22, the tail end of the expansion cover 22 is flush with the tail end of the opened tail pneumatic switch 21, the mixing effect of air flow and pre-combustion air flow is improved, and the combustion efficiency is improved.

In summary, the combined power engine of the present application eliminates the lobe mixer, and through structural optimization, the air flow and the gas-rich gas flow are cross-mixed, and the cross-mixing mode is higher in mixing efficiency than the parallel mixing mode using the lobe mixer, so that the combustion efficiency is also improved, and the length of the combustion chamber can be designed to be shorter. The booster rocket 12 and the switchable fuel supply pipe and the oxidant supply pipe are arranged, and the combustion generates driving force to promote the Mach number of the ATR detonation rocket combined power engine.

The above are only some embodiments of the present application, and the protection scope of the present application is not limited to the above embodiments, and it should be pointed out that, for a person skilled in the art, several modifications and adaptations without departing from the innovative design of the present application shall also fall within the protection scope of the present application.

Claims (10)

1. An ATR detonation rocket combined power engine is characterized by comprising an outer cylinder (1), an inner cylinder (2), an outer cylinder air inlet switch (3), an inner cylinder air inlet switch (4), a gas compressor (5), a connecting shaft (6), a turbine (7), a precombustion container (8), a core cylinder (9), a first gas mixing pipe (10), an expanding shrinkage cover (11) and a boosting rocket (12), and further comprising a first fuel supply pipe (13), a second fuel supply pipe (14), a first oxidant supply pipe (15) and a second oxidant supply pipe (16);

the outer cylinder (1) is sleeved outside the inner cylinder (2), so that an outer duct (101) is formed between the outer cylinder (1) and the inner cylinder (2); the outer cylinder air inlet switch (3) is arranged in the outer duct (101); the inner cylinder air inlet switch (4) is arranged at the air inlet end of the inner cylinder (2);

the compressor (5) and the turbine (7) are connected through the connecting shaft (6); the outer edge of the air compressor (5) is adjacent to the inner wall of the inner cylinder (2); the precombustion vessel (8) is sleeved outside the connecting shaft (6), and the precombustion vessel (8) is provided with an outlet which is communicated with the turbine (7); the first fuel supply pipe (13) and the first oxidant supply pipe (15) are respectively communicated with the precombustion vessel (8);

the core barrel (9) wraps the precombustion vessel (8) and the turbine (7); the expansion shrinkage cover (11) is wrapped outside the core barrel (9); the inner end of the first air mixing pipe (10) is communicated with the core barrel (9), and the outer end of the first air mixing pipe (10) penetrates through the side wall of the expansion shrinkage cover (11);

the boosting rocket (12) is arranged in the expanding and contracting cover (11); the tail end of the expansion and contraction cover (11) opposite to the boosting rocket (12) is provided with an opening or an openable seal;

the second fuel supply pipe (14) and the second oxidant supply pipe (16) are communicated with the boosting rocket (12); the air outlet end of the outer duct (101) is converged with the air outlet end of the boosting rocket (12).

2. An ATR detonation rocket combination power engine according to claim 1, characterized in that the expanding and contracting cowl (11) has an expanding portion (111) expanding in the radial direction and a contracting portion (112) gradually contracting in the radial direction in the gas flowing direction in this order.

3. An ATR detonation rocket combination power engine according to claim 2, characterized in that the outer end of the first gas mixing tube (10) penetrates the enlarged portion (111).

4. An ATR detonation rocket combination power engine according to claim 3, characterized in that the ATR detonation rocket combination power engine further comprises a second gas mixing pipe (17); the pipe diameter of the second gas mixing pipe (17) is 10-20% of the pipe diameter of the first gas mixing pipe (10);

the inner end of the second gas mixing pipe (17) is communicated with the pipe body of the first gas mixing pipe (10), and the outer end penetrates through the side wall of the expansion shrinkage cover (11);

the outer end of the second gas mixing pipe (17) faces upstream relative to the outer end of the first gas mixing pipe (10) along the gas flowing direction.

5. The ATR detonation rocket combination power engine according to claim 2, characterized in that it further comprises a fuel source (18) and an oxidant source (19); -said fuel source (18) being connected to said first fuel supply pipe (13) and to said second fuel supply pipe (14), respectively; the oxidant source (19) is connected to the first oxidant supply pipe (15) and the second oxidant supply pipe (16), respectively.

6. An ATR detonation rocket combination power engine according to claim 5, characterized in that the second fuel supply pipe (14) and the second oxidant supply pipe (16) each penetrate the expanding and contracting cover (11) upstream of the expanding portion (111) in the direction of gas flow and in turn communicate with the booster rocket (12).

7. ATR detonation rocket combination power engine according to any of claims 1 to 6, characterized in that the expanding and contracting cowl (11) comprises a main cowl (113) and a tail cowl (114) which are hermetically connected; an initiating explosive device (115) is arranged between the main cover (113) and the tail cover (114).

8. The ATR detonation rocket combination power engine according to claim 1, characterized in that it further comprises a rectifying cone (20); -said cone (20) is mounted upstream of said compressor (5) in the direction of gas flow;

the ATR detonation rocket combined power engine comprises a plurality of inner cylinder air inlet switches (4); each inner cylinder air inlet switch (4) comprises a first cover plate (401) and a first telescopic device (402); one end of the first cover plate (401) is hinged to the inner wall of the inner cylinder (2); the first cover plate (401) is provided with a convex surface part (4011) protruding towards the rectifying cone (20); one end of the first telescopic device (402) is connected with the inner wall of the inner cylinder (2), and the other end of the first telescopic device is hinged to the inner wall of the convex surface part (4011); the plurality of first cover plates (401) can be enclosed into a cone shape after being mutually close.

9. The ATR detonation rocket combination power engine according to claim 1, characterized in that it comprises a plurality of the outer cylinder air intake switches (3); each outer cylinder air inlet switch (3) comprises a second cover plate (301) and a second telescopic device (302); one end of the second cover plate (301) is hinged to the inner wall of the outer cylinder (1); one end of the second telescopic device (302) is connected with the inner wall of the inner cylinder (2), and the other end of the second telescopic device is hinged with the second cover plate (301); the second cover plates (301) can be surrounded into a curved ring shape which is matched with the outer duct (101) after rotating inwards.

10. The ATR detonation rocket combination power engine according to claim 1, characterized in that a plurality of air outlets (102) are formed between the tail of the outer barrel (1) and the tail of the inner barrel (2);

the ATR detonation rocket combined power engine further comprises a plurality of tail pneumatic switches (21), and the tail pneumatic switches are arranged at the air outlets (102) one by one; each tail pneumatic switch (21) is hinged to the tail end of the inner cylinder (2) and can cover the air outlet (102) under the pushing of air flow in the inner cylinder (2) or can open the air outlet (102) under the pushing of air flow in the outer cylinder (1).