CN117662325A - An 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

An ATR detonation rocket combined power engine

Technical field

The present application relates to the technical field of rocket engines, and more specifically, to an ATR detonation rocket combined power engine.

Background technique

ATR (Air Turbo Rocket) engine is an organic fusion of rocket engine and aviation turbine engine. The core components include: compressor, gas generator, turbine, lobe mixer, combustion chamber and 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 to the turbine, thereby sucking in air. The sucked air passes through the compressor and passes through the lobe mixer (petal-shaped cross-section) with the gas passing through the turbine. The mixing device) is mixed in parallel, burned in the combustion chamber, and then ejected from the tail nozzle, thereby generating reverse thrust. The ATR engine has the advantages of large thrust-to-weight ratio and high specific impulse in the low-speed section. However, it is limited by the component parameter matching of the ATR engine and the adjustment ability of the gas generator. The working Mach number of the ATR engine is low, and the use of this lobe mixer In the blending method, the combustion efficiency is low. In order to improve the combustion efficiency, it is necessary to lengthen the residence time of the fuel and oxidizer in the combustion chamber. Therefore, the combustion chamber of the ATR engine is longer, generally about 1.5 meters, making the ATR engine heavier.

Contents of the invention

In view of the fact that the ATR engine adopts the parallel mixing method of the lobe mixer, the combustion efficiency is low and the combustion chamber is long, making the ATR engine heavier. This application uses another fuel and air mixing method to remove By using a lobe mixer and improving the mixing efficiency and combustion efficiency through structural optimization to form detonation combustion to generate propulsion, the combustion chamber can be designed to be shorter. To this end, this application specifically adopts the following technical solutions.

An ATR detonation rocket combined power engine, including an outer cylinder, an inner cylinder, an air inlet switch for the outer cylinder, an air inlet switch for the inner cylinder, a compressor, a connecting shaft, a turbine, and a pre-combustion container installed in the inner cylinder , the core tube, the first air mixing tube, the expansion and contraction cover and the booster rocket, and also include a first fuel supply tube, a second fuel supply tube, a first oxidant supply tube and a second oxidant supply tube.

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 installed in the outer duct. The inner cylinder air inlet switch is installed 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 barrel. The pre-combustion container is annularly sleeved outside the connecting shaft, and the pre-combustion container has an outlet, and the outlet leads to the turbine. The first fuel supply pipe and the first oxidant supply pipe are respectively connected to the pre-combustion container.

The core barrel wraps the pre-combustion container and the turbine. The expansion and contraction cover is wrapped around the core tube. The inner end of the first air mixing pipe is connected to the core cylinder, and the outer end of the first air mixing pipe penetrates the side wall of the expansion and contraction cover.

The booster rocket is installed in the expansion and contraction cover. The expansion and contraction cover has an opening or an openable seal relative to the tail end of the booster rocket.

The second fuel supply pipe and the second oxidizer supply pipe are connected to the booster rocket. The air outlet end of the outer duct merges with the air outlet end of the booster rocket.

By adopting the above technical solution, the first fuel supply pipe and the first oxidant supply pipe can respectively introduce fuel and oxidant into the pre-combustion container, perform an oxidation reaction, and generate high-temperature fuel-rich gas. The turbine drives the turbine to rotate, and the turbine drives the compressor to rotate through the connecting shaft. The air sucked by the compressor is transported downstream. The axial air flow and the lateral fuel-rich gas flow are cross-mixed outside the expansion and contraction hood. The cross-mixing method is similar. Compared with the parallel mixing method using a lobe mixer, the mixing efficiency is high, thus improving the combustion efficiency. The length of the combustion chamber (equivalent to the length of the expansion and contraction hood) can be designed to be shorter, which can be 0.3~0.5m . The narrow flow channel and wide flow channel formed between the expansion and contraction cover and the inner cylinder first accelerate the combustion airflow, and then ignite after being mixed with the oxidant and fuel to generate a detonation wave, thereby generating power.

In addition to the above combustion methods, the air inlet switch of the outer cylinder and the inner cylinder can also be switched to allow air to enter from the outer duct between the outer cylinder and the inner cylinder through the first fuel supply pipe and the second fuel supply pipe. The switch between the first oxidizer supply pipe and the second oxidizer supply pipe can be switched to inject fuel and oxidizer into the booster rocket. The tail end of the booster rocket can eject the mixed airflow after the reaction of fuel and oxidizer, and the outer duct The air coming out is cross-mixed and burned to generate propulsion, which increases the Mach number of the ATR detonation rocket combination power engine, which can be increased from 4Ma to 6Ma.

As an improvement of the ATR detonation rocket combined power engine, the expansion and contraction cover has an expansion part that expands in the radial direction and a contraction part that gradually shrinks in the radial direction along the gas flow direction.

By adopting the above technical solution, the expansion part of the expansion-shrinking cover and the inner cylinder create a narrow channel, which can accelerate the air flow, and the contraction part and the inner cylinder create an expansion channel, which increases the detonation space for the combustion air flow.

As an improvement of the ATR detonation rocket combined power engine, the outer end of the first air mixing tube penetrates the enlarged portion.

By adopting the above technical solution, the pre-gas flow is discharged from the expansion part, where the air flow has a fast flow rate, is not easy to backflow, improves the mixing efficiency, improves the safety factor, and improves the detonation combustion efficiency.

As an improvement of the ATR detonation rocket combined power engine, the ATR detonation rocket combined power engine also includes a second air mixing tube. The diameter of the second air mixing pipe is 10% to 20% of the diameter of the first air mixing pipe. The inner end of the second air mixing pipe is connected to the body of the first air mixing pipe, and the outer end penetrates the side wall of the expansion and contraction cover. Along the gas flow direction, the outer end of the second gas mixing tube faces upstream of the gas flow relative to the outer end of the first gas mixing tube.

The air flow rate discharged from the first gas mixing pipe is fast and the mixing distance is short, which may result in insufficient mixing. By adopting the above technical solution, the diameter of the second gas mixing pipe is set to be 10 times the diameter of the first gas mixing pipe. ~20%, the air flow discharged from the second air mixing pipe is premixed with the air to improve the mixing efficiency while maintaining a high safety factor.

It should be noted that the downstream mentioned above refers to a position far away from the starting end of the flowing airflow, and the upstream refers to a position relatively close to the starting end of the flowing airflow.

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

By adopting the above technical solution, the first fuel supply pipe or the second fuel supply pipe can be selected to pass in fuel, and the first oxidant supply pipe or the second oxidant supply pipe can be selected to pass in oxidant, Powered by ATR detonation engines or booster rockets.

As an improvement of the ATR detonation rocket combined power engine, in the gas flow direction, the second fuel supply pipe and the second oxidant supply pipe both penetrate the expansion and contraction from the upstream of the expansion part. The shroud is in turn connected to the booster rocket.

By adopting the above technical solution, the second fuel supply pipe and the second oxidant supply pipe will not interfere with the operation of the detonation wave downstream of the enlarged portion, resulting in less energy loss of the detonation wave and providing higher power.

As an improvement of the ATR detonation rocket combined power engine, the expansion and contraction cover includes a main cover and a tail cover that are hermetically connected. A pyrotechnic product is installed between the main cover and the tail cover.

By adopting the above technical solution, when you want to switch the booster rocket to increase the Mach number, you only need to trigger the pyrotechnics through a pyrotechnics igniter and blow up the tail cover. Then the nozzle of the booster rocket is opened, and the rocket is started. After the second fuel supply pipe and the second oxidizer supply pipe are injected with fuel and oxidizer, the rocket engine starts to work to produce a boosting effect.

As an improvement of the ATR detonation rocket combined power engine, the ATR detonation rocket combined power engine also includes a rectifying cone. In the gas flow direction, the rectifying cone is installed upstream of the compressor. The ATR detonation rocket combined power engine includes a plurality of inner cylinder air intake switches. Each inner cylinder air inlet switch includes a first cover plate and a first telescopic device. One end of the first cover is hinged on the inner wall of the inner cylinder. The first cover plate has a convex portion protruding toward the rectifying cone. One end of the first telescopic device is connected to the inner wall of the inner cylinder, and the other end is hinged to the inner wall of the convex portion. The plurality of first cover plates can form a cone shape after being close to each other.

By adopting the above technical solution, the rectifying cone can guide the air flow to the effective air guiding area of the compressor and increase the air circulation. The plurality of first cover plates can form a cone shape when they are close to each other, that is, the air inlet channel of the inner cylinder is closed, and air can be taken in from the outer bypass, which provides the necessary conditions for air flow switching.

As an improvement of the ATR detonation rocket combined power engine, the ATR detonation rocket combined power engine includes a plurality of outer cylinder air intake switches. Each outer cylinder air inlet switch includes a second cover plate and a second retractor. One end of the second cover is hinged on 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 is hinged to the second cover. The plurality of second cover plates can be rotated inward to form a curved ring shape suitable for the outer duct.

By adopting the above technical solution, a plurality of second cover plates can block the outer duct to allow air to be taken in from the inner cylinder, thereby realizing switching of the air inlet channels.

As an improvement of the ATR detonation rocket combined power engine, multiple air outlets are formed between the tail of the outer cylinder and the tail of the inner cylinder. The ATR detonation rocket combined power engine also includes a plurality of tail pneumatic switches, which are installed at the plurality of air outlets one by one. Each of the tail pneumatic switches is hinged at the tail end of the inner cylinder and can cover the air outlet driven by the air flow in the inner barrel or open the air outlet driven by the air flow in the outer barrel.

By adopting the above technical solution, the tail of the outer barrel shrinks inward, causing the airflow to flow sideways to the tail end of the booster rocket, forming a cross-mixing effect and improving the mixing efficiency. The tail pneumatic switch is driven by the air flow in the inner cylinder or the air flow in the outer duct to close or open the outer duct. It does not require other power driving parts. The tail pneumatic switch can be made of heat-resistant silicon carbide or carbon fiber, which can adapt to the tail. high temperature environment.

To sum up, the ATR detonation rocket combined power engine of this application has the following beneficial effects:

The axial air flow in the inner cylinder is cross-mixed with the gas-rich gas flow discharged laterally from the core cylinder and the expansion and contraction cover. Compared with the parallel mixing method using a lobe mixer, the cross-mixing method has high mixing efficiency and thus improves In order to improve combustion efficiency, the length of the combustion chamber (equivalent to the length of the expansion and contraction hood) can be designed to be shorter.

The narrow flow channel and wide flow channel formed between the expansion and contraction cover and the inner cylinder first accelerate the combustion airflow at high pressure, and the combustion airflow burns rapidly and expands to generate sonic detonation waves, and then expands to generate supersonic detonation waves, thereby generating power.

By switching the first fuel supply pipe, the second fuel supply pipe, the first oxidizer supply pipe and the second oxidizer supply pipe, it is possible to switch to injecting fuel and oxidizer into the booster rocket, and the tail end of the booster rocket can eject fuel and oxidizer. The mixed airflow after the oxidant reaction cross-mixes with the air coming out of the outer duct, and burns to generate propulsion, which increases the Mach number of the ATR detonation rocket combined power engine.

Description of drawings

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

Figure 2 is another state diagram of the ATR detonation rocket combined power engine of Figure 1.

Figure 3 is a schematic top view of multiple inner cylinder air inlet switches that are close to each other and form a cone shape.

Figure 4 is a schematic top view and a front view of a plurality of outer cylinder air inlet switches that are close to each other and form a curved ring shape.

Figure 5 is a top view of multiple tail pneumatic switches.

FIG. 6 is a schematic front view of multiple tail pneumatic switches of FIG. 5 .

Reference signs: outer cylinder 1, inner cylinder 2, outer cylinder air inlet switch 3, inner cylinder air inlet switch 4, compressor 5, connecting shaft 6, turbine 7, pre-combustion container 8, core cylinder 9, first air mixing pipe 10. Expansion and contraction cover 11, booster rocket 12, first fuel supply pipe 13, second fuel supply pipe 14, first oxidant supply pipe 15, second oxidant supply pipe 16, outer duct 101, expansion part 111, contraction part 112, the second mixing pipe 17, the fuel source 18, the oxidant source 19, the main cover 113, the tail cover 114, the pyrotechnics 115, the rectifying cone 20, the first cover 401, the first telescopic device 402, the convex portion 4011, The second cover 301, the second retractor 302, the air outlet 102, the tail pneumatic switch 21, and the expansion cover 22.

Detailed ways

The ATR detonation rocket combined power engine of the present application will be described in detail below with reference to the accompanying drawings.

As shown in Figures 1 and 2, an ATR detonation rocket combined power engine includes an outer cylinder 1, an inner cylinder 2, an outer cylinder air inlet switch 3, an inner cylinder air inlet switch 4, and a compressed air compressor installed in the inner cylinder 2. Machine 5, connecting shaft 6, turbine 7, pre-combustion container 8, core barrel 9, first mixing pipe 10, expansion and contraction cover 11 and booster rocket 12, also includes a first fuel supply pipe 13, a second fuel supply pipe 14 , the first oxidant supply pipe 15 and the second oxidant supply pipe 16 .

The arrows in Figures 1 and 2 indicate the direction of air flow. Figure 1 is a state diagram when the outer cylinder air inlet switch 3 is closed and the inner cylinder air inlet switch 4 is open. Figure 2 is a state diagram when the air inlet switch 3 of the outer cylinder is turned on and the air inlet switch 4 of the inner cylinder is closed.

The outer cylinder 1 is placed 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 installed in the outer duct 101 to control the air flow interruption at the air inlet end of the outer duct 101. The inner cylinder air inlet switch 4 is installed at the air inlet end of the inner cylinder 2 to control the air flow interruption 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 cylinder 2 to suck in enough air.

The pre-combustion container 8 is ring-enclosed outside the connecting shaft 6. The pre-combustion container 8 has an outlet, and the outlet leads to the turbine 7 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 connected to the pre-combustion container 8. More fuel and less oxidant are oxidized in the pre-combustion container 8, resulting in a pre-combustion effect. At this time, there is still a lot of fuel. After being cracked by high temperature and not fully burned, the pre-combustion gas acts as a fully burned raw material.

The core barrel 9 wraps the pre-combustion container 8 and the turbine 7 . The expansion and contraction cover 11 is wrapped around the end of the core tube 9 . The inner end of the first gas mixing pipe 10 is connected to the core cylinder 9, and the outer end penetrates the side wall of the expansion and contraction cover 11 to lead the pre-gas in the core cylinder 9 to the cavity of the inner cylinder 2, where it mixes with the air flow and explodes.

The booster rocket 12 is installed in the expansion and contraction cover 11. The booster rocket 12 can provide boosting force and increase the Mach number of the combined power engine.

The expansion and contraction cover 11 has an opening or an openable seal relative to the rear end of the booster rocket 12 to provide a jet passage for the booster rocket 12 .

The second fuel supply pipe 14 and the second oxidizer supply pipe 16 are connected to the booster rocket 12 so that the device can switch to supply fuel to the booster rocket 12 .

The air outlet end of the outer duct 101 merges with the air outlet end of the booster rocket 12, and the air discharged from the outer duct 101 can assist in burning the gas of the booster rocket 12 to generate propulsion.

Based on the above structure, the first fuel supply pipe 13 and the first oxidant supply pipe 15 can respectively introduce fuel and oxidant into the pre-combustion container 8 to perform an oxidation reaction to generate high-temperature fuel-rich gas. The high-temperature fuel-rich gas passes through the turbine 7 to drive The turbine 7 rotates, and the turbine 7 drives the compressor 5 to rotate through the connecting shaft 6. The compressor 5 inhales air and sends it downstream. The axial air flow and the lateral fuel-rich gas flow are cross-mixed outside the expansion and contraction hood 11. The cross-mixing method is similar. Compared with the parallel mixing method using a lobe mixer, the mixing efficiency is high, thus improving the combustion efficiency. The length of the combustion chamber (equivalent to the length of the expansion and contraction cover 11) can be designed to be shorter, which can be 0.3~0.5 m. The narrow flow channel and the wide flow channel formed between the expansion and contraction cover 11 and the inner cylinder 2 first accelerate the combustion air flow, and then ignite after being mixed with the oxidant and fuel to generate a detonation wave, thereby generating power.

In addition to the above combustion method, the air can also be switched between the outer cylinder air inlet switch 3 and the inner cylinder air inlet switch 4 to allow air to enter from the outer duct 101 between the outer cylinder 1 and the inner cylinder 2 through the first fuel supply pipe. 13. The switching of the second fuel supply pipe 14, the first oxidizer supply pipe 15 and the second oxidizer supply pipe 16 can be switched to inject fuel and oxidizer into the booster rocket 12, and the tail end of the booster rocket 12 can eject fuel and oxidizer. The mixed airflow after the oxidant reaction is cross-mixed with the air coming out of the outer duct 101, and burned to generate propulsion, which increases the Mach number of the ATR detonation rocket combined power engine, which can be increased from 4 Ma to 6 Ma.

The structure of the expansion and contraction cover 11 may be such that along the gas flow direction, the expansion and contraction cover 11 has an expansion portion 111 that expands in the radial direction and a contraction portion 112 that gradually shrinks in the radial direction. A narrow channel is created between the expanded portion 111 of the expansion-contraction cover 11 and the inner cylinder 2, which can accelerate the passing airflow and provide sufficient fresh raw materials for the detonation wave. An expansion channel is created between the constriction part 112 and the inner cylinder 2 to increase the detonation space for the combustion gas flow.

The location can be the expansion part 111 of the expansion and contraction cover 11 to discharge the pre-gas flow from the expansion part 111. The gas flow here is fast and difficult to backflow, thereby improving the mixing efficiency, safety factor, and detonation combustion efficiency.

The ATR detonation rocket combined power engine may also include a second mixing tube 17 . The diameter of the second air-mixing pipe 17 is 10-20% of the diameter of the first air-mixing pipe 10 . The inner end of the second air mixing pipe 17 is connected to the body of the first air mixing pipe 10 , and the outer end penetrates the side wall of the expansion and contraction cover 11 . Along the gas flow direction, the outer end of the second gas mixing pipe 17 is facing upstream of the gas flow relative to the outer end of the first gas mixing pipe 10 . The airflow discharged from the first gas mixing pipe 10 has a fast flow rate and a short mixing distance, which may result in insufficient mixing. The diameter of the second gas mixing pipe 17 is set to be 10~20% of the diameter of the first gas mixing pipe 10. The air flow discharged from the air pipe 17 is premixed with air to improve the mixing efficiency while maintaining a high safety factor.

It should be noted that the downstream in this embodiment refers to a position far away from the starting end of the flowing airflow, and the upstream refers to a position relatively close to the starting end of the flowing airflow.

The ATR detonation rocket combined power engine may also include a fuel source 18 and an oxidizer source 19 . The fuel can be unbiased dimethylhydrazine, anhydrous hydrazine or kerosene, etc., and the oxidant can be liquid oxygen. The 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. In this solution, the first fuel supply pipe 13 or the second fuel supply pipe 14 can be selected to pass in the fuel, and the first oxidant supply pipe 15 or the second oxidant supply pipe 16 can be selected to pass in the oxidant, so as to use the ATR detonation engine or the auxiliary engine. Push rocket 12 to provide power.

Along the gas flow direction, the second fuel supply pipe 14 and the second oxidant supply pipe 16 preferably both penetrate the expansion and contraction cover 11 from the upstream of the expansion part 111 and then communicate with the booster rocket 12, so that the second fuel supply pipe 14 and The second oxidant supply pipe 16 will not interfere with the operation of the detonation wave downstream of the enlarged portion 111, resulting in less energy loss of the detonation wave and providing higher power.

The expansion and contraction cover 11 may include a main cover 113 and a tail cover 114 that are hermetically connected. A pyrotechnic product 115 is installed between the main cover 113 and the tail cover 114 . The tail cover 114 can be made of high temperature resistant and lightweight materials such as silicon carbide, carbon fiber, etc. When you want to switch the booster rocket 12 to increase the Mach number, you only need to trigger the pyrotechnics 115 through a pyrotechnics 115 igniter, blow up the tail cover 114, and then the nozzle of the booster rocket 12 is opened, and the rocket starts. After the second fuel supply pipe 14 and the second oxidizer supply pipe 16 are injected with fuel and oxidizer, the rocket engine starts to work to produce a boosting effect.

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

When the booster rocket 12 is working, open the outer cylinder air inlet switch 3 to open the outer duct 101, close the inner cylinder air inlet switch 4 to close the air inlet end of the inner cylinder 2, and the air flow enters the space between the inner cylinder 2 and the outer cylinder 1. In Waihan Road 101.

The combined power engine is installed in the aircraft. When flying, the air flow speed is fast and the air inlet end cannot be completely closed. However, the outer cylinder air inlet switch 3 and the inner cylinder air inlet switch 4 of this design can be used to switch the air inlet channel, which reduces the Operational difficulty.

As shown in Figure 3, the ATR detonation rocket combined power engine may also include a rectifying cone 20. The rectifying cone 20 is installed upstream of the compressor 5 in the gas flow direction. The ATR detonation rocket combined power engine includes multiple inner cylinder air intake switches 4. Each inner cylinder air inlet switch 4 includes a first cover 401 and a first retractor 402 . One end of the first cover 401 is hinged on the inner wall of the inner cylinder 2 . The first cover 401 has a convex portion 4011 protruding toward the rectifying cone 20 . One end of the first telescopic device 402 is connected to the inner wall of the inner cylinder 2 , and the other end is hinged to the inner wall of the convex portion 4011 . The plurality of first cover plates 401 can form a cone shape after being close to each other. The rectifying cone 20 can guide the air flow to the effective air guiding area of the compressor 5 to increase the air circulation. The plurality of first cover plates 401 can form a cone shape after being close to each other, that is, the air inlet channel of the inner cylinder 2 is closed, and air can be taken in from the outer duct 101, which provides the necessary conditions for air flow switching.

Combining Figures 2 and 4, the ATR detonation rocket combined power engine may include multiple outer cylinder air intake switches 3. Each outer cylinder air inlet switch 3 includes a second cover 301 and a second retractor 302 . One end of the second cover 301 is hinged on 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 301 . The plurality of second cover plates 301 can be formed into a curved ring shape suitable for the outer duct 101 after being rotated inward, so that the plurality of second cover plates 301 can block the outer duct 101 to allow air intake from the inner cylinder 2 to achieve air intake. Switching of air channels. The upper part of FIG. 4 is a top view of a plurality of second cover plates 301 that are rotated inward to form a curved ring shape adapted to the outer duct 101 , and the lower part is a front view of the curved ring shape.

Referring to FIG. 2 , optionally, multiple air outlets 102 are formed between the tail portion of the outer cylinder 1 and the inner cylinder 2 , such as four. The ATR detonation rocket combined power engine also includes a plurality of tail pneumatic switches 21. Refer to Figure 5. For example, there are four, which are installed at the multiple air outlets 102 one by one. Refer to Figure 6. The shape of the tail pneumatic switch 21 can be a curved ring piece. Shape, as shown in Figure 5, it is arc-shaped when viewed from above, and it is square when viewed from the front, as shown in Figure 6. Each tail pneumatic switch 21 is hinged at the rear end of the inner cylinder 2 and can cover the air outlet 102 driven by the air flow in the inner barrel 2 or open the air outlet 102 driven by the air flow in the outer barrel 1 . The tail of the outer cylinder 1 shrinks inward, causing the airflow to flow sideways to the tail end of the booster rocket 12, forming a cross-mixing effect and improving the mixing efficiency. 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. No other power driving parts are required, and the tail pneumatic switch 21 can be made of heat-resistant silicon carbide or carbon fiber. Made of other materials, it can adapt to the high temperature environment of the tail.

Optionally, the ATR detonation rocket combined power engine also includes a trumpet-shaped expansion cover 22. The end of the expansion cover 22 is flush with the end of the opened tail pneumatic switch 21 to improve the mixing effect of the air flow and the pre-gas flow. Improve combustion efficiency.

To sum up, the combined power engine of this application removes the lobe mixer, and through structural optimization, the air flow and the fuel-rich gas flow are cross-mixed. Compared with the parallel mixing method using the lobe mixer, the cross-mixing method The mixing efficiency is high, which also improves the combustion efficiency, and the length of the combustion chamber can be designed to be shorter. Install booster rocket 12 and switchable fuel supply pipes and oxidizer supply pipes to generate propulsion through combustion and increase the Mach number of the ATR detonation rocket combined power engine.

The above are only some embodiments of the present application. The protection scope of the present application is not limited to the above-mentioned embodiments. It should be pointed out that for those of ordinary skill in this technical field, several improvements and improvements can be made without departing from the creative design of the present application. Retouching should also fall within the scope of protection of this 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).