Rotary detonation afterburner system capable of regulating and controlling jet temperature of aviation kerosene

Abstract

The invention relates to the field of aero-engines, and provides a rotary detonation afterburner system capable of regulating and controlling the injection temperature of aviation kerosene, which comprises a rotary detonation afterburner, a fuel tank, an oxygen bottle, a first fuel supply pipeline, a second fuel supply pipeline and a first gas supply pipeline, a first channel is arranged in the side wall of the rotary detonation afterburner, the fuel tank is communicated with the first channel through a first oil supply pipeline, and the first channel is communicated with the interior of the rotary detonation afterburner through a second oil supply pipeline; the oxygen bottle communicates with the interior of the rotary detonation afterburner through a first gas supply pipeline, and the oxygen bottle is used for supplying oxygen to the interior of the rotary detonation afterburner in the detonation stage of the rotary detonation afterburner. The rotary detonation afterburner solves the problem that the rotary detonation afterburner is difficult to detonate and maintain.

Description

Technical Field

[0001] This application relates to the field of aeroengines, and particularly to a rotating detonation afterburner system capable of regulating the injection temperature of aviation kerosene. Background Art

[0002] The afterburner is an important component of a turbofan engine, which can significantly improve the thrust performance of the engine and enable high-difficulty flight maneuvers of the aircraft.

[0003] The inflow conditions of the afterburner are relatively complex. The gas after combustion in the main combustion chamber has a low oxygen content, and the radial flow of the gas is uneven when it is introduced into the afterburner through the turbine. These characteristics pose certain difficulties to the successful initiation and maintenance of the rotating detonation afterburner. Although oxygen supplementation to the rotating detonation afterburner can help with the successful initiation of rotating detonation, during the continuous flight of the aircraft, the demand for oxygen is too large, and the method of carrying a large number of oxygen cylinders for high-speed aircraft is not feasible for engineering applications. Therefore, it is difficult to meet the continuous operation requirements of the rotating detonation afterburner. Summary of the Invention

[0004] In order to solve the problems of difficult initiation and maintenance existing in the rotating detonation afterburner, this application provides a rotating detonation afterburner system capable of regulating the injection temperature of aviation kerosene.

[0005] The rotating detonation afterburner system capable of regulating the injection temperature of aviation kerosene provided by this application adopts the following technical solutions: A rotating detonation afterburner system capable of regulating the injection temperature of aviation kerosene includes a rotating detonation afterburner, a fuel tank, an oxygen cylinder, a first fuel supply pipeline, a second fuel supply pipeline, and a first gas supply pipeline; A first channel is provided inside the side wall of the rotating detonation afterburner. The fuel tank is connected to the first channel through the first fuel supply pipeline, and the first channel is connected to the inside of the rotating detonation afterburner through the second fuel supply pipeline; The oxygen cylinder is connected to the inside of the rotating detonation afterburner through the first gas supply pipeline, and the oxygen cylinder is used to supply oxygen to the inside of the rotating detonation afterburner during the initiation stage of the rotating detonation afterburner.

[0006] By adopting the above technical solution, the oxygen cylinder meets the oxygen supply requirement during the detonation initiation of the rotating detonation afterburner. After the detonation is completed, the high temperature generated by combustion can heat the aviation kerosene in the first channel, so that the aviation kerosene can be quickly ignited and fully burned after entering the rotating detonation afterburner, reducing the residue of unburned hydrocarbons, improving the effective utilization rate of oxygen, and then reducing the requirement for oxygen content. As a result, even if the oxygen cylinder stops supplying oxygen subsequently, the vacuum kerosene can still burn stably and fully, maintaining the working state of the rotating detonation afterburner. In addition, the vacuum kerosene can absorb heat when flowing through the first channel, helping to cool down the rotating detonation afterburner.

[0007] Optionally, the rotating detonation afterburner system capable of regulating the injection temperature of aviation kerosene further includes a gas supply assembly and a second gas supply pipeline; The gas supply assembly is connected to the inside of the rotating detonation afterburner through the second gas supply pipeline, and the gas supply assembly is used to introduce air into the inside of the rotating detonation afterburner.

[0008] By adopting the above technical solution, the introduction of the gas supply assembly and the second gas supply pipeline enables the rotating detonation afterburner to continuously obtain air supply during operation, thus effectively improving the combustion efficiency and stability. Specifically: Since the oxygen content requirement for maintaining the stable operation of the rotating detonation afterburner is reduced after preheating the aviation kerosene, the stable operation of the rotating detonation afterburner can be maintained only by introducing air, and there is no need to supply oxygen through the oxygen cylinder anymore.

[0009] Optionally, the gas supply assembly includes a compressor.

[0010] By adopting the above technical solution, the gas supply assembly includes a compressor. The compressor can meet the cooling requirement of the rotating detonation afterburner by introducing high-pressure air into it, and the compressor is originally one of the components of the aeroengine. Selecting the compressor as the gas supply assembly does not require additional cost.

[0011] The introduction of high-pressure air helps to maintain a stable rotating detonation wave, ensuring the continuity and reliability of the combustion process.

[0012] By precisely controlling the high-pressure air, the temperature and pressure in the combustion chamber can be better regulated, the combustion conditions can be optimized, and the pollutant emissions can be reduced.

[0013] Optionally, a second channel is further provided inside the side wall of the rotating detonation afterburner. The second channel has a connecting part, and the second channel is connected to the inside of the rotating detonation afterburner through the connecting part; The air supply component is communicated with the second channel through the second air supply pipeline.

[0014] By adopting the above technical solution, the working performance of the rotating detonation afterburner can be improved. Specifically: When the high-pressure air flows through the second channel, it can help cool the high-temperature wall surface of the rotating detonation afterburner, thereby reducing the cooling requirement of the rotating detonation afterburner. Compared with traditional engines, the amount of air required to cool the rotating detonation afterburner is reduced, and thus more air can flow through the main combustion chamber and the turbine and then be introduced into the rotating detonation afterburner, thereby improving the propulsion efficiency of the engine.

[0015] After the high-pressure air enters the interior of the rotating detonation afterburner, it can form an air film between the flame and the inner wall of the rotating detonation afterburner, thereby playing a heat insulation role.

[0016] Optionally, the second channel is located inside the first channel, and the communication part includes mixing holes.

[0017] By adopting the above technical solution, the second channel is located inside the first channel, so that the first channel and the second channel can form a double-layer heat absorption and cooling structure. By controlling the air intake volume of the second channel, the heat used to heat the aviation kerosene in the first channel can be regulated, and thus the aviation kerosene injection temperature of the rotating detonation afterburner can be controlled. The air in the second channel enters the rotating detonation afterburner through the mixing holes, which is not only convenient in structural setting, but also helps the air to enter the rotating detonation afterburner at an appropriate pressure and be fully mixed with the aviation kerosene.

[0018] Optionally, the rotating detonation afterburner has an annular side wall, and both the first channel and the second channel are arranged inside the annular side wall; The number of the mixing holes is multiple, and the multiple mixing holes are uniformly distributed on the annular side wall.

[0019] By adopting the above technical solution, the rotating detonation afterburner has an annular side wall, and both the first channel and the second channel are arranged inside the annular side wall, so that the aviation kerosene in the first channel and the high-pressure air in the second channel can fully and uniformly absorb heat, improving the preheating effect of the aviation kerosene and the cooling effect on the rotating detonation afterburner. The multiple mixing holes are uniformly distributed on the annular side wall, which can ensure the full mixing of the high-pressure air and the fuel, thereby improving the combustion efficiency and stability.

[0020] Optionally, the rotating detonation afterburner system capable of regulating the aviation kerosene injection temperature further includes an atomizing nozzle, and the atomizing nozzle is connected to the second fuel supply pipeline and is used for injecting aviation kerosene into the rotating detonation afterburner.

[0021] By adopting the above technical solution, the atomizing nozzle is connected to the second fuel supply pipeline and injects aviation kerosene with adjustable temperature into the rotating detonation afterburning chamber, which can effectively improve the atomization effect of the fuel, thereby enhancing the mixing degree of the fuel and the oxidant, and improving the combustion efficiency and stability.

[0022] Optionally, the rotating detonation afterburning chamber system for injecting aviation kerosene with adjustable temperature satisfies one of the following conditions: ① The atomizing nozzle is located at the end of the rotating detonation afterburning chamber; ② The rotating detonation afterburning chamber has an annular side wall, the first channel is arranged inside the annular side wall, and a plurality of nozzle groups are arranged on the inner side of the annular side wall. The plurality of nozzle groups are evenly spaced along the axial direction of the rotating detonation afterburning chamber. Each nozzle group includes a plurality of the atomizing nozzles evenly spaced in the circumferential direction.

[0023] By adopting the above technical solution, when the atomizing nozzle is located at the end of the rotating detonation afterburning chamber, the setting of the second fuel supply pipeline and the atomizing nozzle is more convenient. When the rotating detonation afterburning chamber has an annular side wall, the first channel is arranged inside the annular side wall, and a plurality of nozzle groups are arranged on the inner side of the annular side wall, multi-point uniform injection of fuel can be realized, further improving the combustion uniformity and combustion efficiency, reducing local overheating at the same time, and prolonging the service life of the equipment.

[0024] Optionally, the rotating detonation afterburning chamber system for injecting aviation kerosene with adjustable temperature further includes a main combustion chamber, a third fuel supply pipeline, a first valve, a second valve and a third valve; The first channel is communicated with the main combustion chamber through the third fuel supply pipeline; The first valve is arranged on the first fuel supply pipeline, the second valve is arranged on the second fuel supply pipeline, and the third valve is arranged on the third fuel supply pipeline.

[0025] By adopting the above technical solution, effective control of the fuel supply path can be achieved. Specifically: The first valve is arranged on the first fuel supply pipeline, and the fuel supply amount from the fuel tank to the first channel of the rotating detonation afterburning chamber can be accurately adjusted, thereby ensuring the stability and reliability of the fuel supply.

[0026] The second valve is arranged on the second fuel supply pipeline and is used to control the fuel flow in the first channel into the rotating detonation afterburning chamber, further improving the controllability of the fuel injection.

[0027] The third valve is arranged on the third fuel supply pipeline, enabling the first channel to communicate with the main combustion chamber through the third fuel supply pipeline, achieving flexible distribution of fuel between different combustion regions and enhancing the overall efficiency and adaptability of the system.

[0028] Optionally, the rotatable detonation afterburner combustion chamber system capable of regulating the injection temperature of aviation kerosene further includes a fourth fuel supply pipeline and a fourth valve. The fuel tank communicates with the main combustion chamber through the fourth fuel supply pipeline, and the fourth valve is arranged on the fourth fuel supply pipeline.

[0029] By adopting the above technical solution, the arrangement of the fourth fuel supply pipeline and the fourth valve enables the fuel tank to directly supply fuel to the main combustion chamber, improving the flexibility and reliability of the system. The fourth valve can control the fuel flow rate to ensure stable fuel supply under different working conditions, thereby optimizing the combustion efficiency and performance.

[0030] In summary, the present application includes at least one of the following beneficial technical effects: 1. By arranging the first channel, preheating of aviation kerosene before entering the rotatable detonation afterburner combustion chamber is achieved, reducing the requirement for oxygen content when the rotatable detonation afterburner combustion chamber maintains stable operation; 2. The oxygen cylinder supplies oxygen to the rotatable detonation afterburner combustion chamber through the first air supply pipeline during the detonation initiation stage, enhancing the intensity of the initial combustion reaction and facilitating detonation; 3. The aviation kerosene in the first channel, the high-pressure gas in the second channel, and the gas film formed by the high-pressure gas can constitute a multi-layer cooling structure to help cool the rotatable detonation afterburner combustion chamber; 4. Since the aviation kerosene in the first channel absorbs a part of the combustion chamber heat, the requirement for the high-pressure gas in the second channel is reduced, enabling more high-pressure air to participate in combustion through the main combustion chamber and improving the engine propulsion efficiency.

[0031] 5. By controlling the gas volume of the high-pressure gas in the second channel, the temperature of the aviation kerosene injected into the combustion chamber through the aviation kerosene in the first channel can be controlled. By controlling the appropriate temperature of the aviation kerosene, the requirement for the incoming flow oxygen content is reduced, and the combustion efficiency is improved. Description of the Drawings

[0032] Figure 1 is a circuit diagram of the fuel and gas path of a rotatable detonation afterburner combustion chamber system capable of regulating the injection temperature of aviation kerosene provided by the present application.

[0033] Figure 2 is a partial structural schematic diagram of the rotatable detonation afterburner combustion chamber of a rotatable detonation afterburner combustion chamber system capable of regulating the injection temperature of aviation kerosene provided by the present application.

[0034] Figure 3 This is provided by the present application Figure 2 An enlarged schematic view of location A in

[0035] Explanation of reference numerals: 1. Air supply assembly; 2. Main combustion chamber; 3. Rotating detonation afterburner; 301. First channel; 302. Second channel; 303. Mixing holes; 4. Fuel tank; 5. Oxygen cylinder; 6. First fuel supply pipeline; 7. Second fuel supply pipeline; 8. Third fuel supply pipeline; 9. Fourth fuel supply pipeline; 10. First air supply pipeline; 11. Second air supply pipeline; 12. Atomizing nozzle; 13. First valve; 14. Second valve; 15. Third valve; 16. Fourth valve. Detailed implementation manners

[0036] The following further elaborates on the present application in conjunction with the Figures 1 to 3 accompanying drawings.

[0037] As Figures 1 to 3 shown, an embodiment of the present application discloses a rotating detonation afterburner system capable of regulating the injection temperature of aviation kerosene, including: an air supply assembly 1, a main combustion chamber 2, a turbine, a rotating detonation afterburner 3, a fuel tank 4, an oxygen cylinder 5, a first fuel supply pipeline 6, a second fuel supply pipeline 7, a third fuel supply pipeline 8, a fourth fuel supply pipeline 9, a first air supply pipeline 10, and a second air supply pipeline 11.

[0038] Specifically, the fuel tank 4 is used to store the fuel (aviation kerosene) required for the main combustion chamber 2 and the rotating detonation afterburner 3. The fuel tank 4 is connected to the main combustion chamber 2 through the fourth fuel supply pipeline 9. When the rotating detonation afterburner 3 does not need to operate, the fuel tank 4 supplies fuel to the main combustion chamber 2 through the fourth fuel supply pipeline 9.

[0039] The oxygen cylinder 5 is connected to the inside of the rotating detonation afterburner 3 through the first air supply pipeline 10. When the rotating detonation afterburner 3 needs to operate, oxygen can be supplied to the inside of the rotating detonation afterburner 3 through the oxygen cylinder 5, thereby facilitating the successful detonation of the rotating detonation afterburner 3.

[0040] The rotating detonation afterburner 3 can be of a cylindrical structure. A first channel 301 and a second channel 302 are provided inside the annular side wall thereof. Both the first channel 301 and the second channel 302 can be annular chambers, and the second channel 302 is located inside the first channel 301.

[0041] The fuel tank 4 is connected to the first channel 301 through the first fuel supply pipeline 6, and the first channel 301 is connected to the interior of the rotating detonation afterburner 3 through the second fuel supply pipeline 7. The fuel in the fuel tank 4 first enters the first channel 301 and then enters the rotating detonation afterburner 3. A large amount of heat generated after the fuel in the rotating detonation afterburner 3 burns can preheat the fuel in the first channel 301. The preheating can enable the fuel to burn fully, reduce the amount of oxygen consumed by incomplete combustion, and lower the requirement for the supplied oxygen content. Secondly, the preheating can reduce the viscosity of the fuel, so that the fuel can be atomized into smaller droplets after entering the interior of the rotating detonation afterburner 3, which is convenient for the fuel to mix and contact with oxygen fully, improve the combustion efficiency, and also helps to lower the requirement for the supplied oxygen content.

[0042] The air supply component 1 is connected to the second channel 302 through the second air supply pipeline 11. The second channel 302 has a connecting part, and the second channel 302 is connected to the interior of the rotating detonation afterburner 3 through the connecting part. The air supply component 1 is used to introduce air (specifically high-pressure air) into the second channel 302, and the high-pressure air in the second channel 302 enters the interior of the rotating detonation afterburner 3 through the connecting part. When the high-pressure air flows through the second channel 302, it can cool the rotating detonation afterburner 3. And by controlling the amount of high-pressure air introduced into the second channel 302, the temperature of the fuel entering the rotating detonation afterburner 3 through the first channel 301 can be adjusted.

[0043] Since the injection temperature is suitable for rapid atomization and mixing after fuel preheating, the requirement for the supplied oxygen content is reduced. Therefore, even if the oxygen cylinder 5 stops supplying oxygen and only the oncoming flow is supplied through the core engine (including the compressor, the main combustion chamber 2, and the turbine), the rotating detonation afterburner 3 can still operate stably, which helps to reduce the oxygen consumption in the oxygen cylinder 5, so that the aircraft does not need to carry a large number of oxygen cylinders 5. At the same time, due to the cooling effect of the aviation kerosene in the first channel on the combustion chamber, the amount of high-pressure air introduced for cooling the rotating detonation afterburner 3 is reduced, so that more high-pressure air generated by the compressor can enter the rotating detonation afterburner 3 after flowing through the main combustion chamber 2 and the turbine in sequence, which is beneficial to improving the propulsion efficiency of the engine.

[0044] Among them, an atomizing nozzle 12 can be set to be connected to the second fuel supply pipeline 7, and fuel is injected into the rotating detonation afterburner 3 through the atomizing nozzle 12, which helps the fuel to be atomized fully and thus improve the combustion efficiency.

[0045] For example, the atomizing nozzle 12 can be located at the end of the rotating detonation afterburner 3 on the side close to the main combustion chamber 2, and the number of the atomizing nozzles 12 can be multiple, and the multiple atomizing nozzles 12 are arranged at equal intervals circumferentially.

[0046] For another example, a plurality of nozzle groups are provided on the inner side of the annular side wall of the rotating detonation afterburner combustion chamber 3, and the plurality of nozzle groups are evenly spaced along the axial direction of the rotating detonation afterburner combustion chamber 3. The nozzle groups include a plurality of atomizing nozzles 12 evenly spaced along the circumferential direction. By jointly injecting fuel through the plurality of atomizing nozzles 12, the fuel distribution can be made more uniform.

[0047] The air supply component 1 can be a compressor. A turbine is provided between the main combustion chamber 2 and the rotating detonation afterburner 3. In a conventional engine, the high-pressure air generated by the compressor flows through the main combustion chamber 2 and the turbine before entering the rotating detonation afterburner 3. In the embodiment of the present application, a compressor provided by a conventional aircraft engine is selected as the air supply component 1, and a portion of the air volume is introduced into the second channel 302 through the second air supply line 11, thereby cooling the rotating detonation afterburner 3. The connecting portion can be a mixing hole 303, and the number of the mixing holes 303 is multiple, and the multiple mixing holes 303 are evenly distributed on the annular side wall, so that the high-pressure air in the second channel 302 can enter the interior of the rotating detonation afterburner 3 more evenly, so as to fully contact with the fuel and avoid the problem of poor local cooling effect or even failure.

[0048] Secondly, after entering the interior of the rotating detonation afterburner combustion chamber 3, the high-pressure air can form an air film between the flame and the inner wall of the rotating detonation afterburner combustion chamber 3. The air film can prevent the flame from contacting the inner wall of the rotating detonation afterburner combustion chamber 3, and can also reduce the contact between the fuel and the inner wall of the rotating detonation afterburner combustion chamber 3, thereby playing a heat insulation effect. Combined with the heat absorption effect of the fuel in the first channel 301 and the high-pressure air in the second channel 302, a multi-layer cooling structure is formed, which effectively cools the rotating detonation afterburner combustion chamber 3 and rationally utilizes the heat emitted by the fuel combustion.

[0049] Furthermore, first channel 301 communicates with main combustion chamber 2 via third fuel supply line 8. Since fuel combustion generates a significant amount of heat, to enhance cooling and prevent overheating of the fuel within first channel 301, more fuel can be introduced into first channel 301 to absorb more heat. However, normal operation of the rotating detonation afterburner 3 may not consume this much fuel. In this case, excess high-temperature fuel can be introduced into main combustion chamber 2 via third fuel supply line 8 to meet the operating requirements of main combustion chamber 2, thereby achieving a superior cooling effect and improving combustion efficiency within main combustion chamber 2.

[0050] In addition, by arranging the first channel 301 outside the second channel 302, it is convenient for high-pressure air to enter the inside of the rotating detonation afterburner 3 through the mixing holes 303. At the same time, compared with the high-pressure air in the second channel 302, the fuel in the first channel 301 is also farther from the internal heat source of the rotating detonation afterburner 3, which can prevent the fuel from being over-preheated and then undergoing thermal decomposition to a certain extent, and avoid the generation of carbon deposits or small hydrocarbon molecules, thus affecting the combustion stability.

[0051] Furthermore, a first valve 13 is provided on the first fuel supply pipeline 6, a second valve 14 is provided on the second fuel supply pipeline 7, a third valve 15 is provided on the third fuel supply pipeline 8, and a fourth valve 16 is provided on the fourth fuel supply pipeline 9. By changing the valve opening degree, the fuel delivery amount and / or delivery path can be changed. For example, when the third valve 15 is opened so that part of the fuel in the first channel 301 enters the inside of the main combustion chamber 2, the opening degree of the fourth valve 16 can be reduced so that the fuel injected into the main combustion chamber 2 is within a reasonable range.

Claims

1. A rotating detonation afterburner combustion chamber system capable of regulating the injection temperature of aviation kerosene, characterized in that, Comprising: A rotating detonation afterburner (3), a fuel tank (4), an oxygen cylinder (5), a first fuel supply pipeline (6), a second fuel supply pipeline (7), and a first air supply pipeline (10); Inside the side wall of the rotating detonation afterburner (3), there is a first channel (301). The fuel tank (4) is connected to the first channel (301) through the first fuel supply pipeline (6), and the first channel (301) is connected to the inside of the rotating detonation afterburner (3) through the second fuel supply pipeline (7); The oxygen cylinder (5) is connected to the inside of the rotating detonation afterburner (3) through the first air supply pipeline (10), and the oxygen cylinder (5) is used to supply oxygen to the inside of the rotating detonation afterburner (3) during the detonation initiation stage of the rotating detonation afterburner (3).

2. The rotating detonation afterburning combustion chamber system for regulating the injection temperature of aviation kerosene according to claim 1, characterized in that: The rotating detonation afterburner system capable of regulating the injection temperature of aviation kerosene further includes an air supply assembly (1) and a second air supply pipeline (11); The air supply assembly (1) is connected to the inside of the rotating detonation afterburner (3) through the second air supply pipeline (11), and the air supply assembly (1) is used to introduce air into the inside of the rotating detonation afterburner (3).

3. A rotating detonation afterburner combustion chamber system capable of regulating the injection temperature of aviation kerosene according to claim 2, characterized in that: The air supply assembly (1) includes a compressor.

4. A rotating detonation afterburner combustion chamber system capable of regulating the injection temperature of aviation kerosene according to claim 2, characterized in that: Inside the side wall of the rotating detonation afterburner (3), there is also a second channel (302). The second channel (302) has a connecting part, and the second channel (302) is connected to the inside of the rotating detonation afterburner (3) through the connecting part; The air supply assembly (1) is connected to the second channel (302) through the second air supply pipeline (11).

5. A rotating detonation afterburner combustion chamber system capable of regulating the injection temperature of aviation kerosene according to claim 4, characterized in that: The second channel (302) is located inside the first channel (301), and the connecting part includes mixing holes (303).

6. The rotating detonation afterburner combustion chamber system capable of regulating the injection temperature of aviation kerosene according to claim 5, characterized in that: The rotating detonation afterburner (3) has an annular side wall, and both the first channel (301) and the second channel (302) are provided inside the annular side wall; The number of the mixing holes (303) is multiple, and the multiple mixing holes (303) are evenly distributed on the annular side wall.

7. A rotating detonation afterburner combustion chamber system for regulating the injection temperature of aviation kerosene according to claim 1, characterized in that: The rotating detonation afterburner system capable of regulating the injection temperature of aviation kerosene further includes an atomizing nozzle (12). The atomizing nozzle (12) is connected to the second fuel supply pipeline (7) and is used to inject aviation kerosene into the rotating detonation afterburner (3).

8. A rotating detonation afterburner combustion chamber system capable of regulating the injection temperature of aviation kerosene according to claim 7, characterized in that: The rotating detonation afterburner system capable of regulating the injection temperature of aviation kerosene satisfies one of the following conditions: ① The atomizing nozzle (12) is located at the end of the rotating detonation afterburner (3); ② The rotating detonation afterburner (3) has an annular side wall. The first channel (301) is provided inside the annular side wall. Inside the annular side wall, there are multiple groups of nozzle groups evenly spaced along the axial direction of the rotating detonation afterburner (3). Each nozzle group includes multiple atomizing nozzles (12) evenly spaced circumferentially.

9. A rotating detonation afterburner combustion chamber system capable of regulating the injection temperature of aviation kerosene according to claim 1, characterized in that: The rotating detonation afterburner combustion chamber system capable of regulating the injection temperature of aviation kerosene further includes a main combustion chamber (2), a third fuel supply pipeline (8), a first valve (13), a second valve (14), and a third valve (15); The first channel (301) is communicated with the main combustion chamber (2) through the third fuel supply pipeline (8); The first valve (13) is arranged on the first fuel supply pipeline (6), the second valve (14) is arranged on the second fuel supply pipeline (7), and the third valve (15) is arranged on the third fuel supply pipeline (8).

10. A rotating detonation afterburner combustion chamber system capable of regulating the injection temperature of aviation kerosene according to claim 9, characterized in that: The rotating detonation afterburner combustion chamber system capable of regulating the injection temperature of aviation kerosene further includes a fourth fuel supply pipeline (9) and a fourth valve (16). The fuel tank (4) is communicated with the main combustion chamber (2) through the fourth fuel supply pipeline (9), and the fourth valve (16) is arranged on the fourth fuel supply pipeline (9).

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