Gas atomization injection concave cavity system for actively cooling fuel and injection organization combustion method

Abstract

The invention relates to the technical field of scramjet engines, solves the technical problem that in the application of a scramjet engine active cooling technology, kerosene switches spray holes due to temperature rise and phase change, and consequently the combustion efficiency of an engine is reduced, and particularly relates to a gas atomization injection concave cavity system for actively cooling fuel and an injection organization combustion method. Kerosene flows into an engine wall surface cooling channel to actively cool the wall surface of the supersonic combustion chamber, meanwhile, oxidant gas is divided into two paths, and one path enters an oxidant gas pipeline through an adjustable throttling device and is mixed with the kerosene to form aerated atomized kerosene; and the other path of oxygen is sprayed from the oxidant spraying hole through the electromagnetic stop valve and the sonic flowmeter and forms a low-speed oxygen-enriched backflow area in the concave cavity. According to the kerosene injection device, it can be ensured that the density change of kerosene inflated through the injection holes is very small along with kerosene temperature rise and density reduction, the jet flow penetration depth and the fuel gas mixing efficiency are relatively stable, and therefore the problem that the combustion efficiency of an engine is reduced due to kerosene phase change injection hole switching is effectively solved.

Description

Technical Field

[0001] The invention relates to the technical field of scramjet engines, and in particular to an aerosol injection cavity system for actively cooling fuel and an injection organization combustion method. Background Art

[0002] The active cooling technology of scramjet engines is to first pass the fuel through the cooling channel set on the engine wall to cool the combustion chamber, and then spray it into the combustion chamber for combustion. On the one hand, the combustion chamber is thermally protected and the service life of the combustion chamber can be extended; on the other hand, the fuel is heated up after cooling the wall, achieving the effect of preheating, which can improve the combustion efficiency and obtain greater thrust.

[0003] Before the supersonic combustion chamber is ignited, the temperature of the liquid hydrocarbon fuel is relatively low. Therefore, it is restricted by physical processes such as fuel injection, atomization, evaporation, and gas mixing. The ignition delay time is long, and ignition and flame stabilization in the combustion chamber are difficult. After the combustion chamber is ignited, the total temperature of the combustion chamber increases, and the temperature of the fuel flowing out through the combustion chamber cooling channel also increases. When the fuel enters the supercritical state from the liquid state, the density decreases sharply, so it is necessary to increase the nozzle area to maintain the stability of the fuel flow rate and injection pressure.

[0004] The current solution is to set a valve control on the upstream pipeline of the nozzle to switch the fuel nozzles with different cross-sectional areas as the fuel properties change. However, when switching, the nozzle area increases instantly, resulting in a decrease in injection pressure, a drop in the total pressure and thrust of the combustion chamber, and a decrease in engine combustion efficiency, which may even cause flameout. Summary of the invention

[0005] In view of the shortcomings of the prior art, the present invention provides an aerosol injection cavity system for actively cooling fuel and an injection organization combustion method, which solves the technical problem that in the application of active cooling technology for scramjet engines, kerosene switches the spray hole due to temperature increase phase change, resulting in reduced engine combustion efficiency.

[0006] In order to solve the above technical problems, the present invention provides the following technical solutions: an aerosol injection cavity system for actively cooling fuel, comprising a kerosene supply module for supplying room temperature kerosene to an engine wall cooling channel by extrusion or pumping, and an oxidant gas supply module for supplying oxidant gas, wherein the kerosene flows into the engine wall cooling channel to actively cool the wall of a supersonic combustion chamber and then enters an oxidant gas pipeline built into the injection cavity integrated module;

[0007] The outlet of the oxidant gas supply module is connected to a three-way element for dividing the oxidant gas into two paths, one path of the three-way element is connected to an adjustable flow device which is connected to the oxidant gas pipeline and has an adjustable opening control, the oxidant gas and the kerosene which absorbs the heat of the wall of the supersonic combustion chamber are mixed in the oxidant gas pipeline to form aerated atomized kerosene, and are sprayed out from the atomized kerosene spray holes whose axes are arranged at right angles to the surface of the injection cavity integrated module to form a transverse injection atomized kerosene jet;

[0008] The other path of the three-way element is connected to the electromagnetic stop valve and the sonic flowmeter in sequence. A concave cavity including a concave cavity bottom surface is arranged downstream of the atomized kerosene nozzle, and an oxidant nozzle hole connected to the outlet of the sonic flowmeter is arranged on the bottom surface of the concave cavity. The oxidant gas passes through the sonic flowmeter and is sprayed from the oxidant nozzle hole into the concave cavity to form a low-speed oxygen-rich reflux zone.

[0009] Furthermore, the injection cavity integrated module also includes an igniter vertically mounted on the bottom surface of the cavity and located downstream of the oxidant nozzle, and the working surface of the igniter is coplanar with the bottom surface of the cavity to achieve the ignition function.

[0010] Furthermore, the engine wall cooling channel includes a cooling channel inlet connected to the outlet of the kerosene supply module, and a cooling channel outlet connected to the kerosene inlet pipeline arranged on the injection cavity integrated module, and a temperature sensor for monitoring the oil temperature is arranged at the cooling channel outlet.

[0011] Furthermore, the other end of the kerosene inlet pipeline is connected to an annular confluence cavity arranged on the injection cavity integrated module, the outlet of the annular confluence cavity is connected to a kerosene pipeline, and the kerosene pipeline is connected to the oxidant gas pipeline through a liquid inlet hole arranged on the oxidant gas pipeline.

[0012] Furthermore, the liquid inlet hole is any one of a straight hole, an inclined hole or a tangential hole, the number of the liquid inlet holes is at least 4, and the cross-sectional shape of the liquid inlet hole is at least one of a circular, elliptical, rectangular, diamond or raindrop shape.

[0013] Furthermore, the number of the aerosolized kerosene spray holes is one or more, and the cross-sectional shape of the aerosolized kerosene spray holes is one of circular, elliptical, rectangular, diamond or raindrop-shaped.

[0014] Furthermore, the oxidant gas pipeline is coaxial with and communicates with the atomized kerosene nozzle.

[0015] Furthermore, the plurality of kerosene pipelines are parallel to the oxidant gas pipeline and are evenly distributed around the circumference thereof.

[0016] The technical solution also provides a method for spraying tissue combustion applied to the above-mentioned aerosol spray cavity system, the method comprising the following steps:

[0017] S1. The kerosene supplied by the kerosene supply module flows into the cooling groove of the engine wall through the cooling groove inlet, actively cools the combustion chamber wall, and then flows out from the cooling groove outlet to the kerosene inlet pipeline, flows into the kerosene pipeline through the annular confluence cavity, and flows into the oxidant gas pipeline through the liquid inlet hole;

[0018] S2, the oxidant gas supplied by the oxidant gas supply module flows through the three-way element and is divided into two paths, one of which flows into the oxidant gas pipeline arranged on the injection cavity integrated module after passing through the adjustable flow device, and is mixed with the kerosene entering the oxidant gas pipeline from the liquid inlet hole to form aerated atomized kerosene, and then is sprayed out from the atomized kerosene spray hole to form a horizontal atomized kerosene jet;

[0019] S3, the other oxidant gas flows through the electromagnetic stop valve and the sonic flowmeter in sequence, and then is ejected from the oxidant spray hole arranged on the bottom surface of the cavity;

[0020] S4. During different working stages of the engine, the oil temperature at the outlet of the cooling channel is monitored by a temperature sensor to control the opening of the adjustable flow device, and the on-off of the electromagnetic stop valve is combined to realize the engine organization combustion.

[0021] Furthermore, in step S4, the specific process includes:

[0022] During the cold start stage of the engine, the combustion chamber has not yet been ignited, and the kerosene flowing out of the cooling groove outlet on the combustion chamber wall is room temperature kerosene. At this time, the electromagnetic stop valve is open, and the adjustable flow device is open to the maximum degree;

[0023] A portion of the atomized kerosene is ejected from the atomized kerosene nozzle holes upstream of the cavity to form a transverse atomized kerosene jet. The pressure in the atomized kerosene nozzle holes is higher than the ambient pressure in the combustion chamber. The bubbles mixed in the transverse atomized kerosene jet further expand and rupture, causing the kerosene wrapped outside the bubbles to break up and form droplets with smaller particle sizes.

[0024] At the same time, another part of the oxidant gas is ejected from the oxidant nozzle holes on the bottom surface of the cavity after passing through the sonic flowmeter, forming a low-speed oxygen-rich reflux zone in the cavity. At this time, the igniter arranged downstream of the bottom surface of the cavity works to ignite the room-temperature kerosene in the oxygen-rich environment.

[0025] After the combustion chamber is ignited, the igniter stops working, the electromagnetic stop valve is turned off, and all the oxidant gas supplied by the oxidant gas supply module enters the oxidant gas pipeline through the adjustable flow device to aerate and atomize the kerosene, and is laterally sprayed from the atomized kerosene nozzle hole. Under the oscillation of the shear layer, a part of the transverse atomized kerosene jet enters the concave cavity through the shear layer oscillation, and burns in the low-speed oxygen-rich reflux zone in the concave cavity to form a high-temperature oxygen-rich flame stabilization zone, thereby achieving stable combustion of kerosene.

[0026] As the temperature of kerosene increases after actively cooling the combustion chamber wall, the kerosene enters a supercritical state from a liquid state. During the oil temperature increase process, the temperature of the oil at the outlet of the cooling channel is monitored by a temperature sensor, and the adjustable flow device is controlled to reduce the throttling opening, so that the flow rate of the oxidant gas passing through the adjustable flow device is reduced, and the mass ratio of the oxidant gas to the liquid kerosene entering the oxidant gas pipeline is reduced;

[0027] When the temperature sensor monitors that the kerosene has completely entered the supercritical state, the adjustable flow device is completely shut down, and the oxidant gas no longer enters the oxidant gas pipeline through the adjustable flow device. The supercritical kerosene flowing out of the engine wall cooling groove passes through the kerosene inlet pipeline, the annular confluence cavity, the kerosene pipeline, the liquid inlet hole, and the oxidant gas pipeline, and then is laterally ejected from the atomized kerosene nozzle to form a supercritical kerosene lateral jet, while the concave cavity plays a flame stabilizing role.

[0028] By means of the above technical solution, the present invention provides an aerosol injection cavity system for actively cooling fuel and an injection organization combustion method, which has at least the following beneficial effects:

[0029] 1. The present invention can reduce the oxidant gas flow rate of the aerated atomized kerosene by reducing the opening of the adjustable flow device as the temperature of the kerosene actively cools the combustion chamber wall, and the kerosene enters the supercritical state from the liquid state. That is, the gas-liquid mass ratio of the oxidant gas to the kerosene is reduced. When the kerosene enters the supercritical state, the gas-liquid mass ratio drops to zero. This method ensures that as the temperature of the kerosene rises and the density decreases, the density of the aerated kerosene in the nozzle hole changes very little, and the jet penetration depth and the gas mixing efficiency are relatively stable, thereby effectively avoiding the problem of reduced engine combustion efficiency due to the switching of the nozzle hole due to the phase change of the kerosene.

[0030] 2. The present invention uses oxidant gas to atomize kerosene and spray it horizontally, which can reduce the atomized particle size of kerosene, increase the penetration depth, and is beneficial to improving the gas mixing efficiency and shortening the mixing characteristic time. At the same time, the kerosene jet containing oxidant can enhance the chemical reaction activity and improve the ignition performance of low-temperature liquid kerosene. The injection of oxidant in the cavity forms an oxygen-rich reflow zone, which helps to stabilize combustion and thus solves the problem of difficulty in ignition and flame stabilization during the cold start process of the engine in active cooling technology.

[0031] 3. After the combustion chamber is ignited, the present invention can regulate the oxidant gas to enter the oxidant gas pipeline to aerate and atomize the kerosene, and then spray it laterally from the atomized kerosene nozzle hole, so that the horizontal atomized kerosene jet burns in the low-speed oxygen-rich reflux zone in the concave cavity to form a high-temperature oxygen-rich flame-stabilizing zone, thereby achieving stable combustion of kerosene, which helps to broaden the combustion and flame-stabilizing range. BRIEF DESCRIPTION OF THE DRAWINGS

[0032] The drawings described herein are used to provide a further understanding of the present application and constitute a part of the present application. The illustrative embodiments of the present application and their descriptions are used to explain the present application and do not constitute an improper limitation on the present application. In the drawings:

[0033] Figure 1 It is a structural schematic diagram of the aerosol injection cavity system of the present invention;

[0034] Figure 2 Schematic diagram of the flow field of the atomized kerosene lateral jet in the present invention.

[0035] In the figure: 1. kerosene supply module; 2. cooling channel inlet; 3. engine wall cooling channel; 4. cooling channel outlet; 5. injection cavity integrated module; 6. kerosene inlet pipeline; 7. annular confluence cavity; 8. kerosene pipeline; 9. liquid inlet hole; 10. oxidant gas pipeline; 11. oxidant gas supply module; 12. three-way element; 13. adjustable flow device; 14. atomized kerosene nozzle; 15. electromagnetic stop valve; 16. sonic flowmeter; 17. oxidant nozzle; 18. cavity bottom; 19. igniter; 20. temperature sensor; 21. cavity; 22. aerated atomized kerosene; 23. transverse atomized kerosene jet; 24. shear layer; 25. low-speed oxygen-rich reflux zone. DETAILED DESCRIPTION

[0036] In order to make the above-mentioned purposes, features and advantages of the present invention more obvious and easy to understand, the present invention is further described in detail below with reference to the accompanying drawings and specific implementation methods, so that the implementation process of how the present application uses technical means to solve technical problems and achieve technical effects can be fully understood and implemented accordingly.

[0037] Embodiment 1

[0038] This embodiment is to solve the problem of difficulty in ignition and flame stabilization during cold start of active cooling engine. Figure 1 and Figure 2This embodiment proposes an aerosol injection cavity system for actively cooling fuel, including a kerosene supply module 1 for supplying normal temperature kerosene to the engine wall cooling channel 3 by extrusion or pumping, the outlet of the kerosene supply module 1 is connected to the cooling channel inlet 2 on the engine wall cooling channel 3, the cooling channel outlet 4 is connected to the kerosene inlet pipeline 6 arranged on the injection cavity integrated module 5, the other end of the kerosene inlet pipeline 6 is connected to the annular confluence cavity 7 arranged on the injection cavity integrated module 5, the outlet of the annular confluence cavity 7 is connected to the kerosene pipeline 8, and the kerosene pipeline 8 is connected to the oxidant gas pipeline 10 through the liquid inlet hole 9 arranged on the oxidant gas pipeline 10, and multiple kerosene pipelines 8 are parallel to the oxidant gas pipeline 10 and uniformly distributed around the circumference thereof. The liquid inlet hole 9 is any one of a straight hole, an inclined hole or a tangential hole, the number of the liquid inlet holes 9 is at least 4, and the cross-sectional shape of the liquid inlet hole 9 is at least one of a circular, elliptical, rectangular, diamond or raindrop shape. A temperature sensor 20 for monitoring the oil temperature is provided at the cooling channel outlet 4. The kerosene flows into the engine wall cooling channel 3 to actively cool the supersonic combustion chamber wall and then enters the oxidant gas pipeline 10 built into the injection cavity integrated module 5.

[0039] The oxidant gas supply module 11 is used to supply oxidant gas. A three-way element 12 for dividing the oxidant gas into two paths is connected to the outlet of the oxidant gas supply module 11. One path of the three-way element 12 is connected to an adjustable flow device 13 which is connected to the oxidant gas pipeline 10 and has an adjustable opening control. The oxidant gas and kerosene that absorbs the heat from the wall of the supersonic combustion chamber are mixed in the oxidant gas pipeline 10 to form aerated atomized kerosene, and are sprayed out from atomized kerosene nozzles 14 whose axis is arranged at right angles to the surface of the injection cavity integrated module 5 to form a transverse injection atomized kerosene jet. The oxidant gas pipeline 10 is coaxial with and connected to the atomized kerosene nozzles 14. The number of the atomized kerosene nozzles 14 is one or more, and the cross-sectional shape of the atomized kerosene nozzles 14 is one of circular, elliptical, rectangular, diamond or raindrop-shaped.

[0040] The other path of the three-way element 12 is connected to the electromagnetic stop valve 15 and the sonic flowmeter 16 in sequence. A concave cavity 21 including a concave cavity bottom surface 18 is provided downstream of the atomized kerosene spray hole 14, and an oxidant spray hole 17 connected to the outlet of the sonic flowmeter 16 is provided on the concave cavity bottom surface 18. After passing through the sonic flowmeter 16, the oxidant gas is sprayed from the oxidant spray hole 17 into the concave cavity 21 to form a low-speed oxygen-rich reflux zone. The igniter 19 is vertically installed on the concave cavity bottom surface 18 and is located downstream of the oxidant spray hole 17, and the working surface of the igniter 19 is coplanar with the concave cavity bottom surface 18 to achieve the ignition function.

[0041] After the combustion chamber is ignited, this embodiment can regulate the oxidant gas to enter the oxidant gas pipeline 10 to aerate and atomize the kerosene, and then spray it laterally from the atomized kerosene nozzle hole 14, so that the horizontal atomized kerosene jet 23 oscillates through the shear layer 24 and enters the concave cavity 21, and burns in the low-speed oxygen-rich reflux zone 25 in the concave cavity 21 to form a high-temperature oxygen-rich flame-stabilizing zone, thereby achieving stable combustion of kerosene, thereby helping to broaden the combustion and flame-stabilizing range.

[0042] This embodiment uses oxidant gas to atomize kerosene and spray it horizontally, which can reduce the atomized particle size of kerosene, increase the penetration depth, and is beneficial to improving the gas mixing efficiency and shortening the mixing characteristic time. At the same time, the kerosene jet containing oxidant can enhance the chemical reaction activity and improve the ignition performance of low-temperature liquid kerosene. The injection of oxidant in the cavity forms an oxygen-rich reflow zone, which helps to stabilize combustion. This embodiment solves the problem of difficulty in ignition and flame stabilization during the cold start process of the engine in active cooling technology from the above three aspects.

[0043] Embodiment 2

[0044] Based on the first embodiment, this embodiment aims to solve the problem of reduced engine combustion efficiency caused by switching the spray hole due to the phase change of kerosene. Figure 1 and Figure 2 This embodiment proposes a method for spraying and burning tissue applied to the aerosol spray cavity system proposed in the first embodiment, and the method includes the following steps:

[0045] S1, kerosene supplied by kerosene supply module 1 flows into engine wall cooling channel 3 through cooling channel inlet 2, actively cools combustion chamber wall, flows out through cooling channel outlet 4 to kerosene inlet pipeline 6, flows into kerosene pipeline 8 through annular confluence cavity 7, and flows into oxidant gas pipeline 10 through liquid inlet hole 9;

[0046] S2, the oxidant gas supplied by the oxidant gas supply module 11 flows through the three-way element 12 and is divided into two paths, one of which flows into the oxidant gas pipeline 10 provided on the injection cavity integrated module 5 after passing through the adjustable flow device 13, and is mixed with the kerosene entering the oxidant gas pipeline 10 from the liquid inlet hole 9 to form aerated atomized kerosene 22, and then is sprayed out from the atomized kerosene spray hole 14 to form a transverse atomized kerosene jet 23. The oxidant gas is at least one of the following: oxygen, hydrogen peroxide catalytic decomposition gas, nitrous oxide catalytic decomposition gas, and high-temperature nitrous oxide gas.

[0047] S3, the other oxidant gas flows through the electromagnetic stop valve 15 and the sonic flowmeter 16 in sequence, and is ejected from the oxidant injection hole 17 provided on the bottom surface 18 of the concave cavity;

[0048] S4, at different working stages of the engine, the oil temperature at the cooling channel outlet 4 is monitored by the temperature sensor 20, the opening of the adjustable flow device 13 is controlled, and the on-off of the electromagnetic stop valve 15 is combined to realize the engine organization combustion. The specific process includes:

[0049] During the cold start phase of the engine, the combustion chamber has not yet been ignited, and the kerosene flowing out of the cooling groove outlet 4 on the combustion chamber wall is room temperature kerosene. At this time, the electromagnetic shut-off valve 15 is open, and the adjustable flow device 13 is at its maximum opening; a portion of the aerated atomized kerosene 22 is ejected from the atomized kerosene nozzle 14 upstream of the concave cavity 21 to form a transverse atomized kerosene jet 23. The pressure in the atomized kerosene nozzle 14 is higher than the ambient pressure in the combustion chamber, and the bubbles mixed in the transverse atomized kerosene jet 23 further expand and rupture, causing the kerosene wrapped outside the bubbles to break and form droplets with smaller particle sizes. The transverse injection of the transverse atomized kerosene jet 23 can increase the jet penetration depth, shorten the gas mixing distance, and improve the gas mixing efficiency. The transverse atomized kerosene jet 23 contains oxidant gas, which can form an oxygen-rich jet, thereby shortening the ignition time and improving the ignition performance of room temperature kerosene.

[0050] At the same time, another part of the oxidant gas is ejected from the oxidant nozzle 17 on the bottom surface 18 of the cavity after passing through the sonic flowmeter 16, forming a low-speed oxygen-rich reflux zone 25 in the cavity 21. At this time, the igniter 19 arranged downstream of the bottom surface 18 of the cavity works to ignite the room temperature kerosene in the oxygen-rich environment.

[0051] After the combustion chamber is ignited, the igniter 19 stops working, the electromagnetic stop valve 15 is closed, and all the oxidant gas supplied by the oxidant gas supply module 11 enters the oxidant gas pipeline 10 through the adjustable flow device 13 to aerate and atomize the kerosene, and is laterally sprayed by the atomized kerosene nozzle 14. Under the oscillation action of the shear layer 24, a part of the horizontal atomized kerosene jet 23 oscillates through the shear layer 24 into the concave cavity 21, and burns in the low-speed oxygen-rich reflux zone 25 in the concave cavity 21 to form a high-temperature oxygen-rich flame stabilization zone, thereby realizing stable combustion of kerosene.

[0052] As the temperature of kerosene rises after actively cooling the combustion chamber wall, kerosene enters the supercritical state from the liquid state. During the process of oil temperature rising, the oil temperature at the cooling channel outlet 4 is monitored by the temperature sensor 20, and the adjustable flow device 13 is controlled to reduce the throttling opening, so that the oxidant gas flow rate through the adjustable flow device 13 is reduced, and the mass ratio of the oxidant gas to liquid kerosene entering the oxidant gas pipeline 10 is reduced.

[0053] When the temperature sensor 20 monitors and finds that the kerosene has completely entered the supercritical state, the adjustable flow device 13 is completely shut down, and the oxidant gas no longer enters the oxidant gas pipeline 10 through the adjustable flow device 13. The supercritical kerosene flowing out of the engine wall cooling groove 3 passes through the kerosene inlet pipeline 6, the annular confluence cavity 7, the kerosene pipeline 8, the liquid inlet hole 9, and the oxidant gas pipeline 10, and is laterally ejected from the atomized kerosene nozzle 14 to form a supercritical kerosene lateral jet. At the same time, the concave cavity 21 plays a flame stabilizing role.

[0054] This embodiment can reduce the oxidant gas flow rate of the aerated atomized kerosene by reducing the opening of the adjustable flow device as the temperature of the kerosene actively cools the combustion chamber wall surface, and the kerosene enters the supercritical state from the liquid state. That is, the gas-liquid mass ratio of the oxidant gas to the kerosene is reduced. When the kerosene enters the supercritical state, the gas-liquid mass ratio drops to zero. This method ensures that as the temperature of the kerosene rises and the density decreases, the density of the aerated kerosene in the nozzle hole changes very little, and the jet penetration depth and the gas mixing efficiency are relatively stable, thereby effectively avoiding the problem of reduced engine combustion efficiency due to the switching of the nozzle hole due to the phase change of the kerosene.

[0055] Each embodiment in this specification is described in a progressive manner, and each embodiment focuses on the differences from other embodiments. The same or similar parts between the embodiments can be referred to each other. For the above embodiments, since they are basically similar to the method embodiments, the description is relatively simple, and the relevant parts can be referred to the partial description of the method embodiments.

[0056] The above implementation methods have been described in detail. Specific examples are used herein to illustrate the principles and implementation methods of the present invention. The description of the above embodiments is only used to help understand the method of the present invention and its core idea. At the same time, for those skilled in the art, according to the idea of ​​the present invention, there will be changes in the specific implementation methods and application scope. In summary, the content of this specification should not be understood as a limitation on the present invention.

Claims

1. An aerosol injection cavity system for actively cooling fuel, comprising a kerosene supply module (1) for supplying room temperature kerosene to an engine wall cooling channel (3) by extrusion or pumping, and an oxidant gas supply module (11) for supplying oxidant gas, characterized in that: The kerosene flows into the engine wall cooling channel (3) to actively cool the wall of the supersonic combustion chamber, and then enters the oxidant gas pipeline (10) built into the injection cavity integrated module (5); The outlet of the oxidant gas supply module (11) is connected to a three-way element (12) for dividing the oxidant gas into two paths, one path of the three-way element (12) is connected to an adjustable flow device (13) which is in communication with the oxidant gas pipeline (10) and has an adjustable opening control, the oxidant gas and the kerosene which absorbs the heat of the wall of the supersonic combustion chamber are mixed in the oxidant gas pipeline (10) to form aerated atomized kerosene, and are sprayed out from the atomized kerosene spray hole (14) whose axis is arranged at a right angle to the surface of the injection cavity integrated module (5) to form a horizontal injection atomized kerosene jet; The other path of the three-way element (12) is connected to the electromagnetic stop valve (15) and the sonic flowmeter (16) in sequence. A concave cavity (21) including a concave cavity bottom surface (18) is provided downstream of the atomized kerosene spray hole (14). An oxidant spray hole (17) connected to an outlet of the sonic flowmeter (16) is provided on the concave cavity bottom surface (18). The oxidant gas passes through the sonic flowmeter (16) and is sprayed from the oxidant spray hole (17) into the concave cavity (21) to form a low-speed oxygen-rich reflux zone.

2. The aerosol injection cavity system according to claim 1, characterized in that: The injection cavity integrated module (5) further comprises an igniter (19) vertically mounted on the cavity bottom surface (18) and located downstream of the oxidant injection hole (17), and the working surface of the igniter (19) is coplanar with the cavity bottom surface (18) to achieve an ignition function.

3. The aerosol injection cavity system according to claim 1, characterized in that: The engine wall cooling channel (3) comprises a cooling channel inlet (2) connected to the outlet of a kerosene supply module (1), and a cooling channel outlet (4) connected to a kerosene inlet pipeline (6) provided on an injection cavity integrated module (5), wherein a temperature sensor (20) for monitoring oil temperature is provided at the cooling channel outlet (4).

4. The aerosol injection cavity system according to claim 5, characterized in that: The other end of the kerosene inlet pipeline (6) is connected to an annular confluence cavity (7) arranged on the injection cavity integrated module (5), and the outlet of the annular confluence cavity (7) is connected to a kerosene pipeline (8), and the kerosene pipeline (8) is connected to the oxidant gas pipeline (10) through a liquid inlet hole (9) arranged on the oxidant gas pipeline (10).

5. The aerosol injection cavity system according to claim 4, characterized in that: The liquid inlet hole (9) is any one of a straight hole, an inclined hole or a tangential hole, the number of the liquid inlet holes (9) is at least 4, and the cross-sectional shape of the liquid inlet hole (9) is at least one of a circular shape, an elliptical shape, a rectangular shape, a diamond shape or a raindrop shape.

6. The aerosol injection cavity system according to claim 1, characterized in that: The number of the atomized kerosene spray holes (14) is one or more, and the cross-sectional shape of the atomized kerosene spray holes (14) is one of a circular shape, an elliptical shape, a rectangular shape, a diamond shape or a raindrop shape.

7. The aerosol injection cavity system according to claim 1, characterized in that: The oxidant gas pipeline (10) is coaxial with and communicates with the atomized kerosene spray hole (14).

8. The aerosol injection cavity system according to claim 4, characterized in that: The plurality of kerosene pipelines (8) are parallel to the oxidant gas pipeline (10) and are evenly distributed around the circumference thereof.

9. A method for spraying tissue combustion applied to the aerosol spray cavity system according to any one of claims 1 to 8, characterized in that: The method comprises the following steps: S1, kerosene supplied by the kerosene supply module (1) flows into the engine wall cooling channel (3) through the cooling channel inlet (2), actively cools the combustion chamber wall, flows out from the cooling channel outlet (4) to the kerosene inlet pipeline (6), flows into the kerosene pipeline (8) through the annular confluence cavity (7), and flows into the oxidant gas pipeline (10) through the liquid inlet hole (9); S2, the oxidant gas supplied by the oxidant gas supply module (11) flows through the three-way element (12) and is divided into two paths, one of which flows into the oxidant gas pipeline (10) arranged on the injection cavity integrated module (5) after passing through the adjustable flow device (13), and is mixed with the kerosene entering the oxidant gas pipeline (10) from the liquid inlet hole (9) to form aerated atomized kerosene (22), and then is sprayed out from the atomized kerosene spray hole (14) to form a transverse atomized kerosene jet (23); S3, the other oxidant gas flows through the electromagnetic stop valve (15) and the sonic flow meter (16) in sequence, and is then ejected from the oxidant injection hole (17) provided on the bottom surface (18) of the cavity; S4. During different working stages of the engine, the oil temperature at the cooling channel outlet (4) is monitored by the temperature sensor (20), the opening of the adjustable flow device (13) is controlled, and the on-off of the electromagnetic stop valve (15) is combined to realize the engine organization combustion.

10. The method for injecting tissue combustion according to claim 9, characterized in that: In step S4, the specific process includes: During the cold start phase of the engine, the combustion chamber has not yet been ignited, and the kerosene flowing out of the cooling channel outlet (4) on the combustion chamber wall is kerosene at room temperature. At this time, the electromagnetic stop valve (15) is open, and the adjustable flow device (13) is at its maximum opening; A portion of the aerated atomized kerosene (22) is sprayed from the atomized kerosene spray hole (14) upstream of the concave cavity (21) to form a transverse atomized kerosene jet (23). The pressure in the atomized kerosene spray hole (14) is higher than the ambient pressure in the combustion chamber. The bubbles mixed in the transverse atomized kerosene jet (23) further expand and burst, causing the kerosene wrapped outside the bubbles to break up and form droplets with smaller particle sizes. At the same time, another part of the oxidant gas is ejected from the oxidant injection hole (17) on the bottom surface (18) of the cavity after passing through the sonic flow meter (16), forming a low-speed oxygen-rich reflux zone (25) in the cavity (21). At this time, the igniter (19) arranged downstream of the bottom surface (18) of the cavity works to ignite the room-temperature kerosene in the oxygen-rich environment. After the combustion chamber is ignited, the igniter (19) stops working, the electromagnetic stop valve (15) is closed, and all the oxidant gas supplied by the oxidant gas supply module (11) enters the oxidant gas pipeline (10) through the adjustable flow device (13) to aerate and atomize the kerosene, and is laterally sprayed from the atomized kerosene nozzle (14). Under the oscillation of the shear layer (24), a part of the transverse atomized kerosene jet (23) oscillates through the shear layer (24) into the concave cavity (21), and burns in the low-speed oxygen-rich reflux zone (25) in the concave cavity (21) to form a high-temperature oxygen-rich flame stabilization zone, thereby achieving stable combustion of the kerosene. As the temperature of the kerosene increases after actively cooling the combustion chamber wall, the kerosene enters a supercritical state from a liquid state. During the oil temperature increase process, the temperature of the oil at the cooling channel outlet (4) is monitored by a temperature sensor (20), and the adjustable flow device (13) is controlled to reduce the throttling opening, so that the flow rate of the oxidant gas passing through the adjustable flow device (13) is reduced, and the mass ratio of the oxidant gas to the liquid kerosene entering the oxidant gas pipeline (10) is reduced; When the temperature sensor (20) monitors and finds that the kerosene has completely entered the supercritical state, the adjustable flow device (13) is completely shut down, and the oxidant gas no longer enters the oxidant gas pipeline (10) through the adjustable flow device (13). The supercritical kerosene flowing out of the engine wall cooling groove (3) passes through the kerosene inlet pipeline (6), the annular confluence cavity (7), the kerosene pipeline (8), the liquid inlet hole (9), and the oxidant gas pipeline (10), and is laterally ejected from the atomized kerosene nozzle hole (14) to form a supercritical kerosene lateral jet, while the concave cavity (21) plays a flame stabilizing role.

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