An aerosol injection cavity system for actively cooling fuel and an injection-organized combustion method

Abstract

The present invention relates to the field of scramjet engine technology and addresses the technical problem of reduced engine combustion efficiency caused by kerosene's temperature-increasing phase change and nozzle switching during the application of active cooling technology in scramjet engines. The invention particularly relates to an aerosolized injection cavity system for actively cooling fuel and a method for organizing injection combustion. The system actively cools the supersonic combustion chamber wall by flowing kerosene into cooling channels on the engine wall. Simultaneously, oxidizer gas is divided into two paths: one path, which enters an oxidizer gas pipeline through an adjustable flow device and mixes with kerosene to form aerated atomized kerosene; the other path, which is ejected from the oxidizer nozzle via an electromagnetic shutoff valve and a sonic flowmeter, forms a low-speed oxygen-rich recirculation zone within the cavity. The present invention ensures that as the kerosene heats and its density decreases, the density of the aerated kerosene in the nozzle nozzle changes minimally, maintaining relatively stable jet penetration depth and gas mixing efficiency, thereby effectively avoiding the problem of reduced engine combustion efficiency caused by kerosene's phase change and nozzle switching.

Description

Technical Field

[0001] The present 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-organized combustion method. Background Art

[0002] Active scramjet cooling technology involves passing fuel through cooling channels built into the engine walls to cool the combustion chamber before injection into the combustion chamber for combustion. This provides thermal protection for the combustion chamber, extending its operating life. Furthermore, the fuel heats up after cooling the walls, creating a preheating effect that improves combustion efficiency and yields greater thrust.

[0003] Before ignition in a supersonic combustor, the liquid hydrocarbon fuel is relatively cold. This leads to long ignition delays due to physical processes such as fuel injection, atomization, evaporation, and gas mixing, making ignition and flame stabilization difficult. After ignition, the total chamber temperature rises, and so does the temperature of the fuel flowing through the combustor's cooling channels. As the fuel transitions from liquid to supercritical, its density drops dramatically, necessitating an increased nozzle area to maintain stable fuel flow and injection pressure.

[0004] The current solution involves installing valves in the upstream piping of the nozzles to switch between nozzles of varying cross-sectional areas as the fuel's physical properties change. However, the nozzle area increases momentarily during this switch, resulting in a drop in injection pressure, total combustion chamber pressure, and thrust, reducing engine combustion efficiency and potentially even causing flameout. Summary of the Invention

[0005] In response to the shortcomings of the existing technology, the present invention provides an aerosol injection cavity system for actively cooling fuel and a method for organizing injection combustion, which solves the technical problem of reduced engine combustion efficiency caused by kerosene switching nozzles due to phase change caused by temperature increase in the application of active cooling technology in scramjet engines.

[0006] To solve the above technical problems, the present invention provides the following technical solutions: an aerosolized 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. The kerosene flows into the engine wall cooling channel to actively cool the supersonic combustion chamber wall, 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 component for dividing the oxidant gas into two paths. One path of the three-way component is connected to an adjustable flow device that is in communication with the oxidant gas pipeline and has an adjustable opening control. The oxidant gas and kerosene that absorbs heat from the walls of the supersonic combustion chamber are mixed in the oxidant gas pipeline to form aerated atomized kerosene, which is then ejected from atomized kerosene nozzles arranged at right angles to the surface of the injection cavity integrated module to form a horizontal injection atomized kerosene jet.

[0008] The other path of the three-way element is connected to an electromagnetic shut-off valve and a sonic flowmeter in sequence. A concave cavity including a concave cavity bottom surface is provided downstream of the atomized kerosene nozzle, and an oxidant nozzle hole connected to the outlet of the sonic flowmeter is provided on the bottom surface of the concave cavity. After passing through the sonic flowmeter, the oxidant gas 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 installed vertically 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 provided at the cooling channel outlet.

[0011] Furthermore, the other end of the kerosene inlet pipeline is connected to an annular confluence cavity provided 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 provided 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 circle, an ellipse, a rectangle, a diamond or a 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 aerosolized spray cavity system, the method comprising the following steps:

[0017] S1. The kerosene supplied by the kerosene supply module flows into the engine wall cooling channel through the cooling channel inlet, actively cools the combustion chamber wall, and then flows out of the cooling channel 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 component and is divided into two paths. One path flows through the adjustable flow device and then flows into the oxidant gas pipeline provided on the injection cavity integrated module. It mixes with the kerosene entering the oxidant gas pipeline through the liquid inlet to form aerated atomized kerosene, which is then ejected from the atomized kerosene nozzle 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 is ejected from the oxidant nozzle provided 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 at the same time, the on-off of the electromagnetic shut-off valve is combined to realize the engine organization combustion.

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

[0022] 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 on the combustion chamber wall is room temperature kerosene. At this time, the electromagnetic shut-off valve is open, and the adjustable flow device is opened to the maximum degree;

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

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

[0025] After the combustion chamber is ignited, the igniter stops working and the electromagnetic shut-off valve is closed. 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 then sprayed laterally from the atomizing kerosene nozzle. Under the oscillation of the shear layer, a portion of the transverse atomized kerosene jet oscillates through the shear layer and enters the concave cavity. It burns in the low-speed oxygen-rich recirculation zone within the concave cavity to form a high-temperature oxygen-rich stable flame zone, achieving stable combustion of the kerosene.

[0026] 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 is monitored by a temperature sensor, and the throttling opening of the adjustable flow device is controlled to decrease, thereby reducing the flow rate of the oxidant gas passing through the adjustable flow device and reducing the mass ratio of the oxidant gas to liquid kerosene entering the oxidant gas pipeline.

[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 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-organized combustion method, which has at least the following beneficial effects:

[0029] 1. The present invention reduces the oxidant gas flow rate of the aerated kerosene by decreasing the opening of the adjustable flow device as the kerosene actively cools the combustion chamber walls, shifting from a liquid state to a supercritical state. This reduces the gas-to-liquid mass ratio of oxidant gas to kerosene. When the kerosene enters the supercritical state, the gas-to-liquid mass ratio drops to zero. This method ensures minimal changes in the density of the aerated kerosene at the nozzles as the kerosene heats and decreases in density. This ensures relatively stable jet penetration depth and gas mixing efficiency, effectively avoiding the problem of reduced engine combustion efficiency caused by nozzle switching caused by kerosene phase changes.

[0030] 2. The present invention uses oxidant gas to atomize kerosene and then sprays it horizontally, reducing the atomized kerosene particle size and increasing penetration depth, which helps improve gas mixing efficiency and shortens the characteristic mixing time. Furthermore, the oxidant-containing kerosene jet enhances chemical reactivity and improves the ignition performance of cryogenic liquid kerosene. Injecting oxidant into the cavity creates an oxygen-rich recirculation zone, which helps stabilize combustion and thus resolves the difficulty of ignition and flame stabilization during engine cold starts, a problem often encountered with 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 horizontally from the atomized kerosene nozzle, 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 stable flame zone, thereby achieving stable combustion of kerosene, thereby helping to broaden the combustion and flame stability 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 Schematic diagram of the structure of the aerosol injection cavity system of the present invention;

[0034] Figure 2 Schematic diagram of the flow field of the atomized kerosene transverse 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. Solenoid stop valve; 16. Sonic flowmeter; 17. Oxidant nozzle; 18. Cavity bottom; 19. Igniter; 20. Temperature sensor; 21. Cavity; 22. Aerated atomized kerosene; 23. Horizontal atomized kerosene jet; 24. Shear layer; 25. Low-speed oxygen-rich reflux zone. DETAILED DESCRIPTION

[0036] To make the above-mentioned objectives, features, and advantages of the present invention more clearly understood, the present invention is further described below in detail with reference to the accompanying drawings and specific embodiments. This will enable a full understanding of how this application employs technical means to solve technical problems and achieve technical effects, and to implement the invention accordingly.

[0037] Example 1

[0038] This embodiment is to solve the problem of difficulty in ignition and flame stabilization during the cold start process of the active cooling engine. Figure 1 and Figure 2This embodiment proposes an aerosolized injection cavity system for actively cooling fuel. The system includes a kerosene supply module 1 that supplies ambient-temperature kerosene to an engine wall cooling channel 3 by extrusion or pumping. The outlet of the kerosene supply module 1 is connected to a cooling channel inlet 2 on the engine wall cooling channel 3. The cooling channel outlet 4 is connected to a kerosene inlet pipe 6 provided on an injection cavity integrated module 5. The other end of the kerosene inlet pipe 6 is connected to an annular confluence chamber 7 provided on the injection cavity integrated module 5. The outlet of the annular confluence chamber 7 is connected to a kerosene pipeline 8, which communicates with an oxidant gas pipeline 10 via a liquid inlet hole 9 provided on the oxidant gas pipeline 10. Multiple kerosene pipelines 8 are parallel to the oxidant gas pipeline 10 and evenly distributed around the oxidant gas pipeline 10. The liquid inlet holes 9 are any of straight, oblique, or tangential holes. There are at least four liquid inlet holes 9, and the cross-sectional shape of the liquid inlet holes 9 is at least one of circular, elliptical, rectangular, diamond, or raindrop-shaped. 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. 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 that is connected to the oxidant gas pipeline 10 and has an adjustable opening control. The oxidant gas and kerosene that absorbs 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 the atomizing kerosene nozzle 14 whose axis is arranged at right angles to the surface of the injection cavity integrated module 5 to form a horizontal injection atomizing kerosene jet. The oxidant gas pipeline 10 is coaxial with and penetrates the atomizing kerosene nozzle 14. The number of the atomizing kerosene nozzle 14 is one or more, and the cross-sectional shape of the atomizing kerosene nozzle 14 is one of circular, elliptical, rectangular, diamond or raindrop-shaped.

[0040] The other end of the three-way element 12 connects to a solenoid shutoff valve 15 and a sonic flowmeter 16. Downstream of the atomized kerosene nozzle 14 is a concave cavity 21 containing a concave bottom 18. This bottom 18 also houses an oxidizer nozzle 17, which communicates with the outlet of the sonic flowmeter 16. After passing through the sonic flowmeter 16, the oxidizer gas is ejected from the oxidizer nozzle 17 into the concave cavity 21, creating a low-speed, oxygen-rich recirculation zone. An igniter 19 is mounted perpendicular to the concave bottom 18, downstream of the oxidizer nozzle 17. Its operating surface is coplanar with the cavity bottom 18, enabling ignition.

[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 atomizing kerosene nozzle 14, so that the horizontal atomizing kerosene jet 23 oscillates through the shear layer 24 and enters the concave cavity 21, and burns in the low-speed oxygen-rich recirculation 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 then sprays it horizontally. This reduces the atomized kerosene particle size, increases penetration depth, and improves gas mixing efficiency and shortens the characteristic mixing time. Furthermore, the oxidant-containing kerosene jet enhances chemical reactivity and improves the ignition performance of cryogenic liquid kerosene. Injecting oxidant into the cavity creates an oxygen-rich recirculation zone, which contributes to stable combustion. This embodiment addresses the difficulty of ignition and flame stabilization during engine cold starts in active cooling technology through these three aspects.

[0043] Example 2

[0044] Based on the first embodiment, this embodiment aims to solve the problem of reduced engine combustion efficiency caused by switching the nozzle hole due to the phase change of kerosene. Figure 1 and Figure 2 This embodiment proposes a method for spraying tissue combustion applied to the aerosol spray cavity system proposed in the first embodiment, the method comprising 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 the combustion chamber wall, and then flows out from cooling channel outlet 4 to kerosene inlet pipe 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. Oxidant gas supplied by oxidant gas supply module 11 flows through tee element 12 and is divided into two paths. One path passes through adjustable flow device 13 and flows into oxidant gas pipeline 10 provided on injection cavity integrated module 5. It mixes with kerosene entering oxidant gas pipeline 10 through liquid inlet 9 to form aerated atomized kerosene 22. The atomized kerosene is then ejected from atomized kerosene nozzles 14 to form transverse atomized kerosene jets 23. The oxidant gas can be at least one of the following: oxygen, hydrogen peroxide catalytic decomposition gas, nitrous oxide catalytic decomposition gas, or 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 nozzle 17 provided on the bottom surface 18 of the cavity;

[0048] S4. During different engine operation stages, the temperature sensor 20 monitors the oil temperature at the cooling channel outlet 4, controls the opening of the adjustable flow device 13, and simultaneously switches the electromagnetic shut-off valve 15 on and off to achieve engine combustion. The specific process includes:

[0049] During the cold start phase of the engine, before ignition in the combustion chamber, the kerosene flowing out of the cooling channel 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 atomizing kerosene nozzle 14 upstream of the cavity 21 to form a transverse atomizing kerosene jet 23. The pressure within the atomizing kerosene nozzle 14 is higher than the ambient pressure within the combustion chamber. The bubbles mixed within the transverse atomizing kerosene jet 23 further expand and rupture, causing the kerosene encased in the bubbles to break up and form smaller droplets. The lateral injection of the transverse atomizing kerosene jet 23 increases the jet penetration depth, shortens the gas mixing distance, and improves the gas mixing efficiency. The oxidant gas contained in the transverse atomizing kerosene jet 23 forms an oxygen-rich jet, thereby shortening the ignition time and improving the ignition performance of the 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 and the electromagnetic shut-off valve 15 is closed. 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 atomizing 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, the 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 flow rate of the oxidant gas passing 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 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, while the concave cavity 21 plays a flame stabilizing role.

[0054] This embodiment reduces the oxidant gas flow rate of the aerated kerosene by decreasing the opening of the adjustable flow device as the kerosene temperature rises after actively cooling the combustion chamber walls, shifting the kerosene from a liquid state to a supercritical state. This reduces the gas-to-liquid mass ratio of oxidant gas to kerosene. When the kerosene enters the supercritical state, the gas-to-liquid mass ratio drops to zero. This method ensures minimal changes in the density of the aerated kerosene in the nozzles as the kerosene heats and decreases in density. This ensures relatively stable jet penetration depth and gas mixing efficiency, effectively avoiding the problem of reduced engine combustion efficiency caused by nozzle switching caused by kerosene phase changes.

[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 in detail. For the above embodiments, since they are basically similar to the method embodiments, the description is relatively simple. For relevant parts, please refer to the partial description of the method embodiments.

[0056] The above embodiments provide a detailed introduction to the present invention. 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 ideas. At the same time, for those skilled in the art, according to the ideas of the present invention, there may be changes in the specific implementation methods and application scopes. In summary, the contents of this specification should not be understood as limiting 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 supersonic combustion chamber wall and then enters the oxidant gas pipeline (10) built into the injection cavity integrated module (5); The engine wall cooling channel (3) comprises a cooling channel inlet (2) connected to the outlet of the kerosene supply module (1), and a cooling channel outlet (4) connected to the kerosene inlet pipeline (6) provided on the injection cavity integrated module (5); a temperature sensor (20) for monitoring oil temperature is provided at the cooling channel outlet (4); 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, and 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 that absorbs the heat of the supersonic combustion chamber wall are mixed in the oxidant gas pipeline (10) to form aerated atomized kerosene, which is then sprayed out from the atomized kerosene nozzle (14) whose axis is arranged at right angles 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 nozzle (14), and an oxidant nozzle (17) connected to the 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 nozzle (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 other end of the kerosene inlet pipeline (6) is connected to an annular confluence cavity (7) provided on the injection cavity integrated module (5); the outlet of the annular confluence cavity (7) is connected to a kerosene pipeline (8), and the kerosene pipeline (8) is communicated with the oxidant gas pipeline (10) through a liquid inlet hole (9) provided on the oxidant gas pipeline (10).

4. The aerosol injection cavity system according to claim 3, characterized in that: The liquid inlet holes (9) are any one of straight holes, oblique holes or tangential holes, the number of the liquid inlet holes (9) is at least 4, and the cross-sectional shape of the liquid inlet holes (9) is at least one of circular, elliptical, rectangular, diamond or raindrop-shaped.

5. 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 circle, an ellipse, a rectangle, a diamond or a raindrop shape.

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

7. The aerosol injection cavity system according to claim 3, 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.

8. A method for spraying tissue combustion applied to the aerosol spray cavity system according to any one of claims 1 to 7, characterized in that: The method comprises the following steps: S1, the 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, and then 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) 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 ejected from the atomized kerosene nozzle hole (14) to form a horizontal 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 ejected from the oxidant nozzle (17) provided on the bottom surface (18) of the cavity; S4. During different engine operation stages, 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 engine combustion is achieved by combining the on-off of the electromagnetic shut-off valve (15).

9. The method for injecting tissue combustion according to claim 8, 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 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 hole (14) upstream of the cavity (21) to form a transverse atomized kerosene jet (23). The pressure in the atomized kerosene nozzle 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 rupture, causing the kerosene wrapped outside the bubbles to break up and form droplets with smaller particle sizes. At the same time, another portion of the oxidant gas passes through the sonic flow meter (16) and is ejected from the oxidant nozzle hole (17) on the bottom surface (18) of the cavity, 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 shut-off valve (15) is turned off, and all the oxidant gas supplied by the oxidant gas supply module (11) enters the oxidant gas pipe (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 action of the shear layer (24), a part of the transverse 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 stable flame zone, thereby achieving stable combustion of the kerosene; As the temperature of the kerosene increases after the kerosene actively cools 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 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, while the concave cavity (21) plays a role in stabilizing the flame.

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