Gas atomization injection concave cavity device based on nitrous oxide and gas atomization injection and atomization mixing flame stabilizing method

Abstract

The invention relates to the technical field of wide-range ramjet engines, solves the technical problems of difficult ignition and flame stabilization in a combustion chamber and high combustion difficulty of wide Mach number organizations caused by cold start of fuel in a supersonic combustion chamber, and particularly relates to a nitrous oxide-based gas atomization injection concave cavity device and a gas atomization injection and atomization mixing flame stabilization method. Comprising an injection concave cavity integration module arranged on the supersonic combustion chamber and a gas atomization kerosene spray hole with an outlet formed in the surface of the injection concave cavity integration module, and a concave cavity is formed in the downstream of the gas atomization kerosene spray hole. High-temperature nitrous oxide gas and kerosene are mixed in the injection concave cavity integration module to form kerosene which is inflated and atomized by the high-temperature nitrous oxide gas, and the kerosene is transversely injected at the upstream of the concave cavity through the gas atomization kerosene injection hole. The ignition performance of liquid kerosene can be improved, meanwhile, the atomization particle size can be reduced, the jet flow penetration depth can be increased, the fuel gas mixing efficiency is improved, and the supersonic combustion flame stabilizing range of the liquid kerosene is widened.

Description

Technical Field

[0001] The invention relates to the technical field of wide-range ramjet engines, and in particular to a gas atomization injection cavity device based on nitrous oxide and a gas atomization injection atomization mixing flame stabilization method. Background Art

[0002] Liquid hydrocarbon fuel in a supersonic combustion chamber mainly undergoes the stages of fuel injection atomization, fuel-air mixing, ignition and stable combustion. The entire process is usually completed within a few milliseconds of fuel residence time, so it is required that the fuel must be quickly mixed with the incoming air after injection, and corresponding flame stabilization measures must be taken to ensure that the fuel is fully burned and releases heat within a short residence time, and finally converted into thrust.

[0003] However, during the cold start of the supersonic combustion chamber, due to the low temperature of the liquid hydrocarbon fuel, it is restricted by physical processes such as fuel droplet breakup, atomization, evaporation, and gas mixing, resulting in a long ignition delay time and difficulty in ignition and flame stabilization in the combustion chamber. In addition, for wide-range ramjet engines in flight conditions of Ma<4.0, the fuel cannot self-ignite due to the low total temperature of the incoming flow (<900K). For flight conditions of Ma>7, the ultra-high-speed flow reduces the mixing efficiency of fuel and air, shortens the fuel residence time, and increases the difficulty of combustion organization. Summary of the invention

[0004] In view of the shortcomings of the prior art, the present invention provides a nitrous oxide-based gas atomization injection cavity device and a gas atomization injection atomization mixing flame stabilization method, which solves the technical problems of ignition and flame stabilization difficulties in the combustion chamber caused by cold start of supersonic combustion chamber fuel and the high difficulty in organizing combustion over a wide Mach number.

[0005] In order to solve the above technical problems, the present invention provides the following technical solutions: a nitrous oxide-based aerosol injection cavity device, comprising a supply module for supplying liquid nitrous oxide to a heat exchange module by extrusion supply or pump pressure supply, wherein the heat exchange module changes the liquid nitrous oxide from a liquid state into a gaseous high-temperature nitrous oxide gas after absorbing heat and raising the temperature;

[0006] The gas atomization injection cavity integrated module also includes an injection cavity integrated module arranged on the supersonic combustion chamber, and a gas atomization kerosene spray hole with an outlet disposed on the surface of the injection cavity integrated module, a cavity is arranged downstream of the gas atomization kerosene spray hole, high-temperature nitrous oxide gas and kerosene are mixed in the injection cavity integrated module to form aerated atomized kerosene aerated and atomized by the high-temperature nitrous oxide gas, and the aerated atomized kerosene is sprayed laterally upstream of the cavity through the gas atomization kerosene spray hole;

[0007] The cavity includes a front end face of the cavity perpendicular to the surface of the injection cavity integrated module, and a bottom face of the cavity parallel to the surface of the injection cavity integrated module and perpendicular to the front end face of the cavity. The inclined surface connecting the bottom face of the cavity and the surface of the injection cavity integrated module constitutes a rear end face of the cavity.

[0008] Furthermore, the length-to-depth ratio of the cavity is 5-8, the angle between the rear end face of the cavity and the bottom face of the cavity is 40°-50°, and the distance from the front end face of the cavity to the atomizing kerosene nozzle is 15-30 times the equivalent diameter of the nozzle.

[0009] Furthermore, the heat exchange module includes a heat exchange pipeline arranged on the surface of the heat source, the heat exchange pipeline has a liquid nitrous oxide inlet and a gaseous nitrous oxide outlet, the liquid nitrous oxide inlet is connected to the outlet of the supply module through the pipeline, and the gaseous nitrous oxide outlet is connected to the sonic flowmeter.

[0010] Furthermore, the heat source surface is at least one of the outer wall of the combustion chamber, the outer wall of the gas generator or the gas turbine casing, and the heat exchange pipeline is in the form of a single S-shaped or multiple parallel cooling channels, and the cross-section of the cooling channel is rectangular or circular.

[0011] Furthermore, the outlet of the heat exchange module is connected to a sonic flowmeter, and the high-temperature nitrous oxide gas generates a critical cross section at the throat of the sonic flowmeter, thereby achieving throttling of the high-temperature nitrous oxide gas.

[0012] Furthermore, the injection cavity integrated module includes a kerosene inlet pipeline arranged thereon, and a nitrous oxide gas pipeline connected to the outlet of the sonic flowmeter, the nitrous oxide gas pipeline is coaxial with and penetrates the atomized kerosene nozzle, a plurality of liquid inlet holes are arranged on the nitrous oxide gas pipeline, and the nitrous oxide gas pipeline is connected to the kerosene pipeline through the liquid inlet holes;

[0013] The kerosene inlet pipeline is connected to the kerosene pipeline after passing through the annular kerosene confluence chamber. Multiple kerosene pipelines are parallel to the nitrous oxide gas pipeline and are evenly distributed around the circumference thereof. The injection cavity integrated module is provided with an igniter vertically mounted on the bottom surface of the cavity, and the working surface of the igniter is coplanar with the bottom surface of the cavity.

[0014] 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.

[0015] Furthermore, the number of the aerosolized kerosene spray holes can be one or more, the cross-sectional shape of the aerosolized kerosene spray holes is one of circular, elliptical, rectangular, diamond or raindrop-shaped, and the axis of the aerosolized kerosene spray holes is at right angles to the surface of the injection cavity integrated module.

[0016] Furthermore, the injection cavity integrated module is processed by at least one of machining, welding or additive manufacturing integrated forming.

[0017] The technical solution also provides a gas atomization injection atomization mixing flame stabilization method applied to the above-mentioned gas atomization injection cavity device, the method comprising the following steps:

[0018] S1. The supply module transports liquid nitrous oxide to the liquid nitrous oxide inlet of the heat exchange module through a pipeline, and then the nitrous oxide flows through the heat exchange pipeline arranged on the surface of the heat source. The nitrous oxide takes away heat from the surface of the heat source to cool and protect the heat source. At the same time, the nitrous oxide absorbs heat and heats up, and changes from a liquid state to a gaseous high-temperature nitrous oxide gas;

[0019] S2, high-temperature gaseous nitrous oxide flows out from the gaseous nitrous oxide outlet of the heat exchange module, and generates a critical cross section at the throat of the sonic flowmeter to achieve throttling of the high-temperature nitrous oxide gas;

[0020] S3, the high-temperature nitrous oxide gas flowing out of the sonic flowmeter enters the nitrous oxide gas pipeline, and the kerosene flows through the kerosene inlet pipeline, the kerosene confluence chamber, the kerosene pipeline, and then enters the nitrous oxide gas pipeline through the liquid inlet hole, and mixes with the high-temperature nitrous oxide gas in the nitrous oxide gas pipeline to form kerosene aerated and atomized by the high-temperature nitrous oxide gas;

[0021] S4, the kerosene atomized by the high-temperature nitrous oxide gas is sprayed laterally upstream of the cavity through the atomized kerosene spray hole, forming a lateral jet of atomized kerosene in the supersonic combustion chamber;

[0022] S5. The difference in air velocity between the mainstream of the combustion chamber and the concave cavity forms a cavity shear layer at the front end of the cavity. A portion of the oxygen-containing atomized kerosene oscillates into the cavity through the shear layer and burns in the cavity to form a high-temperature, oxygen-rich, low-speed reflux zone, thereby broadening the combustion flame stabilization range.

[0023] By means of the above technical solution, the present invention provides a gas atomization injection cavity device based on nitrous oxide and a gas atomization injection atomization mixing flame stabilization method, which has at least the following beneficial effects:

[0024] 1. The present invention can help improve the ignition performance of liquid kerosene by forming a jet containing an oxidant in a supersonic combustion chamber, and at the same time can reduce the atomized particle size and increase the jet penetration depth, thereby improving the gas mixing efficiency. In addition, a portion of the atomized kerosene enters the concave cavity through shear layer oscillation, forming a high-temperature, oxygen-rich, low-speed confluence zone in the concave cavity, which helps to broaden the flame stabilization range of the supersonic combustion of liquid kerosene.

[0025] 2. The present invention arranges the concave cavity so that the high-temperature gaseous nitrous oxide is mixed with kerosene to form kerosene aerated and atomized by the high-temperature nitrous oxide gas, and then the kerosene is laterally sprayed upstream of the concave cavity through the atomized kerosene nozzle hole, thereby reducing the atomized particle size and increasing the jet penetration depth, thereby improving the gas mixing efficiency.

[0026] 3. The present invention utilizes the difference in air flow velocity between the mainstream of the supersonic combustion chamber and the concave cavity to form a concave cavity shear layer at the front end surface of the concave cavity, which allows the jet containing the oxidant to oscillate into the concave cavity, and burn in the concave cavity to form a high-temperature, oxygen-rich, low-speed reflow zone, thereby widening the flame stabilization range. BRIEF DESCRIPTION OF THE DRAWINGS

[0027] 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:

[0028] Figure 1 It is a schematic diagram of the structure of the gas atomization injection cavity device of the present invention;

[0029] Figure 2 Schematic diagram of the flow field of the atomized kerosene lateral jet in the present invention.

[0030] In the figure: 1. Supply module; 2. Heat exchange module; 3. Sonic flowmeter; 4. Injection cavity integrated module; 5. Pipeline; 6. Nitrous oxide gas pipeline; 7. Liquid nitrous oxide inlet; 8. Heat source surface; 9. Heat exchange pipeline; 10. Gaseous nitrous oxide outlet; 11. Kerosene inlet pipeline; 12. Kerosene confluence chamber; 13. Kerosene pipeline; 14. Liquid inlet hole; 15. Atomized kerosene spray hole; 16. Cavity; 17. Ignitor; 18. Cavity front end surface; 19. Cavity bottom surface; 20. Cavity rear end surface; 21. Aerated atomized kerosene; 22. Atomized kerosene lateral jet; 23. Combustion chamber mainstream; 24. Shear layer; 25. Low-speed recirculation zone. DETAILED DESCRIPTION

[0031] 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.

[0032] Embodiment 1

[0033] In order to solve the technical problems of ignition and flame stabilization in the combustion chamber caused by cold start of supersonic combustion chamber fuel and high difficulty in organizing combustion at a wide Mach number, please refer to Figure 1-Figure 2This embodiment proposes a gas atomization injection cavity device based on nitrous oxide, which can improve the ignition performance of liquid kerosene, reduce the atomized particle size and increase the jet penetration depth, improve the gas mixing efficiency, and broaden the range of liquid kerosene supersonic combustion flame stabilization. The gas atomization injection cavity device includes a supply module 1 that supplies liquid nitrous oxide to a heat exchange module 2 by extrusion supply or pump pressure supply. The heat exchange module 2 changes the liquid nitrous oxide from a liquid state to a gaseous high-temperature nitrous oxide gas after absorbing heat and heating. The outlet of the heat exchange module 2 is connected to a sonic flowmeter 3, and the high-temperature nitrous oxide gas generates a critical cross section at the throat of the sonic flowmeter 3, thereby realizing throttling of the high-temperature nitrous oxide gas.

[0034] The gas atomization injection cavity integrated module also includes an injection cavity integrated module 4 arranged on the supersonic combustion chamber, and the injection cavity integrated module 4 is processed by at least one of the following methods: mechanical processing, welding or additive manufacturing integrated forming. And the gas atomization kerosene spray hole 15 with the outlet placed on the surface of the injection cavity integrated module 4, the number of the gas atomization kerosene spray hole 15 can be one or more, the cross-sectional shape of the gas atomization kerosene spray hole 15 is one of circular, elliptical, rectangular, diamond or raindrop, and the axis of the gas atomization kerosene spray hole 15 is at right angles to the surface of the injection cavity integrated module 4. A concave cavity 16 is provided downstream of the atomizing kerosene spray hole 15. The high-temperature nitrous oxide gas and kerosene are mixed in the injection concave cavity integrated module 4 to form aerated atomized kerosene 21 aerated and atomized by the high-temperature nitrous oxide gas. The kerosene 21 is laterally sprayed upstream of the concave cavity 16 through the atomizing kerosene spray hole 15, and a jet containing an oxidant is formed in the supersonic combustion chamber. The jet containing the oxidant burns in the concave cavity 16 to form a high-temperature, oxygen-rich, low-speed recirculation zone 25.

[0035] The cavity 16 includes a cavity front face 18 perpendicular to the surface of the injection cavity integrated module 4, and a cavity bottom face 19 parallel to the surface of the injection cavity integrated module 4 and perpendicular to the cavity front face 18. The cavity bottom face 19 and the inclined surface connecting the surface of the injection cavity integrated module 4 constitute the cavity rear face 20. The length-to-depth ratio of the cavity 16 is 5-8, the angle between the cavity rear face 20 and the cavity bottom face 19 is 40°-50°, and the distance from the cavity front face 18 to the atomizing kerosene nozzle 15 is 15-30 times the equivalent diameter of the nozzle. Through the setting of the cavity, the high-temperature gaseous nitrous oxide and kerosene are mixed to form kerosene atomized by the high-temperature nitrous oxide gas, and then the kerosene is sprayed laterally upstream of the cavity through the atomizing kerosene nozzle, thereby reducing the atomized particle size and increasing the jet penetration depth, thereby improving the gas mixing efficiency.

[0036] The injection cavity integrated module 4 includes a kerosene inlet pipeline 11 arranged thereon, and a nitrous oxide gas pipeline 6 connected to the outlet of the sonic flowmeter 3, the nitrous oxide gas pipeline 6 is coaxial with and penetrates the atomized kerosene nozzle 15, a plurality of liquid inlet holes 14 are provided on the nitrous oxide gas pipeline 6, and the nitrous oxide gas pipeline 6 is connected to the kerosene pipeline 13 through the liquid inlet holes 14; the kerosene inlet pipeline 11 is connected to the kerosene pipeline 13 after passing through the annular kerosene confluence cavity 12, and the plurality of kerosene pipelines 13 are parallel to the nitrous oxide gas pipeline 6 and are evenly distributed around the circumference thereof, and the injection cavity integrated module 4 is provided with an igniter 17 vertically mounted on the bottom surface 19 of the cavity, and the working surface of the igniter 17 is coplanar with the bottom surface 19 of the cavity. The liquid inlet hole 14 is any one of a straight hole, an inclined hole or a tangential hole, the number of the liquid inlet holes 14 is at least 4, and the cross-sectional shape of the liquid inlet hole 14 is at least one of a circular, elliptical, rectangular, diamond or raindrop shape.

[0037] The heat exchange module 2 includes a heat exchange pipeline 9 arranged on the heat source surface 8, and the heat exchange pipeline 9 has a liquid nitrous oxide inlet 7 and a gaseous nitrous oxide outlet 10. The liquid nitrous oxide inlet 7 is connected to the outlet of the supply module 1 through the pipeline 5, and the gaseous nitrous oxide outlet 10 is connected to the sonic flowmeter 3. The heat source surface 8 is at least one of the outer wall surface of the combustion chamber, the outer wall surface of the gas generator or the gas turbine shell. The total heat exchange area of ​​the heat exchange pipeline 9 should ensure that the nitrous oxide is completely converted from liquid to gas. The heat exchange pipeline 9 is in the form of a single S-shaped or multiple parallel cooling channels, and the cross-section of the cooling channel is rectangular or circular. The length of the heat exchange pipeline 9 should ensure that the nitrous oxide flowing through it can undergo a phase change from liquid to gas after absorbing heat.

[0038] This embodiment can help improve the ignition performance of liquid kerosene by forming a jet containing an oxidant in the supersonic combustion chamber, while reducing the atomized particle size and increasing the jet penetration depth, thereby improving the gas mixing efficiency. In addition, a portion of the atomized kerosene enters the concave cavity through shear layer oscillation, forming a high-temperature, oxygen-rich, low-speed confluence zone in the concave cavity, which helps to broaden the flame stabilization range of the liquid kerosene supersonic combustion.

[0039] Embodiment 2

[0040] Based on Example 1, please refer to Figure 1-Figure 2 This embodiment proposes a gas atomization spray atomization mixing flame stabilization method applied to a gas atomization spray cavity device, the method comprising the following steps:

[0041] S1. The supply module 1 transports liquid nitrous oxide to the liquid nitrous oxide inlet 7 of the heat exchange module 2 through the pipeline 5. Then, the nitrous oxide flows through the heat exchange pipeline 9 arranged on the surface 8 of the heat source. The nitrous oxide takes away heat from the surface 8 of the heat source to cool and protect the heat source. At the same time, the nitrous oxide absorbs heat and changes its temperature from liquid to gaseous high-temperature nitrous oxide gas.

[0042] S2, high-temperature gaseous nitrous oxide flows out from the gaseous nitrous oxide outlet 10 of the heat exchange module 2, and a critical cross section is generated at the throat of the sonic flowmeter 3 to achieve throttling of the high-temperature nitrous oxide gas, wherein the total temperature T0, total pressure P0 at the gaseous nitrous oxide outlet 10 and the throat area A of the sonic flowmeter 3 are * Determining the flow rate of high temperature nitrous oxide gas Right now:

[0043]

[0044] Wherein, R is the gas constant of hydrogen peroxide high temperature decomposition; γ is the specific heat ratio of hydrogen peroxide high temperature decomposition gas.

[0045] S3. The high-temperature nitrous oxide gas flowing out of the sonic flowmeter 3 enters the nitrous oxide gas pipeline 6. The kerosene flows through the kerosene confluence chamber 12 and the kerosene pipeline 13 through the kerosene inlet pipeline 11, enters the nitrous oxide gas pipeline 6 through the liquid inlet hole 14, and mixes with the high-temperature nitrous oxide gas in the nitrous oxide gas pipeline 6 to form aerated atomized kerosene 21 aerated and atomized by the high-temperature nitrous oxide gas.

[0046] S4, the kerosene 21 atomized by the high-temperature nitrous oxide gas is sprayed laterally upstream of the concave cavity 16 through the atomized kerosene spray hole 15, forming an atomized kerosene transverse jet 22 in the supersonic combustion chamber. Because the pressure in the atomized kerosene spray hole 15 is higher than the ambient pressure in the supersonic combustion chamber, the bubbles in the atomized kerosene transverse jet 22 further expand and rupture, causing the kerosene wrapped outside the bubbles to break and form droplets with smaller particle sizes. The atomized kerosene transverse jet 22 can increase the jet penetration depth, shorten the gas mixing distance, and improve the gas mixing efficiency. The high-temperature nitrous oxide containing oxygen elements is mixed into the atomized kerosene transverse jet 22 to form a jet containing an oxidant, which can shorten the ignition time and enhance the combustion performance.

[0047] S5. The difference in air flow velocity between the mainstream 23 of the combustion chamber and the concave cavity 16 forms a concave cavity shear layer 24 at the front end surface 18 of the concave cavity. A portion of the oxygen-containing atomized kerosene oscillates into the concave cavity 16 through the shear layer 24 and burns in the concave cavity 16 to form a high-temperature, oxygen-rich, low-speed recirculation zone 25, thereby widening the combustion flame stabilization range.

[0048] This embodiment utilizes the difference in air flow velocity between the mainstream of the supersonic combustion chamber and the concave cavity, and is able to form a cavity shear layer at the front end face of the cavity, causing the jet containing the oxidant to oscillate into the cavity, and burn in the cavity to form a high-temperature, oxygen-rich, low-speed reflow zone, thereby achieving a widened flame stabilization range.

[0049] 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.

[0050] 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. A nitrous oxide-based aerosol injection cavity device, comprising a supply module (1) for supplying liquid nitrous oxide to a heat exchange module (2) by extrusion supply or pump pressure supply, characterized in that: The heat exchange module (2) changes the liquid nitrous oxide from a liquid state into a gaseous high-temperature nitrous oxide gas after absorbing heat and raising the temperature; The gas atomization injection cavity integrated module also includes an injection cavity integrated module (4) arranged on the supersonic combustion chamber, and a gas atomization kerosene spray hole (15) whose outlet is arranged on the surface of the injection cavity integrated module (4); a cavity (16) is arranged downstream of the gas atomization kerosene spray hole (15); high-temperature nitrous oxide gas and kerosene are mixed in the injection cavity integrated module (4) to form aerated atomized kerosene (21) aerated and atomized by the high-temperature nitrous oxide gas, and the aerated atomized kerosene (21) is sprayed laterally upstream of the cavity (16) through the gas atomization kerosene spray hole (15); The concave cavity (16) comprises a concave cavity front end face (18) perpendicular to the surface of the injection concave cavity integrated module (4), and a concave cavity bottom face (19) parallel to the surface of the injection concave cavity integrated module (4) and perpendicular to the concave cavity front end face (18), and the inclined surface connecting the concave cavity bottom face (19) and the surface of the injection concave cavity integrated module (4) constitutes a concave cavity rear end face (20).

2. The aerosol injection cavity device according to claim 1, characterized in that: The length-to-depth ratio of the cavity (16) is 5-8, the angle between the cavity rear end surface (20) and the cavity bottom surface (19) is 40°-50°, and the distance from the cavity front end surface (18) to the atomized kerosene spray hole (15) is 15-30 times the equivalent diameter of the spray hole.

3. The aerosol injection cavity device according to claim 1, characterized in that: The heat exchange module (2) comprises a heat exchange pipeline (9) arranged on the surface of the heat source (8), the heat exchange pipeline (9) having a liquid nitrous oxide inlet (7) and a gaseous nitrous oxide outlet (10), the liquid nitrous oxide inlet (7) being connected to the outlet of the supply module (1) via a pipeline (5), and the gaseous nitrous oxide outlet (10) being connected to a sonic flowmeter (3).

4. The aerosol injection cavity device according to claim 3, characterized in that: The heat source surface (8) is at least one of the outer wall surface of the combustion chamber, the outer wall surface of the gas generator or the gas turbine casing, and the heat exchange pipeline (9) is in the form of a single S-shaped or multiple parallel cooling channels, and the cross-section of the cooling channel is rectangular or circular.

5. The aerosol injection cavity device according to claim 1, characterized in that: The outlet of the heat exchange module (2) is connected to a sonic flowmeter (3), and the high-temperature nitrous oxide gas generates a critical cross section at the throat of the sonic flowmeter (3), thereby achieving throttling of the high-temperature nitrous oxide gas.

6. The aerosol injection cavity device according to claim 5, characterized in that: The injection cavity integrated module (4) comprises a kerosene inlet pipeline (11) arranged thereon, and a nitrous oxide gas pipeline (6) connected to an outlet of a sonic flowmeter (3); the nitrous oxide gas pipeline (6) is coaxial with and penetrates an atomized kerosene spray hole (15); a plurality of liquid inlet holes (14) are arranged on the nitrous oxide gas pipeline (6), and the nitrous oxide gas pipeline (6) is connected to a kerosene pipeline (13) via the liquid inlet holes (14); The kerosene inlet pipeline (11) is connected to a kerosene pipeline (13) after passing through an annular kerosene confluence chamber (12); a plurality of kerosene pipelines (13) are parallel to the nitrous oxide gas pipeline (6) and are evenly distributed around the nitrous oxide gas pipeline (6); the injection cavity integrated module (4) is provided with an igniter (17) vertically mounted on the cavity bottom surface (19); and a working surface of the igniter (17) is coplanar with the cavity bottom surface (19).

7. The aerosol injection cavity device according to claim 1, characterized in that: The liquid inlet hole (14) is any one of a straight hole, an inclined hole or a tangential hole, the number of the liquid inlet holes (14) is at least 4, and the cross-sectional shape of the liquid inlet hole (14) is at least one of a circular shape, an elliptical shape, a rectangular shape, a diamond shape or a raindrop shape.

8. The aerosol injection cavity device according to claim 1, characterized in that: The number of the atomized kerosene spray holes (15) can be one or more, the cross-sectional shape of the atomized kerosene spray holes (15) is one of a circular, elliptical, rectangular, diamond or raindrop shape, and the axis of the atomized kerosene spray holes (15) is at right angles to the surface of the injection cavity integrated module (4).

9. The aerosol injection cavity device according to claim 1, characterized in that: The injection cavity integrated module (4) is processed by at least one of mechanical processing, welding or additive manufacturing integrated forming.

10. A gas atomization spray atomization mixing flame stabilization method applied to the gas atomization spray cavity device according to any one of claims 1 to 9, characterized in that: The method comprises the following steps: S1, the supply module (1) transports liquid nitrous oxide to the liquid nitrous oxide inlet (7) of the heat exchange module (2) through the pipeline (5), and then the nitrous oxide flows through the heat exchange pipeline (9) arranged on the surface of the heat source (8), and the nitrous oxide takes away heat from the surface of the heat source (8) to cool and protect the heat source. At the same time, the nitrous oxide absorbs heat and heats up, and then changes from liquid to gaseous high-temperature nitrous oxide gas; S2, high-temperature gaseous nitrous oxide flows out from the gaseous nitrous oxide outlet (10) of the heat exchange module (2), and generates a critical cross section at the throat of the sonic flow meter (3), thereby achieving throttling of the high-temperature nitrous oxide gas; S3, the high-temperature nitrous oxide gas flowing out of the sonic flow meter (3) enters the nitrous oxide gas pipeline (6), and the kerosene flows through the kerosene inlet pipeline (11), the kerosene confluence chamber (12), and the kerosene pipeline (13), and then enters the nitrous oxide gas pipeline (6) through the liquid inlet hole (14), and is mixed with the high-temperature nitrous oxide gas in the nitrous oxide gas pipeline (6), thereby forming an aerated atomized kerosene (21) atomized by the high-temperature nitrous oxide gas; S4, the atomized kerosene (21) atomized by the high-temperature nitrous oxide gas is laterally sprayed upstream of the cavity (16) through the atomized kerosene spray hole (15), forming an atomized kerosene transverse jet (22) in the supersonic combustion chamber; S5. The difference in air velocity between the main flow (23) of the combustion chamber and the air flow in the concave cavity (16) forms a concave cavity shear layer (24) at the front end surface (18) of the concave cavity. A portion of the oxygen-containing atomized kerosene oscillates through the shear layer (24) into the concave cavity (16) and burns in the concave cavity (16) to form a high-temperature, oxygen-rich, low-speed recirculation zone (25), thereby widening the combustion and flame stabilization range.

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