A gas atomization injection cavity device based on nitrous oxide and a gas atomization injection atomization mixing flame stabilization method

Abstract

The present invention relates to the field of wide-range ramjet engines, addressing the technical issues of difficult ignition and flame stabilization in a supersonic combustion chamber caused by cold-start fuel, as well as the difficulty in organizing combustion over a wide Mach number. The invention particularly relates to a nitrous oxide-based atomized injection cavity device and a method for atomizing and mixing flames. The device comprises an injection cavity integrated module disposed on a supersonic combustion chamber, and an atomizing kerosene nozzle orifice with an outlet located on a surface of the injection cavity integrated module. A cavity is disposed downstream of the atomizing kerosene nozzle orifice. High-temperature nitrous oxide gas and kerosene are mixed in the injection cavity integrated module to form kerosene atomized with the high-temperature nitrous oxide gas, which is then injected laterally upstream of the cavity through the atomizing kerosene nozzle orifice. The present invention can improve the ignition performance of liquid kerosene, while also reducing the atomized particle size and increasing the jet penetration depth, thereby enhancing the gas mixing efficiency and broadening the range of liquid kerosene supersonic combustion flame stabilization.

Description

Technical Field

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

[0002] Liquid hydrocarbon fuel undergoes the following stages within a supersonic combustor: fuel injection atomization, fuel-air mixing, ignition, and stable combustion. This entire process typically occurs within a fuel residence time of a few milliseconds. Therefore, after injection, the fuel must be quickly and thoroughly mixed with the incoming air, and appropriate flame stabilization measures must be employed to ensure that the fuel fully burns within this brief residence time, releasing heat that is ultimately converted into thrust.

[0003] However, during the cold start of a supersonic combustor, due to the low temperature of the liquid hydrocarbon fuel, it is constrained 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-band 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 the fuel and air, shortens the fuel residence time, and increases the difficulty of combustion organization. Summary of the Invention

[0004] In response to the shortcomings of the existing technology, 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 difficulty in ignition and flame stabilization in the combustion chamber caused by cold start of supersonic combustion chamber fuel and the high difficulty in organizing combustion in a wide Mach number.

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

[0006] The aerosol injection cavity device also includes an injection cavity integrated module disposed on the supersonic combustion chamber, and an aerosolized kerosene nozzle hole having an outlet located on a surface of the injection cavity integrated module. A cavity is disposed downstream of the aerosolized kerosene nozzle hole. High-temperature nitrous oxide gas and kerosene are mixed in the injection cavity integrated module to form aerated atomized kerosene aerated with the high-temperature nitrous oxide gas, which is then laterally injected upstream of the cavity through the aerosolized kerosene nozzle hole.

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

[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 aerosolized 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 having 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 a 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 provided thereon, and a nitrous oxide gas pipeline connected to the outlet of the sonic flowmeter, the nitrous oxide gas pipeline being coaxial with and extending through the atomized kerosene nozzle, and having a plurality of liquid inlet holes provided on the nitrous oxide gas pipeline, and the nitrous oxide gas pipeline being 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 its circumference. 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 circle, an ellipse, a rectangle, a diamond or a raindrop shape.

[0015] Furthermore, the number of the atomized kerosene nozzles can be one or more, the cross-sectional shape of the atomized kerosene nozzles is one of circular, elliptical, rectangular, diamond or raindrop-shaped, and the axis of the atomized kerosene nozzles 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 method for gas atomization injection atomization mixing and stabilizing flame 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. The nitrous oxide then flows through the heat exchange pipeline provided on the surface of the heat source. The nitrous oxide removes 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, then changes from liquid to gaseous, forming high-temperature nitrous oxide gas.

[0019] S2. The 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, thereby throttling 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. The kerosene flows through the kerosene inlet pipeline, the kerosene confluence chamber, and the kerosene pipeline, and then enters the nitrous oxide gas pipeline through the liquid inlet hole. The kerosene is mixed with the high-temperature nitrous oxide gas in the nitrous oxide gas pipeline to form kerosene 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 atomizing kerosene nozzle hole, forming an atomized kerosene transverse jet in the supersonic combustion chamber;

[0022] S5. The difference in air flow 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 recirculation zone, thereby widening the combustion flame stabilization range.

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

[0024] 1. The present invention forms a jet containing an oxidant within a supersonic combustion chamber, thereby improving the ignition performance of liquid kerosene. It also reduces the atomized particle size, increases the jet penetration depth, and enhances the gas mixing efficiency. Furthermore, a portion of the atomized kerosene enters the cavity through shear layer oscillation, forming a high-temperature, oxygen-rich, low-speed confluence zone within the cavity, which helps broaden the flame stabilization range of the liquid kerosene supersonic combustion.

[0025] 2. The present invention uses the cavity to mix high-temperature gaseous nitrous oxide with kerosene to form kerosene atomized by the high-temperature nitrous oxide gas. The kerosene is then 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.

[0026] 3. The present invention utilizes the difference in air flow velocity between the mainstream of the supersonic combustion chamber and the air flow in the cavity to form a cavity shear layer at the front end surface of the cavity, which causes the jet containing the oxidant to oscillate into the cavity and burn in the cavity to form a high-temperature, oxygen-rich, low-speed recirculation 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 Schematic diagram of the structure of the aerosol injection cavity device of the present invention;

[0029] Figure 2 Schematic diagram of the flow field of the atomized kerosene transverse 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 nozzle hole; 16. Cavity; 17. Ignitor; 18. Cavity front face; 19. Cavity bottom face; 20. Cavity rear face; 21. Aerated atomized kerosene; 22. Atomized kerosene lateral jet; 23. Combustion chamber mainstream; 24. Shear layer; 25. Low-speed recirculation zone. DETAILED DESCRIPTION

[0031] 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 uses technical means to solve technical problems and achieve technical effects, and to implement the invention accordingly.

[0032] Example 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 the difficulty of organizing combustion at a wide Mach number, please refer to Figure 1-Figure 2This embodiment proposes a nitrous oxide-based atomized injection cavity device that can improve the ignition performance of liquid kerosene, while also reducing the atomized particle size and increasing the jet penetration depth, thereby enhancing the gas mixing efficiency and widening the flame stability range of liquid kerosene supersonic combustion. The atomized injection cavity device includes a supply module 1 that supplies liquid nitrous oxide to a heat exchange module 2 via extrusion or pump pressure. The heat exchange module 2 heats up the liquid nitrous oxide, converting it from a liquid phase into a gaseous, high-temperature nitrous oxide gas. A sonic flowmeter 3 is connected to the outlet of the heat exchange module 2. The high-temperature nitrous oxide gas passes through the throat of the sonic flowmeter 3, generating a critical cross section to throttle the high-temperature nitrous oxide gas.

[0034] The aerosol injection cavity device also includes an injection cavity integrated module 4 disposed on the supersonic combustion chamber. The injection cavity integrated module 4 is manufactured by at least one of the following methods: machining, welding, or additive manufacturing. Furthermore, an aerosolized kerosene nozzle 15 is located on the surface of the injection cavity integrated module 4. The number of aerosolized kerosene nozzles 15 can be one or more, and the cross-sectional shape of the aerosolized kerosene nozzles 15 is one of circular, elliptical, rectangular, diamond, or raindrop-shaped. The axis of the aerosolized kerosene nozzle 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 nozzle 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 injected upstream of the concave cavity 16 through the atomizing kerosene nozzle 15 and forms a jet containing an oxidant 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] Cavity 16 includes a front face 18 perpendicular to the surface of the injection cavity integrated module 4, and a bottom face 19 parallel to the surface of the injection cavity integrated module 4 and perpendicular to the front face 18. The inclined surface connecting the bottom face 19 and the surface of the injection cavity integrated module 4 forms a rear face 20. The length-to-depth ratio of cavity 16 is 5-8, the angle between rear face 20 and bottom face 19 is 40-50 degrees, and the distance from front face 18 to atomizing kerosene nozzle 15 is 15-30 times the equivalent diameter of the nozzle. The cavity configuration allows high-temperature gaseous nitrous oxide to mix with kerosene to form atomized kerosene aerated with high-temperature nitrous oxide gas. This is then 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 provided 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. The nitrous oxide gas pipeline 6 is provided with multiple liquid inlet holes 14, 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. The multiple kerosene pipelines 13 are parallel to the nitrous oxide gas pipeline 6 and are evenly distributed around it. The injection cavity integrated module 4 is provided with an igniter 17 mounted vertically 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 holes 14 are any of straight holes, oblique holes or tangential holes. The number of the liquid inlet holes 14 is at least 4, and the cross-sectional shape of the liquid inlet holes 14 is at least one of circular, elliptical, rectangular, diamond or raindrop-shaped.

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

[0038] This embodiment forms a jet containing an oxidizer in a supersonic combustion chamber, which can help improve the ignition performance of liquid kerosene. At the same time, it 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 liquid kerosene supersonic combustion.

[0039] Example 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. The nitrous oxide then flows through the heat exchange pipeline 9 provided on the surface of the heat source 8. 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.

[0042] 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 flowmeter 3 to achieve throttling of the high temperature nitrous oxide gas, wherein the total temperature at the gaseous nitrous oxide outlet 10 is , total pressure Sonic flowmeter 3 throat area Determine the flow rate of high-temperature nitrous oxide gas ,Right now:

[0043]

[0044] in, is the gas constant for the high-temperature decomposition of hydrogen peroxide; 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 via 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. Atomized kerosene 21, atomized by high-temperature nitrous oxide, is laterally ejected upstream of cavity 16 through atomized kerosene nozzle 15, forming atomized kerosene transverse jet 22 within the supersonic combustion chamber. Because the pressure within atomized kerosene nozzle 15 is higher than the ambient pressure within the supersonic combustion chamber, the bubbles within atomized kerosene transverse jet 22 further expand and rupture, causing the kerosene encased in the bubbles to break up and form smaller droplets. Atomized kerosene transverse jet 22 increases jet penetration depth, shortens the gas mixing distance, and improves gas mixing efficiency. High-temperature nitrous oxide, containing oxygen, is mixed into atomized kerosene transverse jet 22 to form an oxidant-containing jet, shortening ignition time and enhancing combustion performance.

[0047] S5. The difference in air flow velocity between the main flow 23 in 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 and flame stabilization range.

[0048] This embodiment utilizes the difference in air flow velocity between the mainstream of the supersonic combustion chamber and the air flow in the cavity to form a cavity shear layer at the front end face of the cavity, which causes the jet containing the oxidant to oscillate into the cavity, and burn in the cavity to form a high-temperature, oxygen-rich, low-speed recirculation zone, thereby widening the 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 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.

[0050] 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. 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 liquid to gaseous high-temperature nitrous oxide gas after absorbing heat and raising the temperature; The aerosol injection cavity device further comprises an injection cavity integrated module (4) arranged on the supersonic combustion chamber, and an aerosolized kerosene nozzle hole (15) with an outlet located on the surface of the injection cavity integrated module (4); a cavity (16) is provided downstream of the aerosolized kerosene nozzle hole (15); high-temperature nitrous oxide gas and kerosene are mixed in the injection cavity integrated module (4) to form aerosolized kerosene (21) aerosolized by the high-temperature nitrous oxide gas, and the aerosolized kerosene (21) is laterally injected upstream of the cavity (16) through the aerosolized kerosene nozzle hole (15); The cavity (16) includes a cavity front end 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 end face (18), and an inclined surface connecting the cavity bottom face (19) and the surface of the injection cavity integrated module (4) constitutes a 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 to 8, the angle between the rear end surface (20) of the cavity and the bottom surface (19) of the cavity is 40° to 50°, and the distance from the front end surface (18) of the cavity to the atomizing kerosene nozzle (15) is 15 to 30 times the equivalent diameter of the nozzle.

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 the 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 of the combustion chamber, the outer wall of the gas generator, or the gas turbine housing. 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) includes a kerosene inlet pipeline (11) provided thereon, and a nitrous oxide gas pipeline (6) connected to the outlet of the sonic flowmeter (3), the nitrous oxide gas pipeline (6) being coaxial with and interpenetrating the atomized kerosene nozzle (15), the nitrous oxide gas pipeline (6) being provided with a plurality of liquid inlet holes (14), and the nitrous oxide gas pipeline (6) being connected to the kerosene pipeline (13) via the liquid inlet holes (14); The kerosene inlet pipeline (11) is connected to the kerosene pipeline (13) after passing through the annular kerosene confluence chamber (12). The 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 the working surface of the igniter (17) is coplanar with the cavity bottom surface (19).

7. The aerosol injection cavity device according to claim 6, characterized in that: The liquid inlet holes (14) are any one of straight holes, oblique holes or tangential holes, the number of the liquid inlet holes (14) is at least 4, and the cross-sectional shape of the liquid inlet holes (14) is at least one of circular, elliptical, rectangular, diamond or raindrop-shaped.

8. The aerosol injection cavity device according to claim 1, characterized in that: The number of the atomized kerosene spray holes (15) is one or more, the cross-sectional shape of the atomized kerosene spray holes (15) is one of a circle, an ellipse, a rectangle, a diamond or a raindrop shape, and the axis of the atomized kerosene spray hole (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 machining, welding or additive manufacturing integrated forming.

10. A method for gas atomization spraying, atomization mixing and flame stabilization applied to the gas atomization spraying 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) provided 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 flowmeter (3), thereby achieving throttling of the high-temperature nitrous oxide gas; S3, the high-temperature nitrous oxide gas flowing out of the sonic flowmeter (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), forming aerated atomized kerosene (21) aerated and atomized by the high-temperature nitrous oxide gas; S4, the atomized kerosene (21) atomized by the high-temperature nitrous oxide gas is laterally ejected upstream of the cavity (16) through the atomized kerosene nozzle hole (15), forming an atomized kerosene transverse jet (22) in the supersonic combustion chamber; S5. The difference in air flow velocity between the main flow (23) in 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 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 flame stabilization range.

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