A wide-range rotating detonation engine overall structure and operation method thereof

Abstract

The present invention discloses a wide-range rotating detonation engine overall structure and an operating method thereof, belonging to the technical field of rotating detonation ramjet engines. It comprises an air inlet, the air inlet is connected to an outer ring transition section, the outer ring transition section is connected to a constant direct injection section, the constant direct injection section is connected to an expansion cavity section, and the expansion cavity section is connected to a tail nozzle; an inner column is provided in the outer ring transition section and the constant direct injection section, a packaging block is provided on the surface of the constant direct injection section, and the inner column is movably connected to a plug nozzle. The wide-range rotating detonation engine overall structure of the present invention ensures that the equipment can adapt to a wide range of flight conditions from low to high Mach numbers through the air inlet and plug nozzle structures. The lip and the adjustable throat work together to achieve dynamic adjustment of the airflow rate. The plug nozzle flexibly adjusts the throat area to adapt to the working range from low Mach number to high Mach number by moving the screw back and forth in the inner column guide rail.

Description

Technical Field

[0001] The present invention relates to the technical field of rotating detonation ramjet engines, and in particular to a wide-range rotating detonation engine overall structure and an operating method thereof. Background Art

[0002] Rotating detonation combustion is characterized by a short combustion distance and high combustion efficiency. Compared to traditional slow-burning ramjets, ramjets employing rotating detonation combustion have shorter axial lengths, lighter structures, and higher combustion efficiency. However, traditional rotating detonation ramjets have disadvantages such as a narrow operating speed range and significant impact of operating altitude changes on detonation wave characteristics, making them unsuitable for engines operating over a wide range. To address these issues, the present invention proposes a wide-range rotating detonation engine structure and operating method. Adjustable intake ducts are used to adjust intake parameters, combined with control of the injection area, combustion area, and throat area to achieve stable rotating detonation combustion over a wide speed and altitude range. Summary of the Invention

[0003] In response to the above-mentioned problems, the present invention aims to provide a wide-range rotating detonation engine structure and an operating method thereof, which ensures that the equipment can adapt to a wide range of flight conditions from low to high Mach numbers through optimized inlet design and dynamic adjustment structure. The lip and the adjustable throat work together to achieve dynamic adjustment of airflow compression and expansion. Through the design of the outer ring transition section, multiple static and dynamic pressure measurement points are set on the surface to achieve real-time monitoring of the combustion state. The plug nozzle moves back and forth in the inner column guide through the screw, and the throat area is flexibly adjusted to adapt to the working range from low Mach number to high Mach number.

[0004] In order to achieve the above object, the technical solution adopted by the present invention is as follows:

[0005] A wide-range rotating detonation engine overall structure and an operating method thereof, comprising an air intake duct, wherein the air intake duct is connected to an outer ring transition section, the outer ring transition section is connected to a direct injection oil section, the direct injection oil section is connected to an expansion cavity section, and the expansion cavity section is connected to a tail nozzle; an inner column is provided in the outer ring transition section and the direct injection oil section, a packaging block is provided on the surface of the direct injection oil section, and the inner column is movably connected to a plug nozzle.

[0006] Furthermore, the air intake duct includes an air intake cone, a suction groove for air intake is provided on the tail surface of the air intake cone, the tail of the air intake cone is connected to a gas collecting cavity, a lip is provided on the surface of the gas collecting cavity, a variable throat is provided between the gas collecting cavity and the lip, and the gas collecting cavity is connected to an exhaust channel.

[0007] Furthermore, a plurality of first static pressure measuring points, a plurality of first dynamic pressure measuring points and a transfer column are provided in the outer ring transfer section, and a support plate mounting groove is also provided on the surface of the outer ring transfer section, and the transfer column is respectively connected to the inner column and the exhaust channel.

[0008] Furthermore, the support plate mounting groove includes a notch and a threaded hole corresponding to the notch, and the notch passes through the inner column; a packaging block is correspondingly provided on the support plate mounting groove, and the packaging block includes a sealing block matching the notch and a sealing cover matching the threaded hole; a second fuel inlet is provided on the sealing cover, and a liquid collecting cavity and a plurality of injection holes corresponding to the liquid collecting cavity are provided on the sealing block.

[0009] Furthermore, the surface of the direct injection oil section is provided with multiple groups of first annular injections, second static pressure measuring points and second dynamic pressure measuring points; the first annular injection includes a first fuel inlet on the outer surface of the direct injection oil section and a nozzle on the inner surface of the direct injection oil section.

[0010] Furthermore, the expansion cavity section includes an expansion section and a cavity section; the surface of the expansion section is provided with multiple groups of second annular sprays and multiple third static pressure measuring points.

[0011] Furthermore, the expansion cavity section is connected to a tail nozzle, and the tail nozzle is also provided with a throat liner.

[0012] Furthermore, the plug-type nozzle includes a lead screw and a streamlined cone, and a guide rail matching the lead screw is provided in the inner column.

[0013] The method for operating the entire structure of a wide-range rotating detonation engine as described above is characterized by comprising the following steps:

[0014] S1: After the combustion chamber is inhaled, the direct injection section, the second annular injection section of the expansion cavity section, and the injection hole points of the packaging block begin to spray oil. After a certain period of time, the oil-air mixture in the combustion chamber is ignited to form a rotating detonation wave.

[0015] S2: When the Mach number is Ma2.0-Ma3.0, the lip and the variable throat move backward, and the plug nozzle retreats, forming a local cavity in the combustion chamber. The injection points are selected along the airflow in the last four groups of first and second ring jets. The combustion area is located in the local cavity. When the flame stabilization equivalence ratio limit is approached, the injection holes of the encapsulation block are opened to achieve flame stabilization in a wider range.

[0016] S3: When the Mach number is Mach 4.0-Mach 5.0, the lip, variable throat, and plug nozzle move forward, and the injection point is selected along the fourth to seventh groups of first ring injection along the airflow, and the combustion area is located in the large-size combustion zone;

[0017] S4: When the Mach number is Ma6.0-Ma7.0, the lip moves backward to control the shock wave seal, the variable throat moves forward, the plug nozzle moves forward, and the local cavity is completely closed. The injection point is located in the first four groups of first ring jets along the airflow, and the combustion area is located in the small-size combustion zone.

[0018] The beneficial effects of the present invention are:

[0019] 1. The overall structure of the wide-range rotating detonation engine of the present invention ensures that the equipment can adapt to a wide range of flight conditions from low to high Mach numbers through optimized air inlet design and dynamic adjustment structure. The lip and adjustable throat work together to achieve dynamic adjustment of airflow compression and expansion. Through the design of the outer ring transition section, multiple static and dynamic pressure measuring points are set on the surface to achieve real-time monitoring of the combustion status. The plug-type nozzle moves back and forth in the inner column guide through the screw, and the throat area is flexibly adjusted to adapt to the working range from low Mach number to high Mach number. The direct injection oil section ensures different combustion requirements through multiple sets of ring injection designs, and the dynamic and static pressure measuring points further monitor the flow field stability of the combustion chamber.

[0020] 2. The outer ring adapter section of this invention features multiple static and dynamic pressure measurement points on its surface, providing real-time monitoring capabilities and ensuring combustion stability. The internal adapter column connects to the inner column and expansion section, supporting the movement of the plug nozzle. The encapsulation block design provides a fuel delivery path, and the secondary fuel inlet, combined with the injection port, enables efficient fuel injection according to different combustion requirements.

[0021] 3. The present invention ensures that the equipment can adapt to flight conditions in a wide range of speeds from low to high Mach numbers through optimized inlet duct design and dynamic adjustment structure. The intake cone optimizes the efficiency of airflow introduction through streamlined design, and the suction and removal grooves effectively absorb low-energy airflow in the boundary layer to avoid airflow separation. The air collecting cavity is combined with the suction and exhaust channel to ensure smooth airflow discharge. The lip and the adjustable throat work together to achieve dynamic adjustment of airflow compression and expansion to meet the requirements of different Mach number working conditions. At low Mach numbers, the lip moves backward to increase the intake flow; at medium Mach numbers, the lip moves forward to compress the airflow and improve combustion efficiency. At high Mach numbers, the inlet lip moves backward to control the shock wave seal and ensure the intake flow.

[0022] 4. The plug nozzle, through the precise coordination of the leadscrew and streamlined cone, dynamically adjusts the throat area according to varying operating conditions, adapting to changes in airflow velocity and pressure and improving combustion chamber efficiency. Furthermore, multiple static and dynamic pressure measurement points within the device's outer ring adapter section, direct injection section, and expansion cavity section enable real-time monitoring and feedback of the combustion chamber's status, ensuring safe and reliable operation. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] Figure 1It is a structural schematic diagram of the overall structure of the wide-range rotating detonation engine in the present invention.

[0024] Figure 2 This is a front view of the overall structure of the wide-range rotating detonation engine in the present invention.

[0025] Figure 3 It is a cross-sectional view of the overall structure of the wide-range rotating detonation engine in the present invention.

[0026] Figure 4 Schematic diagram of the structure of the air intake duct in the present invention.

[0027] Figure 5 It is a structural schematic diagram of the outer ring transition section in the present invention.

[0028] Figure 6 It is a structural schematic diagram of the encapsulation block in the present invention.

[0029] Figure 7 It is a cross-sectional view of the packaging block in the present invention.

[0030] Figure 8 This is a cross-sectional view of the packaging block in the present invention from another angle.

[0031] Figure 9 It is a structural schematic diagram of the medium direct injection oil section of the present invention.

[0032] Figure 10 It is a cross-sectional view of the medium direct injection oil section of the present invention.

[0033] Figure 11 It is a structural schematic diagram of the expanded concave cavity section in the present invention.

[0034] Figure 12 This is a schematic structural diagram of the expanded cavity section from another angle in the present invention.

[0035] Figure 13 It is a cross-sectional view of the expanded concave cavity section in the present invention.

[0036] Figure 14 It is a structural schematic diagram of the plug-type nozzle in the present invention.

[0037] Figure 15 It is a structural schematic diagram of the throat liner in the present invention.

[0038] Among them: 1. Inlet duct; 2. Adapter column; 3. Outer ring adapter section; 4. Direct injection section; 5. Expander cavity section; 6. Tail nozzle; 7. Inner column; 8. Plug nozzle; 9. Throat liner; 11. Inlet cone; 12. Suction groove; 13. Gas collecting cavity; 14. Lip; 15. Variable throat; 16. Exhaust channel; 31. First static pressure measuring point; 32. First dynamic pressure measuring point; 33. Support plate mounting groove; 34. First flange; 35. Packing block; 41. First ring nozzle; 42. Second static pressure measuring point; 43. Second dynamic pressure measuring point; 44. Third flange; 51 , expansion section; 52, concave cavity section; 53, fourth flange; 61, fifth flange; 81, screw; 82, streamlined cone; 331, notch; 332, threaded hole; 351, blocking block; 352, cover; 411, first fuel inlet; 412, nozzle; 511, second annular nozzle; 512, third static pressure measuring point; 521, pre-explosion pipe interface; 522, high-frequency pressure sensor interface; 523, fourth static pressure measuring point; 524, plasma igniter mounting panel; 3511, liquid collecting chamber; 3512, injection hole; 3521, second fuel inlet. DETAILED DESCRIPTION

[0039] In order to enable those skilled in the art to better understand the technical solution of the present invention, the technical solution of the present invention is further described below in conjunction with the accompanying drawings and embodiments.

[0040] In the description of the present invention, it should be understood that the terms "upper", "lower", "front", "back", "left", "right", "front end", "back end", "inside", "outside", etc., indicating directions or positional relationships, are based on the directions or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific direction, be constructed and operated in a specific direction, and therefore cannot be understood as a limitation on the present invention.

[0041] It should also be noted that, in the description of this application, unless otherwise expressly specified or limited, the terms "disposed," "installed," "connected," and "connected" should be understood broadly. For example, they can refer to fixed connections, detachable connections, or integral connections; they can refer to direct connections, indirect connections through an intermediate medium, or internal connections between two components. Those skilled in the art will understand the specific meanings of the above terms in this application based on the specific circumstances.

[0042] Refer to the attached Figure 1-15The structure of a wide-range rotating detonation engine shown in the figure includes an intake duct 1, the intake duct 1 is connected to an outer ring transition section 3, the outer ring transition section 3 is connected to an equal direct injection oil section 4, and the equal direct injection oil section 4 is connected to an expansion cavity section 5; an inner column 7 is provided in the outer ring transition section 3 and the equal direct injection oil section 4, a packaging block 35 is provided on the surface of the equal direct injection oil section 4, and the inner column 7 is movably connected to a plug nozzle 8.

[0043] The air intake duct 1 includes an air intake cone 11, a suction groove 12 is provided on the rear surface of the air intake cone 11, the rear of the air intake cone 11 is connected to a gas collecting cavity 13, a movable lip 14 is provided on the surface of the gas collecting cavity 13, a variable throat 15 is provided between the gas collecting cavity 13 and the lip 14, and the gas collecting cavity 13 is connected to an exhaust channel 16.

[0044] It should be noted that the intake cone 11 features threads at its rear end, allowing the lip 14 to be moved forward or backward via a motor. The streamlined design of the intake cone 11 optimizes airflow efficiency. The suction groove 12 effectively absorbs low-energy boundary layer airflow. The plenum 13 integrates with the exhaust channel 16 to ensure smooth airflow discharge. The lip 14 works in conjunction with the variable throat 15 to dynamically adjust airflow to meet the demands of varying Mach numbers. At low Mach numbers, the lip 14 moves backward to increase intake flow; at medium Mach numbers, the lip 14 moves forward to compress the airflow and improve combustion efficiency. At high Mach numbers, the lip 14 moves backward to control the shock wave seal and maintain intake flow.

[0045] The surface of the outer ring transition section 3 is provided with multiple first static pressure measuring points 31, multiple first dynamic pressure measuring points 32 and a transition column 2. Both ends of the outer ring transition section 3 are provided with a first flange 34. The surface of the outer ring transition section 3 is also provided with a support plate mounting groove 33. The transition column 2 is respectively connected to the inner column 7 and the air intake duct 1.

[0046] Specifically, the first static pressure measuring point 31 and the first dynamic pressure measuring point 32 are used to monitor the airflow state within the combustion chamber in real time, providing data support for adjusting combustion parameters and ensuring operational stability. The first flange 34 facilitates the installation and connection of the outer ring adapter section 3 with other components, improving the structural stability and airtightness.

[0047] The support plate mounting slot 33 includes a slot 331 and a threaded hole 332 corresponding to the slot 331 , and the slot 331 passes through the inner column 7 ;

[0048] The support plate mounting groove 33 is provided with a sealing block 35 corresponding to the sealing block 35. The sealing block 35 includes a sealing block 351 that matches the notch 331 and a sealing cover 352 that matches the threaded hole 332.

[0049] The cover 352 is provided with a second fuel inlet 3521 , and the blocking block 351 is provided with a liquid collecting cavity 3511 and a plurality of injection holes 3512 corresponding to the liquid collecting cavity 3511 .

[0050] Specifically, the design of the packaging block 35 provides a fuel delivery path. The second fuel inlet 3521 is combined with the injection hole 3512 to achieve efficient fuel injection. The threaded hole 332 and the cover 352 are combined to facilitate quick assembly and disassembly, improving the convenience of system maintenance.

[0051] The surface of the direct injection oil section 4 is provided with multiple groups of first annular nozzles 41, second static pressure measuring points 42 and second dynamic pressure measuring points 43, and third flanges 44 are provided at both ends of the direct injection oil section 4; the first annular nozzle 41 includes a first fuel inlet 411 on the outer surface of the direct injection oil section 4 and a nozzle 412 on the inner surface of the direct injection oil section 4, and each of the second dynamic pressure measuring points 43 is processed with M10×1.0 threads.

[0052] It should be noted that the multiple groups of first annular nozzles 41 of the direct injection oil section 4, the first annular nozzle 41 includes an external first fuel inlet 411 and an internal nozzle 412, to achieve uniform distribution of fuel and ensure the sufficiency and stability of combustion. The second dynamic pressure measuring point 43 and the second static pressure measuring point 42 provide the ability to monitor the airflow state in real time, providing reliable data support for the fuel injection adjustment of the combustion chamber. The third flange 44 connection improves the convenience of connecting the direct injection oil section 4 with other sections, while ensuring airtightness. The design of the threaded interface facilitates the installation and disassembly of the pressure sensor and improves maintenance efficiency.

[0053] The expansion concave cavity section 5 includes an expansion section 51 and a concave cavity section 52, and fourth flanges 53 are connected to both ends of the expansion concave cavity section 5; the expansion section 51 is connected to the fourth flange 53 and the concave cavity section 52 respectively, and the radius of the expansion section 51 gradually increases from the end connected to the fourth flange 53 to the concave cavity section 52. The surface of the expansion section 51 is provided with multiple groups of second annular jets 511 and multiple third static pressure measuring points 512. The surface of the concave cavity section 52 is provided with multiple pre-explosion pipe interfaces 521, multiple high-frequency pressure sensor interfaces 522 and multiple fourth static pressure measuring points 523. The surface of the concave cavity section 52 is also provided with a plasma igniter installation panel 524.

[0054] Specifically, the gradually expanding cross-sectional design of the expansion section 51 ensures stable expansion of the high-pressure airflow during the expansion process, converting kinetic energy into thrust output, significantly improving combustion efficiency. The third static pressure measurement point 512 and the high-frequency pressure sensor interface 522 monitor the airflow status at key locations in real time, ensuring the stability and safety of the combustion chamber operation.

[0055] The expansion cavity section 5 is connected to the tail nozzle 6. A fifth flange 61 is provided at the connection between the tail nozzle 6 and the expansion cavity section 5. The tail nozzle 6 is also provided with a throat liner 9. The radius of the tail nozzle 6 gradually increases from the side close to the fifth flange 61.

[0056] The tail nozzle 6's gradually expanding cross-section further optimizes the airflow expansion process, improving thrust output efficiency. It should be noted that the throat liner 9 is made of graphite and is designed to withstand high temperatures, extending the nozzle's service life. The fifth flange 61 ensures airtightness and stability.

[0057] The plug-type nozzle 8 includes a lead screw 81 and a streamlined cone 82 , and a guide rail matching the lead screw 81 is provided in the inner column 7 .

[0058] Specifically, the plug nozzle 8, driven by a screw 81, moves its streamlined cone 82 axially within the guide rails of the inner column 7, flexibly adjusting the throat area to accommodate operating conditions from low to high Mach numbers. This design ensures dynamic optimization of airflow velocity and pressure distribution, improving the wide-range adaptability and efficiency of the combustion chamber.

[0059] The working principle of the wide-range rotating detonation engine structure of the present application is as follows:

[0060] First, the flange connections between the intake duct 1, outer ring adapter section 3, and direct injection section 4 are inspected to ensure airtightness and mechanical stability. During combustion initiation, the airflow is evenly guided through the intake cone 11's suction grooves 12. Multiple groups of first annular jets 41 within the direct injection section 4 uniformly inject fuel. Second static pressure measurement points 42 and second dynamic pressure measurement points 43 monitor the flow field in real time, providing a precise basis for fuel distribution and injection adjustment. During the ignition phase, the plasma igniter or pre-detonator interface 521 in the expansion cavity section 5 triggers ignition, optimizing airflow expansion through the gradually increasing cross-sectional shape of the expansion section 51.

[0061] During operation, at low Mach numbers (Ma2.0-Ma3.0), the inlet lip 14 moves rearward to increase intake flow, the plug nozzle 8 moves rearward, and the throat area increases. When approaching the flame stability equivalence ratio limit, the injection hole 3512 opens, achieving flame stability over a wider range. At medium Mach numbers (Ma4.0-Ma5.0), the inlet lip 14 moves forward to control intake flow, the variable throat 25 moves forward, reducing the throat area, and the plug nozzle moves forward, gradually reducing the throat area. At high Mach numbers (Ma6.0-Ma7.0), the inlet lip 14 moves rearward to control shock wave sealing and ensure intake flow, while the plug nozzle 8 moves forward to reduce the throat area. The plug nozzle 8 is driven by a screw 81 to achieve axial movement of the streamlined cone 82 within the guide rail of the inner column 7, flexibly adjusting the throat area to adapt to operating conditions from low to high Mach numbers.

[0062] Through the above-mentioned operation process, the design of the overall structure of the rotating detonation engine achieves wide adaptability from low Mach numbers to high Mach numbers.

[0063] The basic principles, main features, and advantages of the present invention are shown and described above. Those skilled in the art should understand that the present invention is not limited to the foregoing embodiments. The foregoing embodiments and descriptions are merely illustrative of the principles of the present invention. Various changes and modifications may be made to the present invention without departing from the spirit and scope of the present invention. Such changes and modifications are intended to fall within the scope of the present invention. The scope of protection claimed in the present invention is defined by the appended claims and their equivalents.

Claims

1. A wide-range rotating detonation engine structure, characterized by: The invention comprises an air intake duct (1), the air intake duct (1) is connected to an outer ring transition section (3), the outer ring transition section (3) is connected to a direct injection section (4), the direct injection section (4) is connected to an expansion cavity section (5), and the expansion cavity section (5) is connected to a tail nozzle (6); An inner column (7) is provided in the outer ring transition section (3) and the direct injection section (4), a packaging block (35) is provided on the surface of the direct injection section (4), and a plug-type nozzle (8) is movably connected to the inner column (7); A support plate mounting groove (33) is provided on the surface of the outer ring transition section (3), the support plate mounting groove (33) comprising a notch (331) and a threaded hole (332) corresponding to the notch (331), and the notch (331) passes through the inner column (7); A packaging block (35) is correspondingly provided on the support plate mounting groove (33), and the packaging block (35) includes a blocking block (351) matched with the notch (331) and a sealing cover (352) matched with the threaded hole (332); The sealing cover (352) is provided with a second fuel inlet (3521), and the blocking block (351) is provided with a liquid collecting cavity (3511) and a plurality of injection holes (3512) corresponding to the liquid collecting cavity (3511); The surface of the direct injection section (4) is provided with a plurality of first annular injections (41), second static pressure measuring points (42), and second dynamic pressure measuring points (43); the first annular injections (41) include a first fuel inlet (411) on the outer surface of the direct injection section (4) and a nozzle (412) on the inner surface of the direct injection section (4); The expansion cavity section (5) comprises an expansion section (51) and a cavity section (52); a surface of the expansion section (51) is provided with a plurality of second annular sprays (511) and a plurality of third static pressure measuring points (512).

2. The wide-range rotating detonation engine structure according to claim 1, characterized in that: The air inlet duct (1) comprises an air inlet cone (11), a surface of the tail of the air inlet cone (11) is provided with a suction groove (12) for air intake, the tail of the air inlet cone (11) is connected to a gas collecting cavity (13), a surface of the gas collecting cavity (13) is provided with a lip (14), a variable throat (15) is provided between the gas collecting cavity (13) and the lip (14), and the gas collecting cavity (13) is connected to an exhaust channel (16).

3. The wide-range rotating detonation engine structure according to claim 2, characterized in that: The outer ring transition section (3) is provided with a plurality of first static pressure measuring points (31), a plurality of first dynamic pressure measuring points (32) and a transition column (2), and the transition column (2) is respectively connected to the inner column (7) and the exhaust channel (16).

4. The wide-range rotating detonation engine structure according to claim 3, characterized in that: The expansion cavity section (5) is connected to a tail nozzle (6), and the tail nozzle (6) is further provided with a throat liner (9).

5. The wide-range rotating detonation engine structure according to claim 4, characterized in that: The plug-type nozzle (8) comprises a lead screw (81) and a streamlined cone (82), and a guide rail matching the lead screw (81) is provided in the inner column (7).

6. The method for operating a wide-range rotating detonation engine structure according to claim 5, characterized in that: The following steps are included: S1: After the combustion chamber is inhaled, the direct injection section (4), the second annular injection (511) of the expansion cavity section (5), and the injection hole (3512) begin to spray oil. After a certain period of time, the oil-gas mixture in the combustion chamber is ignited to form a rotating detonation wave. S2: When the Mach number is Ma2.0-Ma3.0, the lip (14) moves backward, the variable throat (15) moves backward, the plug nozzle (8) moves backward, and a local cavity is formed in the combustion chamber. The injection point is selected along the last four groups of the first ring nozzle (41) and the second ring nozzle (511) of the airflow. The combustion area is located in the local cavity. When it approaches the flame stabilization equivalence ratio limit, the injection hole (3512) of the package block (35) opens to spray oil, achieving flame stabilization in a wider range. S3: When the Mach number is Ma4.0-Ma5.0, the lip (14) moves forward, the variable throat (15) moves forward, the plug nozzle (8) moves forward, and the injection point is selected along the fourth to seventh groups of first ring nozzles (41) along the airflow, and the combustion area is located in the large-size combustion area; S4: When the Mach number is Ma6.0-Ma7.0, the lip (14) moves backward to control the shock wave seal, the variable throat (15) moves forward, the plug nozzle (8) moves forward, and the local cavity is completely closed. The injection point is located in the first four groups of first ring nozzles (41) along the airflow, and the combustion area is located in the small-sized combustion area.

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