Wide-range rotary detonation engine complete machine structure and operation method thereof

Abstract

The invention discloses a whole structure of a wide-range rotary detonation engine and an operation method of the whole structure, and belongs to the technical field of rotary detonation ramjet engines. Comprising an air inlet channel, the air inlet channel is connected with an outer ring switching section, the outer ring switching section is connected with an equal-direction oil injection section, the equal-direction oil injection section is connected with an expansion concave cavity section, and the expansion concave cavity section is connected with an exhaust nozzle; an inner column is arranged in the outer ring switching section and the equal direct oil injection section, a packaging block is arranged on the surface of the equal direct oil injection section, and the inner column is movably connected with a plug type spray pipe. According to the whole structure of the wide-range rotary detonation engine, the condition that equipment adapts to wide-speed-range flight conditions from low Mach number to high Mach number is ensured through the air inlet channel and the plug type spray pipe structure. The lip and the adjustable throat work cooperatively, and dynamic adjustment of the airflow flow is achieved. The plug type spray pipe moves back and forth in the inner column guide rail through the lead screw, and the throat area is flexibly adjusted so as to adapt to the working range from the low Mach number to the high Mach number.

Description

Technical Field

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

[0002] Rotating detonation combustion has the characteristics of short combustion distance and high combustion efficiency. Compared with traditional slow-burning ramjet engines, ramjet engines using rotating detonation combustion have the characteristics of short axial length, light structure mass and high combustion efficiency. Traditional rotating detonation ramjet combustion chambers have the disadvantages of narrow working speed range and large influence of working height changes on detonation wave characteristics, so they are not suitable for engines working in a wide range. In view of the above problems, the present invention proposes a wide-range rotating detonation engine structure and its operation method. The intake parameters are adjusted through an adjustable intake duct, and the injection area, combustion area, and throat area are controlled to achieve stable operation of rotating detonation combustion in a wide speed range and a wide height range. Summary of the invention

[0003] In view of 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 duct 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 measurement points are set on the surface to achieve real-time monitoring of the combustion state. The plug-type nozzle moves the screw back and forth in the inner column guide rail to flexibly adjust the throat area to adapt to the working range from low Mach numbers to high Mach numbers.

[0004] In order to achieve the above object, the technical solution adopted by the present invention is as follows: A wide-range rotating detonation engine overall structure and an operation 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 an equal direct injection oil section, the equal 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 equal direct injection oil section, a packaging block is provided on the surface of the equal direct injection oil section, and the inner column is movably connected to a plug-type nozzle.

[0005] Furthermore, the air intake duct includes an air intake cone, a suction groove for air intake is provided on the rear surface of the air intake cone, the rear of the air intake cone is connected to an air collecting cavity, a lip is provided on the surface of the air collecting cavity, a variable throat is provided between the air collecting cavity and the lip, and the air collecting cavity is connected to an exhaust channel.

[0006] 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.

[0007] 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.

[0008] 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.

[0009] Furthermore, the expansion cavity section includes an expansion section and a cavity section; and the surface of the expansion section is provided with a plurality of second annular sprays and a plurality of third static pressure measuring points.

[0010] Furthermore, the expansion cavity section is connected to a tail nozzle, and the tail nozzle is also provided with a throat liner.

[0011] 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.

[0012] The method for operating the overall structure of a wide-range rotating detonation engine as described above is characterized by comprising the following steps: 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 point of the packaging block start 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 moves backward, the variable throat moves backward, the plug nozzle retreats, and a local cavity is formed in the combustion chamber. The injection point is selected along the airflow of the last four groups of first ring injection and second ring injection. The combustion area is located in the local cavity. When it is close to the flame stabilization equivalence ratio limit, the injection hole of the encapsulation block is opened to achieve a wider range of flame stabilization. S3: When the Mach number is Ma4.0-Ma5.0, the lip moves forward, the variable throat moves forward, the plug nozzle moves forward, 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 area; 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 nozzles along the airflow, and the combustion area is located in the small-size combustion zone.

[0013] The beneficial effects of the present invention are: 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 inlet duct 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 state. 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 equal direct injection oil section uses a multi-group ring injection design to ensure different combustion requirements, and the dynamic and static pressure measuring points further monitor the flow field stability of the combustion chamber.

[0014] 2. The outer ring adapter section of the present invention is provided with multiple static pressure measuring points and dynamic pressure measuring points on its surface, providing real-time monitoring capability to ensure the stability of the combustion state. The internal adapter column is connected to the inner column and the expansion section to provide support for the activity of the plug nozzle. The design of the packaging block provides a fuel delivery path, and the second fuel inlet is combined with the injection hole to achieve efficient fuel injection according to different combustion requirements.

[0015] 3. The present invention ensures that the equipment can adapt to flight conditions in a wide range of low to high Mach numbers through optimized inlet duct design and dynamic adjustment structure. The intake cone optimizes the airflow introduction efficiency through streamlined design, and the suction groove effectively absorbs 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.

[0016] 4. The plug-type nozzle can dynamically adjust the throat area according to different working conditions through the precise coordination of the lead screw and the streamlined cone, adapt to the changing requirements of airflow velocity and pressure, and improve the working efficiency of the combustion chamber. In addition, the multiple static and dynamic pressure measurement points arranged in the outer ring transition section, the direct injection section and the expansion cavity section of the equipment realize the real-time monitoring and feedback of the combustion chamber status, ensuring the safety and reliability of the equipment operation. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1 It is a structural schematic diagram of the whole structure of the wide-range rotating detonation engine in the present invention.

[0018] Figure 2 It is a front view of the overall structure of the wide-range rotating detonation engine in the present invention.

[0019] Figure 3 It is a cross-sectional view of the overall structure of the wide-range rotating detonation engine in the present invention.

[0020] Figure 4 It is a schematic diagram of the structure of the air intake duct in the present invention.

[0021] Figure 5 It is a schematic diagram of the structure of the outer ring transition section in the present invention.

[0022] Figure 6 It is a schematic diagram of the structure of the encapsulation block in the present invention.

[0023] Figure 7 It is a cross-sectional view of the packaging block in the present invention.

[0024] Figure 8 It is a cross-sectional view from another angle of the packaging block in the present invention.

[0025] Fig. 9 It is a schematic diagram of the structure of the medium direct injection oil section of the present invention.

[0026] Fig.10 It is a cross-sectional view of the medium direct injection oil section of the present invention.

[0027] Fig.11 It is a schematic structural diagram of the expansion cavity section in the present invention.

[0028] Fig.12 It is a schematic diagram of the structure of the expanded cavity section at another angle in the present invention.

[0029] Fig.13 It is a cross-sectional view of the expanded cavity section in the present invention.

[0030] Fig.14 It is a schematic diagram of the structure of the plug-type nozzle in the present invention.

[0031] Fig.15 It is a structural schematic diagram of the throat liner in the present invention.

[0032] Among them: 1. Intake duct; 2. Adapter column; 3. Outer ring adapter section; 4. Direct injection section; 5. Expanded cavity section; 6. Tail nozzle; 7. Inner column; 8. Plug nozzle; 9. Throat liner; 11. Intake 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. Packaging 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, lead 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

[0033] 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.

[0034] 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. indicate directions or positional relationships based on the directions or positional relationships shown in the accompanying drawings. They are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific direction, be constructed and operated in a specific direction. Therefore, they should not be understood as limitations on the present invention.

[0035] In the description of this application, it should also be noted that, unless otherwise clearly specified and limited, the terms "set", "install", "connect", and "connect" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a direct connection, or an indirect connection through an intermediate medium, or it can be the internal communication of two elements. For ordinary technicians in this field, the specific meanings of the above terms in this application can be understood according to specific circumstances.

[0036] Refer to the attached Figure 1-15The structure of a wide-range rotating detonation engine shown in the figure includes an intake duct 1, wherein the intake duct 1 is connected to an outer ring transition section 3, wherein the outer ring transition section 3 is connected to an equal direct injection oil section 4, wherein the equal direct injection oil section 4 is connected to an expansion cavity section 5; an inner column 7 is arranged inside the outer ring transition section 3 and the equal direct injection oil section 4, a packaging block 35 is arranged on the surface of the equal direct injection oil section 4, and the inner column 7 is movably connected to a plug-type nozzle 8.

[0037] 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, a gas collecting chamber 13 is connected to the rear of the air intake cone 11, a movable lip 14 is provided on the surface of the gas collecting chamber 13, a variable throat 15 is provided between the gas collecting chamber 13 and the lip 14, and the gas collecting chamber 13 is connected to an exhaust channel 16.

[0038] It should be noted that the tail of the intake cone 11 is provided with threads, and the lip 14 can be driven by a motor to move forward or backward. The intake cone 11 optimizes the airflow introduction efficiency through a streamlined design, and the suction groove 12 effectively absorbs the low-energy airflow in the boundary layer. The air collecting cavity 13 is combined with the exhaust channel 16 to ensure smooth airflow discharge. The lip 14 works in coordination with the variable throat 15 to achieve dynamic adjustment of the airflow flow rate to meet the requirements of different Mach number working conditions. At low Mach numbers, the lip 14 moves backward to increase the intake flow rate; 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 ensure the intake flow rate.

[0039] 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 an adapter column 2. Both ends of the outer ring transition section 3 are provided with first flanges 34. The surface of the outer ring transition section 3 is also provided with a support plate mounting groove 33. The adapter column 2 is respectively connected to the inner column 7 and the air intake duct 1.

[0040] Specifically, the first static pressure measuring point 31 and the first dynamic pressure measuring point 32 are used to monitor the airflow state inside the combustion chamber in real time, and provide data support to adjust the combustion parameters and ensure the operation stability. The first flange 34 facilitates the installation and connection of the outer ring transition section 3 with other components, and improves the stability and air tightness of the structure.

[0041] The support plate installation 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 ; The support plate installation groove 33 is provided with a sealing block 35 correspondingly, and the sealing block 35 includes a sealing block 351 matched with the notch 331 and a sealing cover 352 matched with the threaded hole 332; 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 .

[0042] Specifically, the design of the packaging block 35 provides a fuel delivery path, and the second fuel inlet 3521 is combined with the injection hole 3512 to achieve efficient fuel injection according to the requirements. The threaded hole 332 and the cover 352 are easy to quickly assemble and disassemble, which improves the convenience of system maintenance.

[0043] The surface of the direct injection oil section 4 is provided with multiple groups of first annular sprays 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 spray 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.

[0044] It should be noted that the multiple groups of first annular sprays 41 of the direct injection oil section 4, the first annular spray 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 air tightness. The design of the threaded interface facilitates the installation and disassembly of the pressure sensor and improves maintenance efficiency.

[0045] 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, and a plurality of groups of second annular sprays 511 and a plurality of third static pressure measuring points 512 are provided on the surface of the expansion section 51, a plurality of pre-explosion pipe interfaces 521, a plurality of high-frequency pressure sensor interfaces 522 and a plurality of fourth static pressure measuring points 523 are provided on the surface of the concave cavity section 52, and a plasma igniter installation panel 524 is also provided on the surface of the concave cavity section 52.

[0046] Specifically, the gradually expanding cross-sectional design of the expansion section 51 enables the high-pressure airflow to expand stably during the expansion process, converting kinetic energy into thrust output, significantly improving the combustion efficiency. The third static pressure measurement point 512 and the high-frequency pressure sensor interface 522 monitor the airflow state at key positions in real time to ensure the stability and safety of the combustion chamber operation.

[0047] The expansion cavity section 5 is connected to a tail nozzle 6 , and 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 .

[0048] The tail nozzle 6 further optimizes the airflow expansion process through the gradually enlarged cross-section design and improves the thrust output efficiency. It should be noted that the throat liner 9 is made of graphite material, and the throat liner 9 is designed to be resistant to high temperatures, which prolongs the service life of the nozzle, and the fifth flange 61 ensures air tightness and stability.

[0049] 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 .

[0050] Specifically, the plug nozzle 8 is driven by the lead screw 81 to realize the axial movement of the streamlined cone 82 in the guide rail of the inner column 7, flexibly adjusting the throat area to adapt to working conditions from low Mach number to high Mach number. This design ensures the dynamic optimization of air flow velocity and pressure distribution, and improves the wide-range adaptability and high efficiency of the combustion chamber.

[0051] The working principle of the overall structure of a wide-range rotating detonation engine of the present application is as follows: First, the air tightness and mechanical stability are ensured by checking the flange connection between the intake duct 1, the outer ring adapter section 3 and the direct injection section 4. When the combustion starts, the airflow is evenly guided by the suction groove 12 of the intake cone 11, and the multiple groups of first ring sprays 41 in the direct injection section 4 evenly spray fuel. The second static pressure measuring point 42 and the second dynamic pressure measuring point 43 monitor the flow field state in real time, providing accurate fuel distribution and injection adjustment basis; in the ignition stage, the plasma igniter or pre-explosion pipe interface 521 in the expansion cavity section 5 triggers ignition, and the airflow expansion is optimized through the gradually increasing cross-sectional shape of the expansion section 51.

[0052] During operation, when in low Mach number (Ma2.0-Ma3.0) working condition, the inlet lip 14 moves backward to increase the intake flow, the plug nozzle 8 moves backward, the throat area increases, and when approaching the flame stabilization equivalence ratio limit, the injection hole 3512 opens to achieve a larger range of flame stabilization; when working at medium Mach number (Ma4.0-Ma5.0), the inlet lip 14 moves forward to control the intake flow, the variable throat 25 moves forward, the throat area decreases, the plug nozzle moves forward, and the throat area gradually decreases; in high Mach number (Ma6.0-Ma7.0) working condition, the inlet lip 14 moves backward to control the shock wave seal, ensure the intake flow, the plug nozzle 8 moves forward, and the throat area is reduced. The plug nozzle 8 is driven by the screw 81 to realize the axial movement of the streamlined cone 82 in the guide rail of the inner column 7, and the throat area is flexibly adjusted to adapt to the working conditions from low Mach number to high Mach number.

[0053] 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.

[0054] The above shows and describes the basic principles, main features and advantages of the present invention. It should be understood by those skilled in the art that the present invention is not limited to the above embodiments, and the above embodiments and descriptions are only for explaining the principles of the present invention. Without departing from the spirit and scope of the present invention, the present invention may have various changes and improvements, which fall within the scope of the present invention to be protected. The scope of protection of the present invention is defined by the attached claims and their equivalents.

Claims

1. A wide-range rotating detonation engine complete structure, characterized in that: 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 an equal direct injection section (4), the equal 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 inside 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).

2. The wide-range rotating detonation engine structure according to claim 1, characterized in that: The air intake duct (1) comprises an air intake cone (11), a suction groove (12) for air intake is provided on the rear surface of the air intake cone (11), a gas collecting chamber (13) is connected to the rear of the air intake cone (11), a lip (14) is provided on the surface of the gas collecting chamber (13), a variable throat (15) is provided between the gas collecting chamber (13) and the lip (14), and the gas collecting chamber (13) is connected to an exhaust passage (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); a support plate mounting groove (33) is also provided on the surface of the outer ring transition section (3); and the transition column (2) is respectively connected to the inner column (7) and the exhaust passage (16).

4. The wide-range rotating detonation engine structure according to claim 3, characterized in that: The support plate installation groove (33) comprises 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 installation groove (33), and the packaging block (35) comprises 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).

5. The wide-range rotating detonation engine structure according to claim 4, characterized in that: The surface of the direct injection oil section (4) is provided with a plurality of groups of first annular sprays (41), second static pressure measuring points (42) and second dynamic pressure measuring points (43); The first annular injection (41) comprises 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).

6. The wide-range rotating detonation engine structure according to claim 5, characterized in that: The expansion cavity section (5) comprises an expansion section (51) and a cavity section (52); The surface of the expansion section (51) is provided with a plurality of second annular spray nozzles (511) and a plurality of third static pressure measuring points (512).

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

8. The wide-range rotating detonation engine structure according to claim 7, 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).

9. The method for operating the wide-range rotating detonation engine structure as claimed in claim 8, characterized in that: The following steps are included: S1: After the combustion chamber is inhaled, the equal direct injection section (4), the second annular injection (511) of the expansion cavity section (5) and the injection hole (3512) start to spray oil, and 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 airflow of the last four groups of first ring nozzles (41) and second ring nozzles (511). The combustion area is located in the local cavity. When the flame stabilization equivalence ratio limit is approached, the injection hole (3512) of the packaging block (35) is opened to spray oil, so as to achieve flame stabilization in a larger 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) of 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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