A wide-range rotating detonation combustion chamber flow channel structure and operation method thereof

Abstract

The present invention discloses a wide-range rotating detonation combustion chamber flow path structure and its operating method, belonging to the technical field of rotating detonation ramjet engines. The structure comprises a device throat, an expansion section, and an outer ring adapter section. The expansion section is connected to an outer ring adapter at one end away from the device throat. The outer ring adapter is connected to a constant direct injection section, which is connected to an expansion cavity section, which is connected to a tail nozzle housing. An inner column is provided within the outer ring adapter and the constant direct injection section, and the inner column is movably connected to a plug nozzle. The wide-range rotating detonation combustion chamber flow path structure of the present invention achieves real-time monitoring of the combustion state by setting multiple static and dynamic pressure measurement points on the surface of the outer ring adapter section. The plug nozzle flexibly adjusts the throat area to adapt to the operating range from low Mach numbers to high Mach numbers by moving the screw back and forth within the inner column guide rail. The constant direct injection section adopts a multi-group ring injection design to meet different combustion requirements. The expansion cavity section is equipped with a pre-detonation pipe interface and a plasma igniter mounting panel to meet multiple working ignition requirements.

Description

Technical Field

[0001] The present invention relates to the technical field of rotating detonation ramjet engines, and in particular to a flow channel structure of a wide-range rotating detonation combustion chamber 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-burn ramjets, ramjets employing rotating detonation combustion have shorter axial length, lighter weight, 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 flow path structure and operating method for a wide-range rotating detonation combustion chamber. By controlling the injection area, combustion area, and throat area, stable rotating detonation combustion is achieved over a wide speed and altitude range. Summary of the Invention

[0003] To address the above-mentioned problems, the present invention aims to provide a wide-range rotating detonation combustion chamber flow channel structure and its operating method. 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 status. The plug nozzle moves back and forth within the inner column guide through the screw, flexibly adjusting the throat area to adapt to the working range from low Mach number to high Mach number. The direct injection oil section adopts a multi-group annular injection design to meet different combustion requirements. The expansion cavity section consists of a gradually expanding expansion section and a cavity section that forms a recirculation zone. It is equipped with a pre-detonation tube interface and a plasma igniter mounting panel.

[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 combustion chamber flow channel structure includes a device throat and a first expansion section, wherein the first expansion section is connected to an outer ring transition section at an end away from the device throat, the outer ring transition section is connected to a direct oil injection section, the direct oil 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 direct oil injection section, and the inner column is movably connected to a plug nozzle.

[0006] Furthermore, the surface of the outer ring transition section is provided with multiple first static pressure measuring points, multiple first dynamic pressure measuring points and transition columns. The surface of the outer ring transition section is also provided with support plate installation grooves, and the transition columns are respectively connected to the inner column and the first expansion section.

[0007] Furthermore, the support plate mounting groove includes a mounting groove and a threaded hole corresponding to the mounting groove, the inner column is provided with a center cone block matching the mounting groove, and the center cone block is provided with four mounting threads and two disassembly screws; the support plate mounting groove is provided with a mounting groove encapsulation block corresponding to the mounting groove, and the mounting groove encapsulation block includes a sealing block matching the mounting groove.

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

[0010] Furthermore, the expansion cavity section is connected to a tail nozzle shell, a fifth flange is provided at the connection between the tail nozzle shell and the expansion cavity section, and the tail nozzle shell 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 flow channel structure of a wide-range rotating detonation combustion chamber as described above is characterized by comprising the following steps:

[0013] S1: After the combustion chamber is charged with air, the first annular injection point in the direct injection section and the second annular injection point in the expansion cavity section start to inject oil. After a certain period of injection, the oil-air mixture in the combustion chamber is ignited to form a rotating detonation wave.

[0014] S2: When the Mach number is Ma2.0-Ma3.0, the nozzle moves backward, forming a local cavity in the combustion chamber. The injection points are selected along the airflow of the last four groups of first and second ring jets, and the combustion area is located in the local cavity.

[0015] S3: When the Mach number is Mach 4.0-Mach 5.0, the nozzle moves forward, and the injection point is selected along the fourth to seventh groups of first ring spray along the airflow, and the combustion area is located in the large-size combustion zone;

[0016] S4: When the Mach number is Ma6.0-Ma7.0, the plug nozzle moves forward, completely closing the local cavity, the injection point is located in the first four groups of first ring nozzles, and the combustion area is located in the small-size combustion zone.

[0017] The beneficial effects of the present invention are:

[0018] 1. The wide-range rotating detonation combustion chamber flow channel structure of the present invention is designed with multiple static and dynamic pressure measuring points and dynamic pressure measuring points on the surface through the design of the outer ring transition section, so as to realize real-time monitoring of the combustion status. 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. The direct injection oil section ensures different combustion requirements through the design of multiple sets of ring injections, and the dynamic and static pressure measuring points further monitor the flow field stability of the combustion chamber; the expansion cavity section is composed of a gradually expanding expansion section and a cavity section that forms a recirculation zone, and is equipped with a pre-explosion tube interface and a plasma igniter installation panel to meet multiple working ignition requirements.

[0019] 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. An internal adapter column connects to the inner column and expansion section, providing support for the movement of the plug nozzle. The combination of support plate mounting slots and a center cone block further enhances the modular design, facilitating component disassembly and maintenance while ensuring the airtightness of the combustion chamber.

[0020] 3. The present invention's plug-type nozzle consists of a screw drive mechanism and a streamlined cone. Rotation of the screw causes the cone to move back and forth along a guide rail within the inner column, thereby varying the throat area. This adjustment method allows for dynamic adaptation across a range of Mach numbers, from low to high, ensuring that the airflow velocity and pressure distribution consistently meet the combustion chamber's operating requirements.

[0021] 4. The direct injection section utilizes multiple annular injections to ensure fuel injection is tailored to specific needs. Dynamic and static pressure measurement points monitor combustion conditions in real time, providing stable flow support. The expansion cavity section, comprised of a gradually expanding expansion section and a recirculation zone, is equipped with a pre-detonation tube interface and a plasma igniter mounting panel to accommodate multiple ignition requirements. These two elements work together to ensure efficient combustion and thrust output across a wide range of Mach numbers, ensuring both wide adaptability and combustion stability. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] Figure 1 It is a structural schematic diagram of the flow channel structure of the wide-range rotating detonation combustion chamber in the present invention.

[0023] Figure 2 This is a front view of the flow channel structure of the wide-range rotating detonation combustion chamber in the present invention.

[0024] Figure 3 It is a side view of the flow channel structure of the wide-range rotating detonation combustion chamber in the present invention.

[0025] Figure 4 For the present invention Figure 3 Cross-sectional view of AA in the figure.

[0026] Figure 5 For the present invention Figure 3 Cross-sectional view of the BB.

[0027] Figure 6 It is a structural schematic diagram of the outer ring transition section in the present invention.

[0028] Figure 7 It is a structural schematic diagram of the support plate installation groove in the present invention.

[0029] Figure 8 This is a bottom view of the support plate installation groove of the present invention.

[0030] Figure 9 It is a structural schematic diagram of the medium direct injection oil section of the present invention.

[0031] Figure 10 It is a cross-sectional view of the medium direct injection oil section of the present invention.

[0032] Figure 11 It is a structural schematic diagram of the expanded concave cavity section in the present invention.

[0033] Figure 12 It is a cross-sectional view of the expanded concave cavity section in the present invention.

[0034] Figure 13 It is a structural schematic diagram of the plug-type nozzle in the present invention.

[0035] Figure 14 It is a structural schematic diagram of the throat liner in the present invention.

[0036] Figure 15 It is a structural schematic diagram of the center cone block in the present invention.

[0037] Figure 16 This is a schematic structural diagram of the expanded cavity section from another angle in the present invention.

[0038] Among them: 1. Equipment throat; 2. First expansion section; 3. Outer ring transition section; 4. Direct injection section; 5. Expansion cavity section; 6. Tail nozzle shell; 7. Inner column; 8. Plug nozzle; 9. Throat liner; 11. First flow channel; 12. Fixing block; 13. First shell; 21. Second flow channel; 22. Second shell; 31. First static pressure measuring point; 32. First dynamic pressure measuring point; 33. Support plate mounting groove; 34. First flange; 35. Mounting groove packaging block; 36. Adapter column; 41. First ring nozzle; 42. Second static pressure measuring point; 43. Second dynamic pressure measuring point; 44. Third Flange; 51, second expansion section; 52, concave cavity section; 53, fourth flange; 61, fifth flange; 71, center cone block; 81, lead screw; 82, streamlined cone; 331, mounting groove; 332, threaded hole; 351, blocking block; 352, second flange; 411, 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; 711, mounting thread; 712, removal screw. 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 1-16The shown structure is a wide-range rotating detonation combustion chamber flow channel structure, comprising a device throat 1 and a first expansion section 2, wherein the first expansion section 2 is connected to an outer ring transition section 3 at the end away from the device throat 1, the outer ring transition section 3 is connected to a direct injection oil section 4, the direct injection oil section 4 is connected to an expansion cavity section 5, and the expansion cavity section 5 is connected to a tail nozzle outer shell 6; an inner column 7 is provided in the outer ring transition section 3 and the direct injection oil section 4, and the inner column 7 is movably connected to a plug nozzle 8.

[0043] The equipment throat includes a first flow channel 11 , a fixing block 12 and a first shell 13 . The first flow channel 11 is provided at the center of the equipment throat, and the first flow channel 11 is fixed to the first shell 13 through the fixing block 12 .

[0044] The expansion section includes a second flow channel 21 and a second shell 22 . The second flow channel 21 is located at the center of the expansion section. The second flow channel 21 is fixed to the second shell 22 via the fixing block 12 .

[0045] The outer ring transition section 3 is provided with multiple first static pressure measuring points 31, multiple first dynamic pressure measuring points 32 and transition columns 36. 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 transition columns 36 are respectively connected to the inner column 7 and the first expansion section 2.

[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 mounting slot 331 and a threaded hole 332 corresponding to the mounting slot 331. The inner column 7 is provided with a central conical block 71 that matches the mounting slot 331. The central conical block 71 has four mounting threads 711 and two removal screws 712. A mounting slot encapsulation block 35 is correspondingly provided on the support plate mounting slot 33. The mounting slot encapsulation block 35 includes a blocking block 351 that matches the mounting slot 331 and a second flange 352 that matches the threaded hole 332. The support plate mounting slot 33, its associated central conical block 71, and the mounting slot encapsulation block 35 facilitate the installation and removal of components within the combustion chamber.

[0048] 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 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.

[0049] It should be noted that the multiple sets of first annular nozzles 41 in the direct injection section 4 include external fuel inlets 411 and internal nozzles 412, allowing fuel to be injected according to different requirements. Second dynamic pressure measurement points 43 and second static pressure measurement points 42 provide real-time monitoring of airflow conditions, providing reliable data support for fuel injection adjustment in the combustion chamber. Third flange 44 facilitates connection between the direct injection section 4 and other sections while ensuring airtightness.

[0050] The expansion concave cavity section 5 includes a second 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 second expansion section 51 is connected to the fourth flange 53 and the concave cavity section 52 respectively, and the radius of the second expansion section 51 gradually increases from the end connected to the fourth flange 53 to the concave cavity section 52. The surface of the second expansion section 51 is provided with multiple groups of second annular jets 511 and multiple third static pressure measuring points 512, and 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.

[0051] Specifically, the gradually expanding cross-sectional design of the second 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 high-frequency pressure sensor interface 522 monitor the airflow state at key locations in real time, ensuring the stability and safety of the combustion chamber operation.

[0052] The expansion cavity section 5 is connected to the tail nozzle shell 6, and a fifth flange 61 is provided at the connection between the tail nozzle shell 6 and the expansion cavity section 5. The tail nozzle shell 6 is also provided with a throat liner 9; the radius of the tail nozzle shell 6 gradually increases from the side close to the fifth flange 61.

[0053] Specifically, the tail nozzle housing 6, through its gradually expanding cross-section design, further optimizes the airflow expansion process and improves thrust output efficiency. It should be noted that the throat liner 9 is made of graphite material and is designed to be high-temperature resistant, extending the nozzle's service life. The fifth flange 61 ensures airtightness and stability.

[0054] 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 .

[0055] 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.

[0056] The working principle of a wide-range rotating detonation combustion chamber flow channel structure of the present application is as follows:

[0057] First, the flange connections between the equipment throat 1, first expansion section 2, outer ring adapter section 3, and direct injection section 4 are inspected to ensure the airtightness and mechanical stability of the flow path. During combustion initiation, 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.

[0058] During operation, at low Mach numbers (Ma2.0-Ma3.0), the nozzle plug 8 moves rearward, increasing the throat area, reducing airflow velocity, and optimizing combustion efficiency. At medium Mach numbers (Ma4.0-Ma5.0), the nozzle plug 8 moves forward, gradually reducing the throat area. At high Mach numbers (Ma6.0-Ma7.0), the nozzle plug 8 moves forward, completely sealing the local cavity. Throughout this process, the first static pressure measuring point 31 and the first dynamic pressure measuring point 32 of the outer ring transition section 3 continuously monitor flow field parameters to ensure combustion stability. The nozzle plug 8, driven by a lead screw 81, enables axial movement of the streamlined cone 82 within the guide rail of the inner column 7, flexibly adjusting the throat area to accommodate operating conditions from low to high Mach numbers.

[0059] Through the above-mentioned operation process, the design of the rotating detonation combustion chamber flow channel achieves wide adaptability from low Mach number to high Mach number.

[0060] 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 combustion chamber flow channel structure, characterized by: The invention comprises a device throat (1) and a first expansion section (2), wherein the first expansion section (2) is connected to an outer ring transition section (3) at one end away from the device throat (1), the outer ring transition section (3) is connected to a direct injection oil section (4), the direct injection oil section (4) is connected to an expansion cavity section (5), and the expansion cavity section (5) is connected to a tail nozzle shell (6); the tail nozzle shell (6) is further provided with a throat liner (9); An inner column (7) is provided in the outer ring transition section (3) and the equal direct injection section (4), and the inner column (7) is movably connected to a plug nozzle (8); the throat liner (9) is sleeved on the outside of the plug nozzle (8); the plug nozzle (8) includes a lead screw (81) and a streamlined cone (82), and a guide rail matched with the lead screw (81) is provided in the inner column (7); 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 and adapting to working conditions from low Mach number to high Mach number; The surface of the direct injection oil section (4) is provided with a plurality of first ring sprays (41), second static pressure measuring points (42) and second dynamic pressure measuring points (43); The expansion cavity section (5) comprises a second expansion section (51) and a cavity section (52); a surface of the second 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 flow channel structure of a wide-range rotating detonation combustion chamber according to claim 1, characterized in that: The surface of 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 (36). The surface of the outer ring transition section (3) is also provided with a support plate mounting groove (33). The transition column (36) is respectively connected to the inner column (7) and the first expansion section (2).

3. The flow channel structure of a wide-range rotating detonation combustion chamber according to claim 2, characterized in that: The support plate mounting groove (33) comprises a mounting groove (331) and a threaded hole (332) corresponding to the mounting groove (331); a mounting groove encapsulation block (35) is correspondingly provided on the support plate mounting groove (33); the mounting groove encapsulation block (35) comprises a blocking block (351) matched with the mounting groove (331); The inner column (7) is provided with a central cone block (71) that matches the mounting groove (331), and the central cone block (71) is provided with four mounting threads (711) and two disassembly screws (712).

4. The flow channel structure of a wide-range rotating detonation combustion chamber according to claim 3, characterized in that: The first annular nozzle (41) comprises a 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).

5. The flow channel structure of a wide-range rotating detonation combustion chamber according to claim 4, characterized in that: The expansion cavity section (5) is connected to a tail nozzle housing (6), and a fifth flange (61) is provided at the connection between the tail nozzle housing (6) and the expansion cavity section (5).

6. The method for operating a flow channel structure of a wide-range rotating detonation combustion chamber according to claim 5, characterized in that: The following steps are included: S1: After the combustion chamber is inlet, the first annular injection point (41) in the direct injection section (4) and the second annular injection point (511) in the expansion cavity section (5) start 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. S2: When the Mach number is Ma2.0-Ma3.0, the plug nozzle (8) moves backward, forming a local cavity in the combustion chamber. The injection points are selected along the last four groups of the first ring nozzle (41) and the second ring nozzle (511) of the airflow, and the combustion area is located in the local cavity. S3: When the Mach number is Ma4.0-Ma5.0, 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 plug nozzle (8) moves forward, completely closing the local cavity, the injection point is located in the first four groups of first ring nozzles (41), and the combustion area is located in the small-sized combustion area.

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