Wide-range rotary detonation combustion chamber runner structure and operation method thereof

Abstract

The invention discloses a wide-range rotary detonation combustion chamber runner structure and an operation method thereof, and belongs to the technical field of rotary detonation ramjet engines. Comprising an equipment throat, an expansion section and an outer ring switching section, the end, away from the equipment throat, of the expansion section is connected with an outer ring switching device, the outer ring switching device is connected with an equal direct oil injection section, the equal direct oil injection section is connected with an expansion concave cavity section, and the expansion concave cavity section is connected with an exhaust nozzle shell; an inner column is arranged in the outer ring switching device and the equal-straight oil injection section and movably connected with a plug type spray pipe. According to the flow channel structure of the wide-range rotary detonation combustion chamber, a plurality of static and dynamic pressure measuring points are arranged on the surface of the outer ring switching section, so that the combustion state is monitored in real time; 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. The equal direct oil injection section ensures different combustion requirements through a multi-group annular injection design; the expansion concave cavity section is provided with a pre-explosion pipe connector and a plasma igniter installation panel, and the multi-work ignition requirement is met.

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 combustion chamber flow channel structure 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 structural 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 response to the above problems, the present invention proposes a wide-range rotating detonation combustion chamber flow channel structure and its operation method. The stable operation of rotating detonation combustion in a wide speed range and a wide height range is achieved by controlling the injection area, combustion area and throat area. Summary of the invention

[0003] In view of the above-mentioned problems, the present invention aims to provide a wide-range rotating detonation combustion chamber flow channel structure and its operation method. Through the design of the outer ring transition section, multiple static and dynamic pressure measurement points are set on the surface to realize real-time monitoring of the combustion state. The plug nozzle moves back and forth in the inner column guide through the lead 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 ensures different combustion requirements through multiple sets of ring injection design. The expansion cavity section consists of a gradually expanding expansion section and a cavity section that forms a reflow zone, and is equipped with a pre-explosion tube interface and a plasma igniter installation panel.

[0004] In order to achieve the above object, the technical solution adopted by the present invention is as follows: A wide-range rotating detonation combustion chamber flow channel structure comprises 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 an equal direct injection oil section, the equal direct injection oil section is connected to an expansion concave cavity section, and the expansion concave 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, and the inner column is movably connected to a plug nozzle.

[0005] Furthermore, the surface of the outer ring transition section is provided with a plurality of first static pressure measuring points, a plurality of first dynamic pressure measuring points and a transition column, and the surface of the outer ring transition section is also provided with a support plate mounting groove, and the transition column is respectively connected to the inner column and the first expansion section.

[0006] 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 blocking block matching the mounting groove, and the center cone blocking block is provided with four mounting threads and two disassembly top screws; the support plate mounting groove is correspondingly provided with a mounting groove packaging block, and the mounting groove packaging block includes a sealing block matching the mounting groove.

[0007] 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.

[0008] Furthermore, the expansion cavity section includes a second expansion section and a cavity section; the surface of the second expansion section is provided with a plurality of second annular sprays and a plurality of third static pressure measuring points.

[0009] Furthermore, the expansion concave cavity section is connected to a tail nozzle shell, a fifth flange is provided at a connection between the tail nozzle shell and the expansion concave cavity section, and the tail nozzle shell is also provided with a throat liner.

[0010] 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.

[0011] 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: S1: After the combustion chamber is inhaled, the first annular injection point in the equal 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-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 plug nozzle retreats, forming a local cavity in the combustion chamber. The injection point is 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. S3: When the Mach number is Ma4.0-Ma5.0, the plug nozzle moves forward, and the injection point is selected along the fourth to seventh groups of the first ring spray 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 plug nozzle moves forward, completely closing the local cavity, the injection point is located in the first ring nozzle of the first four groups, and the combustion area is located in the small-sized combustion zone.

[0012] The beneficial effects of the present invention are: 1. The flow channel structure of the wide-range rotating detonation combustion chamber of the present invention is designed with an outer ring transition section, and multiple static and dynamic pressure measuring points and dynamic pressure measuring points are set on the surface to realize 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 equal direct injection oil section ensures different combustion requirements through multiple sets of ring injection design, 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 reflow zone, and is equipped with a pre-detonation tube interface and a plasma igniter installation panel to meet multiple working ignition requirements.

[0013] 2. The outer ring transition section of the present invention is provided with multiple static and dynamic pressure measurement points on its surface, providing real-time monitoring capabilities to ensure the stability of the combustion state. The internal transition column is connected to the inner column and the expansion section to provide support for the movement of the plug nozzle. The combination of the support plate mounting groove and the center cone block further enhances the modular design of the structure, making the disassembly and maintenance of the components more convenient while ensuring the airtightness of the combustion chamber.

[0014] 3. The plug nozzle of the present invention is composed of a screw drive mechanism and a streamlined cone. Through the rotation of the screw, the cone moves forward and backward along the guide rail inside the inner column, thereby changing the throat area. This adjustment method can achieve dynamic adaptation within the range of low Mach number to high Mach number, ensuring that the airflow speed and pressure distribution always meet the working requirements of the combustion chamber.

[0015] 4. The direct injection section ensures that the fuel is injected according to different requirements through multiple sets of annular injection design. At the same time, the dynamic pressure and static pressure measurement points monitor the combustion state in real time to provide stable flow field support for combustion; the expansion cavity section consists of a gradually expanding expansion section and a cavity section that forms a reflow zone, equipped with a pre-explosion tube interface and a plasma igniter installation panel to meet multiple working ignition requirements. The synergistic effect of the two enables the combustion chamber to achieve efficient combustion and thrust output at different Mach numbers, with both wide-range adaptability and combustion stability. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] 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.

[0017] Figure 2 It is a front view of the flow channel structure of the wide-range rotating detonation combustion chamber in the present invention.

[0018] Figure 3 It is a side view of the flow channel structure of the wide-range rotating detonation combustion chamber in the present invention.

[0019] Figure 4 For the present invention Figure 3 Sectional view of AA.

[0020] Figure 5 For the present invention Figure 3 Cross-sectional view of BB.

[0021] Figure 6 It is a schematic diagram of the structure of the outer ring transition section in the present invention.

[0022] Figure 7 It is a structural schematic diagram of the support plate installation groove in the present invention.

[0023] Figure 8 It is a bottom view of the support plate installation groove in the present invention.

[0024] Fig. 9 It is a schematic diagram of the structure of the medium direct injection oil section of the present invention.

[0025] Fig.10 It is a cross-sectional view of the medium direct injection oil section of the present invention.

[0026] Fig.11 It is a schematic diagram of the structure of the expanded cavity section in the present invention.

[0027] Fig.12 It is a cross-sectional view of the expanded cavity section in the present invention.

[0028] Fig.13 It is a schematic diagram of the structure of the plug-type nozzle in the present invention.

[0029] Fig.14 It is a structural schematic diagram of the throat liner in the present invention.

[0030] Fig.15 It is a schematic structural diagram of the center cone block in the present invention.

[0031] Fig.16 It is a schematic diagram of the structure of the expanded cavity section at another angle in the present invention.

[0032] 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 encapsulation 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 ring 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

[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] See attached Figure 1-16A wide-range rotating detonation combustion chamber flow channel structure shown includes 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 an equal direct injection oil section 4, the equal 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; an inner column 7 is provided in the outer ring transition section 3 and the equal direct injection oil section 4, and the inner column 7 is movably connected to a plug nozzle 8.

[0037] The equipment throat includes a first flow channel 11 , a fixing block 12 and a first shell 13 . The first flow channel 11 is arranged at the center of the equipment throat. The first flow channel 11 is fixed to the first shell 13 through the fixing block 12 .

[0038] The expansion section includes a second flow channel 21 and a second shell 22 . The second flow channel 21 is disposed at the center of the expansion section. The second flow channel 21 is fixed to the second shell 22 through the fixing block 12 .

[0039] 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. Both ends of the outer ring transition section 3 are provided with a first flange 34. A support plate mounting groove 33 is also provided on the surface of the outer ring transition section 3. The transition column 36 is respectively connected to the inner column 7 and the first expansion section 2.

[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 mounting groove 33 includes a mounting groove 331 and a threaded hole 332 corresponding to the mounting groove 331. The inner column 7 is provided with a central cone block 71 matching the mounting groove 331. The central cone block 71 is provided with four mounting threads 711 and two disassembly top screws 712. The support plate mounting groove 33 is provided with a mounting groove encapsulation block 35 correspondingly. The mounting groove encapsulation block 35 includes a blocking block 351 matching the mounting groove 331 and a second flange 352 matching the threaded hole 332. The support plate mounting groove 33 and its matching central cone block 71 and the mounting groove encapsulation block 35 make the combustion chamber convenient for the installation and removal of components.

[0042] 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 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.

[0043] It should be noted that the multiple groups of first annular injections 41 of the direct injection section 4 include an external fuel inlet 411 and an internal nozzle 412, so that the fuel can be injected according to different requirements. 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 section 4 with other sections, while ensuring air tightness.

[0044] 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, and a plurality of second annular sprays 511 and a plurality of third static pressure measuring points 512 are provided on the surface of the second 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.

[0045] Specifically, the gradually enlarging cross-sectional design of the second expansion section 51 enables the high-pressure airflow to expand stably 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 state at key positions in real time to ensure the stability and safety of the combustion chamber operation.

[0046] The expansion cavity section 5 is connected to a tail nozzle shell 6, a fifth flange 61 is provided at the connection between the tail nozzle shell 6 and the expansion cavity section 5, and 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.

[0047] Specifically, the tail nozzle housing 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 airtightness and stability.

[0048] 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 .

[0049] 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.

[0050] The working principle of a wide-range rotating detonation combustion chamber flow channel structure of the present application is: First, the air tightness and mechanical stability of the flow channel are ensured by checking the flange connection between the equipment throat 1, the first expansion section 2, the outer ring transition section 3 and the direct injection section 4. When the combustion starts, the multiple groups of first ring sprays 41 in the direct injection section 4 spray fuel evenly, and 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.

[0051] During operation, when working at a low Mach number (Ma2.0-Ma3.0), the plug nozzle 8 moves backward, the throat area increases, the airflow velocity is reduced, and the combustion efficiency is optimized; when working at a medium Mach number (Ma4.0-Ma5.0), the plug nozzle 8 moves forward, and the throat area gradually decreases; when working at a high Mach number (Ma6.0-Ma7.0), the plug nozzle 8 moves forward and completely closes the local cavity. During the whole 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 the flow field parameters to ensure the stability of the combustion state. 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 working conditions from low Mach numbers to high Mach numbers.

[0052] 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.

[0053] 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 combustion chamber flow channel structure, characterized in that: 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 an end away from the device throat (1), 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 housing (6); An inner column (7) is provided inside the outer ring transition section (3) and the direct injection section (4), and the inner column (7) is movably connected to a plug-type nozzle (8).

2. A wide-range rotating detonation combustion chamber flow channel structure 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 installation groove (33). The transition column (36) is respectively connected to the inner column (7) and the first expansion section (2).

3. A wide-range rotating detonation combustion chamber flow channel structure 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); the inner column (7) is provided with a central cone block (71) matching the mounting groove (331); the central cone block (71) is provided with four mounting threads (711) and two disassembly screws (712); A mounting groove encapsulation block (35) is correspondingly provided on the support plate mounting groove (33), and the mounting groove encapsulation block (35) comprises a blocking block (351) matched with the mounting groove (331).

4. A wide-range rotating detonation combustion chamber flow channel structure according to claim 3, 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 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. A wide-range rotating detonation combustion chamber flow channel structure according to claim 4, characterized in that: The expansion cavity section (5) comprises a second expansion section (51) and a cavity section (52); A plurality of groups of second annular spray nozzles (511) and a plurality of third static pressure measuring points (512) are provided on the surface of the second expansion section (51).

6. A wide-range rotating detonation combustion chamber flow channel structure according to claim 5, characterized in that: The expansion cavity section (5) is connected to a tail nozzle shell (6), a fifth flange (61) is provided at the connection between the tail nozzle shell (6) and the expansion cavity section (5), and the tail nozzle shell (6) is also provided with a throat liner (9).

7. A wide-range rotating detonation combustion chamber flow channel structure according to claim 6, 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).

8. The method for operating the flow channel structure of a wide-range rotating detonation combustion chamber according to claim 7, characterized in that: The following steps are included: S1: After the combustion chamber is inhaled, the first annular injection point (41) in the equal direct injection section (4) and the second annular injection point (511) in the expansion cavity section (5) start to inject 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 plug nozzle (8) moves backward, a local cavity is formed in the combustion chamber, and the injection point is selected along the airflow of the last four groups of first annular nozzles (41) and second annular nozzles (511), 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 to completely close the local cavity, the injection point is located at the first four groups of first ring nozzles (41), and the combustion area is located in the small-sized combustion area.

Images