Modular continuous rotary detonation engine

Abstract

The application provides a modularized continuous rotating detonation engine, which comprises an annular cavity, an injection structure, a combustion chamber space adjusting structure and a tail injection module. The annular cavity is formed by a first combustion chamber outer ring inner wall and a first combustion chamber inner ring outer wall in the first combustion chamber, and comprises an oxidant annular cavity and a first combustion chamber annular cavity which are communicated through a narrow gap; the first combustion chamber outer ring is provided with an oxidant injection inlet which is communicated with the oxidant annular cavity, and the first combustion chamber inner ring front end is provided with a first fuel chamber injection structure which is communicated with the first combustion chamber annular cavity. The combustion chamber space adjusting structure is located between the annular cavity and the tail injection structure, and is used for adjusting any one or more of the length, width and shape of the first combustion chamber annular cavity. The injection structure comprises an oxidant injection structure and a first fuel chamber injection structure. The continuous rotating detonation engine designed by the application adopts a modularized design, and has strong adaptability and can meet the requirements of different carriers on different installation spaces and different thrusts.

Description

Technical Field

[0001] This invention relates to the field of engine design technology, specifically to a modular continuous rotary detonation engine. Background Technology

[0002] Knock is a combustion mode that couples shock waves and flames. Due to its fast chemical reaction rate, rapid flame propagation, and ability to generate extremely high pressure and temperature, it is widely used in engines to form knock engines, including pulse knock engines and continuous rotary knock engines.

[0003] Among them, the continuous rotating detonation engine is a type of continuous rotating detonation engine with a single annular slit, which has the following advantages: 1. Only one successful detonation is needed, and the detonation wave can propagate continuously along the circumference of the combustion chamber; 2. It has a fast combustion rate, high heat release intensity, and a compact combustion chamber structure, which can shorten the engine length; 3. It has pressurization characteristics, which can reduce the number of compressor stages in a turbine engine or reduce the total pressure loss in the intake duct of a ramjet engine, which is beneficial to simplifying the design of the propulsion system and improving the thrust-to-weight ratio of the engine; 4. It can operate in air-breathing mode or rocket mode, and its operating range can vary from subsonic to supersonic at high Mach numbers.

[0004] Research on continuous rotating detonation engines has gradually attracted widespread attention in the scientific and technological community. Studies have revealed the following drawbacks of existing continuous rotating detonation engines: 1. Simple structure, mostly single-annular slot, but without the use of new lightweight materials, the thrust-to-weight ratio of engines made from a single material is relatively low; 2. Low space utilization in a single combustion chamber, with the inner ring of the annular slot combustion chamber being mostly solid or purely hollow for weight reduction, which does not generate thrust and wastes space; 3. Compared to multi-annular slot combustion chambers, their combustion chambers only have one specification, and the combustion annular slot space is not adjustable, for example, it cannot be enlarged or reduced, or its number increased, or coupled ignition and detonation can be modified, thus not fundamentally changing the engine's power output; 4. Limited adjustable thrust range. The main ways to increase thrust with a single annular slot are to optimize combustion, improve the mixing effect of oxidizer and fuel, and increase flow rate, but since the cross-section of the combustion chamber is fixed, its adjustable range is limited.

[0005] Therefore, it is necessary to improve the existing continuous rotating detonation engine. Summary of the Invention

[0006] To address the problems of low thrust-to-weight ratio, low combustion chamber space utilization, large space waste, non-adjustable combustion annular gap space, and small thrust adjustable range of detonation engines, this invention designs a modular continuous rotating detonation engine. This continuous rotating detonation engine adopts a modular design, and the detonation engine is formed by assembling various parts, which can meet the different needs of different carriers.

[0007] The technical solution to achieve the purpose of the invention is as follows: a modular continuous rotating detonation engine, including an annular cavity and a combustion chamber space adjustment structure.

[0008] The annular cavity is formed by the inner peripheral wall of the outer ring of the first combustion chamber and the outer peripheral wall of the inner ring of the first combustion chamber inside it. It includes an oxidant annular cavity and a first combustion chamber annular cavity connected by a narrow slit. An oxidant injection port connected to the oxidant annular cavity is provided on the outer ring of the first combustion chamber. A first fuel chamber injection structure connected to the first combustion chamber annular cavity is provided at the front end of the inner ring of the first combustion chamber.

[0009] The combustion chamber space adjustment structure is located between the annular cavity and the tail injection structure, and is used to adjust any one or more of the length, width, and shape of the first combustion chamber annular cavity;

[0010] The injection structure includes a first oxidant injection structure and a first fuel chamber injection structure, and the first oxidant injection structure is provided with an oxidant injection port.

[0011] The combustion chamber space adjustment structure includes a second combustion chamber outer ring and a second combustion chamber inner ring. The inner peripheral wall of the second combustion chamber outer ring and the inner peripheral wall of the second combustion chamber inner ring form a second combustion chamber annular cavity that communicates with the first combustion chamber annular cavity.

[0012] The second combustion chamber outer ring is located between the first combustion chamber outer ring and the tail nozzle outer ring of the tail nozzle structure, and the second combustion chamber inner ring is located between the first combustion chamber inner ring and the tail nozzle tail cone of the tail nozzle structure.

[0013] In one embodiment of the second combustion chamber outer ring, the second combustion chamber outer ring is installed via a flange between the first combustion chamber outer ring and the tail spray outer ring of the tail spray structure.

[0014] Furthermore, the distance between the inner peripheral wall of the second combustion chamber outer ring and the center of the detonation engine is equal to the distance between the inner peripheral wall of the first combustion chamber outer ring and the center of the detonation engine, and the second combustion chamber outer ring and the first combustion chamber outer ring are provided with mutually cooperating positioning parts.

[0015] In one alternative embodiment of the second combustion chamber ring, the front end of the second combustion chamber ring abuts against the rear end of the first combustion chamber ring, and the rear end of the second combustion chamber ring abuts against the front end of the tail cone of the tail nozzle.

[0016] In another optional embodiment of the second combustion chamber ring, the front end of the second combustion chamber ring and the rear end of the first combustion chamber ring are fastened together by a fastening segment that matches each other, and the length of the fastening segment is equal to the length of the first combustion chamber ring.

[0017] Furthermore, the inner peripheral wall of the snap-fit ​​section on the inner ring of the second combustion chamber is provided with an internal thread, and the outer peripheral wall of the snap-fit ​​section on the inner ring of the first combustion chamber is provided with an external thread that mates with the internal thread.

[0018] In a third alternative embodiment of the inner ring of the second combustion chamber, the injection structure includes a second fuel chamber injection structure located within the annular cavity of the second combustion chamber. The second fuel injection structure is disposed on the outer ring of the second combustion chamber and includes a second fuel injection port and a plurality of second nozzles communicating with the annular cavity of the second combustion chamber.

[0019] In a fourth alternative embodiment of the second combustion chamber inner ring, the combustion chamber space adjustment structure further includes an annular cavity shape adjustment section.

[0020] Furthermore, the annular cavity shape adjustment part is formed by machining arc-shaped surfaces on any one or more of the inner peripheral wall of the first combustion chamber outer ring, the inner peripheral wall of the second combustion chamber outer ring, the outer peripheral wall of the second combustion chamber inner ring, and the outer peripheral wall of the first combustion chamber inner ring.

[0021] In an alternative embodiment of the continuously rotating detonation engine, the first and second combustion chamber rings are machined with weight-reduction structures.

[0022] Compared with existing technologies, the beneficial effects of this invention are as follows: The continuous rotary detonation engine designed in this invention modularizes components such as the outer combustion chamber ring, inner combustion chamber ring, tail spray structure, oxidizer injection port, and fuel chamber injection structure. During use, only appropriate specifications need to be selected and combined according to requirements, which can meet the needs of different carriers for different installation spaces and thrust. Furthermore, the modular design of the continuous rotary detonation engine has a wide range of applications, is convenient for replacement and maintenance, and through modular combination, a detonation engine with multiple injection systems can be generated. It has strong robustness; when one injection system becomes blocked, another injection system can be activated to maintain normal engine operation. Attached Figure Description

[0023] To more clearly illustrate the technical solutions of the embodiments of the present invention, the accompanying drawings used in the description of the embodiments will be briefly introduced below.

[0024] Figure 1 This is a perspective view of a continuous rotating detonation engine in a specific embodiment;

[0025] Figure 2 for Figure 1 A cross-sectional schematic diagram of a continuously rotating detonation engine;

[0026] Figure 3 This is a perspective view of another type of continuously rotating detonation engine in a specific embodiment;

[0027] Figure 4 for Figure 3 A cross-sectional schematic diagram of a continuous rotating detonation engine;

[0028] Figure 5This is a cross-sectional schematic diagram of the third type of continuous rotating detonation engine in a specific implementation embodiment;

[0029] Figure 6 This is a schematic diagram of the annular cavity shape adjustment part in a specific embodiment;

[0030] Among them, 1. First fuel chamber injection structure; 101. Hollow shell; 102. First fuel injection port; 103. First nozzle; 2. Oxidizer injection port; 21. Second oxidizer injection port; 3. First combustion chamber outer ring; 4. First combustion chamber inner ring; 41. Fastening section; 5. Second combustion chamber inner ring; 51. Arc-shaped surface; 6. Flange; 7. Second combustion chamber outer ring; 71. Positioning part; 8. Tail spray outer ring; 9. Tail spray pipe tail cone; 10. Narrow slit; 11. Second fuel injection port; 110. Second nozzle; 100. Oxidizer annular cavity; 200. First combustion chamber annular cavity; 300. Second combustion chamber annular cavity. Detailed Implementation

[0031] The present invention will be further described below with reference to specific embodiments, and the advantages and features of the present invention will become clearer as a result. However, these embodiments are merely exemplary and do not constitute any limitation on the scope of the present invention. Those skilled in the art should understand that modifications or substitutions can be made to the details and form of the technical solutions of the present invention without departing from the spirit and scope of the present invention, but all such modifications and substitutions fall within the protection scope of the present invention.

[0032] This specific embodiment discloses a modular continuous rotary detonation engine, which includes an annular cavity, a combustion chamber space adjustment structure, an injection structure, and a tail spray structure. The combustion chamber space adjustment structure is located between the annular cavity and the tail spray structure, and is used to adjust any one or more of the length, width, and shape of the first combustion chamber annular cavity 200. The injection structure includes a first oxidant injection structure and a first fuel chamber injection structure 1, and the first oxidant injection structure is provided with an oxidant injection port. Both the first oxidant injection structure and the first fuel chamber injection structure 1 are assembled to the annular cavity by disassembly.

[0033] See Figures 1 to 4 As shown, the annular cavity is formed by the inner peripheral wall of the outer ring 3 of the first combustion chamber and the outer peripheral wall of the inner ring 4 of the first combustion chamber, and includes an oxidant annular cavity 100 and a first combustion chamber annular cavity 200 connected by a narrow slit 10. The outer ring 3 of the first combustion chamber is provided with an oxidant injection port 2 that communicates with the oxidant annular cavity 100, and the front end of the inner ring 4 of the first combustion chamber is provided with a first fuel chamber injection structure 1 that communicates with the first combustion chamber annular cavity 200.

[0034] In one embodiment of the combustion chamber space adjustment structure, see Figures 1 to 4As shown, the combustion chamber space adjustment structure includes a second combustion chamber outer ring 7 and a second combustion chamber inner ring 5. The inner peripheral wall of the second combustion chamber outer ring 7 and the inner peripheral wall of the second combustion chamber inner ring 5 surround each other to form a second combustion chamber annular cavity 300 that communicates with the first combustion chamber annular cavity 200.

[0035] Among them, see Figures 1 to 4 As shown, the second combustion chamber outer ring 7 is disposed between the first combustion chamber outer ring 3 and the tail spray outer ring 8 of the tail spray structure, and the second combustion chamber inner ring 5 is disposed between the first combustion chamber inner ring 4 and the tail spray pipe tail cone 9 of the tail spray structure.

[0036] In one embodiment of the outer ring 7 of the second combustion chamber, see [link to embodiment]. Figures 1 to 4 As shown, the second combustion chamber outer ring 7 is installed between the first combustion chamber outer ring 3 and the tail spray outer ring 8 of the tail spray structure via flange 6.

[0037] Optionally, see Figure 2 and Figure 4 As shown, the distance between the inner peripheral wall of the second combustion chamber outer ring 7 and the center of the detonation engine is equal to the distance between the inner peripheral wall of the first combustion chamber outer ring 3 and the center of the detonation engine. The second combustion chamber outer ring 7 and the first combustion chamber outer ring 3 are provided with mutually cooperating positioning parts 71. The positioning parts 71 can make the second combustion chamber outer ring 7 and the first combustion chamber outer ring 3 aligned. On the one hand, it facilitates the fixed connection between the two. On the other hand, it can ensure that the distance between the inner peripheral walls of the two is the same as that between the center of the detonation engine, ensuring that the width of the first combustion chamber annular cavity 200 and the second combustion chamber annular cavity 300 is the same, and ensuring that the airflow smoothly transitions at the joint between the second combustion chamber outer ring 7 and the first combustion chamber outer ring 3.

[0038] In an optional embodiment of the second combustion chamber ring 5, the front end of the second combustion chamber ring 5 abuts against the rear end of the first combustion chamber ring 4, and the rear end of the second combustion chamber ring 5 abuts against the front end of the tail cone 9 of the tail nozzle, so that the end faces of both ends of the second combustion chamber ring 5 are aligned with the end faces of the first combustion chamber ring 4 and the tail cone 9 of the tail nozzle, respectively, and then connected by screws or pins. At this time, the positions of the second combustion chamber ring 5, the first combustion chamber ring 4, and the tail cone 9 of the tail nozzle are on the same plane. In this structure, after adding the second combustion chamber ring 5 and the second combustion chamber outer ring 7, the width of the combustion chamber annular cavity of the continuously rotating detonation engine does not change, that is, the width of the combustion chamber annular cavity is the distance between the outer peripheral wall of the first combustion chamber ring 4 and the inner peripheral wall of the first combustion chamber outer ring 3 (or the second combustion chamber outer ring 7).

[0039] In another alternative embodiment of the inner ring 5 of the second combustion chamber, in order to achieve a change in the width of the annular cavity of the combustion chamber of the continuous rotary detonation engine according to the requirements of the carrier, see [reference needed]. Figure 2 and Figure 4As shown, the front end of the second combustion chamber inner ring 5 and the rear end of the first combustion chamber inner ring 4 are fastened together by a matching fastening section 41, and the length of the fastening section 41 is equal to the length of the first combustion chamber inner ring 4. When the second combustion chamber inner ring 5 is fastened to the first combustion chamber inner ring 4, the distance between the outer peripheral wall of the second combustion chamber inner ring 5 and the inner peripheral wall of the first combustion chamber outer ring 3 (or the second combustion chamber outer ring 7) is the width of the combustion chamber annular cavity.

[0040] Optionally, see Figure 2 and Figure 4 As shown, the inner circumferential wall of the snap-fit ​​section 41 on the second combustion chamber ring 5 is provided with an internal thread, and the outer circumferential wall of the snap-fit ​​section 41 on the first combustion chamber ring 4 is provided with an external thread that matches the internal thread. The connection stability between the second combustion chamber ring 5 and the first combustion chamber ring 4 can be improved through the threaded connection.

[0041] In a third alternative embodiment of the second combustion chamber ring 5, see [link to third embodiment]. Figure 3 and Figure 4 As shown, the injection structure also includes a second fuel chamber injection structure located within the annular cavity 300 of the second combustion chamber. The second fuel chamber injection structure is disposed on the outer ring 7 of the second combustion chamber and includes a second fuel injection port 11 and a plurality of second nozzles 110 communicating with the annular cavity 300 of the second combustion chamber. The second fuel chamber injection structure can replenish fuel to the annular cavity 300 of the second combustion chamber, further improving the thrust of the continuous rotating detonation engine.

[0042] In another improvement to the continuously rotating detonation engine, in order to change the shape of the first combustion chamber annular cavity 200 and / or the second combustion chamber annular cavity 300, the combustion chamber space adjustment structure includes an annular cavity shape adjustment section. See also Figure 6 As shown, the annular cavity shape adjustment part is formed by machining arc-shaped surfaces 51 on any one or more of the inner peripheral wall of the first combustion chamber outer ring 3, the inner peripheral wall of the second combustion chamber outer ring 7, the outer peripheral wall of the second combustion chamber inner ring 5, and the outer peripheral wall of the first combustion chamber inner ring 4. The arc-shaped surfaces 51 can adjust the outer surface shape of the first combustion chamber annular cavity 200 and / or the second combustion chamber annular cavity 300 to form detonation combustion annular channels of different shapes, making it easier to form detonation waves.

[0043] In an alternative embodiment of the continuously rotating detonation engine, the first combustion chamber ring 4 and the second combustion chamber ring 5 are machined with weight-reducing structures.

[0044] In another improvement to the aforementioned continuous rotary detonation engine, when a second combustion chamber annular cavity 300 is added, in order to ensure a sufficient supply of oxidizer, [the following is implied:] Figures 1 to 4 The positions of the first fuel chamber injection structure 1 and the first oxidizer injection structure are interchanged, see [reference]. Figure 5As shown, the first fuel chamber injection structure 1 is located at the narrow slit 10, and a nozzle is used as the first nozzle 103 to inject fuel from the narrow slit 10. At the same time, the first oxidizer injection structure is detachably installed at the front section of the inner ring 4 of the first combustion chamber, and multiple oxidizer injection ports 2 are connected to the annular cavity 200 of the first combustion chamber to provide oxidizer.

[0045] The continuous rotary detonation engine designed in this invention modularizes components such as the outer combustion chamber ring, inner combustion chamber ring, tail spray structure, oxidizer injection port, and fuel chamber injection structure. By selecting appropriate specifications and combining them according to requirements, it can meet the needs of different carriers for varying installation spaces and thrust. Furthermore, the modular design of the continuous rotary detonation engine offers wide adaptability, convenient replacement and maintenance, and, through modular combination, can create a detonation engine with multiple injection systems. It exhibits strong robustness; if one injection system becomes blocked, another injection system can be activated to maintain normal engine operation.

[0046] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the protection scope of the present invention.

[0047] Furthermore, it should be understood that although this specification describes embodiments, not every embodiment contains only one independent technical solution. This narrative style is merely for clarity. Those skilled in the art should consider the specification as a whole, and the technical solutions in each embodiment can also be appropriately combined to form other embodiments that can be understood by those skilled in the art.

Claims

1. A modular continuous rotary detonation engine, characterized in that, include: The annular cavity is formed by the inner peripheral wall of the outer ring (3) of the first combustion chamber and the outer peripheral wall of the inner ring (4) of the first combustion chamber inside it, including an oxidant annular cavity (100) and a first combustion chamber annular cavity (200) connected by a narrow slit (10); the outer ring (3) of the first combustion chamber is provided with an oxidant injection port (2) connected to the oxidant annular cavity (100), and the front end of the inner ring (4) of the first combustion chamber is provided with a first fuel chamber injection structure (1) connected to the first combustion chamber annular cavity (200); A combustion chamber space adjustment structure is located between the annular cavity and the tail spray structure, and is used to adjust any one or more of the length, width, and shape of the first combustion chamber annular cavity (200); The injection structure includes a first oxidant injection structure and a first fuel chamber injection structure (1), and the first oxidant injection structure is provided with the oxidant injection port (2). The combustion chamber space adjustment structure includes a second combustion chamber outer ring (7) and a second combustion chamber inner ring (5), and the inner peripheral wall of the second combustion chamber outer ring (7) and the inner peripheral wall of the second combustion chamber inner ring (5) surround each other to form a second combustion chamber annular cavity (300) that communicates with the first combustion chamber annular cavity (200). The second combustion chamber outer ring (7) is located between the first combustion chamber outer ring (3) and the tail nozzle outer ring (8) of the tail nozzle structure, and the second combustion chamber inner ring (5) is located between the first combustion chamber inner ring (4) and the tail nozzle tail cone (9) of the tail nozzle structure.

2. The continuous rotating detonation engine according to claim 1, characterized in that: The second combustion chamber outer ring (7) is installed between the first combustion chamber outer ring (3) and the tail spray outer ring (8) of the tail spray structure via a flange (6).

3. The continuous rotating detonation engine according to claim 2, characterized in that: The distance between the inner peripheral wall of the second combustion chamber outer ring (7) and the center of the detonation engine is equal to the distance between the inner peripheral wall of the first combustion chamber outer ring (3) and the center of the detonation engine, and the second combustion chamber outer ring (7) and the first combustion chamber outer ring (3) are provided with mutually cooperating positioning parts (71).

4. The continuous rotating detonation engine according to claim 1, characterized in that: The front end of the second combustion chamber ring (5) abuts against the rear end of the first combustion chamber ring (4), and the rear end of the second combustion chamber ring (5) abuts against the front end of the tail nozzle tail cone (9).

5. The continuous rotating detonation engine according to claim 1, characterized in that: The front end of the second combustion chamber ring (5) is fastened to the rear end of the first combustion chamber ring (4) by a fastening segment (41) that cooperates with each other, and the length of the fastening segment (41) is equal to the length of the first combustion chamber ring (4).

6. The continuous rotating detonation engine according to claim 5, characterized in that: The inner circumferential wall of the snap-fit ​​section (41) on the second combustion chamber ring (5) is provided with an internal thread, and the outer circumferential wall of the snap-fit ​​section (41) on the first combustion chamber ring (4) is provided with an external thread that matches the internal thread.

7. The continuous rotating detonation engine according to any one of claims 4 to 6, characterized in that: The injection structure includes a second fuel chamber injection structure located within the annular cavity (300) of the second combustion chamber; The second fuel chamber injection structure is disposed on the outer ring (7) of the second combustion chamber, including a second fuel injection port (11) and a plurality of second nozzles (110) communicating with the annular cavity (300) of the second combustion chamber.

8. The continuous rotating detonation engine according to claim 1, characterized in that: The combustion chamber space adjustment structure also includes an annular cavity shape adjustment section.

9. The continuous rotating detonation engine according to claim 8, characterized in that: The annular cavity shape adjustment part is formed by machining an arc-shaped surface (51) on any one or more of the inner peripheral wall of the first combustion chamber outer ring (3), the inner peripheral wall of the second combustion chamber outer ring (7), the outer peripheral wall of the second combustion chamber inner ring (5), and the outer peripheral wall of the first combustion chamber inner ring (4).

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