A continuous rotating detonation engine

Abstract

The present invention discloses a continuous rotating detonation engine, comprising an engine body, the engine body is provided with an oxidant flow channel, comprising a first cavity, a second cavity surrounding the first cavity, and a plurality of third cavities, the first cavity is connected to an intake joint, the first cavity peripheral wall is provided with a circumferentially distributed first equalizing flow hole, the first equalizing flow hole is connected to the second cavity, a plurality of third cavities are evenly distributed along the circumference of the second cavity, the third cavity is provided with a second equalizing flow hole and a third equalizing flow hole, the second equalizing flow hole is connected to the second cavity, the engine body is also provided with a mixing chamber, and the third equalizing flow hole is connected to the mixing chamber. The present invention improves the structure of the oxidant flow channel, can improve the uniformity of oxidant distribution, and the uniformity of mixing with fuel, to ensure the combustion stability and thrust performance of the continuous rotating detonation engine.

Description

Technical Field

[0001] The invention relates to the technical field of engines, and in particular to a continuous rotating detonation engine. Background Art

[0002] The continuous rotating detonation engine is based on continuous rotating detonation technology. It releases and accumulates energy through physical and chemical reactions and continues the process through detonation wave transmission. It has potential important application prospects in the field of jet propulsion.

[0003] Among them, the uniformity of the oxidizer and fuel mixing is the key to the formation of continuous rotating detonation waves. Uneven oxidizer distribution may lead to poor uniformity of oxidizer and fuel mixing, affecting the combustion stability of the rotating detonation engine and causing loss of engine thrust performance. In conventional engines, the oxidizer is generally mixed with the fuel by collision, which cannot meet the mixing uniformity requirements of the continuous rotating detonation engine.

[0004] Therefore, it is urgent to design an oxidizer flow channel that meets the requirements of a continuous rotating detonation engine, improve the uniformity of oxidizer distribution, and ensure the combustion stability of the engine. Summary of the invention

[0005] The purpose of the present invention is to provide a continuous rotating detonation engine, which improves the uniformity of oxidant distribution and the uniformity of mixing with fuel, and ensures the combustion stability and thrust performance of the continuous rotating detonation engine.

[0006] In order to solve the above technical problems, the present invention provides a continuous rotating detonation engine, comprising an engine body, wherein the engine body is provided with an oxidant flow channel, wherein the oxidant flow channel comprises a first cavity located in the middle, a second cavity arranged around the first cavity, and a plurality of third cavities, wherein the first cavity is communicated with an intake joint, wherein:

[0007] The peripheral wall of the first cavity is provided with first flow balancing holes distributed along the circumferential direction, and the first flow balancing holes are connected to the second cavity. The plurality of third cavities are evenly distributed along the circumference of the second cavity, and the third cavity is provided with second flow balancing holes and third flow balancing holes, and the second flow balancing holes are connected to the second cavity. The engine body is also provided with a mixing chamber, and the third flow balancing holes are connected to the mixing chamber.

[0008] The present invention is provided with an oxidant flow channel as described above, and the oxidant first enters the first cavity from the air intake joint for pressure stabilization, and then enters the second cavity through the first circumferential equalizing hole for pressure stabilization again; then, the oxidant inside the second cavity enters the third cavity through the second equalizing hole, and then is injected into the mixing chamber through the third equalizing hole at the other end of the third cavity, so as to achieve the mixing of fuel and oxidant. Since the third cavity is evenly distributed along the circumference of the second cavity, the oxidant entering the third cavity from the second cavity can also be evenly distributed along the circumference, so that the oxidant entering the mixing chamber can be evenly mixed with the fuel along the circumference, ensuring the formation of a continuous rotating detonation wave, and then ensuring the combustion stability and thrust performance of the continuous rotating detonation engine of the present invention.

[0009] Optionally, the axial upper portion of the third cavity is located inside the second cavity, and the portion is located inside the mixing chamber. The second flow balancing hole and the third flow balancing hole are both arranged on the peripheral wall of the third cavity and are respectively distributed along the circumferential direction. The second flow balancing hole and the third flow balancing hole are staggered along the axial direction of the third cavity.

[0010] Optionally, a diameter of the first flow balancing hole is larger than a diameter of the second flow balancing hole and a diameter of the third flow balancing hole.

[0011] Optionally, the oxidant flow channel further includes an installation cavity connected to the first cavity, and the installation cavity is used for installing the air inlet connector.

[0012] Optionally, the engine body is further provided with a fuel flow channel, and the peripheral wall of the mixing chamber is provided with fourth flow equalizing holes distributed along the circumferential direction, and the fuel flow channel is connected to the mixing chamber through the fourth flow equalizing holes.

[0013] Optionally, the engine body is provided with a combustion chamber, and the combustion chamber is connected with the mixing chamber through a nozzle hole.

[0014] The fuel flow channel is arranged inside the outer wall of the combustion chamber, the end of the fuel flow channel close to the tail of the combustion chamber is the inlet end, and is connected to the fuel joint, and the end of the fuel flow channel close to the head of the combustion chamber is the outlet end, and is connected to the mixing chamber.

[0015] Optionally, the fuel flow channels are distributed in a spiral shape around the axis of the outer wall of the combustion chamber.

[0016] Optionally, the outer wall of the combustion chamber is provided with an annular hole at one end near the tail, and a mounting hole connected to the annular hole, the mounting hole extends radially outward, the fuel joint is installed inside the mounting hole, and the fuel flow channel is connected to the annular flow channel at one end near the tail of the combustion chamber.

[0017] Optionally, the nozzle comprises a constant diameter section located in the middle, and a flared section connected to both ends of the constant diameter section, and the diameter of the flared section gradually increases in a direction away from the constant diameter section.

[0018] Optionally, the engine body is formed by an additive manufacturing process. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] Figure 1 A schematic structural diagram of a specific embodiment of the continuous rotating detonation engine provided by the present invention;

[0020] Figure 2 for Figure 1 The structural diagram of the second angle of the continuous rotating detonation engine;

[0021] Figure 3 for Figure 1 The structural diagram of the third angle of the continuous rotating detonation engine;

[0022] Figure 4 for Figure 1 An axial cross-sectional view of an engine block in a continuous rotating detonation engine;

[0023] Figure 5 for Figure 1 A radial cross-sectional view of an engine block in a continuous rotating detonation engine;

[0024] Figure 6 for Figure 1 Another axial cross-sectional view of an engine block in a continuous rotating detonation engine;

[0025] Figure 7 for Figure 1 Another radial cross-sectional view of an engine body in a continuous rotating detonation engine;

[0026] Figure 8 for Figure 1 Radial cross-section of a continuous rotating detonation engine;

[0027] in, Figure 1-Figure 8 The reference numerals in the figures are described as follows:

[0028] 1-engine body; 11-first cavity; 11a-first equalizing hole; 12-second cavity; 13-third cavity; 13a-second equalizing hole; 13b-third equalizing hole; 14-mixing chamber; 14a-fourth equalizing hole; 15-installation cavity; 16-combustion chamber; 16a-annular flow channel; 17-fuel flow channel; 18-nozzle hole;

[0029] 2- Fuel connector. DETAILED DESCRIPTION

[0030] In order to enable those skilled in the art to better understand the technical solution of the present invention, the present invention is further described in detail below in conjunction with the accompanying drawings and specific embodiments.

[0031] The words "first", "second", etc. mentioned in this article are only for the convenience of describing two or more structures or components with the same or similar structures and / or functions, and do not imply any special limitation on the order and / or importance.

[0032] Herein, the term "plurality" refers to a number of two or more.

[0033] Please refer to Figure 1-Figure 5 , Figure 1 A schematic structural diagram of a specific embodiment of the continuous rotating detonation engine provided by the present invention; Figure 2 for Figure 1 The structural diagram of the second angle of the continuous rotating detonation engine; Figure 3 for Figure 1 The structural diagram of the third angle of the continuous rotating detonation engine; Figure 4 for Figure 1 An axial cross-sectional view of an engine block in a continuous rotating detonation engine; Figure 5 for Figure 1 Radial cross-section of the engine block in a continuously rotating detonation engine.

[0034] The present invention provides a continuous rotating detonation engine, comprising an engine body 1, wherein the engine body 1 is provided with an oxidant flow channel, wherein the oxidant flow channel comprises a first cavity 11 located in the middle, a second cavity 12 arranged around the first cavity 11, and three third cavities 13, wherein the first cavity 11 is communicated with an intake joint, wherein:

[0035] The peripheral wall of the first cavity 11 is provided with first flow balancing holes 11a distributed along the circumferential direction, and the first cavity 11 is connected with the second cavity 12 through the first flow balancing holes 11a. The three third cavities 13 are evenly distributed along the circumference of the second cavity 12, and the third cavity 13 is provided with second flow balancing holes 13a and third flow balancing holes 13b, and the third cavity 13 is connected with the second cavity 12 through the second flow balancing holes 13a. The engine body 1 is also provided with a mixing chamber 14, and the third cavity 13 is connected with the mixing chamber 14 through the third flow balancing holes 13b.

[0036] The present invention is provided with an oxidant flow channel as described above, and the oxidant first enters the first cavity 11 from the air intake joint for pressure stabilization, and then enters the second cavity 12 through the circumferential first equalizing hole 11a for pressure stabilization again; then, the oxidant in the second cavity 12 enters the third cavity 13 through the second equalizing hole 13a, and then is injected into the mixing chamber 14 through the third equalizing hole 13b at the other end of the third cavity 13, so as to achieve the mixing of fuel and oxidant. Since the third cavity 13 is evenly distributed along the circumference of the second cavity 12, the oxidant entering the third cavity 13 from the second cavity 12 can also be evenly distributed along the circumference, so that the oxidant entering the mixing chamber 14 can also be evenly mixed with the fuel along the circumference, ensuring the formation of a continuous rotating detonation wave, and then ensuring the combustion stability and thrust performance of the continuous rotating detonation engine of the present invention.

[0037] Among them, the number of the third cavities 13 is three in this embodiment. In practical applications, the number of the third cavities 13 is not limited as long as the uniformity of the circumferential distribution can be ensured; therefore, in practical applications, the number of the third cavities 13 can be more than two. In addition, the size of each cavity and each flow-averaging hole in the oxidant flow channel can be adaptively designed according to the overall size of the engine and relevant performance parameters.

[0038] Among them, the positions at which the second flow equalizing hole 13a and the third flow equalizing hole 13b are arranged in the third cavity 13 are not unique. For example, the second flow equalizing hole 13a can be arranged on one end wall of the third cavity 13, and the third flow equalizing hole 13b is arranged on the other end wall of the third cavity 13. In this way, the second cavity 12, the third cavity 13, and the mixing chamber 14 are completely staggered along the axial direction; in this embodiment, the axial part of the third cavity 13 is located inside the second cavity 12, and part is located inside the mixing chamber 14. The second flow equalizing hole 13a and the third flow equalizing hole 13b are both arranged on the peripheral wall of the third cavity 13 and are distributed circumferentially respectively. The second flow equalizing hole 13a and the third flow equalizing hole 13b are staggered along the axial direction of the third cavity 13.

[0039] It can be understood that the configuration of the present invention can effectively reduce the axial size of the engine body 1, reduce the space occupied by the engine of the present invention, reduce the weight of the engine, meet the weight reduction requirements of the aerospace system, and is a more preferred technical solution.

[0040] Furthermore, in the present embodiment, the diameter of the first flow balancing hole 11a is greater than the diameters of the second flow balancing hole 13a and the third flow balancing hole 13b. Since the diameter of the first flow balancing hole 11a is larger, the flow resistance of the oxidant when flowing through the first flow balancing hole 11a can be reduced. Since the diameters of the second flow balancing hole 13a and the third flow balancing hole 13b are smaller, the flow rate of the oxidant can be increased through the second flow balancing hole 13a and the third flow balancing hole 13b, and the related flow rate can be controlled.

[0041] like Figure 4 As shown, the oxidant flow channel also includes a mounting cavity 15 connected to the first cavity 11, and the mounting cavity 15 is used to install the air intake connector.

[0042] There is no limitation on the connection method between the air inlet connector and the mounting cavity 15 , such as threaded connection, interference fit, welding fixation, etc.

[0043] Please refer to Figure 6-Figure 8 , Figure 6 for Figure 1 Another axial cross-sectional view of an engine block in a continuous rotating detonation engine; Figure 7 for Figure 1 Another radial cross-sectional view of an engine body in a continuous rotating detonation engine; Figure 8 for Figure 1 Radial cross-section of a continuous rotating detonation engine.

[0044] In the present invention, the engine body 1 is further provided with a fuel flow channel 17, and the peripheral wall of the mixing chamber 14 is provided with fourth flow equalizing holes 14a distributed along the circumferential direction, and the fuel flow channel 17 is connected to the mixing chamber 14 through the fourth flow equalizing holes 14a.

[0045] As configured above, the fuel entering the mixing chamber 14 can be evenly distributed along the circumferential direction, thereby allowing the oxidizer and the fuel to be evenly mixed along the circumferential direction, ensuring the formation of a continuous rotating detonation wave, thereby ensuring the combustion stability and thrust performance of the continuous rotating detonation engine of the present invention.

[0046] Furthermore, in the present invention, the engine body 1 is also provided with a combustion chamber 16, and the combustion chamber 16 is connected to the mixing chamber 14 through the nozzle hole 18. The fuel flow channel 17 is arranged inside the outer wall of the combustion chamber 16, and the end of the fuel flow channel 17 close to the tail of the combustion chamber 16 is the inlet end and is connected to the fuel joint 2, and the end of the fuel flow channel 17 close to the head of the combustion chamber 16 is the outlet end and is connected to the mixing chamber 14.

[0047] As configured above, the fuel enters the fuel flow channel 17 through the fuel connector 2, and flows along the fuel flow channel 17 from the tail of the combustion chamber 16 to the head of the combustion chamber 16. During the flow, the fuel drives the aerodynamic heat absorbed by the wall to avoid excessively high wall temperature, thereby playing a cooling role. At the same time, the absorbed heat preheats the fuel. Finally, the fuel enters the mixing chamber 14 to mix and collide with the oxidant.

[0048] It can be seen that the continuous rotating detonation engine of the present invention adopts regenerative cooling to cool the wall of the combustion chamber 16. On the one hand, there is no need to separately use a cooling source and related structures, so that the overall structure of the engine is simpler and lighter, meeting the weight reduction requirements of the aerospace system and improving the thrust-to-weight ratio of the engine; on the other hand, the engine heat is effectively used to preheat the fuel, thereby ensuring the combustion performance of the engine and providing a greater thrust effect.

[0049] Among them, the fuel flow channel 17 of this embodiment is distributed in a spiral shape around the axis of the outer wall of the combustion chamber 16, achieving uniform cooling of the outer wall of the combustion chamber 16, improving the cooling effect, and ensuring the continuous operation of the continuous rotating detonation engine of the present invention under longer working conditions.

[0050] Furthermore, an annular flow channel 16a and a mounting hole connected to the annular flow channel 16a are provided at one end of the outer wall of the combustion chamber 16 near the tail, the mounting hole extends radially outward, the fuel connector 2 is installed in the mounting hole, and one end of the fuel flow channel 17 near the tail is connected to the annular flow channel 16a.

[0051] Of course, in practical applications, the fuel flow channel 17 can also be implemented in a variety of ways. For example, the fuel flow channel 17 includes multiple straight flow channels extending axially, and the multiple straight flow channels are evenly distributed along the circumference of the outer wall of the combustion chamber 16. The end of the straight flow channel close to the head of the combustion chamber 16 is connected to the fourth equalizing flow hole 14a one by one to ensure that the fuel entering the mixing chamber 14 can also be evenly distributed along the circumference. The end of the straight flow channel close to the tail of the combustion chamber 16 is connected to the fuel joint 2 through the annular flow channel 16a.

[0052] Please continue to refer to Figure 6 In this embodiment, the nozzle hole 18 specifically includes an equal diameter section located in the middle, and an expanded section connected to both ends of the equal diameter section. The diameter of the expanded section gradually increases in the direction away from the equal diameter section. In this way, the mixed gas can obtain a certain flow rate when flowing through the nozzle hole 18, and then be injected into the combustion chamber 16. The combustion chamber 16 is ignited by the spark plug / high-energy ignition device / electric ignition structure to ensure the combustion performance of the engine.

[0053] Of course, in practical applications, there is no limitation on the specific structure of the nozzle hole 18. For example, a flared section may be provided only at one end close to the combustion chamber 16, or only at one end close to the mixing chamber 14. Alternatively, it is also feasible to install the nozzle structure in a one-to-one correspondence in the nozzle holes 18.

[0054] The engine body 1 of the present invention can be formed by machining, or can also be formed by an additive manufacturing process.

[0055] Additive Manufacturing (AM) is a technology that uses a gradual accumulation of materials to manufacture solid parts. Compared with traditional material removal-cutting processing technology, it can omit many machining and welding processes, and can ensure the dimensional accuracy of related positions, reduce the processing cost of the engine body 1, and improve processing efficiency. It provides strong assistance for the engineering application of the engine and is a more preferred technical solution.

[0056] The above is a detailed introduction to a continuous rotating detonation engine provided by the present invention. The principles and implementation methods of the present invention are described in detail using specific examples. The description of the above embodiments is only used to help understand the method and core idea of ​​the present invention. It should be pointed out that for ordinary technicians in this technical field, the present invention can also be improved and modified without departing from the principles of the present invention, and these improvements and modifications also fall within the scope of protection of the claims of the present invention.

Claims

1. A continuous rotating detonation engine, characterized in that: The invention comprises an engine body (1), wherein the engine body (1) is provided with an oxidant flow channel, wherein the oxidant flow channel comprises a first cavity (11) located in the middle, a second cavity (12) arranged around the first cavity (11), and a plurality of third cavities (13), wherein the first cavity (11) is communicated with an air intake joint, wherein: The peripheral wall of the first cavity (11) is provided with first flow balancing holes (11a) distributed along the circumferential direction, and the first flow balancing holes (11a) are connected to the second cavity (12); a plurality of the third cavities (13) are evenly distributed along the circumference of the second cavity (12); the third cavity (13) is provided with second flow balancing holes (13a) and third flow balancing holes (13b), and the second flow balancing holes (13a) are connected to the second cavity (12); the engine body (1) is also provided with a mixing chamber (14), and the third flow balancing holes (13b) are connected to the mixing chamber (14).

2. The continuous rotating detonation engine according to claim 1, characterized in that: The third cavity (13) is partially located in the second cavity (12) in the axial direction, and partially located in the mixing chamber (14); the second flow balancing hole (13a) and the third flow balancing hole (13b) are both arranged on the peripheral wall of the third cavity (13) and are respectively distributed in the circumferential direction; the second flow balancing hole (13a) and the third flow balancing hole (13b) are staggered in the axial direction of the third cavity (13).

3. The continuous rotating detonation engine according to claim 1, characterized in that: The diameter of the first flow balancing hole (11a) is greater than the diameters of the second flow balancing hole (13a) and the third flow balancing hole (13b).

4. The continuous rotating detonation engine according to claim 1, characterized in that: The oxidant flow channel further comprises an installation cavity (15) connected to the first cavity (11), and the installation cavity (15) is used for installing the air inlet joint.

5. The continuous rotating detonation engine according to claim 1, characterized in that: The engine body (1) is also provided with a fuel flow channel (17), and the peripheral wall of the mixing chamber (14) is provided with fourth flow-balancing holes (14a) distributed along the circumferential direction, and the fuel flow channel (17) is connected to the mixing chamber (14) through the fourth flow-balancing holes (14a).

6. The continuous rotating detonation engine according to claim 5, characterized in that: The engine body (1) is provided with a combustion chamber (16), and the combustion chamber (16) is connected to the mixing chamber (14) through a nozzle hole (18). The fuel flow channel (17) is arranged inside the outer wall of the combustion chamber (16); one end of the fuel flow channel (17) close to the tail of the combustion chamber (16) is an inlet end and is connected to the fuel joint (2); and one end of the fuel flow channel (17) close to the head of the combustion chamber (16) is an outlet end and is connected to the mixing chamber (14).

7. The continuous rotating detonation engine according to claim 6, characterized in that: The fuel flow channel (17) is distributed in a spiral shape around the axis of the outer wall of the combustion chamber (16).

8. The continuous rotating detonation engine according to claim 7, characterized in that: The outer wall of the combustion chamber (16) is provided with an annular flow channel (16a) at one end close to the tail, and a mounting hole connected to the annular flow channel (16a), the mounting hole extending radially outward, the fuel joint (2) being mounted inside the mounting hole, and the fuel flow channel (17) is connected to the annular flow channel (16a) at one end close to the tail of the combustion chamber (16).

9. The continuous rotating detonation engine according to claim 6, characterized in that: The nozzle hole (18) comprises a constant diameter section located in the middle, and a flared section connected to at least one end of the constant diameter section, and the diameter of the flared section gradually increases in a direction away from the constant diameter section.

10. The continuous rotating detonation engine according to any one of claims 1 to 9, characterized in that: The engine body (1) is formed by an additive manufacturing process.

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