A knocking combustion device based on a wall surface microstructure combustion chamber and a control method

Abstract

This invention provides a rotary detonation combustion device based on wall microstructures, comprising: a combustion chamber and an ignition mechanism, an inner wall cooling mechanism, an outer wall cooling mechanism, and a fuel mechanism connected to the combustion chamber; the fuel mechanism for supplying combustible fuel to the combustion chamber; the ignition mechanism for controlling the ignition of the combustible fuel in the combustion chamber; the inner wall cooling mechanism for cooling the inner wall of the combustion chamber after the combustible fuel in the combustion chamber ignites and generates detonation; and the outer wall cooling mechanism for cooling the outer wall of the combustion chamber after the combustible fuel in the combustion chamber ignites and generates detonation. In this embodiment of the invention, the channel effectively increases the residence time of the coolant on the inner and outer walls, prevents the coolant from being blown away by the detonation shock wave, extends the cooling time for the coolant to form a cooling layer, and induces localized high-temperature and high-pressure electricity in the combustion chamber after the detonation wave sweeps, thus mitigating the impact of the inert coolant on the propagation stability of the detonation wave.

Description

Technical Field

[0001] This invention relates to the field of thermal protection technology for detonation combustion chambers, and more specifically, to a detonation combustion device and control method based on a wall microstructure combustion chamber. Background Technology

[0002] Engines are crucial power sources, and the rotating detonation combustion method within engines is gradually replacing isobaric combustion due to its advantages such as self-pressurization and high gas temperature. However, the flow field in rotating detonation combustion exhibits high-frequency periodic changes. These changes disrupt the integrity of the coolant on the engine sidewalls, causing film cooling to fail and reducing the engine's cooling efficiency. Summary of the Invention

[0003] To address the aforementioned problems, the present invention aims to provide a detonation combustion device and control method based on a wall-mounted microstructure combustion chamber.

[0004] In a first aspect, embodiments of the present invention provide a rotary detonation combustion device based on wall microstructures, characterized in that the device includes: an ignition mechanism, a combustion chamber, an inner wall cooling mechanism, an outer wall cooling mechanism, and a fuel mechanism;

[0005] The ignition mechanism, inner wall cooling mechanism, outer wall cooling mechanism, and fuel mechanism are all connected to the combustion chamber. The inner wall cooling mechanism is embedded in the outer wall cooling mechanism. The combustion chamber is located between the outer wall cooling mechanism and the inner wall cooling mechanism. The fuel mechanism is located at the end of the outer wall cooling mechanism away from the combustion chamber. The ignition mechanism is installed on the outer wall cooling mechanism and extends into the combustion chamber.

[0006] The fuel mechanism is used to supply combustible fuel to the combustion chamber;

[0007] The ignition mechanism is used to control the ignition of combustible fuel in the combustion chamber;

[0008] The inner wall cooling mechanism is used to cool the inner wall of the combustion chamber after the combustible fuel in the combustion chamber is ignited and produces a knock.

[0009] The outer wall cooling mechanism is used to cool the outer wall of the combustion chamber after the combustible fuel in the combustion chamber is ignited and produces a knock.

[0010] Secondly, embodiments of the present invention also provide a combustion chamber control method based on wall microstructure, the method being applied to the rotary detonation combustion device of the first aspect described above, the method comprising:

[0011] The coolant is injected into the inner wall cooling mechanism and the outer wall cooling mechanism respectively, and a heat-resistant protective film is formed in the combustion chamber;

[0012] The combustible fuel is controlled to be injected from the fuel mechanism into the combustion chamber;

[0013] The ignition mechanism is ignited, and the combustible fuel is detonated in the combustion chamber.

[0014] The combustion products generated by the flammable fuel after detonation are ejected from the communication port.

[0015] Thirdly, embodiments of the present invention also provide an engine, including: the rotary detonation combustion device of the first aspect described above.

[0016] In the solutions provided in the first to third aspects of this application, combustible fuel is injected into the combustion chamber through a fuel mechanism, and an ignition mechanism ignites the combustible fuel in the combustion chamber and generates detonation. An inner wall cooling mechanism cools and protects the inner wall of the combustion chamber, and an outer wall cooling mechanism cools and protects the outer wall of the combustion chamber. Compared with related technologies where the combustion chamber lacks inner and outer wall cooling mechanisms, thus failing to cool the inner and outer walls, the inner wall cooling mechanism on the inner wall of the combustion chamber and the outer wall cooling mechanism on the outer wall of the combustion chamber can achieve heat exchange with the interior of the combustion chamber, further improving the thermal protection effect of the combustion chamber.

[0017] To make the above-mentioned objects, features and advantages of the present invention more apparent and understandable, preferred embodiments are described below in detail with reference to the accompanying drawings. Attached Figure Description

[0018] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0019] Figure 1 A perspective view of the rotary detonation combustion device provided in an embodiment of the present invention is shown;

[0020] Figure 2 A longitudinal cross-sectional structural schematic diagram of the rotary detonation combustion device provided in an embodiment of the present invention is shown;

[0021] Figure 3 This shows a schematic cross-sectional view of the rotating detonation combustion device provided in an embodiment of the present invention when the channel is rectangular;

[0022] Figure 4This diagram shows a cross-sectional view of the rotating detonation combustion device provided in an embodiment of the present invention when the channel is triangular.

[0023] Icons: 10. Combustion chamber; 11. Inner wall; 12. Connecting port; 13. Outer wall; 14. Channel; 15. Inner passage; 16. Inner reservoir; 17. Inner coolant nozzle; 18. Outer passage opening; 19. Outer reservoir; 20. Outer coolant nozzle; 21. Fuel ring opening; 22. Fuel chamber; 23. Oxidizer ring gap; 24. Fuel nozzle; 25. Ignition element; 26. Conical component. Detailed Implementation

[0024] In the description of this invention, it should be understood that the terms "center," "longitudinal," "lateral," "length," "width," "thickness," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," "clockwise," and "counterclockwise," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this invention.

[0025] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of this invention, "a plurality of" means two or more, unless otherwise explicitly specified.

[0026] In this invention, unless otherwise explicitly specified and limited, the terms "installation," "connection," "linking," and "fixing," etc., should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal connection of two components. Those skilled in the art can understand the specific meaning of the above terms in this invention according to the specific circumstances.

[0027] Combustion within an engine can be categorized into detonation and knock. As a form of turbocharged combustion, knock combustion boasts high theoretical thermal cycle efficiency and has garnered widespread attention from both academia and industry. Rotary knock, a type of knock combustion, exhibits high fuel combustion efficiency, good environmental performance, and superior dynamic performance. Consequently, rotary knock engines have received increasing attention in recent years and have become a new hot research area in engine development. However, rotary knock engines still face certain challenges, particularly regarding their walls' ability to withstand high thermal loads. Therefore, research on wall thermal protection for rotary knock engines is crucial. Thermal protection for rotary knock engines is primarily divided into active and passive thermal protection. Among these, film cooling, as an effective active thermal protection technology, has been widely adopted and applied in high-heat-flux wall thermal protection.

[0028] However, the combustion chamber of a rotary detonation engine has high-frequency periodic changes in the flow field. The intense high temperature and pressure can easily disturb and severely damage the gas film protective layer (or liquid film protective layer) on the wall, making it impossible for the gas film protective layer to accumulate on the inner wall of the combustion chamber for a long time, resulting in a significant reduction in the cooling effect of the inner wall of the combustion chamber.

[0029] To address the aforementioned technical problems, the present invention proposes the following embodiments:

[0030] Example 1

[0031] This invention provides a rotary detonation combustion device based on wall microstructures, see [link / reference]. Figure 1 The diagram shows a three-dimensional representation of a rotary detonation combustion device. The device includes an ignition mechanism, a combustion chamber 10, an inner wall cooling mechanism, an outer wall cooling mechanism, and a fuel mechanism. The ignition mechanism, inner wall cooling mechanism, outer wall cooling mechanism, and fuel mechanism are all connected to the combustion chamber 10. The inner wall cooling mechanism is embedded in the outer wall cooling mechanism. The combustion chamber 10 is located between the outer wall cooling mechanism and the inner wall cooling mechanism. The fuel mechanism is located at the end of the outer wall cooling mechanism away from the combustion chamber 10. The ignition mechanism is installed on the outer wall cooling mechanism and extends into the combustion chamber 10. The fuel mechanism is used to supply combustible fuel to the combustion chamber 10. The ignition mechanism is used to control the ignition of the combustible fuel in the combustion chamber 10. The inner wall cooling mechanism is used to cool the inner wall of the combustion chamber 10 after the combustible fuel in the combustion chamber 10 is ignited and detonation occurs. The outer wall cooling mechanism is used to cool the outer wall of the combustion chamber 10 after the combustible fuel in the combustion chamber 10 is ignited and detonation occurs.

[0032] In this embodiment, the combustion chamber 10 is formed by the gap between the inner wall cooling mechanism and the outer wall cooling mechanism. The combustion chamber is an annular cavity structure, and only one side of the annular cavity has a connecting port 12 that communicates with the outside. The inner wall cooling mechanism consists of two parts: a cylindrical structure located inside the combustion chamber 10 and a conical member 26 extending to the outside through the connecting port. The cylindrical structure and the conical member 26 are integrally connected. The high-temperature gas generated after detonation inside the combustion chamber 10 is discharged from the connecting port 12 along the conical member 26. The airflow passing through the conical member 26 can increase the engine thrust. In particular, the conical member 26 is a plug nozzle, which is beneficial to increasing the expansion degree of the engine outlet airflow and improving the engine thrust. The working principle of the plug nozzle is common knowledge in the art and will not be described in detail here. It should be noted that the inner wall cooling mechanism refers to the collective term for all structures on the inner ring wall of the combustion chamber 10 with an annular cavity structure. Therefore, the inner wall cooling mechanism cannot be simply understood as having only one inner wall structure according to its literal meaning. In fact, the part of the inner wall cooling mechanism located inside the combustion chamber is a cylindrical structure.

[0033] In one implementation, see Figure 2 The schematic diagram of the longitudinal cross-sectional structure of the rotary detonation combustion device shown illustrates that the combustion chamber 10 includes an inner wall 11 and an outer wall 13. Both the inner wall 11 and the outer wall 13 of the combustion chamber 10 are provided with multiple channels 14. The coolant from the inner wall cooling mechanism enters the channels 14 of the inner wall 11, and the coolant from the outer wall cooling mechanism enters the channels 14 of the outer wall 13. The combustion products generated after the combustible fuel enters the combustion chamber 10 and undergoes detonation are discharged from the connecting port 12. Furthermore, different combustible fuels produce different combustion products after combustion. In this embodiment, the combustible fuel can be a gaseous fuel or a liquid fuel. If the combustible fuel is hydrogen, the combustion product is water; if the combustible fuel is kerosene, the combustion products are carbon dioxide and water.

[0034] In this embodiment, the inner wall 11 refers to the surface of the inner ring of the annular cavity structure combustion chamber 10, and the outer wall 13 refers to the surface of the outer ring of the annular cavity structure combustion chamber 10. The channels 14 are arranged in an array along the circumferential direction of the combustion chamber 10. The channels 14 enable the formation of multiple microstructures on the inner wall 11 and outer wall 13, and the surfaces of the inner wall 11 and outer wall 13 of the combustion chamber 10 are uneven. The channels 14 in the combustion chamber 10 can prolong the coolant residence time and reduce the intensity of the detonation wave. Therefore, see... Figure 3 The diagram shows a cross-sectional view of the rotary detonation combustion device when the channel is rectangular, and see also [reference]. Figure 4The diagram shown is a cross-sectional view of the rotating detonation combustion device when the channel is triangular. The channel 14 can be a rectangular channel or a triangular channel. Here, the specific shape, size and arrangement of the channel 14 are not specifically limited.

[0035] In one embodiment, the inner wall cooling mechanism includes: an inner channel 15, an inner storage cavity 16, and an inner coolant spray nozzle 17; one end of the inner channel 15 is connected to the outside, and the other end is connected to the inner storage cavity 16; one end of the inner coolant spray nozzle 17 is connected to the inner storage cavity 16, and the other end is connected to the combustion chamber 10; the coolant is injected into the inner storage cavity 16 through the inner channel 15, and the coolant in the inner storage cavity 16 is sprayed into the combustion chamber 10 through the inner coolant spray nozzle 17, so that the coolant of the inner wall cooling mechanism enters the channel 14 of the inner sidewall 11. The external wall cooling mechanism includes: an external channel port 18, an external storage cavity 19, and an external coolant spray nozzle 20; one end of the external channel port 18 is connected to the outside, and the other end is connected to the external storage cavity 19; one end of the external coolant spray nozzle 20 is connected to the external storage cavity 19, and the other end is connected to the combustion chamber 10; the coolant is injected into the external storage cavity 19 through the external channel port 18, and the coolant in the external storage cavity 19 is sprayed into the combustion chamber 10 through the external coolant spray nozzle 20, so that the coolant of the external wall cooling mechanism enters the channel 14 of the outer side wall 13.

[0036] In this embodiment, both the inner and outer wall cooling mechanisms are filled with coolant. The coolant can be either gaseous or liquid, and can be selected according to requirements. The specific medium of the coolant is not limited here. Specifically, the combustible fuel during detonation in the combustion chamber 10 and the high-temperature combustion gases produced after combustion both have a certain axial velocity, capable of generating significant kinetic energy. Therefore, the inner coolant nozzle 17 and the outer coolant nozzle 20 need to have a certain tilt angle so that the sprayed coolant can move along the axial direction of the combustion chamber 10, facilitating the diffusion of the coolant along the surfaces of the inner wall 11 and outer wall 13 of the combustion chamber 10. This forms a protective layer on the surfaces of the inner wall 11 and outer wall 13 of the combustion chamber 10, isolating the high-temperature combustion gases produced after the combustible fuel combustion from the inner wall 11 and outer wall 13 of the combustion chamber 10. Meanwhile, the array of channels 14 on the inner wall 11 and outer wall 13 of the combustion chamber 10 can effectively increase the residence time of the coolant on the inner wall 11 and outer wall 13 of the combustion chamber, and the coolant in the channels 14 is not easily blown away by the detonation shock wave, effectively improving the thermal protection effect of the inner wall 11 and outer wall 13; combustible fuel is injected into the combustion chamber 10 through the fuel mechanism, and the ignition mechanism ignites the combustible fuel in the combustion chamber 10 and generates detonation. The channels 14 can induce the combustion chamber 10 to generate local high temperature and high pressure electricity after the detonation wave sweeps, improving the influence of the inert coolant on the propagation stability of the detonation wave.

[0037] Specifically, the inner coolant nozzle 17 needs to be located at the center of the channel 14 on the inner sidewall of the combustion chamber 10, and the outer coolant nozzle 20 needs to be located at the center of the channel 14 on the outer sidewall of the combustion chamber 10. This facilitates the rapid filling of the channel 14 when coolant is injected into it.

[0038] In one embodiment, the fuel mechanism includes: a fuel ring opening 21, a fuel chamber 22, an oxidant annular slit 23, and a fuel injection port 24; the fuel ring opening 21 is connected to the fuel chamber 22; one end of the fuel injection port 24 communicates with the fuel chamber 22, and the other end communicates with the oxidant annular slit 23; the oxidant annular slit 23 communicates with the combustion chamber 10; the oxidant annular slit 23 contains an oxidant; the combustible fuel enters the fuel chamber 22 from the fuel ring opening 21, and the combustible fuel in the fuel chamber 22 is then injected into the oxidant annular slit 23 from the fuel injection port 24 to combine with the oxidant contained in the oxidant annular slit 23, resulting in combustible fuel doped with the oxidant; the combustible fuel doped with the oxidant enters the combustion chamber 10 and is ignited by the ignition mechanism. Specifically, an oxidant injection port exists between the oxidant annular slit and the outside.

[0039] In this embodiment, the fuel chamber 22 is a disc-shaped chamber with a certain thickness. At its center is an inner channel 15 for coolant injection. The gap between the inner channel 15 and the disc-shaped fuel chamber is the fuel ring opening 21. It should be noted that the inner channel 15 only communicates with the inner storage chamber 16, not with the fuel chamber 22. The fuel injection holes 24 around the combustion chamber 10 can inject combustible fuel into the oxidizer ring slit 23 at a certain pressure. The oxidizer ring slit 23 is a two-end connected structure; one end communicates with the combustion chamber 10, and the other end communicates with the outside through an oxidizer injection hole. Oxidizer can enter the oxidizer ring slit 23 from the outside through the oxidizer injection hole. Specifically, the "outside world" mentioned above refers to the "outside world" of the rotary detonation combustion device. Outside the rotary detonation combustion device are other necessary structures for other engines (which can be aircraft engines, marine engines, or vehicle engines). Therefore, the "outside world" mentioned above should not be interpreted as a broad exposure to the outdoor environment.

[0040] In one embodiment, the ignition mechanism includes a connecting pipe and an ignition element 25; one end of the connecting pipe extends to the outer wall of the combustion chamber 10 and communicates with the outside, and the other end extends to the combustion chamber 10; the ignition element 25 is disposed on the connecting pipe; the ignition element 25 releases a high-energy electric arc and ignites the combustible fuel in the combustion chamber 10, thereby completing the ignition operation.

[0041] In this embodiment, the ignition element 25 includes, but is not limited to, an electric spark plug, a detonation tube, or a plasma igniter.

[0042] In summary, the rotary detonation combustion device based on wall microstructure proposed in this invention injects combustible fuel into the combustion chamber through a fuel mechanism, ignites the combustible fuel in the combustion chamber 10 through an ignition mechanism to generate detonation, cools and protects the inner sidewall 11 of the combustion chamber through an inner wall cooling mechanism, and cools and protects the outer sidewall 13 of the combustion chamber through an outer wall cooling mechanism. Compared with related technologies that do not have inner and outer wall cooling mechanisms in the combustion chamber and therefore cannot cool the inner and outer walls of the combustion chamber, the inner wall cooling mechanism on the inner sidewall 11 of the combustion chamber 10 and the outer wall cooling mechanism on the outer sidewall 13 of the combustion chamber 10 can achieve heat exchange with the interior of the combustion chamber 10, thereby further improving the thermal protection effect of the combustion chamber 10.

[0043] Example 2

[0044] This invention also proposes a combustion chamber control method based on wall microstructure, which is applied to the rotary detonation combustion device described in Embodiment 1. The method includes:

[0045] The coolant is injected into the inner wall cooling mechanism and the outer wall cooling mechanism respectively, and a heat-resistant protective film is formed in the combustion chamber 10;

[0046] The combustible fuel is controlled to be injected from the fuel mechanism into the combustion chamber 10;

[0047] The ignition mechanism is ignited, and the combustible fuel is detonated in the combustion chamber 10.

[0048] The combustion products generated by the flammable fuel after detonation are ejected from the communication port 12.

[0049] In summary, the present invention proposes a combustion chamber control method based on wall microstructure. Combustible fuel is injected into the combustion chamber via a fuel mechanism, and an ignition mechanism ignites the fuel within the combustion chamber 10, generating detonation. An inner wall cooling mechanism cools and protects the inner sidewall 11 of the combustion chamber, and an outer wall cooling mechanism cools and protects the outer sidewall 13 of the combustion chamber. Compared to related technologies where the combustion chamber lacks both inner and outer wall cooling mechanisms, thus failing to cool the inner and outer walls, the inner wall cooling mechanism on the inner sidewall 11 of the combustion chamber 10 and the outer wall cooling mechanism on the outer sidewall 13 of the combustion chamber 10 enable heat exchange with the interior of the combustion chamber 10, further enhancing the thermal protection effect of the combustion chamber 10.

[0050] Example 3

[0051] This invention also discloses an engine, including the rotary detonation combustion device proposed in Embodiment 1 above. Therefore, this engine possesses all the technical effects described in Embodiment 1 above, and will not be repeated here.

[0052] The above description is merely a specific embodiment of the present invention, but the scope of protection of the present invention is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the scope of the technology disclosed in the present invention should be included within the scope of protection of the present invention. Therefore, the scope of protection of the present invention should be determined by the scope of the claims.

Claims

1. A rotary detonation combustion device based on wall microstructure, characterized in that, The device includes: an ignition mechanism, a combustion chamber, an inner wall cooling mechanism, an outer wall cooling mechanism, and a fuel mechanism; The ignition mechanism, inner wall cooling mechanism, outer wall cooling mechanism, and fuel mechanism are all connected to the combustion chamber. The inner wall cooling mechanism is embedded in the outer wall cooling mechanism. The combustion chamber is located between the outer wall cooling mechanism and the inner wall cooling mechanism. The fuel mechanism is located at the end of the outer wall cooling mechanism away from the combustion chamber. The ignition mechanism is installed on the outer wall cooling mechanism and extends into the combustion chamber. The fuel mechanism is used to supply combustible fuel to the combustion chamber; The ignition mechanism is used to control the ignition of combustible fuel in the combustion chamber; The inner wall cooling mechanism is used to cool the inner wall of the combustion chamber after the combustible fuel in the combustion chamber is ignited and produces a knock. The outer wall cooling mechanism is used to cool the outer wall of the combustion chamber after the combustible fuel in the combustion chamber is ignited and produces a knock. The combustion chamber includes: an inner wall, a connecting port, and an outer wall; The inner wall and the outer wall of the combustion chamber are provided with multiple channels; The connection port is connected to the outside world; The inner wall cooling mechanism includes: an inner channel, an inner reservoir, and an inner coolant spray nozzle; One end of the inner channel is connected to the outside, and the other end is connected to the inner storage cavity; One end of the internal coolant injection hole is connected to the internal storage cavity, and the other end is connected to the combustion chamber; The outer wall cooling mechanism includes: an outer channel opening, an outer storage cavity, and an outer coolant spray hole; One end of the external channel is connected to the outside, and the other end is connected to the external storage cavity; One end of the external coolant nozzle is connected to the external reservoir cavity, and the other end is connected to the combustion chamber; One end of the external coolant nozzle connected to the combustion chamber is located at the center of the channel provided on the outer side wall of the combustion chamber, and the other end of the internal coolant nozzle connected to the combustion chamber is located at the center of the channel on the inner side wall of the combustion chamber. The fuel mechanism includes: a fuel ring opening, a fuel chamber, an oxidizer ring slit, and a fuel injection hole; The fuel ring opening is connected to the fuel chamber; One end of the fuel injection hole is connected to the fuel chamber, and the other end is connected to the oxidant annular seam; The oxidant annular seam is connected to the combustion chamber; The oxidant ring gap contains the oxidant.

2. The rotary detonation combustion device according to claim 1, characterized in that, The coolant of the inner wall cooling mechanism enters the channel of the inner side wall, and the coolant of the outer wall cooling mechanism enters the channel of the outer side wall. The combustion products generated after the combustible fuel enters the combustion chamber and undergoes detonation are discharged from the connecting port.

3. The rotary detonation combustion device according to claim 2, characterized in that, The coolant is injected into the inner storage chamber through the inner channel, and the coolant in the inner storage chamber is sprayed into the combustion chamber through the inner coolant nozzle, so that the coolant of the inner wall cooling mechanism enters the channel of the inner side wall.

4. The rotary detonation combustion device according to claim 3, characterized in that, The coolant is injected into the outer storage chamber through the outer channel, and the coolant in the outer storage chamber is sprayed into the combustion chamber through the outer coolant nozzle, so that the coolant of the outer wall cooling mechanism enters the channel of the outer wall.

5. The rotary detonation combustion device according to claim 4, characterized in that, The combustible fuel enters the fuel chamber through the fuel ring opening, and the combustible fuel in the fuel chamber is then injected into the oxidant ring gap through the fuel injection hole to combine with the oxidant contained in the oxidant ring gap, thereby obtaining the combustible fuel doped with the oxidant. The combustible fuel doped with the oxidant enters the combustion chamber and is ignited by the ignition mechanism.

6. The rotary detonation combustion device according to claim 5, characterized in that, The ignition mechanism includes: a connecting pipe and an ignition element; One end of the connecting pipe extends to the outer wall of the combustion chamber and communicates with the outside, and the other end extends to the combustion chamber. The ignition element is disposed on the connecting pipe. The ignition element releases a high-energy electric arc and ignites the combustible fuel in the combustion chamber, thus completing the ignition operation.

7. The rotary detonation combustion device according to claim 6, characterized in that, A tapered component is provided on the side surface of the inner wall cooling mechanism that faces the same direction as the opening of the communication port.

8. A combustion chamber control method based on wall microstructure, said method being applied to the rotary detonation combustion device of claim 7 above, characterized in that, The method includes: The coolant is injected into the inner wall cooling mechanism and the outer wall cooling mechanism respectively, and a heat-resistant protective film is formed in the combustion chamber; The combustible fuel is controlled to be injected from the fuel mechanism into the combustion chamber; The ignition mechanism is ignited, and the combustible fuel is detonated in the combustion chamber. The combustion products generated by the flammable fuel after detonation are ejected from the communication port.

9. An engine, characterized in that, include: The rotary detonation combustion device as described in claim 7 above.

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