CN117552891B - A rotary detonation engine based on multiple cavities and pits on the wall and its control method - Google Patents

Abstract

The invention provides a rotary detonation engine and a control method based on multiple cavities and pits on the wall, including: an injection mechanism, a combustion chamber, a center column and an ignition device; the combustion chamber includes: a combustion chamber head, a combustion chamber The middle part and the tail part of the combustion chamber; a first annular cavity is formed between the side wall of the center column close to the head of the combustion chamber and the inner surface of the head part of the combustion chamber, and the side wall of the center column close to the middle part of the combustion chamber and the inner surface of the middle part of the combustion chamber A second annular cavity is formed between them; multiple pits are provided on the inner surface of the combustion chamber; the injection mechanism is located at the head of the combustion chamber and injects toward the rear of the combustion chamber; the ignition device is located on the outer wall of the head of the combustion chamber. and extends into the combustion chamber. The invention intercepts and decelerates the fuel injected into the combustion chamber through the first and second annular concave cavities, and preheats the subsequent fuel; the injected fuel can be further decelerated through the pits on the surface of the fuel chamber, and the fuel injected into the combustion chamber is preheated. Heat changes the physical and chemical properties of the fuel, allowing the fuel to be fully burned.

Description

A rotary detonation engine based on multiple cavities and pits on the wall and its control method

Technical field

The present invention relates to the field of engine technology, and specifically to a rotary detonation engine based on multiple cavities and pits on the wall and a control method.

Background technique

Rotating detonation engines can be applied to aircraft. Rotating detonation engines have self-supercharging characteristics and can enhance the aerospace propulsion performance of aircraft. However, when a rotating detonation engine uses aviation kerosene as fuel, the large carbon atoms in aviation kerosene have inert physical and chemical properties during combustion, which will lead to unstable detonation wave propagation during the detonation process and affect the kinetic energy of the engine.

Contents of the invention

In order to solve the above problems, the purpose of embodiments of the present invention is to provide a rotary detonation engine and a control method based on multiple cavities and pits on the wall.

In the first aspect, embodiments of the present invention provide a rotary detonation engine based on multiple cavities and pits on the wall, including: an injection mechanism, a combustion chamber, a center column and an ignition device;

The central column is located at the center of the combustion chamber, and the radial direction of the central column is the same as the extension direction of the combustion chamber axis;

The combustion chamber includes: a combustion chamber head, a combustion chamber middle and a combustion chamber tail; a first ring is formed between the side wall of the center column close to the combustion chamber head and the inner surface of the combustion chamber head. A second annular cavity is formed between the side wall of the central column near the middle part of the combustion chamber and the inner surface of the middle part of the combustion chamber;

A plurality of pits are provided on the inner surface of the combustion chamber;

The injection mechanism is located at the head of the combustion chamber and injects towards the rear of the combustion chamber;

The ignition device is located on the outer wall of the combustion chamber head and extends into the combustion chamber;

The injection mechanism injects fuel into the combustion chamber, the ignition device ignites the fuel in the combustion chamber, and the fuel generates energy toward the combustion chamber after inducing detonation in the first annular cavity. The thrust of the tail, the fuel detonates in the second annular cavity and generates thrust towards the tail of the combustion chamber. After the fuel detonates, it forms a low-speed stationary cyclone in the pit and generates thrust towards the end of the combustion chamber. The thrust at the rear of the combustion chamber, wherein the thrust produced by the fuel toward the rear of the combustion chamber after inducing detonation in the first annular cavity is smaller than the thrust produced by the fuel toward the rear after inducing detonation in the second annular cavity Thrust at the end of the combustion chamber.

In a second aspect, embodiments of the present invention also provide a control method for a rotating detonation engine. The method is applied to the rotating detonation engine described in the first aspect. The method includes:

injecting the fuel from the fuel nozzle into the fuel chamber;

The oxidant is controlled to be injected into the combustion chamber from the oxidant annular gap, and the fuel in the combustion chamber is sheared and mixed; wherein, the pressure at which the oxidant is injected into the combustion chamber is greater than the pressure at which the fuel enters the combustion chamber. pressure;

Start the ignition device to detonate the fuel mixed with the oxidant in the combustion chamber. After the fuel is detonated, a low-speed stationary cyclone is formed in the pit on the side wall of the combustion chamber and a high-temperature gas film is formed;

The fuel is injected into the rear part of the combustion chamber through the feed ring, so that the fuel supplemented at the rear part is mixed with the fuel remaining after combustion in the head and middle part, and burned again.

In a third aspect, embodiments of the present invention also provide a device with a rotating detonation engine, including the rotating detonation engine described in the first aspect.

Among the solutions provided by the above-mentioned first to third aspects of the present application, the embodiment of the present invention proposes a rotary detonation engine based on multiple concave cavities on the wall. Fuel is injected into the combustion chamber through an injection mechanism, and the ignition device is controlled to detonate. The fuel generates detonation, and the location of the detonation in the combustion chamber is controlled according to the flight speed and thrust required for different flight conditions; compared with related technologies in which the fuel is not fully burned in the combustion chamber and causes fuel waste, the first ring The fuel can also be partially intercepted in the hollow cavity and the second annular cavity to decelerate the fuel and prevent the fuel from spreading to the outside too quickly; the injected fuel can be further decelerated through the pits on the surface of the fuel chamber, and The high-speed gas flow generated after combustion is used to flow through the wall pits to form a low-speed stationary cyclone, thereby generating a high-temperature gas film on the outer wall, and preheating the liquid fuel to improve the inert physical and chemical properties of the liquid fuel and improve the propagation stability of rotational detonation.

In order to make the above-mentioned objects, features and advantages of the present invention more obvious and understandable, preferred embodiments are given below and described in detail with reference to the accompanying drawings.

Description of drawings

In order to explain the embodiments of the present invention or the technical solutions in the prior art more clearly, the drawings needed to be used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings in the following description are only These are some embodiments of the present invention. For those of ordinary skill in the art, other drawings can be obtained based on these drawings without exerting creative efforts.

Figure 1 shows a schematic three-dimensional view of a rotary detonation engine provided by an embodiment of the present invention;

Figure 2 shows a schematic diagram of a combustion chamber composed of a combustion chamber head, a combustion chamber middle and a combustion chamber tail provided by an embodiment of the present invention;

Figure 3 shows a schematic cross-sectional structural diagram of a rotary detonation engine provided by an embodiment of the present invention;

Figure 4 shows an enlarged structural schematic diagram of the area A in Figure 3 provided by an embodiment of the present invention;

Figure 5 shows a schematic cross-sectional structural diagram of the rotary detonation engine provided by the embodiment of the present invention after removing the center column;

Figure 6 shows a schematic cross-sectional view of the center column in the rotary detonation engine provided by the embodiment of the present invention.

Icon: 10. Combustion chamber; 11. Center column; 12. Ignition device; 13. Head of combustion chamber; 14. Middle part of combustion chamber; 15. Tail part of combustion chamber; 16. First annular cavity; 17. Second ring 18. Pits; 19. Fuel nozzle; 20. Injection cover; 21. Opening; 22. Feeding ring; 23. Inclined tube; 24. Water-cooled interlayer; 25. Ignition installation port.

Detailed ways

In the description of the present invention, it should be understood that the terms "center", "longitudinal", "transverse", "length", "width", "thickness", "upper", "lower", "front", " The directions or positions indicated by "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", "clockwise", "counterclockwise" etc. The relationship is based on the orientation or positional relationship shown in the drawings, which is only for the convenience of describing the present invention and simplifying the description, and does not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore It should not be construed as a limitation of the present invention.

In addition, the terms “first” and “second” are used for descriptive purposes only and cannot be understood as indicating or implying relative importance or implicitly indicating the quantity of indicated technical features. Therefore, features defined as "first" and "second" may explicitly or implicitly include one or more of these features. In the description of the present invention, "plurality" means two or more than two, unless otherwise explicitly and specifically limited.

In the present invention, unless otherwise clearly stated and limited, the terms "installation", "connection", "connection", "fixing" and other terms should be understood in a broad sense. For example, it can be a fixed connection or a detachable connection. , or integrally connected; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium; it can be an internal connection between two components. For those of ordinary skill in the art, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

The combustion methods inside the aircraft engine can be divided into deflagration and detonation. As a form of supercharged combustion, detonation combustion has the advantage of high theoretical thermal cycle efficiency and has attracted widespread attention from academia and industry. Detonation refers to a combustion method that combines shock waves with flame surfaces. Compared with the more commonly used isobaric combustion, detonation combustion can increase the thermal cycle efficiency by 50%. At the same time, detonation combustion can also Enhanced aerospace propulsion performance. Therefore, detonation combustion has received more and more attention. Pulse detonation engines, oblique detonation engines and rotating detonation engines derived from detonation combustion have been widely studied. Among them, the rotating detonation engine has been widely studied due to its structure. Simplicity and higher working frequency are the focus of research.

The fuel of the rotating detonation engine is divided into gaseous fuel and liquid fuel. Liquid fuel has become the best fuel for the rotating detonation engine because of its advantages of easy transportation, easy preparation and high combustion heat value per unit volume. However, liquid fuel often needs to go through processes such as atomization, evaporation, and blending before detonation occurs. In particular, aviation kerosene in liquid fuel has inert physical and chemical properties because it contains large carbon atoms, resulting in inconsistencies in the detonation process. Stablize.

In response to the above technical problems, the present invention proposes the following embodiments:

Example 1

Referring to the three-dimensional schematic diagram of the rotary detonation engine shown in Figure 1 and the schematic diagram of a combustion chamber composed of a combustion chamber head, a combustion chamber middle and a combustion chamber tail shown in Figure 2, this embodiment provides a multi-cavity wall-based multi-cavity and pit rotary detonation engine, including: an injection mechanism, a combustion chamber 10, a center column 11 and an ignition device 12; the center column 11 is located at the center of the combustion chamber 10, and the radial direction of the center column 11 The extension direction of the axis of the combustion chamber 10 is the same; the combustion chamber 10 includes: a combustion chamber head 13, a combustion chamber middle 14 and a combustion chamber tail 15; the center column 11 is close to the combustion chamber head 13 A first annular cavity 16 is formed between the side wall and the inner surface of the combustion chamber head 13 . A second annular cavity 17 is formed between them; an exhaust port is provided on the right side of the tail portion 15 of the combustion chamber; a plurality of pits 18 are provided on the inner surface of the combustion chamber 10; the injection mechanism is located in the combustion chamber The head 13 is injected toward the tail 15 of the combustion chamber; the ignition device 12 is located on the outer wall of the head 13 of the combustion chamber and extends into the combustion chamber 10 .

Specifically, the injection mechanism injects fuel into the combustion chamber 10 , the ignition device 12 performs an ignition operation on the fuel inside the combustion chamber 10 , and the fuel causes detonation at the first annular cavity 16 to generate thrust toward the rear end 15 of the combustion chamber. , the fuel triggers detonation in the second annular cavity 17 to generate thrust towards the end of the combustion chamber 15. After the fuel detonates, it will form a low-speed stationary cyclone in the pit 18 and generate thrust towards the end of the combustion chamber 15. The first The size of the annular cavity is smaller than the size of the second annular cavity. The thrust generated by the fuel towards the rear part 15 of the combustion chamber after detonation is caused by the fuel in the first annular cavity 16 is smaller than the thrust towards the rear part 15 of the combustion chamber caused by the detonation caused by the fuel in the second annular cavity 17 .

In this embodiment, the fuel injected into the combustion chamber 10 by the injection mechanism may be gaseous fuel or liquid fuel, and the liquid fuel is preferably aviation kerosene. The combustion chamber 10 has an annular cavity structure. The inner ring of the annular cavity is located on the outer surface of the central column 11 , and the outer ring of the annular cavity is located on the outer wall of the combustion chamber 10 . The interior of the combustion chamber 10 is divided into three areas by the combustion chamber head 13, the combustion chamber middle 14 and the combustion chamber tail 15. The pit 18 is located on the outer wall of the combustion chamber 10 corresponding to the combustion chamber head 13 and the combustion chamber middle 14. , the low-speed stationary cyclone formed at the pit 18 after the fuel is injected into the combustion chamber 10 means that after the high-speed airflow generated by the detonation passes through the pit 18, part of the airflow will be intercepted by the pit 18 and the flow speed will be reduced to generate a recirculation area and vortex system. structure. There is no pit 18 on the inner wall of the corresponding combustion chamber 10 at the combustion chamber tail 15. The combustion chamber tail 15 is the area closest to the outside world. The gas generated after the fuel is burned in the combustion chamber head 13 and the combustion chamber middle 14 is emitted from the combustion chamber tail. 15 does not need to stay in the combustion chamber tail 15 for a long time when it is discharged to the outside world. In order to avoid the pits 18 intercepting the exhaust gas, no pits are provided on the inner wall of the combustion chamber 10 where the combustion chamber tail 18 is located.

In one embodiment, referring to the cross-sectional structural schematic diagram of the rotating detonation engine shown in Figure 3 and the enlarged structural diagram of the area A in Figure 3 shown in Figure 4, the injection mechanism includes a fuel nozzle 19 and an injection cover 20 and oxidant annulus. The injection cover 20 is installed on the fuel chamber head 13, and an opening 21 is provided on the injection cover 20; the fuel nozzle 19 communicates with the opening 21 provided on the injection cover 20 ; The fuel is injected into the fuel chamber 10 from the fuel nozzle 19 through the injection cover 20 . The oxidant annular gap injects high-pressure oxidant into the combustion chamber 10 , and the high-pressure oxidant mixes with the fuel in the combustion chamber 10 . Detonation can be caused only after the oxidant and fuel are fully mixed. The position where detonation is caused can be controlled by controlling the flow rate of the oxidizer. For example, when the oxidant flow rate is high, after it is injected into the combustion chamber 10, it can be mixed with the fuel in the middle 14 of the combustion chamber. , start the ignition device 12 at this time. Since the mixing of the oxidant and the fuel in the middle part of the combustion chamber 14 meets the requirements, the knocking is mainly concentrated in the middle part of the combustion chamber 14; when the flow rate of the oxidant is slow, after it is injected into the combustion chamber 10, it can start at the head of the combustion chamber. The fuel is mixed with the combustion chamber head 13. At this time, the ignition device 12 is started, and the knocking is mainly concentrated in the combustion chamber head 13. Among them, the detonation caused by the combustion chamber head 13 can realize low-speed flight of the aircraft, and the detonation caused by the middle part 14 of the combustion chamber can realize the high-speed flight of the aircraft. In particular, it is common knowledge in the art that detonation can realize low-speed or high-speed flight. The specific principle is This will not be repeated here.

In this embodiment, the fuel nozzle 19 is an atomizing nozzle, including but not limited to: a pressure atomizing nozzle, a swirling flow atomizing nozzle, and an impact atomizing nozzle.

The fuel nozzle 19 needs to be installed at the head 13 of the combustion chamber, and the fuel nozzle 19 needs to face the exhaust port at the rear 15 of the combustion chamber. The number of fuel nozzles 19 is multiple, and they are arranged at equal intervals with the central column 11 as the center of the circle. The injection cover 20 is fixedly connected to the combustion chamber 10 through a flange. When the fuel detonates in the combustion chamber 10, the detonation wave heading towards the injection cover 20 can be intercepted by the injection cover 20 and provide reverse direction. Thrust is discharged from the exhaust port. Although the fuel nozzle 19 passes through the opening 21 on the injection cover 20 and enters the combustion chamber 10, the combustion nozzle 19 does not touch the injection cover 20, and there is an oxidant annular gap between them for oxidant injection. In particular, the oxidizing agent is preferably a gaseous oxidizing agent. The flow rate of the oxidant injected into the combustion chamber 10 through the oxidant annular gap is greater than the flow rate of the fuel injected into the combustion chamber 10 through the fuel nozzle 19. The high-speed oxidant gas flow can "shear" and "break" the liquid fuel, accelerating the interaction between the oxidant and the liquid fuel. The mutual mixing makes the fuel with oxidizer burn more fully. At the same time, the recesses of the first annular cavity 16 and the second annular cavity 17 can also intercept part of the oxidant and fuel, so that the oxidant and the liquid fuel are further fully mixed in the recesses.

In one embodiment, the tail 15 of the combustion chamber is equipped with a feeding assembly, wherein the feeding assembly includes: a feeding ring 22 and an inclined tube 23; the feeding ring 22 has a central control structure inside, and the feeding ring 22 It is arranged on the outer wall of the combustion chamber 10 near the tail portion 15 of the combustion chamber; one end of the inclined tube 23 is connected to the feeding annular member 22, and the other end is connected to the combustion chamber 10, so that the feeding annular member 22 is connected to the combustion chamber tail 15 through the inclined tube 23; the fuel feeding ring 22 contains fuel, and the feeding ring 22 can be supplied to the combustion chamber tail 15 through the inclined tube 23. Replenish said fuel.

In this embodiment, although the fuel in the injection mechanism can be gaseous fuel or liquid fuel, the fuel in the feeding assembly needs to be preferably gaseous fuel. This is because the molecules of gaseous fuel are smaller than the molecules of liquid fuel. Easier to mix and detonate. The replenishing component is to replenish the fuel that is not fully burned when the fuel injected by the injection mechanism reaches the end of the combustion chamber 15, so that the incompletely burned fuel is mixed and burned again with the newly replenished fuel, thereby improving the utilization of the fuel. efficiency and reduce fuel waste. In particular, the fuel in the refueling assembly includes, but is not limited to, hydrogen or hydrocarbon gas.

In one embodiment, referring to the schematic cross-sectional structural diagram of the rotating detonation engine with the center column removed as shown in Figure 5 and the schematic cross-sectional view of the central column in the rotating detonation engine shown in Figure 6, the injection mechanism and the feeding assembly are When the outgoing fuel is detonated, high-temperature gas will be generated. Therefore, a water-cooling interlayer 24 is provided on the outer wall of the combustion chamber 10 and the center column 11, and water-cooling liquid is injected into the water-cooling interlayer 24; the water-cooling liquid is injected After the water-cooling interlayer 24 is provided, the outer wall of the combustion chamber 10 and the side wall of the center column 11 can be water-cooled respectively.

In this embodiment, the water-cooling interlayer 24 has the same structure as the combustion chamber 10 and is an annular cavity structure. The water-cooling interlayer 24 is used to cool the side walls of the combustion chamber 10 and reduce the damage caused by the high temperature of the combustion chamber 10 due to knocking. 10 Sidewall ablation occurs.

In this embodiment, an ignition installation port 25 is provided on the outer wall of the combustion chamber 10. The ignition device 12 is located in the ignition installation port 25 and can emit a hot jet into the combustion chamber 10 and trigger fuel detonation. In particular, ignition device 12 includes, but is not limited to, spark plugs, high energy igniters, and plasma burners.

To sum up, the embodiment of the present invention proposes a rotary detonation engine based on multiple cavities on the wall. Fuel is injected into the combustion chamber through an injection mechanism, and the ignition device is controlled to detonate the fuel to generate detonation. According to different flight conditions The required flight speed and thrust control the position where detonation occurs in the combustion chamber; compared with the related technology in which the fuel is not fully burned in the combustion chamber and causes fuel waste, the first annular cavity and the second annular cavity The fuel can also be partially intercepted to decelerate the fuel to prevent the fuel from spreading to the outside too quickly; the injected fuel can be further decelerated through the pits on the surface of the fuel chamber, and the high-speed gas flow generated after combustion is used to flow through The wall pits 18 form a low-speed stationary cyclone to generate a high-temperature gas film on the outer wall, and preheat the liquid fuel to improve the inert physical and chemical properties of the liquid fuel and enhance the propagation stability of rotational detonation.

Example 2

An embodiment of the present invention also proposes a control method for a rotating detonation engine, which is applied to the rotating detonation engine based on multiple cavities on the wall described in Embodiment 1. The method includes:

injecting the fuel from the fuel nozzle into the fuel chamber;

The oxidant is controlled to be injected into the combustion chamber from the oxidant annular gap, and the fuel in the combustion chamber is sheared and mixed; wherein, the pressure at which the oxidant is injected into the combustion chamber is greater than the pressure at which the fuel enters the combustion chamber. pressure;

Start the ignition device to detonate the fuel mixed with the oxidant in the combustion chamber. After the fuel is detonated, a low-speed stationary cyclone is formed in the pit on the side wall of the combustion chamber and a high-temperature gas film is formed;

The fuel is injected into the rear part of the combustion chamber through the feed ring, so that the fuel supplemented at the rear part is mixed with the fuel remaining after combustion in the head and middle part, and burned again.

To sum up, in summary, the embodiment of the present invention proposes a rotary detonation engine based on multiple cavities on the wall. Fuel is injected into the combustion chamber through an injection mechanism, and the ignition device is controlled to detonate the fuel to generate detonation. The position where detonation occurs in the combustion chamber is controlled according to the flight speed and thrust required for different flight conditions; compared with the waste of fuel caused by insufficient combustion of fuel in the combustion chamber in related technologies, the first annular cavity and the third The fuel can also be partially intercepted in the two-ring cavity to decelerate the fuel and prevent the fuel from spreading to the outside too quickly. The pits on the surface of the fuel chamber can further decelerate the injected fuel and utilize the energy generated after combustion. The high-speed gas flow flows through the wall pit to form a low-speed stationary cyclone, thereby generating a high-temperature gas film on the outer wall, preheating the liquid fuel to improve the inert physical and chemical properties of the liquid fuel and improving the propagation stability of rotational detonation.

Example 3

An embodiment of the present invention also discloses a device with a rotating detonation engine, including a rotating detonation engine based on multiple cavities on the wall proposed in the above-mentioned Embodiment 1. Therefore, this engine has all the technical effects in the above-mentioned Embodiment 1, which will not be repeated here.

The above are only specific embodiments of the present invention, but the protection scope of the present invention is not limited thereto. Any person familiar with the technical field can easily think of changes or substitutions within the technical scope disclosed in the present invention. All solutions shall be covered by the protection scope of the present invention. Therefore, the protection scope of the present invention should be subject to the protection scope of the claims.

Claims (8)

1. A rotary detonation engine based on multiple cavities and pits on the wall, which is characterized by including: an injection mechanism, a combustion chamber, a center column and an ignition device; The center column is located at the center of the combustion chamber, and the axis direction of the center column is the same as the extension direction of the axis of the combustion chamber; The combustion chamber includes: a combustion chamber head, a combustion chamber middle and a combustion chamber tail; a first ring is formed between the side wall of the center column close to the combustion chamber head and the inner surface of the combustion chamber head. A second annular cavity is formed between the side wall of the central column near the middle part of the combustion chamber and the inner surface of the middle part of the combustion chamber; A plurality of pits are provided on the inner surface of the combustion chamber. The pits are located on the inner wall of the combustion chamber corresponding to the head of the combustion chamber and the middle of the combustion chamber. There are no pits on the inner wall of the combustion chamber where the tail of the combustion chamber is located; The injection mechanism is located at the head of the combustion chamber and injects towards the rear of the combustion chamber; The ignition device is located on the outer wall of the combustion chamber head and extends into the combustion chamber; The injection mechanism injects fuel into the combustion chamber, the ignition device ignites the fuel in the combustion chamber, and the fuel generates energy toward the combustion chamber after inducing detonation in the first annular cavity. The thrust of the tail, the fuel detonates in the second annular cavity and generates thrust towards the rear of the combustion chamber. After the fuel detonates, it forms a low-speed stationary cyclone in the pit and generates thrust towards the end of the combustion chamber. Thrust at the end of the combustion chamber; The combustion chamber is also provided with: a feed assembly, which includes: a feed ring and an inclined tube; The feeding annular member is arranged on the outer wall of the combustion chamber near the tail of the combustion chamber; One end of the inclined tube is connected to the feeding annular member, and the other end is connected to the combustion chamber, so that the feeding annular member is connected to the tail of the combustion chamber through the inclined tube; The fuel supply annular component contains fuel, and the fuel supply annular component can replenish the fuel to the rear part of the combustion chamber through the inclined tube. 2. The rotating detonation engine according to claim 1, characterized in that the injection mechanism includes: a fuel nozzle and an injection cover; The injection cover is installed on the head of the fuel chamber, and an opening is provided on the injection cover; The fuel nozzle is connected to the opening provided on the injection cover; The fuel is injected from the fuel nozzle through the injection cover into the fuel chamber. 3. The rotary detonation engine according to claim 2, wherein the injection mechanism further includes: an oxidizer annular gap formed between the fuel nozzle and the opening; The oxidant annular gap injects high-pressure oxidant into the combustion chamber, and the high-pressure oxidant mixes with the fuel in the combustion chamber. 4. The rotating detonation engine according to claim 1, wherein the ignition device includes: a spark plug, a high-energy igniter or a plasma burner. 5. The rotary detonation engine according to claim 1, wherein the outer wall of the combustion chamber and the center column are both provided with a water-cooling interlayer, and water-cooling liquid is injected into the water-cooling interlayer; After the water-cooling liquid is injected into the water-cooling interlayer, the outer wall of the combustion chamber and the side wall of the center column are respectively water-cooled. 6. The rotary detonation engine according to claim 3, wherein the fuel nozzle includes: a pressure atomizing nozzle, a swirling atomizing nozzle or an impact atomizing nozzle. 7. A control method for a rotating detonation engine, the method being applied to the rotating detonation engine of claim 3, characterized in that the method includes: injecting the fuel from the fuel nozzle into the combustion chamber; The oxidant is controlled to be injected into the combustion chamber from the oxidant annular gap, and the fuel in the combustion chamber is sheared and mixed; wherein, the pressure at which the oxidant is injected into the combustion chamber is greater than the pressure at which the fuel enters the combustion chamber. pressure; Start the ignition device to detonate the fuel mixed with the oxidant in the combustion chamber. After the fuel is detonated, a low-speed stationary cyclone is formed in the pit on the side wall of the combustion chamber and a high-temperature gas film is formed; The fuel is injected into the rear part of the combustion chamber through the feeding ring, so that the fuel supplemented at the rear part is mixed with the fuel remaining after combustion in the head and middle part, and burned again. 8. A device with a rotating detonation engine, characterized in that it includes: the rotating detonation engine according to any one of the above claims 1-6.