Rotary detonation engine

Abstract

The utility model discloses a rotary detonation engine which is characterized in that the input end of a propellant storage box is connected with an end cover through a sealing connecting piece, and an isolation plate is arranged between the output end of the propellant storage box and a spray pipe and is connected with the output end of the propellant storage box through a sealing connecting piece; one end of the tail cone is connected with the isolation plate, and the other end of the tail cone extends into the spray pipe in the length direction of the spray pipe; the propellant storage box comprises an inner cavity and an outer cavity which are coaxially arranged and independently run, the inner cavity and the outer cavity are used as an oxygen-poor fuel-rich gas generation cavity and an oxygen-rich gas generation cavity respectively, and the combustion chamber, the inner cavity and the outer cavity are ignited and started by an igniter; and flow channels correspondingly communicating with the inner cavity and the outer cavity are formed in the isolation plate, so that oxygen-poor fuel-rich gas and oxygen-rich gas enter the combustion chamber to be mixed and detonated. The device has the advantages of being compact in structure, convenient to maintain, high in mixing efficiency and the like, pressure return can be restrained, combustion products are prevented from flowing back, and rotary detonation mechanism research can be conveniently and repeatedly carried out.

Description

Technical Field

[0001] This utility model belongs to the field of engine technology, specifically relating to a rotary detonation engine. Background Technology

[0002] Rotating detonation engines employ an annular combustion chamber. Propellant is injected from the closed end of the chamber, generating one or more detonation waves that rotate and propagate at the head of the chamber. Combustion products are expelled at high speed from the other end, thus generating thrust. The detonation combustion process approximates isochoric combustion and can achieve self-pressurization, resulting in high cycle efficiency. It is considered the most likely thermodynamic cycle to replace isobaric cycles as the next generation of engine technology. In the aerospace field, rotating detonation engines can operate in both rocket and ramjet modes. In the aviation field, they can be combined with turbine engines to form rotating detonation turbine engines, offering advantages such as high combustion speed, self-pressurization, self-sustaining operation, simple structure, and high efficiency.

[0003] Rotary detonation engines typically employ an annular combustion chamber, closed at one end and open at the other. Fuel and oxidizer are injected axially through numerous micro-nozzles evenly distributed on the closed end. One or more detonation waves, generated after ignition, propagate continuously in a circumferential rotation at the bottom of the combustion chamber in a direction perpendicular to the fuel injection, with an equivalent frequency of 1–50 kHz. When a detonation wave reaches a particular nozzle, the high pressure generated by the detonation exceeds the injection pressure, causing that nozzle to cease operation. After the detonation wave has propagated, the pressure decreases, allowing the nozzle to continue injecting fuel and oxidizer, further supporting the rotational propagation of the detonation wave. Thus, the injection of fuel and oxidizer can be automatically controlled by the detonation wave. The high-temperature, high-pressure combustion products rapidly expand rearward and are discharged at high speed from the open end, generating thrust.

[0004] Although the pressurized combustion of rotating detonation engines has many advantages over isobaric combustion, key technical issues such as fuel injection and mixing, detonation wave propagation control, and intake and exhaust system design still need to be resolved. Therefore, it is particularly important to deepen the understanding of the rotating detonation combustion mechanism and apply rotating detonation engines to practical applications through engineering methods. This necessitates the design of simple, practical, safe, and efficient experimental devices for rapidly and repeatedly conducting experimental research on the rotating detonation mechanism.

[0005] Meanwhile, current research on rotating detonation engines is mostly limited to gaseous fuels. Gaseous fuels suffer from low density and are inconvenient to carry, posing challenges for engineering applications. The efficient mixing of solid fuels with air is a key issue limiting the initiation and stable operation of rotating detonation engines, and it remains to be solved. However, solid powder fuels offer advantages such as high density, good stability, and ease of application. Therefore, solid powder fuels and solid powder oxidizers can be pre-mixed in specific proportions and stored in propellant tanks, facilitating easier experimental research and exploration of engineering applications for rotating detonation engines. Utility Model Content

[0006] The technical problem to be solved by this utility model is to overcome the shortcomings of the prior art and provide a rotary detonation engine that is compact in structure, easy to maintain, has high mixing efficiency, and is conducive to the study of rotary detonation mechanism.

[0007] To solve the above-mentioned technical problems, the present invention adopts the following technical solution:

[0008] A rotary detonation engine includes: an end cap, a propellant tank, a separator plate, a tail cone, a nozzle, seals, fasteners, a first igniter, a second igniter, and a third igniter; the input end of the propellant tank is connected and fixed to the end cap via seals and fasteners, and a separator plate is provided between the output end of the propellant tank and the nozzle; the propellant tank, separator plate, and nozzle are connected and fixed together via seals and fasteners; one end of the tail cone is connected and fixed to the separator plate, and the other end of the tail cone extends along the length of the nozzle. Extending into the nozzle, the tail cone forms an annular combustion chamber with the nozzle, which is ignited by a third igniter; the propellant tank includes an inner chamber and an outer chamber that are coaxially arranged and operate independently. The inner chamber serves as a chamber for generating oxygen-deficient and fuel-rich gases, which is ignited by a first igniter, and the outer chamber serves as a chamber for generating oxygen-rich gases, which is ignited by a second igniter; the isolation plate has flow channels that are respectively connected to the inner chamber and the outer chamber, so as to realize the mixing and ignition of oxygen-deficient and fuel-rich gases in the combustion chamber.

[0009] As a further improvement of this utility model, both ends of the propellant tank are provided with mounting flanges, the output end of the inner chamber is provided with an inner through hole, and the end face of the mounting flange connected to the inner through hole is provided with multiple first Tesla flow channels distributed in a ring. The inlet of the first Tesla flow channel is connected to the inner through hole to realize the unidirectional output of the oxygen-deficient and fuel-rich gas in the inner chamber. The side of the inner chamber is provided with a first igniter mounting hole; the output end of the outer chamber is provided with an outer through hole to realize the output of the oxygen-rich gas in the outer chamber. The side of the outer chamber is provided with a second igniter mounting hole.

[0010] As a further improvement of this utility model, an annular second mounting groove is provided on the outer side of the first Tesla flow channel. The second mounting groove is used to install a sealing element to achieve a sealed connection between the propellant tank and the isolation plate.

[0011] As a further improvement of this utility model, the center of the isolation plate is provided with a through-hole, and one end of the tail cone is provided with an end face step, which is nested in the through-hole to achieve connection and fixation between the tail cone and the isolation plate; the outer periphery of the through-hole is provided with an annular groove, a second annular boss and a through-hole, and the annular groove is provided with multiple through-holes in the inner ring; when the propellant tank is connected and fixed to the isolation plate, the inner ring through-hole is connected to the outlet of the first Tesla flow channel through the annular groove to achieve the delivery of oxygen-deficient and fuel-rich gas in the inner chamber to the combustion chamber; the second annular boss is embedded in the second mounting groove to press the seal; the outer ring through-hole is connected to the outer through-hole to achieve the delivery of oxygen-rich gas in the outer chamber to the combustion chamber, and the mixed gas is ignited and started by the third igniter.

[0012] As a further improvement of this utility model, a second Tesla flow channel is provided between the outer ring through hole and the outer through hole. After the propellant tank is connected and fixed to the isolation plate, the inlet of the second Tesla flow channel is connected to the outer through hole, and the outlet of the second Tesla flow channel is connected to the outer ring through hole, so as to realize the unidirectional transportation of oxygen-enriched gas.

[0013] As a further improvement of this utility model, the nozzle is a circular tube structure with openings at both ends. One end of the nozzle is provided with a mounting flange to connect and fix the nozzle to the propellant tank and the isolation plate. The other end of the nozzle has an outwardly expanding taper, and the side of the nozzle is provided with a third igniter mounting hole.

[0014] As a further improvement of this utility model, the nozzle mounting flange is provided with a fourth mounting groove and a fourth flange hole, and the isolation plate is provided with a third annular boss, a third mounting groove and a third flange hole, the third annular boss and the third mounting groove being located on two end faces of the isolation plate respectively; the mounting flanges at both ends of the propellant tank are provided with a first annular boss and a second flange hole; the fourth mounting groove and the third mounting groove are each provided with a sealing element; when the nozzle is connected and fixed to the propellant tank and the isolation plate, the fasteners pass through the second flange hole, the third flange hole and the fourth flange hole in sequence, the third annular boss is embedded in the fourth mounting groove and the first annular boss is embedded in the third mounting groove to achieve sealing element compression.

[0015] As a further improvement of this utility model, the end cap is provided with a first mounting groove and a first flange hole. A sealing element is provided in the first mounting groove. When the end cap is connected and fixed to the propellant tank, the fastener passes through the first flange hole and the second flange hole, and the first annular boss is embedded in the first mounting groove to achieve the sealing element being pressed.

[0016] As a further improvement of this utility model, a plurality of low-frequency pressure sensors are provided on the inner side of the end cap, and the pressure sensors are used to measure the gas pressure data in the inner chamber and the outer chamber respectively.

[0017] As a further improvement of this utility model, a plurality of high-frequency pressure sensors are arranged radially on the inner wall of the nozzle, and the high-frequency pressure sensors are used to measure the pressure data in the combustion chamber.

[0018] Compared with the prior art, the advantages of this utility model are:

[0019] The rotary detonation engine of this invention comprises an end cap, a propellant tank, a separator plate, a tail cone, a nozzle, an igniter, and sealing connectors, forming its main structure. Specifically, the input end of the propellant tank is connected and fixed to the end cap via sealing connectors, and a separator plate is provided between the output end of the propellant tank and the nozzle. The propellant tank, separator plate, and nozzle are connected and fixed together via sealing connectors. One end of the tail cone is nested and fixed to the separator plate, and the other end of the tail cone extends along the length of the nozzle into the nozzle, forming an annular combustion chamber between the tail cone and the nozzle. The propellant tank includes an inner chamber and an outer chamber that are coaxially arranged and operate independently. The inner chamber is used for oxygen-deficient combustion. The combustion chamber is a fuel-rich gas generating chamber, while the outer chamber is used as an oxygen-rich gas generating chamber. Propellants with different proportions undergo initial combustion and self-pressurization in the oxygen-deficient and fuel-rich gas generating chambers via igniters. The isolation plate has flow channels that connect to the inner and outer chambers respectively, so as to allow the oxygen-deficient and fuel-rich gases to enter the detonation combustion chamber independently, mix, and be ignited by the igniter. The rotary detonation engine of this invention has the advantages of compact structure, easy maintenance, and high mixing efficiency. It can suppress pressure backflow and prevent combustion product backflow, enabling convenient and repeated research on the rotary detonation mechanism. It supports the exploration of detonation wave propagation modes, detonation wave stability, and pressure backflow suppression. Attached Figure Description

[0020] Figure 1 This is a three-dimensional structural principle diagram of the rotary detonation engine in a specific embodiment of this utility model;

[0021] Figure 2 This is a schematic diagram of the cross-sectional structure of the rotary detonation engine in a specific embodiment of this utility model;

[0022] Figure 3 This is a schematic diagram of the main structural principle of the end cap in a specific embodiment of the present utility model;

[0023] Figure 4 for Figure 3 Schematic diagram of the structural principle of the cross-section along the AA direction;

[0024] Figure 5 This is a schematic diagram of the main structural principle of the propellant storage tank in a specific embodiment of this utility model;

[0025] Figure 6 for Figure 5 Schematic diagram of the structural principle of the sectional view along the BB direction;

[0026] Figure 7 This is a top view schematic diagram of the propellant storage tank in a specific embodiment of the present invention.

[0027] Figure 8 This is a schematic diagram of the main structural principle of the chamber isolation plate in a specific embodiment of this utility model;

[0028] Figure 9 for Figure 8 Schematic diagram of the cross-sectional structure in the DD direction;

[0029] Figure 10 This is a schematic diagram of the cross-sectional structure of the coccyx in a specific embodiment of this utility model;

[0030] Figure 11 This is a schematic diagram of the main structural principle of the nozzle in a specific embodiment of this utility model;

[0031] Figure 12 for Figure 11 A schematic diagram of the cross-sectional structure along the EE direction;

[0032] Figure 13 This is a schematic diagram of the ignition process of the rotary detonation engine in a specific embodiment of this utility model;

[0033] Figure 14 This is a schematic diagram illustrating the principle of using a Tesla flow channel to suppress pressure back transmission in a specific embodiment of the rotating detonation engine of this utility model;

[0034] Figure 15 This is a schematic diagram illustrating the principle of using solid powder propellant in the rotary detonation engine in a specific embodiment of this utility model.

[0035] Legend: 1. End cap; 11. First mounting groove; 12. First flange hole; 2. Propellant tank; 21. Inner chamber; 22. Outer chamber; 23. Inner through hole; 24. First Tesla flow channel; 25. Outer through hole; 26. First annular boss; 27. Second mounting groove; 28. Second flange hole; 29. ​​First igniter mounting hole; 210. Second igniter mounting hole; 3. Isolation plate; 31. Countersunk through hole; 32. Second annular boss; 33. Ring 34. Inner ring through hole; 35. Second Tesla flow channel; 36. Outer ring through hole; 37. Third annular boss; 38. Third mounting groove; 39. Third flange hole; 4. Tail cone; 41. End face step; 42. Blind hole; 5. Nozzle; 51. Combustion chamber; 52. Fourth mounting groove; 53. Fourth flange hole; 54. Third igniter mounting hole; 6. Seal; 7. Fastener; 8. First igniter; 9. Second igniter; 10. Third igniter. Detailed Implementation

[0036] The embodiments of this utility model are described in detail below, examples of which are shown in the accompanying drawings, wherein the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The following description is based on the accompanying drawings. Figures 1-15 The described embodiments are exemplary and intended to explain the present invention, and should not be construed as limiting the present invention.

[0037] In the description of this utility model, it should be understood that the terms "length", "width", "upper", "lower", "left", "right", "front", "rear", "vertical", "horizontal", "top", "bottom", "inner", "outer", 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 utility model 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 utility model.

[0038] 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 utility model, "a plurality of" means two or more, unless otherwise explicitly specified.

[0039] In this utility model, unless otherwise explicitly specified and limited, the terms "installation," "connection," "joining," "fixing," and "embedding," etc., should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral part; 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; they can refer to the internal communication of two components or the interaction between two components. Those skilled in the art can understand the specific meaning of the above terms in this utility model according to the specific circumstances.

[0040] Example

[0041] like Figures 1 to 15 As shown, the rotary detonation engine of this invention is mainly used for research and exploration of the mechanism of rotary detonation engines. The rotary detonation engine includes: an end cap 1, a propellant tank 2, a separator plate 3, a tail cone 4, a nozzle 5, a seal 6, fasteners 7, a first igniter 8, a second igniter 9, and a third igniter 10. The input end of the propellant tank 2 is connected and fixed to the end cap 1 via the seal 6 and fasteners 7. A separator plate 3 is provided between the output end of the propellant tank 2 and the nozzle 5. The propellant tank 2, the separator plate 3, and the nozzle 5 are connected and fixed together via the seal 6 and fasteners 7. One end of the tail cone 4 is connected and fixed to the separator plate 3, and the other end of the tail cone 4 extends along the length of the nozzle 5 inside the nozzle 5. An annular combustion chamber 51 is formed between the tail cone 4 and the nozzle 5. The third igniter 10 is connected to the annular combustion chamber 51 through a third igniter mounting hole 54. The propellant tank 2 includes an inner chamber 21 and an outer chamber 22, which are coaxially arranged and operate independently. The annular outer chamber 22 is nested around the outer periphery of the inner chamber 21. In this embodiment, solid powder fuel and solid powder oxidizer are used. The solid powder fuel and solid powder oxidizer are premixed in different proportions and then loaded into the inner chamber 21 and the outer chamber 22 respectively. The inner chamber 21 serves as the oxygen-deficient and fuel-rich gas generation chamber, and the outer chamber 22 serves as the oxygen-rich gas generation chamber. The partition plate 3 is provided with flow channels corresponding to and communicating with the inner chamber 21 and the outer chamber 22 respectively, so as to realize the mixing and ignition of the oxygen-deficient and fuel-rich gas into the combustion chamber 51. Specifically, the annular combustion chamber 51 allows the oxygen-deficient and fuel-rich gas to flow, mix, and undergo detonation combustion.

[0042] In this embodiment, coaxial and independently operating inner chamber 21 and outer chamber 22 are provided in the propellant tank 2. The inner chamber 21 serves as an oxygen-deficient and fuel-rich gas generation chamber, on which a first igniter 8 is installed. The outer chamber 22 serves as an oxygen-rich gas generation chamber, on which a second igniter 9 is installed. Propellants with different proportions undergo initial combustion and self-pressurization in the oxygen-deficient and fuel-rich gas generation chambers. By providing flow channels in the isolation plate 3 that are respectively connected to the inner chamber 21 and the outer chamber 22, the oxygen-deficient and fuel-rich gases can be independently introduced into the combustion chamber 51 for mixing and detonation. The rotary detonation engine of this utility model has the advantages of compact structure, easy maintenance, and high mixing efficiency. It can suppress pressure backflow and prevent combustion product backflow, enabling convenient and repeated research on the rotary detonation mechanism. It supports the exploration of detonation wave propagation mode, detonation wave stability, and pressure backflow suppression.

[0043] like Figures 5 to 7 As shown, in this embodiment, both ends of the propellant tank 2 are provided with mounting flanges to facilitate the connection and fixation of the propellant tank 2 with the end cap 1, the isolation plate 3, and the nozzle 5. The output end of the inner chamber 21 is provided with an inner through hole 23. The mounting flange end face connected to the inner through hole 23 is provided with multiple annularly distributed first Tesla flow channels 24. The inlet of the first Tesla flow channel 24 is connected to the inner through hole 23 to realize the unidirectional output of the oxygen-deficient and fuel-rich gas in the inner chamber 21. The side of the inner chamber 21 is provided with a first igniter mounting hole 29 for installing a first igniter 8. The output end of the outer chamber 22 is provided with an outer through hole 25 to realize the output of the oxygen-rich gas in the outer chamber 22. The side of the outer chamber 22 is provided with a second igniter mounting hole 210 for installing a second igniter 9.

[0044] like Figure 2 and Figure 10 As shown, the end of the tail vertebra 4 is provided with a blind hole 42, which corresponds to the inner through hole 23. The oxygen-deficient and fuel-rich gas in the inner chamber 21 can be buffered in the blind hole 42 and then output to the combustion chamber 51 through the first Tesla flow channel 24.

[0045] In this embodiment, an annular second mounting groove 27 is provided on the outer side of the first Tesla flow channel 24. The second mounting groove 27 is used to install the seal 6 to achieve a sealed connection between the propellant tank 2 and the isolation plate 3.

[0046] like Figure 8 and Figure 9As shown, the center of the isolation plate 3 has a through-hole 31, and one end of the tail cone 4 has an end face step 42, which is nested in the through-hole 31 to connect and fix the tail cone 4 to the isolation plate 3. The outer periphery of the through-hole 31 has an annular groove 33, a second annular boss 32, and a through-hole 36. The annular groove 33 has multiple through-holes 34 evenly distributed in it. After the propellant tank 2 is connected and fixed to the isolation plate 3, the through-hole 34 is connected to the outlet of the first Tesla flow channel 24 through the annular groove 33 to transport the oxygen-deficient and fuel-rich gas in the inner chamber 21 to the combustion chamber 51. The second annular boss 32 is embedded in the second mounting groove 27 to press the seal 6. The through-hole 36 is connected to the outer through-hole 25 to transport the oxygen-rich gas in the outer chamber 22 to the combustion chamber 51.

[0047] Furthermore, a second Tesla flow channel 35 is provided between the outer ring through hole 36 and the outer ring through hole 25. After the propellant tank 2 is connected and fixed to the isolation plate 3, the inlet of the second Tesla flow channel 35 is connected to the outer ring through hole 25, and the outlet of the second Tesla flow channel 35 is connected to the outer ring through hole 36, so as to realize the unidirectional transportation of oxygen-enriched gas.

[0048] In this embodiment, Tesla channels are provided in both the oxygen-deficient and oxygen-rich gas flow channels to suppress pressure backflow and prevent combustion product backflow by utilizing the unidirectional flow characteristics of the Tesla channels.

[0049] like Figure 11 and Figure 12 As shown, in this embodiment, the nozzle 5 is a circular tube structure with openings at both ends. One end of the nozzle 5 is provided with a mounting flange to connect and fix the nozzle 5 to the propellant tank 2 and the isolation plate 3. The other end of the nozzle 5 has an outwardly expanding taper, and the side of the nozzle 5 is provided with a third igniter mounting hole 54.

[0050] In this embodiment, the nozzle 5 has a fourth mounting groove 52 and a fourth flange hole 53 on its mounting flange, and the isolation plate 3 has a third annular boss 37, a third mounting groove 38, and a third flange hole 39 on its isolation plate 3. The third annular boss 37 and the third mounting groove 38 are located on the two end faces of the isolation plate 3, respectively. The mounting flanges at both ends of the propellant tank 2 are provided with a first annular boss 26 and a second flange hole 28. The fourth mounting groove 52 and the third mounting groove 38 are both provided with sealing elements 6. When the nozzle 5 is connected and fixed to the propellant tank 2 and the isolation plate 3, the fastener 7 passes through the second flange hole 28, the third flange hole 39, and the fourth flange hole 53 in sequence. The third annular boss 37 is embedded in the fourth mounting groove 52, and the first annular boss 26 is embedded in the third mounting groove 38 to achieve the sealing element 6 being pressed. The third igniter 10 is installed in the third igniter mounting hole 54.

[0051] like Figure 3 and Figure 4As shown, in this embodiment, the end cap 1 is provided with a first mounting groove 11 and a first flange hole 12. The first mounting groove 11 is provided with a sealing element 6. When the end cap 1 is connected and fixed to the propellant storage tank 2, the fastener 7 passes through the first flange hole 12 and the second flange hole 28. The first annular boss 26 is embedded in the first mounting groove 11 to achieve the sealing element 6 being pressed.

[0052] In this embodiment, the first igniter 8 and the second igniter 9 extend into the inner chamber 21 and outer chamber 22 of the propellant tank 2, respectively, to achieve ignition during the test.

[0053] In this embodiment, multiple low-frequency pressure sensors (not shown in the figure) are provided on the inner side of the end cap 1. The pressure sensors are used to measure the gas pressure data in the inner chamber 21 and the outer chamber 22, respectively. The gas pressure data can be used for the study of the rotational detonation mechanism.

[0054] In this embodiment, the end cap 1, propellant tank 2, separator plate 3, tail cone 4, nozzle 5, and fastener 7 are all made of 304 stainless steel, and the seal 6 is made of nitrile material. In other embodiments, the seal 6 can also be made of tetrafluoroethylene, silicone rubber, or copper, and can be flexibly selected according to the ambient temperature and sealing requirements.

[0055] In this embodiment, multiple high-frequency pressure sensors (not shown in the figure) are arranged radially on the inner wall of the nozzle 5. The high-frequency pressure sensors are used to measure the pressure data in the combustion chamber 51. The combustion chamber pressure data can be used for the analysis of the propagation and stability of the rotating detonation wave.

[0056] In this embodiment, the end cap 1 and the propellant tank 2 are connected by eight sets of M14 high-strength fasteners 7, enabling repeatable and convenient propellant loading to support rapid and repeated testing. The propellant tank 2, the isolation plate 3, and the nozzle 5 are connected by eight sets of M14 high-strength fasteners 7, facilitating disassembly for cleaning and maintenance of the internal flow channels.

[0057] Specifically, the propellant tank 2, the isolation plate 3, and the nozzle 5 are locked and fixed by fasteners 7. At this time, an annular combustion chamber 51 is formed between the inner wall of the nozzle 5 and the tail cone 4. Propellants with different ratios are placed into the inner chamber 21 and the outer chamber 22 of the propellant tank 2, and sealed with end caps 1. The propellant is ignited by an ignition device to generate gas with a certain pressure. The oxygen-deficient and gas-rich gas in the inner chamber 21 enters the combustion chamber 51 in sequence through the inner through hole 23, the first Tesla flow channel 24, and the inner ring through hole 34. The oxygen-rich gas in the outer chamber 22 enters the combustion chamber 51 in sequence through the outer through hole 25, the second Tesla flow channel 35, and the outer ring through hole 36. The oxygen-deficient and gas-rich gas mix in the combustion chamber 51 and are ignited by the third igniter 10.

[0058] like Figure 13As shown, in this embodiment, the basic working process of the ignition control of the rotary detonation engine is as follows: Based on the designed timing sequence, the first igniter 8 is activated to ignite the propellant in the inner chamber 21, and the second igniter 9 is activated to ignite the propellant in the outer chamber 22, generating oxygen-deficient and oxygen-enriched combustion gases respectively. These gases then enter the combustion chamber 51 for mixing. Depending on different operating conditions, the oxygen-deficient and oxygen-enriched gases can undergo automatic secondary combustion or be ignited again by activating the third igniter 10.

[0059] In this embodiment, the first igniter 8 and the second igniter 9 can be selected according to the type of propellant in the inner chamber 21 and the type of propellant in the outer chamber 22 (liquid propellant, solid propellant, powder propellant, etc.), such as a pyrotechnic igniter that can be ignited once or a spark plug igniter that can be ignited repeatedly.

[0060] The third igniter 10 can be a spark plug igniter with repeated continuous ignition to achieve repeated continuous ignition of the combustion chamber 51, so as to realize and control the generation of knock.

[0061] like Figure 14 As shown, the oxygen-deficient and oxygen-enriched combustion gases mix and detonate in the combustion chamber 51 of the detonation engine, instantly generating a high-pressure gas flow. The pressure of this high-pressure gas flow is higher than that of the oxygen-deficient and oxygen-enriched gas in the inner chamber 21 and the oxygen-enriched gas in the outer chamber 22. In this embodiment, the inner chamber 21 and the combustion chamber 51 are connected by a first Tesla flow channel 24, and the outer chamber 22 and the combustion chamber 51 are connected by a second Tesla flow channel 35. The first Tesla flow channel 24 and the second Tesla flow channel 35 have the characteristic of "one-way flow," which can achieve the following: the resistance of the oxygen-deficient and oxygen-enriched gas in the inner chamber 21 flowing into the combustion chamber 51 is small, and the resistance of the oxygen-enriched gas in the outer chamber 22 flowing into the combustion chamber 51 is small, while the resistance of the high-pressure gas flow generated during detonation combustion in the combustion chamber 51 flowing into the inner chamber 21 or the outer chamber 22 is large. This suppresses pressure backflow and prevents combustion product backflow, allowing the detonation engine to operate stably and reliably.

[0062] Preferred, such as Figure 15 As shown, both the inner chamber 21 and the outer chamber 22 are filled with solid powder propellant. The first igniter 8 and the second igniter 9 are single-use pyrotechnic igniters. This can effectively solve the following problems: Current research on rotating detonation engines is mostly limited to gaseous fuels. Gaseous fuels have low density and are inconvenient to carry for engineering applications. The efficient mixing of solid fuels with air directly will be a key issue limiting the initiation and stable operation of rotating detonation engines.

[0063] Specifically, solid powder propellants have advantages such as high density, good stability, and convenient application. Solid powder fuel and solid powder oxidizer can be pre-mixed in proportion and filled into the inner chamber 21 and the outer chamber 22 respectively. After the first igniter 8 and the second igniter 9 are ignited, the oxygen-deficient and fuel-rich gas in the inner chamber 21 and the oxygen-rich gas in the outer chamber 22 are both in gaseous state. They can be mixed more efficiently in the combustion chamber 51, providing a good foundation for the initiation and stable operation of the rotating detonation engine, thereby supporting the convenient exploration of rotating detonation engine test research and engineering applications.

[0064] While the present invention has been disclosed above with reference to preferred embodiments, it is not intended to limit the present invention. Any person skilled in the art can make many possible variations and modifications to the technical solutions of the present invention, or modify them into equivalent embodiments, without departing from the spirit and technical essence of the present invention. Therefore, any simple modifications, equivalent substitutions, equivalent changes, and modifications made to the above embodiments based on the technical essence of the present invention, without departing from the content of the technical solutions of the present invention, shall still fall within the protection scope of the present invention.

Claims

1. A rotary detonation engine, characterized in that, include: End cap (1), propellant tank (2), isolation plate (3), tail cone (4), nozzle (5), seal (6), fastener (7), first igniter (8), second igniter (9), and third igniter (10); the input end of the propellant tank (2) is connected and fixed to the end cap (1) through the seal (6) and fastener (7), and the output end of the propellant tank (2) is provided with an isolation plate (3) between it and the nozzle (5). The propellant tank (2), isolation plate (3), and nozzle (5) are connected and fixed together through the seal (6) and fastener (7); one end of the tail cone (4) is connected and fixed to the isolation plate (3), and the other end of the tail cone (4) runs along the nozzle (5). The length of the tail cone (4) extends inside the nozzle (5), and an annular combustion chamber (51) is formed between the tail cone (4) and the nozzle (5), which is ignited by the third igniter (10); the propellant tank (2) includes an inner chamber (21) and an outer chamber (22) that are coaxially arranged and operate independently. The inner chamber (21) is used as a gas-generating chamber for oxygen-deficient and gas-rich combustion, which is ignited by the first igniter (8). The outer chamber (22) is used as a gas-generating chamber for oxygen-rich combustion, which is ignited by the second igniter (9); the isolation plate (3) is provided with flow channels that are respectively connected to the inner chamber (21) and the outer chamber (22) to realize the mixing and ignition of oxygen-deficient and gas-rich combustion in the combustion chamber (51).

2. The rotary detonation engine according to claim 1, characterized in that, Both ends of the propellant tank (2) are provided with mounting flanges. The output end of the inner chamber (21) is provided with an inner through hole (23). The mounting flange end face connected to the inner through hole (23) is provided with multiple first Tesla flow channels (24) distributed in a ring. The inlet of the first Tesla flow channel (24) is connected to the inner through hole (23) to realize the unidirectional output of the oxygen-deficient and fuel-rich gas in the inner chamber (21). The side of the inner chamber (21) is provided with a first igniter mounting hole (29). The output end of the outer chamber (22) is provided with an outer through hole (25) to realize the output of the oxygen-rich gas in the outer chamber (22). The side of the outer chamber (22) is provided with a second igniter mounting hole (210).

3. The rotary detonation engine according to claim 2, characterized in that, The first Tesla channel (24) has an annular second mounting groove (27) on its outer side. The second mounting groove (27) is used to install a seal (6) to achieve a sealed connection between the propellant tank (2) and the isolation plate (3).

4. The rotary detonation engine according to claim 3, characterized in that, The center of the isolation plate (3) is provided with a through-hole (31), and one end of the tail cone (4) is provided with an end face step (42). The end face step (42) is nested in the through-hole (31) to achieve connection and fixation between the tail cone (4) and the isolation plate (3). The outer periphery of the through-hole (31) is provided with an annular groove (33), a second annular boss (32) and a through outer ring through hole (36). The annular groove (33) is provided with multiple through inner ring through holes (34). When the propellant tank (2) and the isolation plate (3) are connected, the propellant tank (2) and the isolation plate (3) are connected. 3) After the connection is fixed, the inner ring through hole (34) is connected to the outlet of the first Tesla flow channel (24) through the annular groove (33) to realize the oxygen-deficient and fuel-rich gas in the inner chamber (21) to be transported to the combustion chamber (51); the second annular boss (32) is embedded in the second mounting groove (27) to press the seal (6); the outer ring through hole (36) is connected to the outer through hole (25) to realize the oxygen-rich gas in the outer chamber (22) to be transported to the combustion chamber (51), and the mixed gas is ignited and started by the third igniter (10).

5. The rotary detonation engine according to claim 4, characterized in that, A second Tesla flow channel (35) is provided between the outer ring through hole (36) and the outer through hole (25). When the propellant tank (2) is connected and fixed to the isolation plate (3), the inlet of the second Tesla flow channel (35) is connected to the outer through hole (25), and the outlet of the second Tesla flow channel (35) is connected to the outer ring through hole (36) to realize the unidirectional transportation of oxygen-enriched gas.

6. The rotary detonation engine according to claim 4, characterized in that, The nozzle (5) is a round tube structure with openings at both ends. One end of the nozzle (5) is provided with a mounting flange to connect and fix the nozzle (5) to the propellant tank (2) and the isolation plate (3). The other end of the nozzle (5) has an outwardly expanding taper. The side of the nozzle (5) is provided with a third igniter mounting hole (54).

7. The rotary detonation engine according to claim 6, characterized in that, The nozzle (5) has a fourth mounting groove (52) and a fourth flange hole (53) on its mounting flange. The isolation plate (3) has a third annular boss (37), a third mounting groove (38) and a third flange hole (39). The third annular boss (37) and the third mounting groove (38) are located on the two end faces of the isolation plate (3), respectively. The propellant tank (2) has a first annular boss (26) and a second flange hole (28) on its mounting flanges at both ends. The fourth mounting groove (52) and the third mounting groove (38) are both equipped with sealing elements (6). When the nozzle (5) is connected and fixed to the propellant tank (2) and the isolation plate (3), the fastener (7) passes through the second flange hole (28), the third flange hole (39) and the fourth flange hole (53) in sequence. The third annular boss (37) is embedded in the fourth mounting groove (52) and the first annular boss (26) is embedded in the third mounting groove (38) to achieve the sealing element (6) pressing.

8. The rotary detonation engine according to claim 7, characterized in that, The end cap (1) is provided with a first mounting groove (11) and a first flange hole (12). A sealing element (6) is provided in the first mounting groove (11). When the end cap (1) is connected and fixed to the propellant tank (2), the fastener (7) passes through the first flange hole (12) and the second flange hole (28). The first annular boss (26) is embedded in the first mounting groove (11) to achieve the sealing element (6) being pressed.

9. The rotary detonation engine according to any one of claims 1 to 8, characterized in that, Multiple low-frequency pressure sensors are provided on the inner side of the end cap (1). The pressure sensors are used to measure the gas pressure data in the inner chamber (21) and the outer chamber (22), respectively.

10. The rotary detonation engine according to any one of claims 1 to 8, characterized in that, Multiple high-frequency pressure sensors are arranged radially on the inner wall of the nozzle (5), and the high-frequency pressure sensors are used to measure the pressure data in the combustion chamber (51).

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