A dual-channel rotating detonation combustor structure with inlet total pressure regulation function

Abstract

The application relates to a double-channel rotating detonation combustion chamber structure with an inlet total pressure adjusting function, which comprises a Tesla valve arranged at the inlet of the rotating detonation combustion chamber, the Tesla valve comprises a shell and a flow channel, the inlet end and the outlet end of the flow channel are respectively provided with pressure adjusting structures, the radial outer side of the flow channel is provided with an injection channel, the injection channel comprises an air outlet channel and a pressurizing channel communicated with the air outlet channel, and the side, away from the pressurizing channel, of the air outlet channel is provided with an opening and closing assembly for opening or closing the air outlet channel, the opening and closing assembly comprises a supporting plate, a plurality of opening and closing doors and a self-locking driving part, and the self-locking driving part is used for synchronously driving the plurality of opening and closing doors to be close to or away from the outlet side of the air outlet channel. The application has the effects that when the rotating detonation combustion chamber is in an air thin belt, the air intake of the air inlet channel is automatically enhanced, the rotating detonation combustion chamber preferentially intakes the air in the air inlet channel, the air supply of the combustion chamber is ensured, and the adaptability and stability of the combustion chamber in different environments are improved.

Description

Technical Field

[0001] This application relates to the field of aero engines, and in particular to a dual-channel rotary detonation combustor structure with inlet total pressure regulation function. Background Technology

[0002] Detonation combustion is achieved by compressing an explosive mixture with a leading shock wave, causing a high-speed chemical reaction. Due to its advantages such as high heat release per unit time, self-pressurization, high combustion efficiency, and low pollutant emissions, detonation-based propulsion technology is an important future trend in space technology. A rotating detonation combustor is an annular combustor that utilizes detonation combustion, with fuel supplied by multiple nozzles at the combustor head.

[0003] like Figure 1 As shown, in the related technology, the rotary detonation combustion chamber flow channel pressure regulating structure includes an air intake end 2 for communicating with the combustion chamber body 1 and disposed at the inlet of the combustion chamber body 1. The air intake end 2 includes an inner wall 21 and an outer wall 22 coaxially sleeved. An air intake channel 23 for fuel and air to enter the combustion chamber body 1 is left between the inner wall 21 and the outer wall 22. The air intake channel 23 includes a direct flow channel 231 and an expansion flow channel 232 connected together. One end of the direct flow channel 231 is connected to the air intake end and the other end is connected to the expansion flow channel 232. The other end of the expansion flow channel 232 is connected to the combustion chamber body 1, i.e., a convergent-expansion air intake scheme.

[0004] Regarding the aforementioned technologies, the inventors believe that existing rotary detonation combustion chambers suffer from pressure backflow, resulting in significant total pressure loss in the combustion chamber. Summary of the Invention

[0005] To address the issue of significant total pressure loss in the combustion chamber caused by pressure backflow, this application provides a dual-channel rotary detonation combustion chamber structure with inlet total pressure regulation function.

[0006] The dual-channel rotary detonation combustion chamber structure with inlet total pressure regulation function provided in this application adopts the following technical solution:

[0007] A dual-channel rotary detonation combustor structure with inlet total pressure regulation function includes a Tesla valve communicating with the rotary detonation combustor and disposed at the inlet of the rotary detonation combustor. The Tesla valve includes a housing and a flow channel. The housing is coaxially connected to the outer wall of the rotary detonation combustor. The flow channel is coaxially disposed within the housing. The inlet end of the flow channel is used to introduce air, and the outlet end of the flow channel is connected to the annular channel of the rotary detonation combustor.

[0008] Both the inlet and outlet ends of the flow channel are provided with pressure regulating structures. The pressure regulating structures include a gas collecting chamber and an air inlet for connecting the gas collecting chamber and the flow channel. An ejector channel is provided on the radially outer side of the flow channel. The outlet of the ejector channel is connected to the outlet of the rotating detonation combustion chamber, and the outlet of the ejector channel faces away from the inlet of the flow channel. The ejector channel is connected to the gas collecting chamber.

[0009] By adopting the above technical solution, and utilizing the unidirectional flow characteristic of the Tesla valve, the forward channel for air and fuel to enter the rotary detonation combustion chamber is separated from the reverse channel for pressure return and combustion product return. This effectively reduces the obstruction of the forward-entering air and fuel by pressure return and combustion product return, allowing the detonation pressurization to compensate for the total pressure loss generated by the upper intake, thereby increasing the total pressure gain of the rotary detonation combustion chamber. At the same time, it avoids the high temperature of the combustion product return from prematurely igniting the reactants, thus reducing the impact of the combustion product return on the performance of the rotary detonation combustion chamber. Furthermore, the Tesla valve has no moving parts and does not require energy input to achieve unidirectional airflow. Its forward and reverse flows are significantly different, and it does not require internal mechanical movement. It only uses the spatial structure to drive the gas flow and accelerates the gas through the physical structure.

[0010] When air is supplied through air supply equipment such as compressors and turbines, the input air pressure is defined as the incoming flow pressure. However, after rotational detonation occurs, if air needs to continue to be supplied, the incoming flow pressure needs to be increased, which means that the output air pressure of the air supply equipment needs to be increased. This results in a mismatch between the original design parameters of the air supply equipment and the detonation combustion chamber.

[0011] A pressure regulating structure is added at the outlet end of the flow channel, i.e., an impedance wall is added at the outlet end of the flow channel. When the pressure wave generated by the rotary detonation returns to the outlet of the flow channel, due to the cavity effect, the high-pressure air returning enters the gas collection chamber through the air inlet. With this setting, only a slight increase in the incoming flow pressure or no adjustment of the incoming flow pressure is needed to meet the gas supply requirements, making it easy for the gas supply equipment to be directly matched with the detonation combustion chamber.

[0012] During a rotating detonation within the annular channel, the explosive mixture aligned with the detonation wave axis within the channel is difficult to enter due to the immense pressure generated by the detonation wave. Similarly, high-pressure air is also difficult to input. By adding a pressure regulating structure at the inlet end of the channel, the high-pressure air can enter the gas collection chamber at the inlet end of the channel through the air inlet hole of the pressure regulating structure.

[0013] High-pressure air from each gas collecting chamber is collected in the ejector channel and ejected from it. Since the outlet of the ejector channel faces away from the inlet of the flow channel, the high-pressure air ejected from the ejector channel provides propulsion. Because the outlet of the ejector channel is connected to the outlet of the rotary detonation combustion chamber, the ejected high-pressure air reduces the gas pressure at the outlet of the rotary detonation combustion chamber, thereby increasing the pressure difference between the incoming pressure and the gas pressure at the outlet of the rotary detonation combustion chamber. This design increases the intake velocity of the annular channel, which firstly improves the mixing effect of air and fuel, secondly facilitates the entry of the explosive mixture of air and fuel into the annular channel for rotary detonation, and thirdly allows for continuous intake of air into the gas collecting chamber, utilizing the high-pressure air in the gas collecting chamber and improving the utilization rate of high-pressure air.

[0014] Optionally, the ejector channel includes an exhaust channel connected to the outlet of the rotating detonation combustion chamber and a pressurization channel connected to the exhaust channel. The cross-sectional area of ​​the pressurization channel decreases along the arrangement direction from the pressurization channel to the exhaust channel. Furthermore, an opening and closing component for opening or closing the exhaust channel is provided on the side of the exhaust channel away from the pressurization channel.

[0015] By adopting the above technical solution, the air in the ejector channel is transported to the exhaust channel through the pressurization channel during the transmission process, and finally ejected from the exhaust channel. Since the cross-sectional area of ​​the pressurization channel decreases along the direction from the pressurization channel to the exhaust channel, the air velocity passing through the pressurization channel is increased, thereby increasing the air velocity ejected from the ejector channel outlet. This enhances the propulsion effect and further increases the pressure difference between the incoming flow pressure and the air pressure at the outlet of the rotary detonation combustion chamber, thus improving the mixing effect and the supply rate of the explosive mixture. As altitude increases, the air gradually thins. Because atmospheric pressure decreases with altitude, the distance between air molecules increases. When in a thin-air zone, the opening and closing components close, reducing the air intake in the ejector channel and enhancing the air intake in the intake channel. This allows the rotary detonation combustion chamber to preferentially intake air from the intake channel, ensuring air supply to the combustion chamber and improving the adaptability and stability of the combustion chamber in different environments.

[0016] Optionally, the opening / closing component includes:

[0017] The support plate is fixed on the side of the air outlet channel away from the pressurization channel;

[0018] The opening and closing doors are slidably connected to the support plate, and multiple doors are provided. When multiple opening and closing doors are closed, they are arranged in a ring to seal the air outlet channel.

[0019] The self-locking drive component is located between the support plate and the opening and closing door, and is used to synchronously drive multiple opening and closing doors to move closer to or away from the outlet side of the air passage.

[0020] By adopting the above technical solution, when it is necessary to open the exhaust passage, the self-locking drive component moves the opening and closing door away from the exhaust passage outlet, thus opening the exhaust passage; when it is necessary to close the exhaust passage, the self-locking drive component moves multiple opening and closing doors closer to the exhaust passage outlet. When the opening and closing doors are closed, they form a ring shape, thereby completely sealing the exhaust passage and preventing air from flowing out. In high-altitude or thin-air environments, the control of the opening and closing components can reduce the air entering the ejector channel and prioritize the intake of air in the intake channel, ensuring the stable operation of the combustion chamber under different environmental conditions.

[0021] Optionally, the self-locking drive component includes:

[0022] A drive rack is slidably connected to a support plate. Multiple racks are provided, each corresponding to a different door. The drive rack is fixedly connected to the corresponding drive gear.

[0023] Driven gears are rotatably connected to the support plate. Multiple driven gears are provided, and each drive gear corresponds to one of the multiple drive racks. The driven gears and the corresponding drive racks mesh with each other.

[0024] The drive gear ring is rotatably connected to the support plate and meshes with multiple drive gears;

[0025] A drive shaft rotates to a support plate, on which a drive gear and a worm gear are fixedly sleeved, and the drive gear meshes with the drive gear ring.

[0026] A worm gear, rotatably connected to a support plate and meshing with a worm wheel, is also provided with a drive motor at one end of the worm gear; it also includes:

[0027] A gas flow rate sensor is installed in the gas outlet channel to detect the gas flow rate in the gas outlet channel and send out a gas flow rate detection signal.

[0028] The controller, connected to the gas flow rate sensor and the drive motor, is used to receive the gas flow rate detection signal to know the gas flow rate in the outlet channel. When the gas flow rate is lower than the preset flow rate, it sends a control signal to the drive motor to make the drive motor close the outlet channel.

[0029] By adopting the above technical solution, when the gas velocity sensor detects that the gas velocity in the outlet channel is lower than the preset velocity, it sends a gas velocity detection signal to the controller. After receiving the signal, the controller determines whether the gas velocity is lower than the preset value. If it is lower than the preset value, the controller sends a control signal to the drive motor. After receiving the control signal from the controller, the drive motor starts, driving the worm and worm wheel to rotate. The worm wheel drives the drive shaft to rotate, and the drive shaft drives the drive gear and drive gear ring to rotate. The drive gear ring synchronously drives multiple drive gears to rotate. Each driven gear meshes with the corresponding drive rack. The rotation of the drive gear will drive the drive rack and the opening / closing door fixedly connected to it to move synchronously, thereby realizing the opening or closing of the outlet channel. The self-locking drive component has a self-locking function, which can keep the opening / closing door in a stable open or closed state for a long time, even when the drive motor stops working or there is no power input, thus improving the safety of the system. At the same time, in conjunction with the gas velocity sensor and the controller, the pressure regulating structure can quickly respond to changes in gas velocity and adjust the position of the opening / closing door in a timely manner to ensure the stability of the airflow inside the combustion chamber.

[0030] Optionally, the flow channel includes an intake channel, a connecting channel, an arc-shaped return channel, and an expansion channel; one end of the intake channel is used to introduce air, and the other end is connected to the connecting channel; the arc-shaped return channel includes an arc-shaped channel and a straight channel; the straight channel is linearly connected to the connecting channel; the arc-shaped channel is used to connect the straight channel and the intake channel; the angle between the intake channel and the straight channel is an acute angle; the expansion channel is linearly connected to the connecting channel; and the smaller end of the expansion channel is connected to the end of the connecting channel away from the intake channel; the larger end of the expansion channel is connected to the annular channel of the rotating detonation combustion chamber.

[0031] By adopting the above technical solution, during the process of air and fuel entering the annular channel of the rotary detonation combustion chamber in the forward direction, air and fuel sequentially pass through the intake channel, connecting channel, and expansion channel into the rotary detonation combustion chamber. When the pressure wave and / or combustion products generated in the rotary detonation combustion chamber are transmitted back, the pressure wave and / or combustion products sequentially pass through the expansion channel, connecting channel, straight channel, and arc-shaped channel. The straight channel and arc-shaped channel form an arc-shaped return channel. The pressure wave and / or combustion products are transmitted back through the arc-shaped return channel, and the transmitted pressure wave and / or combustion products are weakened by the arc-shaped return channel. Since the pressure wave and combustion product return channel and the air and fuel forward entry channel are two separate channels, the impact of the pressure wave and / or combustion product return on the air and fuel forward entry is very small, thereby reducing the total intake pressure loss and increasing the total pressure gain of the rotary detonation combustion chamber.

[0032] Optionally, the angle between the air intake channel and the straight channel is 30°-45°.

[0033] By adopting the above technical solution, when the angle between the intake channel and the straight channel is 30°-45°, the reverse blocking performance of the Tesla valve is improved as the angle increases, and the unidirectional flow performance of the Tesla valve is best when the angle is 45°.

[0034] Optionally, the housing includes a first connecting cylinder, a second connecting cylinder, and a flow guide block. The first connecting cylinder and the second connecting cylinder are coaxially sleeved together, and the flow guide block is coaxially disposed between the first connecting cylinder and the second connecting cylinder. The first connecting cylinder includes a first connecting segment, a second connecting segment, and a third connecting segment connected in sequence. The second connecting cylinder includes a fourth connecting segment, a fifth connecting segment, and a sixth connecting segment connected in sequence. The flow guide block includes a first straight flow guide surface, an arc-shaped flow guide surface, and a second straight flow guide surface connected in sequence. The end of the first straight flow guide surface away from the arc-shaped flow guide surface is connected to the end of the second straight flow guide surface away from the arc-shaped flow guide surface. The second connecting segment and the fifth connecting segment are parallel. The connecting channel is located between the second connecting segment and the fifth connecting segment. The first connecting segment and the third connecting segment are located at both ends of the second connecting segment and are inclined towards the side away from the fifth connecting segment. The sixth connecting segment is symmetrical to the third connecting segment. The expansion channel is located between the third connecting segment and the sixth connecting segment. The fourth connecting segment is located on the side of the fifth connecting segment close to the first connecting segment and at the end of the fifth connecting segment away from the sixth connecting segment. The air intake channel is located between the first connecting segment and the first straight guide surface. The arc-shaped channel is located between the fourth connecting segment and the arc-shaped guide surface. The straight channel is located between the second straight guide surface and the fifth connecting segment.

[0035] By adopting the above technical solution, the first connecting section, the second connecting section and the third connecting section constitute the first connecting cylinder, the fourth connecting section, the fifth connecting section and the sixth connecting section constitute the second connecting cylinder, and the first straight guide surface, the arc-shaped guide surface and the second straight guide surface constitute the guide block, thereby forming a flow channel. The structure is simple and convenient for mass production.

[0036] Optionally, the first connecting cylinder is provided with a housing on the side away from the second connecting cylinder, and a receiving cavity for accommodating fuel is formed between the housing and the first connecting cylinder. A plurality of fuel injection holes are provided between the receiving cavity and the air intake channel.

[0037] By adopting the above technical solution, fuel is contained in the containment cavity, and the fuel in the containment cavity is injected into the intake channel through the fuel injection hole.

[0038] Optionally, the fuel injection holes are circumferentially spaced on the first connecting segment and located on the side of the first connecting segment closer to the second connecting segment.

[0039] By adopting the above technical solution, the fuel injected from the injection hole enters the second connecting section with the air, and the incoming air provides power for the flow of fuel.

[0040] Optionally, the first straight guide surface is provided with a plurality of first connecting posts circumferentially on the side near the first connecting segment, and the other end of the first connecting post is connected to the first connecting segment. The second straight guide surface is provided with a plurality of second connecting posts circumferentially spaced on the side near the fifth connecting segment, and the second connecting posts are connected to the fifth connecting segment.

[0041] By adopting the above technical solution, the connection between the first connecting section and the first straight guide surface is realized through the first connecting post, and the connection between the fifth connecting section and the second straight guide surface is realized through the second connecting post, which facilitates the connection and fixing of the guide block.

[0042] In summary, this application includes at least one of the following beneficial technical effects:

[0043] 1. The pressure regulating structure can minimize the impact of the detonation wave, so that the incoming flow pressure does not need to be adjusted or only slightly adjusted. This helps to match the air supply equipment with the detonation combustion chamber. The high-pressure air returned by the detonation wave and the input air that cannot continue to enter the flow channel due to the influence of the detonation wave are all collected into the ejector channel through the pressure regulating structure and ejected through the ejector channel. This increases the thrust and widens the pressure difference between the incoming flow pressure and the outlet of the annular channel, which helps to continuously supply the subsequent fuel and air mixing and the explosive mixture.

[0044] 2. As altitude increases, the air gradually thins. Because atmospheric pressure decreases with altitude, the distance between air molecules increases. When in a region with thin air, the opening and closing components close, reducing the air entering the ejector channel and increasing the air intake in the intake channel. This allows the rotary detonation combustion chamber to preferentially intake air from the intake channel, ensuring the air supply to the combustion chamber and improving the adaptability and stability of the combustion chamber in different environments.

[0045] 3. The self-locking drive component has a self-locking function, which can keep the opening and closing door in a stable open or closed state for a long time, even when the drive motor stops working or there is no power input, thus improving the safety of the system. At the same time, in conjunction with the gas flow rate sensor and controller, the pressure regulating structure can quickly respond to changes in gas flow rate and adjust the position of the opening and closing door in a timely manner to ensure the stability of the airflow inside the combustion chamber. Attached Figure Description

[0046] Figure 1 This is a cross-sectional view of the pressure regulating structure of the rotary detonation combustion chamber flow channel in the relevant technology under operating conditions.

[0047] Figure 2 This is a cross-sectional view of the rotating detonation combustion chamber structure in the usage state of Embodiment 1 of this application.

[0048] Figure 3 yes Figure 2 A partial structural diagram.

[0049] Figure 4 yes Figure 2 A schematic diagram of the overall structure of the Tesla valve in the diagram.

[0050] Figure 5 yes Figure 4 A three-dimensional sectional view.

[0051] Figure 6 yes Figure 5 A partial structural diagram.

[0052] Figure 7 yes Figure 4 Exploded view along the axial direction.

[0053] Figure 8 This is a cross-sectional view of the rotating detonation combustion chamber structure in the usage state of Embodiment 2 of this application.

[0054] Figure 9 yes Figure 8 A partial structural diagram.

[0055] Figure 10 This is a perspective sectional view of Embodiment 3 of this application.

[0056] Figure 11 yes Figure 10 Enlarged diagram of point A in the middle.

[0057] Figure 12 This is a schematic diagram of the opening and closing components.

[0058] Figure 13 This is a partial cross-sectional view of the opening and closing component.

[0059] Figure 14 yes Figure 12 Enlarged diagram of point B in the middle.

[0060] Figure 15 This is a schematic diagram of the guide vane structure in Embodiment 3 of this application.

[0061] Figure 16 This is a schematic diagram of the structure of the atomizing nozzle in Embodiment 3 of this application.

[0062] Explanation of reference numerals in the attached figures:

[0063] 1. Combustion chamber body; 2. Intake end; 21. Inner wall; 22. Outer wall; 23. Intake passage; 231. Straight flow passage; 232. Expansion flow passage; 3. Tesla valve; 31. Housing; 311. First connecting cylinder; 3111. First connecting section; 3112. Second connecting section; 3113. Third connecting section; 3114. Extension section; 3115. Atomizing nozzle; 312. Second connecting cylinder; 3121. Fourth connecting section; 3122. Fifth connecting section; 3123. Sixth connecting section; 313. Guide block; 3131. First straight guide surface; 3132. Arc-shaped guide surface; 3133. Second straight guide surface; 3134. First connecting post; 3135. Second connecting post; 32. Flow passage; 321. Intake passage; 322. Connecting passage; 323. Arc-shaped return channel; 3231. Arc-shaped channel; 3232. Straight channel; 324. Expansion channel; 325. Guide vane; 4. Rotary detonation combustion chamber; 41. Annular channel; 5. Outer shell; 6. Receiving cavity; 7. Injection hole; 8. Duct shell; 81. Injector channel; 811. Gas collection channel; 812. Pressurization channel; 813. Gas outlet channel; 9. Pressure regulating structure; 91. Gas collection chamber; 92. Inlet port; 93. Opening and closing assembly; 931. Support plate; 932. Opening and closing door; 933. Chamfer; 934. Self-locking drive component; 9341. Drive rack; 9342. Driven gear; 9343. Drive gear ring; 9344. Drive shaft; 9345. Drive gear; 9346. Worm gear; 9347. Worm; 9348. Drive motor. Detailed Implementation

[0064] The following is in conjunction with the appendix Figure 1-16 This application will be described in further detail.

[0065] like Figure 1 As shown, the rotary detonation combustion chamber flow channel pressure regulating structure in the related technology includes an intake end 2 for communicating with the combustion chamber body 1 and fixedly assembled at the inlet of the combustion chamber body 1. The intake end 2 includes an inner wall 21 and an outer wall 22 coaxially sleeved. An intake channel 23 for fuel and air to enter the combustion chamber body 1 is left between the inner wall 21 and the outer wall 22. The intake channel 23 includes a direct flow channel 231 and an expansion flow channel 232. One end of the direct flow channel 231 is connected to the outside air and the other end is connected to the expansion flow channel 232. The other end of the expansion flow channel 232 is connected to the combustion chamber body 1, i.e., a convergent-expansion intake scheme.

[0066] The detonation wave is a chemical reaction zone caused by a shock wave that rotates at high speed around the combustion chamber body 1. The pressure at the location of the detonation wave is very high. Every time the detonation wave rotates to a new position, pressure back is generated. This pressure back causes the intake end 2 to be blocked. After the intake is blocked, the pressure decays relatively slowly, resulting in a long intake recovery time. When the detonation wave returns to its original position, fresh air and the fuel required for the reaction have not yet had time to be replenished into the combustion chamber body 1, causing the detonation wave to be extinguished.

[0067] The convergent-divergent intake scheme is essentially a supersonic intake scheme. A normal shock wave is formed in the divergent channel 232. This normal shock wave can block the pressure back transmission of the detonation wave. Moreover, the Mach number of the supersonic intake is very high, which can quickly replenish fresh air and fuel required for the reaction, solving the problem of slow intake recovery time. However, the total pressure loss of the engine before and after the normal shock wave is large, and the rotating detonation wave cannot make up for the total pressure loss, resulting in a negative total pressure gain of the entire engine.

[0068] The combustion products are the high-temperature exhaust gas that has already been burned. When the high-temperature exhaust gas in the combustion chamber body 1 accumulates upstream of the intake duct 23, it will consume the reactants that were originally to be detonated and burned upstream in advance. Moreover, the combustion method is the isobaric combustion of a conventional engine. The effective fuel is consumed by isobaric combustion and cannot achieve turbocharging.

[0069] This application discloses a dual-channel rotary detonation combustion chamber structure with inlet total pressure regulation function.

[0070] Example 1:

[0071] like Figure 2 As shown, a dual-channel rotary detonation combustor structure with inlet total pressure regulation function includes a Tesla valve 3 that communicates with and is snap-fitted into the inlet of the rotary detonation combustor 4. The Tesla valve 3 includes a housing 31 and a flow channel 32. The housing 31 is coaxially snap-fitted into the outer wall of the rotary detonation combustor 4. The flow channel 32 is formed inside the housing 31. The inlet end of the flow channel 32 is used to introduce air, and the outlet end of the flow channel 32 communicates with the annular channel 41 of the rotary detonation combustor 4.

[0072] like Figure 2 , Figure 3As shown, the flow channel 32 includes an intake channel 321, a connecting channel 322, an arc-shaped return channel 323, and an expansion channel 324. One end of the intake channel 321 is used to introduce air, and the other end is connected to the connecting channel 322. The arc-shaped return channel 323 includes an arc-shaped channel 3231 and a straight channel 3232. The straight channel 3232 is linearly connected to the connecting channel 322. The arc-shaped channel 3231 is used to connect the straight channel 3232 and the intake channel 321. The angle between the intake channel 321 and the straight channel 3232 is an acute angle. The expansion channel 324 is linearly connected to the connecting channel 322, and the smaller end of the expansion channel 324 is connected to the end of the connecting channel 322 away from the intake channel 321. The larger end of the expansion channel 324 is connected to the annular channel 41 of the rotating detonation combustion chamber 4.

[0073] like Figure 2 As shown in Figure 3, by utilizing the unidirectional flow characteristic of the Tesla valve 3, the forward channel for air and fuel to enter the rotary detonation combustion chamber is separated from the reverse channel for pressure return and combustion product return. This effectively reduces the obstruction of pressure return and combustion product return on the forward-entering air and fuel, allowing the detonation boost to compensate for the total pressure loss generated by the upper intake, thereby increasing the total pressure gain of the rotary detonation combustion chamber. At the same time, it avoids the high temperature of the combustion product return from prematurely igniting the reactants, thus reducing the impact of the combustion product return on the rotary detonation combustion chamber 4.

[0074] Furthermore, the Tesla valve 3 has no moving parts and can achieve unidirectional airflow without the need for energy input. Its forward and reverse flow are very different. It does not require internal mechanical movement, but only uses the spatial structure to drive the gas flow and accelerate the gas through the physical structure.

[0075] Using the anti-backflow structure of the rotary detonation combustion chamber of this application, when air and fuel enter the rotary detonation combustion chamber 4 in the forward direction, the air and fuel enter the rotary detonation combustion chamber 4 in sequence through the intake channel 321, the connecting channel 322 and the expansion channel 324. The pressure wave and / or combustion products generated in the rotary detonation combustion chamber 4 are diverted through the arc-shaped backflow channel 323 after passing through the expansion channel 324 and the connecting channel 322 in sequence. When the pressure wave generated in the rotary detonation combustion chamber 4 is transmitted back, after the pressure wave passes through the expansion channel 324 and the connecting channel 322 in sequence, and reaches the bifurcation of the intake channel 321 and the straight channel 3232, the pressure wave will travel straight, passing through the straight channel 3232 and the arc channel 3231 in sequence. The forward flow channel of air and fuel and the pressure wave transmission channel are two separate paths, which effectively reduces the obstruction of the pressure transmission to the forward-entering air and fuel, so that the detonation pressurization can make up for the loss of total pressure. When the combustion products generated in the rotary detonation combustion chamber 4 are transmitted back, the combustion products pass through the expansion channel 324, the connecting channel 322, the straight channel 3232 and the arc channel 3231 in sequence, which effectively reduces the premature consumption of fuel by the high temperature of the combustion products during transmission. At the same time, the fresh air introduced through the arc return channel 323 and the intake channel 321 cools and dilutes the combustion products, reducing their consumption of fuel when they re-enter the intake channel 321.

[0076] like Figure 3 As shown, the angle between the intake passage 321 and the straight passage 3232 is 30°-45°. As the angle increases, the reverse blocking performance of the Tesla valve 3 improves. When the angle is 45°, the unidirectional flow performance of the Tesla valve 3 is the best. When the angle is 30°-45°, the forward conduction performance of the Tesla valve 3 does not change much. However, when the angle is greater than 60°, the forward conduction performance of the Tesla valve 3 drops sharply.

[0077] like Figure 4 , Figure 5 As shown, the housing 31 includes a first connecting cylinder 311, a second connecting cylinder 312, and a guide block 313. The first connecting cylinder 311 is coaxially sleeved outside the second connecting cylinder 312, and the guide block 313 is coaxially fixed between the first connecting cylinder 311 and the second connecting cylinder 312.

[0078] like Figure 5 , Figure 6As shown, the first connecting cylinder 311 includes a first connecting segment 3111, a second connecting segment 3112, and a third connecting segment 3113 connected in sequence, and the first connecting segment 3111, the second connecting segment 3112, and the third connecting segment 3113 are integrally formed; the second connecting cylinder 312 includes a fourth connecting segment 3121, a fifth connecting segment 3122, and a sixth connecting segment 3123 connected in sequence, and the fourth connecting segment 3121, the fifth connecting segment 3122, and the sixth connecting segment 3123 are integrally formed; the guide block 313 includes a first straight guide surface 3131, an arc-shaped guide surface 3132, and a second straight guide surface 3133 connected in sequence, and the end of the first straight guide surface 3131 away from the arc-shaped guide surface 3132 is connected to the end of the second straight guide surface 3133 away from the arc-shaped guide surface 3132. The second connecting section 3112 is parallel to the fifth connecting section 3122. The connecting channel 322 is located between the second connecting section 3112 and the fifth connecting section 3122. The first connecting section 3111 and the third connecting section 3113 are located at both ends of the second connecting section 3112 and are inclined towards the side away from the fifth connecting section 3122. The sixth connecting section 3123 is symmetrical to the third connecting section 3113. The expansion channel 324 is located between the third connecting section 3113 and the sixth connecting section 3123. The fourth connecting section 3121 is located on the side of the fifth connecting section 3122 close to the first connecting section 3111 and at the end of the fifth connecting section 3122 away from the sixth connecting section 3123. The air intake channel 321 is located between the first connecting section 3111 and the first straight guide surface 3131. The arc-shaped channel 3231 is located between the fourth connecting section 3121 and the arc-shaped guide surface 3132. The straight channel 3232 is located between the second straight guide surface 3133 and the fifth connecting section 3122.

[0079] like Figure 6 As shown, a housing 5 is provided on the side of the first connecting cylinder 311 away from the second connecting cylinder 312. The housing 5 is integrally formed with the first connecting cylinder 311. A receiving cavity 6 for holding fuel is formed between the housing 5 and the first connecting cylinder 311. A plurality of fuel injection holes 7 are circumferentially spaced between the receiving cavity 6 and the air intake channel 321. The fuel injection holes 7 are circumferentially spaced on the first connecting section 3111 and located on the side of the first connecting section 3111 closer to the second connecting section 3112. The fuel is held in the receiving cavity 6 and injected into the air intake channel 321 through the fuel injection holes 7. The fuel injection holes 7 are closer to the connecting channel 322 than the air inlet of the air intake channel 321. That is, the fuel injected from the fuel injection holes 7 enters the second connecting section 3112 with the air and provides power for the flow of fuel through the air.

[0080] like Figure 6 , Figure 7As shown, a plurality of first connecting posts 3134 are installed at equal intervals around the first straight guide surface 3131 near the first connecting section 3111. The other end of the first connecting post 3134 is connected to the first connecting section 3111. A plurality of second connecting posts 3135 are installed at equal intervals around the second straight guide surface 3133 near the fifth connecting section 3122. The second connecting posts 3135 are connected to the fifth connecting section 3122.

[0081] The implementation principle of Embodiment 1 of this application is as follows: When air and fuel enter the rotary detonation combustion chamber 4 in the forward direction, air and fuel sequentially pass through the intake channel 321, the connecting channel 322 and the expansion channel 324 into the rotary detonation combustion chamber 4.

[0082] When the pressure wave generated in the rotating detonation combustion chamber 4 returns, the pressure wave will pass through the expansion channel 324 and the connecting channel 322 in sequence. After reaching the bifurcation of the intake channel 321 and the straight channel 3232, the pressure wave will travel straight and return through the straight channel 3232 and the arc channel 3231 in sequence.

[0083] When the combustion products generated in the rotating detonation combustion chamber 4 are transmitted back, the combustion products are transmitted back sequentially through the expansion channel 324, the connecting channel 322, the straight channel 3232 and the arc channel 3231.

[0084] Example 2:

[0085] like Figure 8 , Figure 9 As shown, the difference between this embodiment and embodiment 1 is that the housing 31 includes a first connecting cylinder 311, a second connecting cylinder 312 and a guide block 313. The first connecting cylinder 311 is coaxially sleeved inside the second connecting cylinder 312, and the guide block 313 is coaxially fixed between the first connecting cylinder 311 and the second connecting cylinder 312.

[0086] The implementation principle of Example 2 is the same as that of Example 1, and will not be repeated here.

[0087] Example 3:

[0088] like Figure 10 , Figure 11As shown, the difference between this embodiment and Embodiment 1 is that the first connecting cylinder 311 further includes an extension section 3114 fixed to the side of the first connecting section 3111 away from the second connecting section 3112. A duct shell 8 is provided on the outer side of the outer shell 5. The duct shell 8 is sleeved on the first connecting cylinder 311, the outer shell 5, and the rotating detonation combustion chamber 4, and the duct shell 8 is fixedly connected to the extension section 3114. The receiving cavity 6 is formed between the first connecting section 3111 and the outer shell 5. Multiple pressure regulating structures 9 are provided on both the second connecting section 3112 and the extension section 3114. The pressure regulating structures 9 on the second connecting section 3112 and the extension section 3114 are all circumferentially distributed around the axis of the shell 31.

[0089] like Figure 11 As shown, the pressure regulating structure 9 includes an air collecting chamber 91 and multiple air inlets 92 communicating with the air collecting chamber 91. The air inlets 92 on the second connecting section 3112 are formed on the surface of the second connecting section 3112 facing the connecting channel 322. The air inlets 92 on the second connecting section 3112 are grouped in sets of three, with the air inlets 92 in the same group evenly distributed along the axial direction of the housing 31, and each group of air inlets 92 is circumferentially distributed around the axis of the housing 31. The air collecting chamber 91 in the pressure regulating structure 9 on the second connecting section 3112 is formed between the second connecting section 3112 and the duct housing 8, and the air inlets 92 communicate with the air collecting chamber 91 on the second connecting section 3112 and the connecting channel 322.

[0090] like Figure 11 As shown, the gas collecting cavity 91 of the pressure regulating structure 9 on the extension section 3114 is formed between the extension section 3114 and the duct shell 8. An air inlet 92 is formed on the extension section 3114, connecting the air inlet 23 and the flow channel 32. The air inlets 92 on the extension section 3114 are arranged in groups of three, with each group of inlets 92 evenly distributed along the axial direction of the shell 31, and each group of inlets 92 is circumferentially distributed around the axis of the shell 31. Through the pressure regulating structure 9, the second connecting section 3112 and the extension section 3114 become resistive walls.

[0091] like Figure 10 , Figure 11As shown, an ejector channel 81 is formed between the duct shell 8, the outer shell 5, the first connecting cylinder 311, and the rotating detonation combustion chamber 4. The ejector channel 81 includes a gas collecting channel 811, a pressurizing channel 812, and a gas outlet channel 813 arranged sequentially along the direction from the connecting channel 322 to the expansion channel 324. Each gas collecting chamber 91 is connected to the gas collecting channel 811. The pressurizing channel 812 connects the gas collecting channel 811 and the gas outlet channel 813. The cross-sectional area of ​​the pressurizing channel 812 decreases along the direction from the pressurizing channel 812 to the gas outlet channel 813. The outlet of the gas outlet channel 813 faces away from the gas collecting channel 811. The gas outlet channel 813 is inclined and faces the outlet of the annular channel 41, and the outlet of the gas outlet channel 813 is connected to the inlet of the rotating detonation combustion chamber 4, i.e., the outlet of the annular channel 41.

[0092] like Figure 10 , Figure 11 As shown, during the return of the detonation wave, high-pressure air enters the gas collecting chamber 91 located on the second connecting section 3112 through the air inlet 92 and flows into the ejector channel 81. Due to the enormous pressure generated by the detonation wave, air aligned with the axis of the detonation wave enters the gas collecting chamber 91 located on the extension section 3114 through the air inlet 92 and flows into the ejector channel 81. The air entering the ejector channel 81 is finally ejected through the exhaust channel 813.

[0093] like Figure 12 , Figure 13 As shown, an opening / closing assembly 93 for opening or closing the air outlet passage 813 is also provided on the side of the air outlet passage 813 away from the pressurization passage 812. The opening / closing assembly 93 includes a support plate 931 fixed to the side of the air outlet passage 813 away from the pressurization passage 812. Multiple opening / closing doors 932 are slidably connected to the support plate 931. The opening / closing doors 932 are tightly fitted to the end of the air outlet passage 813. When the multiple opening / closing doors 932 are closed, they are arranged in a ring to seal the air outlet passage 813. A chamfer 933 is provided on the side of the opening / closing door 932 near the air outlet passage 813. When the opening / closing door 932 is closed, the chamfer 933 applies a certain warning pressure towards the side of the air outlet passage 813 to the opening / closing door 932, so that the opening / closing door 932 is tightly fitted to the outlet of the air outlet passage 813. A self-locking drive component 934 is provided between the support plate 931 and the opening and closing door 932. The self-locking drive component 934 is used to synchronously drive multiple opening and closing doors 932 to move closer to or away from the outlet side of the air outlet channel 813.

[0094] As altitude increases, the air gradually thins. Because atmospheric pressure decreases with altitude, the distance between air molecules increases. When in a thin air zone, the opening and closing component 93 closes the exhaust pipe to reduce the air entering the ejector channel 32 and enhance the air intake in the intake channel 321. This allows the rotating detonation combustion chamber 4 to preferentially intake the air in the intake channel 321, ensuring the supply of air to the combustion chamber.

[0095] When the exhaust passage 813 needs to be closed, the self-locking drive component 934 moves multiple opening and closing doors 932 towards the side closer to the outlet of the exhaust passage 813. When the opening and closing doors 932 are closed, they form a ring shape, thus completely sealing the exhaust passage 813 and preventing air from flowing out. When the exhaust passage 813 needs to be opened, the self-locking drive component 934 moves the opening and closing doors 932 away from the outlet of the exhaust passage 813, thereby opening the exhaust passage 813. In high-altitude or thin-air environments, the control of the opening and closing component 93 can reduce the amount of air entering the ejector channel 32, prioritizing the intake of air into the intake passage 321, and ensuring stable operation of the combustion chamber under different environmental conditions.

[0096] In some embodiments, such as Figure 12 , Figure 14 As shown, the self-locking drive component 934 includes multiple drive racks 9341 slidably connected to a support plate 931. Each drive rack 9341 corresponds to one of the multiple opening / closing doors 932, and each drive rack 9341 is fixedly connected to a corresponding drive gear 9345. Multiple driven gears 9342 are rotatably connected to the support plate 931, each driven gear 9342 corresponding to one of the multiple drive racks 9341, and the driven gears 9342 mesh with their corresponding drive racks 9341. A drive gear ring 9343 is rotatably connected to the support plate 931, and the inner side of the drive gear ring 9343 meshes with multiple drive gears 9345. A drive shaft 9344 is rotatably connected to the support plate 931, and a drive gear 9345 and a worm gear 9346 are fixedly sleeved on the drive shaft 9344. The drive gear 9345 meshes with the drive gear ring 9343. A worm gear 9347 is rotatably connected to the support plate 931. The worm gear 9347 meshes with a worm wheel 9346, and a drive motor 9348 is also provided at one end of the worm gear 9347. The self-locking drive component 934 also includes a gas flow rate sensor and a controller. The gas flow rate sensor is located in the gas outlet channel 813 to detect the gas flow rate in the gas outlet channel 813 and send a gas flow rate detection signal. The controller is connected to the gas flow rate sensor and the drive motor 9348 to receive the gas flow rate detection signal to know the gas flow rate in the gas outlet channel 813. When the gas flow rate is lower than the preset flow rate, a control signal is sent to the drive motor 9348 to close the gas outlet channel 813.

[0097] When the gas flow rate sensor detects that the gas flow rate in the gas outlet channel 813 is lower than the preset flow rate, it sends a gas flow rate detection signal to the controller. After receiving the signal, the controller determines whether the gas flow rate is lower than the preset value. If it is lower than the preset value, the controller sends a control signal to the drive motor 9348. After receiving the control signal from the controller, the drive motor 9348 starts, driving the worm gear 9347 and worm wheel 9346 to rotate. The worm wheel 9346 drives the drive shaft 9344 to rotate. The drive shaft 9344 drives the drive gear 9345 and drive gear ring 9343 to rotate. The drive gear ring 9343 synchronously drives multiple drive gears 9345 to rotate. Each driven gear 9342 meshes with the corresponding drive rack 9341. The rotation of the drive gear 9345 drives the drive rack 9341 and the opening / closing door 932 fixedly connected to it to move synchronously, thereby realizing the opening or closing of the gas outlet channel 813. The self-locking drive component 934 has a self-locking function, which can keep the opening and closing door 932 in a stable open or closed state for a long time, even when the drive motor 9348 stops working or there is no power input, thus improving the safety of the system. At the same time, in conjunction with the gas flow rate sensor and controller, the pressure regulating structure can quickly respond to changes in gas flow rate and adjust the position of the opening and closing door 932 in a timely manner to ensure the stability of the airflow inside the combustion chamber.

[0098] like Figure 11 , Figure 15 As shown, multiple guide vanes 325 are provided within the flow channel 32, which are used to pre-swirl the fuel. The guide vanes 325 are arranged circumferentially around the axis of the housing 31, located within the connecting channel 322 and the expansion channel 324, and are fixed to the second connecting section 3112, the third connecting section 3113, the fifth connecting section 3122, and the sixth connecting section 3123. Guided by the guide vanes 325, the explosive mixture formed by the fuel and air begins to rotate upon entering the annular channel 41.

[0099] like Figure 11 , Figure 16 As shown, the extension section 3114 is equipped with multiple atomizing nozzles 3115, arranged in groups of three. The atomizing nozzles 3115 within the same group are evenly distributed along the axial direction of the housing 31, and each group of atomizing nozzles 3115 is circumferentially distributed around the axis of the housing 31. Each atomizing nozzle 3115 is connected to the receiving cavity 6 via a pipe. The nozzle head of the atomizing nozzle 3115 is located on the side of the extension section 3114 near the flow channel 32, and the atomizing nozzle 3115 is used to spray atomized fuel. After the fuel sprayed by each atomizing nozzle 3115 mixes with air to form a mixture, the proportion of fuel in the fuel-air mixture is no more than 20%.

[0100] like Figure 11 , Figure 16As shown, multiple injection holes 7 are grouped together, with each group of injection holes 7 evenly distributed along the axial direction of the housing 31. In this embodiment, the injection holes 7 are grouped in sets of four. Each time the fuel-air mixture passes through an injection hole 7, the fuel concentration increases by 20%, up to a maximum of 100%. In this embodiment, the injection holes 7 are fine orifices; in other embodiments, the injection holes 7 can also be directly configured as atomizing nozzles.

[0101] The implementation principle of Embodiment 3 of this application is as follows: the pressure regulating structure 9 can minimize the influence of the detonation wave, so that the incoming flow pressure does not need to be adjusted or only slightly adjusted, which helps to match the air supply equipment with the detonation combustion chamber. The high-pressure air returned by the detonation wave and the input air that cannot continue to enter the flow channel 32 due to the influence of the detonation wave are all collected into the ejector channel 81 by the pressure regulating structure 9 and ejected through the ejector channel 81, which increases the thrust and widens the pressure difference between the incoming flow pressure and the outlet of the annular channel 41, which helps to continuously supply the subsequent fuel and air mixing and the explosive mixture.

[0102] The above are all preferred embodiments of this application and are not intended to limit the scope of protection of this application. Therefore, all equivalent changes made in accordance with the structure, shape and principle of this application should be covered within the scope of protection of this application.

Claims

1. A dual-channel rotary detonation combustion chamber structure having an inlet total pressure adjustment function, characterized by: The system includes a Tesla valve (3) that communicates with the rotary detonation combustion chamber (4) and is located at the inlet of the rotary detonation combustion chamber (4). The Tesla valve (3) includes a housing (31) and a flow channel (32). The housing (31) is coaxially connected to the outer wall of the rotary detonation combustion chamber (4). The flow channel (32) is coaxially located inside the housing (31). The inlet end of the flow channel (32) is used to introduce air. The outlet end of the flow channel (32) is connected to the annular channel (41) of the rotary detonation combustion chamber (4). The inlet end and outlet end of the flow channel (32) are both provided with a pressure regulating structure (9). The pressure regulating structure (9) includes a gas collecting chamber (91) and an air inlet (92) for connecting the gas collecting chamber (91) and the flow channel (32). An ejector channel (81) is provided on the radial outer side of the flow channel (32). The outlet of the ejector channel (81) is connected to the outlet of the rotating detonation combustion chamber (4), and the outlet of the ejector channel (81) faces away from the inlet of the flow channel (32). The ejector channel (81) is connected to the gas collecting chamber (91).

2. The dual passage rotary detonation combustion chamber structure with an inlet total pressure adjustment function according to claim 1, characterized in that, The ejector channel (81) includes an exhaust channel (813) connected to the outlet of the rotating detonation combustion chamber (4) and a pressurization channel (812) connected to the exhaust channel (813). The cross-sectional area of ​​the pressurization channel (812) decreases along the arrangement direction from the pressurization channel (812) to the exhaust channel (813). Furthermore, an opening and closing assembly (93) for opening or closing the exhaust channel (813) is provided on the side of the exhaust channel (813) away from the pressurization channel (812).

3. The dual passage rotary detonation combustion chamber structure with inlet total pressure adjustment function according to claim 2, characterized in that, The opening / closing component (93) includes: A support plate (931) is fixed to the side of the air outlet passage (813) away from the pressurization passage (812); The opening and closing doors (932) are slidably connected to the support plate (931), and multiple doors are provided. When multiple doors (932) are closed, they are arranged in a ring to close the air outlet channel (813). A self-locking drive component (934) is disposed between the support plate (931) and the opening and closing door (932) for synchronously driving multiple opening and closing doors (932) to move closer to or away from the outlet side of the air passage (813).

4. The dual passage rotary detonation combustion chamber structure with an inlet total pressure adjustment function according to claim 3, characterized in that, The self-locking drive component (934) includes: A drive rack (9341) is slidably connected to a support plate (931). Multiple racks are provided and correspond one-to-one with multiple opening and closing doors (932). The drive rack (9341) is fixedly connected to the corresponding drive gear (9345). Driven gears (9342) are rotatably connected to support plates (931). Multiple driven gears are provided and correspond one-to-one with multiple drive racks (9341). The driven gears (9342) mesh with the corresponding drive racks (9341). The drive gear ring (9343) is rotatably connected to the support plate (931) and meshes with multiple drive gears (9345); A drive shaft (9344) is connected to a support plate (931). A drive gear (9345) and a worm gear (9346) are fixedly sleeved on the drive shaft (9344). The drive gear (9345) meshes with the drive gear ring (9343). The worm (9347) is rotatably connected to the support plate (931) and meshes with the worm wheel (9346). A drive motor (9348) is also provided at one end of the worm (9347).

5. The dual passage rotary detonation combustion chamber structure with inlet total pressure adjustment function according to claim 4, characterized in that, The self-locking drive component (934) also includes: A gas flow rate sensor is installed in the gas outlet channel (813) to detect the gas flow rate in the gas outlet channel (813) and send a gas flow rate detection signal. The controller, connected to the gas flow rate sensor and the drive motor (9348), is used to receive the gas flow rate detection signal to know the gas flow rate in the gas outlet channel (813). When the gas flow rate is lower than the preset flow rate, it sends a control signal to the drive motor (9348) to make the drive motor (9348) close the gas outlet channel (813).

6. The dual passage rotary detonation combustion chamber structure with an inlet total pressure adjustment function according to any one of claims 1-5, characterized in that, The flow channel (32) includes an air intake channel (321), a connecting channel (322), an arc-shaped return channel (323), and an expansion channel (324). One end of the air intake channel (321) is used to introduce air, and the other end is connected to the connecting channel (322). The arc-shaped return channel (323) includes an arc-shaped channel (3231) and a straight channel (3232). The straight channel (3232) is linearly connected to the connecting channel (322). The arc-shaped channel (3231) is used to connect the straight channel (3232) and the air intake channel. The intake passage (321) and the straight passage (3232) form an acute angle. The expansion passage (324) is directly connected to the connecting passage (322), and the smaller end of the expansion passage (324) is connected to the end of the connecting passage (322) away from the intake passage (321). The larger end of the expansion passage (324) is connected to the annular passage (41) of the rotating detonation combustion chamber (4). The angle between the intake passage (321) and the straight passage (3232) is 30°-45°.

7. The dual passage rotary detonation combustion chamber structure with inlet total pressure adjustment function according to claim 6, characterized in that, The housing (31) includes a first connecting cylinder (311), a second connecting cylinder (312), and a guide block (313). The first connecting cylinder (311) and the second connecting cylinder (312) are coaxially sleeved together, and the guide block (313) is coaxially disposed between the first connecting cylinder (311) and the second connecting cylinder (312). The first connecting cylinder (311) includes a first connecting segment (3111), a second connecting segment (3112), and a third connecting segment (3113) connected in sequence. The second connecting cylinder (312) includes a fourth connecting segment connected in sequence. The connecting section (3121), the fifth connecting section (3122), and the sixth connecting section (3123) are provided. The guide block (313) includes a first straight guide surface (3131), an arc-shaped guide surface (3132), and a second straight guide surface (3133) connected in sequence. The end of the first straight guide surface (3131) away from the arc-shaped guide surface (3132) is connected to the end of the second straight guide surface (3133) away from the arc-shaped guide surface (3132). The second connecting section (3112) is parallel to the fifth connecting section (3122). The connecting channel (322) is located between the second connecting segment (3112) and the fifth connecting segment (3122). The first connecting segment (3111) and the third connecting segment (3113) are located at both ends of the second connecting segment (3112) and inclined towards the side away from the fifth connecting segment (3122). The sixth connecting segment (3123) is symmetrical to the third connecting segment (3113). The expansion channel (324) is located between the third connecting segment (3113) and the sixth connecting segment (3123). The fourth connecting segment (3121) is provided with... The intake channel (321) is located between the first connecting section (3111) and the first straight guide surface (3131), and is located at the end of the fifth connecting section (3122) away from the sixth connecting section (3123). The intake channel (321) is located between the first connecting section (3111) and the first straight guide surface (3131). The arc-shaped channel (3231) is located between the fourth connecting section (3121) and the arc-shaped guide surface (3132). The straight channel (3232) is located between the second straight guide surface (3133) and the fifth connecting section (3122).

8. The dual passage rotary detonation combustion chamber structure with inlet total pressure adjustment function according to claim 7, characterized in that, The first connecting cylinder (311) is provided with a housing (5) on the side away from the second connecting cylinder (312). The housing (5) and the first connecting cylinder (311) form a receiving cavity (6) for accommodating fuel. The receiving cavity (6) and the air intake channel (321) are provided with a plurality of fuel injection holes (7).

9. The dual passage rotary detonation combustion chamber structure with inlet total pressure adjustment function according to claim 8, characterized in that, The oil injection holes (7) are circumferentially spaced on the first connecting section (3111) and located on the side of the first connecting section (3111) closer to the second connecting section (3112).

10. The dual passage rotary detonation combustion chamber structure with an inlet total pressure adjustment function according to claim 7, characterized by, The first straight flow guide surface (3131) is provided with a plurality of first connecting columns (3134) on one side of the first connecting section (3111) in a circumferential direction, one end of the first connecting column (3134) is connected with the first connecting section (3111), and the second straight flow guide surface (3133) is provided with a plurality of second connecting columns (3135) on one side of the fifth connecting section (3122) in a circumferential direction, and the second connecting column (3135) is connected with the fifth connecting section (3122).

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