A rotating detonation combustion chamber having a pressure regulating structure and an ejector passage

Abstract

The application relates to the field of aeroengines, in particular to a rotating detonation combustion chamber with a pressure regulating structure and an injection channel, comprising a duct shell, a combustion chamber body arranged in the duct shell and a Tesla valve arranged at the inlet of the combustion chamber body, the combustion chamber body being provided with an annular channel, the Tesla valve comprising a shell and a flow channel, one end of the shell being fixedly connected with one end of the duct shell, the other end of the shell being coaxially connected with the combustion chamber body, the flow channel being coaxially arranged in the shell, the inlet end of the flow channel being used for air inlet, and the outlet end of the flow channel being communicated with the annular channel in the combustion chamber body; the injection channel is formed between the duct shell, the shell and the combustion chamber body, the inlet end and the outlet end of the flow channel are both provided with a pressure regulating structure, the pressure regulating structure comprises a gas collection cavity and an air inlet hole used for connecting the gas collection cavity with the flow channel, and the injection channel is communicated with the gas collection cavity. The application has the effect of improving the problem that the pressure backflow causes the total pressure loss of the combustion chamber to be large.

Description

Technical Field

[0001] This application relates to the field of aero engines, and in particular to a rotating detonation combustor with a pressure regulating structure and an ejector channel. 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 rotating detonation combustion chamber intake structure includes an intake end 2 for communicating with the combustion chamber body 1 and located 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 passage 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 passage 23 includes a direct flow passage 231 and an expansion flow passage 232 connected together. One end of the direct flow passage 231 is connected to the air intake end and the other end is connected to the expansion flow passage 232. The other end of the expansion flow passage 232 is connected to the combustion chamber body 1, i.e., a convergent-expansion intake scheme.

[0004] Regarding the aforementioned technologies, the inventors believe that the detonation of fuel and air inside the combustion chamber body 1 causes the detonation pressure to be transmitted back to the air intake end 2 of the combustion chamber body 1, resulting in a large total pressure loss in the combustion chamber body 1. 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 rotary detonation combustion chamber with a pressure regulating structure and an ejector channel.

[0006] This application provides a rotary detonation combustion chamber with a pressure regulating structure and an ejector channel, which adopts the following technical solution:

[0007] A rotary detonation combustion chamber with a pressure regulating structure and an ejector channel is characterized in that: it includes a duct shell, inside which a combustion chamber body and a Tesla valve located at the inlet of the combustion chamber body are disposed; the combustion chamber body has an annular channel; the Tesla valve includes a housing and a flow channel; one end of the housing is fixedly connected to one end of the duct shell; the other end of the housing is coaxially connected to the combustion chamber body; 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 communicates with the annular channel inside the combustion chamber body.

[0008] An ejector channel is formed between the duct shell, the shell, and the combustion chamber body. A pressure regulating structure is provided at both the inlet end and the outlet end of the flow channel. The pressure regulating structure includes an air collection chamber and an air inlet for connecting the air collection chamber and the flow channel. The ejector channel is connected to the air collection chamber.

[0009] By adopting the above technical solution, the unidirectional flow characteristic of the Tesla valve is utilized to separate the forward channel for air and fuel to enter the combustion chamber 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 booster to compensate for the total pressure loss generated by the upper intake, thereby increasing the total pressure gain of the rotating 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 rotating 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 knocking 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 combustion chamber body.

[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 rotational 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 combustion chamber body.

[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 combustion chamber body, the ejected high-pressure air reduces the air pressure at the outlet of the combustion chamber body, thereby increasing the pressure difference between the incoming flow pressure and the air pressure at the outlet of the combustion chamber body. 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 rotational detonation; and thirdly, allows for continuous air intake into the gas collecting chamber, utilizing the high-pressure air in the gas collecting chamber and improving the utilization rate of the high-pressure air.

[0014] Optionally, the ejector channel includes a gas collecting channel, a pressurizing channel, and a gas outlet channel connected in sequence. The gas collecting channel is connected to each of the gas collecting chambers, and the end of the gas outlet channel away from the pressurizing channel is located at the outlet of the combustion chamber body.

[0015] By adopting the above technical solution, the air in the ejector channel is transported through the pressurization channel to the exhaust channel during transmission, and finally ejected through 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 gas pressure at the combustion chamber outlet, thus improving the mixing effect and the supply rate of the explosive mixture.

[0016] Optionally, an outer shell is fixedly installed on the outer wall of the housing, and a receiving cavity for accommodating fuel is formed between the outer shell and the housing. The housing has multiple fuel injection holes that connect the receiving cavity and the flow channel.

[0017] By adopting the above technical solution, fuel is contained in the receiving cavity, and the fuel in the receiving cavity is injected into the flow channel through the injection hole.

[0018] Optionally, the outer casing is located between the air inlet at the inlet end of the flow channel and the air inlet at the outlet end of the flow channel, and the outer casing is bent toward the duct shell to reduce the distance between the outer wall of the outer casing and the inner wall of the duct shell.

[0019] By adopting the above technical solution, air enters the gas collecting chamber through the air inlet at the inlet end of the flow channel, and then the air passes between the outer wall of the outer shell and the inner wall of the duct shell, thereby increasing the air velocity. After the air velocity increases, the air passes through the gas collecting chamber at the outlet end of the flow channel, thereby increasing the air velocity in the gas collecting chamber at the outlet end of the flow channel, which facilitates the entry of the detonation wave into the gas collecting chamber through the air inlet during the return propagation.

[0020] Optionally, a plurality of support blocks are fixedly installed on the housing at the outlet of the flow channel. The plurality of support blocks are spaced apart along the circumference of the housing, and an acceleration channel is formed between two adjacent support blocks. The side of the support block away from the housing is fixedly connected to the inner wall of the duct housing, and the air inlet at the outlet end of the flow channel is located between two adjacent support blocks.

[0021] By adopting the above technical solution, the support block supports the duct shell, thereby improving the connection strength between the duct shell and the outer shell. At the same time, the air velocity increases when it flows through the acceleration channel, thereby increasing the pressure difference at both ends of the air inlet at the outlet of the flow channel, which facilitates the entry of the detonation wave into the gas collection chamber through the air inlet during its return.

[0022] Optionally, multiple buffer blocks are fixedly installed on both inner sidewalls of the acceleration channel, and the multiple buffer blocks are arranged at radial intervals along the housing.

[0023] By adopting the above technical solution, after the detonation wave enters the gas collecting chamber at the outlet end of the flow channel, the detonation wave is blocked by the buffer block, thereby reducing the impact of the detonation wave on the duct shell.

[0024] Optionally, the buffer block is inclined from one side of the combustion chamber body to the other side, gradually approaching the housing, while the support block is bent on the side away from the combustion chamber body.

[0025] By adopting the above technical solution, the tilt of the buffer block facilitates the flow of the detonation wave towards the outlet of the ejector channel, thereby increasing the thrust provided by the ejected gas from the ejector channel. The support block is bent on the side away from the combustion chamber body, which facilitates the guidance of air into the acceleration channel.

[0026] Optionally, the acceleration channel is tilted such that the angle between the transmission direction of the acceleration channel and the axis of the housing is acute.

[0027] By adopting the above technical solution, air enters the acceleration channel and is ejected. The air is guided by the tilt of the acceleration channel, causing the air to rotate and flow inside the ejector channel, thereby increasing the thrust provided by the air ejected from the ejector channel.

[0028] Optionally, a shielding ring is fixedly installed on the inner wall of the duct shell near the inlet end of the flow channel. The shielding ring is tangent to the edge of the air intake port away from the combustion chamber body. The shielding ring is inclined from the outer ring to the inner ring, gradually approaching the combustion chamber body.

[0029] By adopting the above technical solution, the shielding ring effectively blocks the backflow of the detonation wave, allowing it to enter the gas collecting chamber from the air inlet at the outlet end of the flow channel, thereby reducing the resistance of the detonation wave to the air entering the flow channel. Simultaneously, the tilt of the shielding ring facilitates the guidance of air from the flow channel into the annular channel, further reducing the shielding ring's resistance to airflow.

[0030] Optionally, the outer wall of the combustion chamber body is provided with a plurality of heat dissipation grooves, which are arranged along the length of the combustion chamber body and are spaced apart along the circumference of the combustion chamber body.

[0031] By adopting the above technical solution, when air flows inside the ejector channel, it carries away the heat from the outer wall of the combustion chamber, thus facilitating heat dissipation from the combustion chamber body. Simultaneously, the heat dissipation grooves increase the contact area between the outer wall of the combustion chamber body and the air, thereby improving heat dissipation capacity.

[0032] In summary, this application includes at least one of the following beneficial technical effects:

[0033] 1. By utilizing the unidirectional flow characteristic of the Tesla valve, the forward channel for air and fuel to enter the 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 knock boost to compensate for the total pressure loss generated by the upper intake, thereby increasing the total pressure gain of the 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 combustion product return on the performance of the combustion chamber.

[0034] 2. Air enters from the inlet end of the flow channel, and the detonation wave returns from the outlet end of the flow channel. When the resistance of the detonation wave return to the air is large, the amount of air entering the gas collecting chamber from the air inlet at the inlet end of the flow channel increases. After the air flows through the gas collecting chamber at the outlet end of the flow channel, the air velocity is fast, thereby increasing the pressure difference between the two ends of the air inlet at the outlet end of the flow channel, and thus accelerating the entry of the detonation wave from the air inlet at the outlet end of the flow channel into the gas collecting chamber.

[0035] 3. Air and detonation wave flow inside the ejector channel and are ejected, thus playing a propulsive role. At the same time, the outlet of the ejector channel is connected to the outlet of the combustion chamber body. The air ejected from the ejector channel can reduce the gas pressure at the outlet of the combustion chamber body, thereby increasing the pressure difference between the inlet end of the flow channel and the outlet end of the combustion chamber body, thus facilitating the entry of air from the flow channel into the annular channel. Attached Figure Description

[0036] Figure 1 This is a cross-sectional view of the rotating detonation combustion chamber intake structure in use in related technologies;

[0037] Figure 2 This is a cross-sectional view of the rotating detonation combustion chamber anti-backflow intake structure of Embodiment 1 of this application in its service state;

[0038] Figure 3 yes Figure 2 Partial structural diagram;

[0039] Figure 4 yes Figure 2A schematic diagram of the overall structure of the Tesla valve in the diagram;

[0040] Figure 5 yes Figure 4 A three-dimensional sectional view;

[0041] Figure 6 yes Figure 5 Partial structural diagram;

[0042] Figure 7 yes Figure 4 Exploded view along the axial direction;

[0043] Figure 8 This is a cross-sectional view of the rotating detonation combustion chamber anti-backflow intake structure of Embodiment 2 of this application in its service state;

[0044] Figure 9 yes Figure 8 Partial structural diagram;

[0045] Figure 10 This is a perspective sectional view of Embodiment 3 of this application;

[0046] Figure 11 yes Figure 10 Enlarged view of point A in the middle;

[0047] Figure 12 This is a schematic diagram of the guide vane structure in Embodiment 3 of this application;

[0048] Figure 13 This is a schematic diagram highlighting the structure of the atomizing nozzle in Embodiment 3 of this application;

[0049] Figure 14 This is an accompanying drawing of Embodiment 4 of this application, and is... Figure 11 A schematic diagram of the structure after adding support blocks;

[0050] Figure 15 This is a schematic diagram of the structure after removing the duct shell in Embodiment 4 of this application;

[0051] Figure 16 This is an accompanying drawing of Embodiment 5 of this application, and is... Figure 11 A schematic diagram of the structure after adding the shielding ring;

[0052] Figure 17 This is a schematic diagram of the structure after removing the duct shell in Embodiment 5 of this application.

[0053] Explanation of reference numerals in the attached drawings: 1. Combustion chamber body; 2. Intake end; 21. Inner wall; 22. Outer wall; 23. Intake passage; 231. Straight flow passage; 232. Expansion 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. Flow surface; 3134, First connecting post; 3135, Second connecting post; 32, Flow channel; 321, Inlet channel; 322, Connecting channel; 323, Arc-shaped return channel; 3231, Arc-shaped channel; 3232, Straight channel; 324, Expansion channel; 325, Guide vane; 4, Annular channel; 5, Outer shell; 6, Receiving cavity; 7, Oil injection hole; 8, Duct shell; 81, Ejector channel; 811, Air collection channel; 812, Pressurization channel; 813, Air outlet channel; 9, Pressure regulating structure; 91, Air collection cavity; 92, Inlet hole; 10, Support block; 11, Acceleration channel; 12, Buffer block; 13, Shielding ring; 14, Heat dissipation groove. Detailed Implementation

[0054] The following is in conjunction with the appendix Figure 1-17 This application will be described in further detail.

[0055] like Figure 1 As shown, the rotary detonation combustion chamber intake structure in the related technology includes an intake end 2 for communicating with and being 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 passage 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 passage 23 includes a direct flow passage 231 and an expansion flow passage 232. One end of the direct flow passage 231 is connected to the outside air and the other end is connected to the expansion flow passage 232. The other end of the expansion flow passage 232 is connected to the combustion chamber body 1, i.e., a convergent-expansion intake scheme.

[0056] 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.

[0057] 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.

[0058] 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.

[0059] This application discloses a rotating detonation combustion chamber with a pressure regulating structure and an ejector channel.

[0060] Example 1:

[0061] like Figure 2 As shown, a rotary detonation combustor with a pressure regulating structure and an ejector channel includes a combustor body 1 and a Tesla valve 3 that communicates with and is snap-fitted into the inlet of the combustor body 1. The combustor body 1 has an annular channel 4 inside. 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 combustor body 1. 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 4 of the combustor body 1.

[0062] like Figure 2 , Figure 3 As 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 4 of the combustion chamber body 1.

[0063] like Figure 2 ,like Figure 3As shown, 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 combustion chamber body 1.

[0064] 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.

[0065] Using the rotary detonation combustion chamber anti-backflow structure of this application, when air and fuel enter the combustion chamber body 1 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 combustion chamber body 1. The pressure wave and / or combustion products generated in the combustion chamber body 1 are diverted through the arc-shaped backflow channel 323 after sequentially passing through the expansion channel 324 and the connecting channel 322. When the pressure wave generated in the combustion chamber body 1 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 knock boost can compensate for the loss of total pressure. When the combustion products generated in the combustion chamber body 1 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 situation of the high temperature of the combustion products consuming fuel prematurely. 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 the fuel consumption after they re-enter the intake channel 321.

[0066] 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.

[0067] like Figure 4 , Figure 5As 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.

[0068] like Figure 5 , Figure 6 As 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.

[0069] like Figure 6As 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.

[0070] like Figure 6 , Figure 7 As 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.

[0071] The implementation principle of Embodiment 1 of this application is as follows: When air and fuel enter the combustion chamber body 1 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 combustion chamber body 1.

[0072] When the pressure wave generated in the combustion chamber body 1 is transmitted back, 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 pass through the straight channel 3232 and the arc channel 3231 in sequence to transmit back.

[0073] When the combustion products generated in the combustion chamber body 1 are returned, the combustion products are returned sequentially through the expansion channel 324, the connecting channel 322, the straight channel 3232 and the arc channel 3231.

[0074] Example 2:

[0075] 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.

[0076] The implementation principle of Example 2 is the same as that of Example 1, and will not be repeated here.

[0077] Example 3:

[0078] like Figure 10 , Figure 11 As 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 combustion chamber body 1, 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, and the outer shell 5 is bent toward the duct shell 8 to reduce the distance between the outer wall of the outer shell 5 and the inner wall of the duct shell 8.

[0079] Multiple pressure regulating structures 9 are provided on 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 housing 31.

[0080] 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.

[0081] 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.

[0082] 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 combustion chamber body 1. The ejector channel 81 includes a gas collecting channel 811, a pressurizing channel 812, and a gas exhaust 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 exhaust channel 813. The cross-sectional area of ​​the pressurizing channel 812 decreases along the direction from the pressurizing channel 812 to the gas exhaust channel 813. The outlet of the gas exhaust channel 813 faces away from the gas collecting channel 811. The gas exhaust channel 813 is inclined and faces the outlet of the annular channel 4, and the outlet of the gas exhaust channel 813 is connected to the inlet of the combustion chamber body 1, i.e., the outlet of the annular channel 4.

[0083] 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.

[0084] like Figure 11 , Figure 12 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 4.

[0085] like Figure 11 , Figure 13 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%.

[0086] like Figure 11 , Figure 13 As 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.

[0087] 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 4, which helps to continuously supply the subsequent fuel and air mixing and the explosive mixture.

[0088] Example 4:

[0089] like Figure 14 , Figure 15 As shown, the difference between this embodiment and embodiment 3 is that multiple support blocks 10 are fixedly installed on the outer wall of the housing 31, and the support blocks 10 are located at the outlet end of the flow channel 32. The multiple support blocks 10 are arranged at intervals along the circumference of the housing 31, and an acceleration channel 11 is formed between two adjacent support blocks 10 for air to pass through. The side of the support block 10 away from the housing 31 is fixedly connected to the inner wall 21 of the duct housing 8, and the side of the support block 10 away from the combustion chamber body 1 is fixedly connected to the side of the outer shell 5 near the combustion chamber body 1.

[0090] The air inlet 92, located at the outlet end of the flow channel 32, is situated between two adjacent support blocks 10. Multiple buffer blocks 12 are fixedly installed on both inner sidewalls of the acceleration channel 11, and these buffer blocks 12 are arranged radially at intervals along the housing 31. The buffer blocks 12 are inclined, gradually approaching the housing 31 from one side near the combustion chamber body 1 to the other, while the support blocks 10 are bent on the side away from the combustion chamber body 1. The inclined arrangement of the acceleration channel 11 ensures that the angle between the transmission direction of the acceleration channel 11 and the axis of the housing 31 is acute.

[0091] The implementation principle of Embodiment 4 of this application is as follows: After combustion and air burn inside the annular channel 4, detonation generates a detonation wave. The return of the detonation wave increases the resistance of air entering the annular channel 4 from the flow channel 32. After the detonation wave increases the resistance to air, the amount of air entering the gas collecting chamber 91 from the air inlet 92 at the inlet of the flow channel 32 increases. Then, the air in the gas collecting chamber 91 at the inlet end of the flow channel 32 enters the gas collecting channel 811. Due to the bending of the outer shell 5, the distance between the outer wall of the outer shell 5 and the inner wall 21 of the duct shell 8 is reduced, thereby accelerating the air flow velocity in the gas collecting channel 811. Afterwards, the air enters the acceleration channel 11, and the cross-sectional area of ​​the acceleration channel 11 is further reduced, thereby further accelerating the air flow velocity.

[0092] The increased airflow speed increases the pressure difference across the inlet 92 at the outlet of flow channel 32, thereby accelerating the return of the detonation wave from the inlet 92 at the outlet of flow channel 32 into the gas collecting chamber 91. By accelerating the return of the detonation wave from the inlet 92 at the outlet of flow channel 32 into the gas collecting chamber 91, the resistance of the return detonation wave to the air is reduced, thus facilitating the entry of air from flow channel 32 into the annular channel 4.

[0093] After the detonation wave enters the gas collecting chamber 91 through the air inlet 92 at the outlet end of the flow channel 32, it is buffered by the buffer block 12, thereby reducing the impact force of the detonation wave on the duct shell 8 and thus reducing the possibility of the duct shell 8 being damaged by impact deformation. At the same time, the inclination of the buffer block 12 helps to guide the detonation wave to flow towards the outlet of the ejector channel 81, thereby increasing the thrust provided by the air ejected from the ejector channel 81.

[0094] Example 5:

[0095] like Figure 16 , Figure 17 As shown, the difference between this embodiment and embodiment 3 is that a baffle ring 13 is fixedly installed on the inner wall 21 of the duct housing 8 near the inlet end of the flow channel 32. The baffle ring 13 is tangent to the edge of the air intake 92 away from the combustion chamber body 1. The baffle ring 13 is inclined and gradually approaches the combustion chamber body 1 from the outer ring to the inner ring. A plurality of heat dissipation grooves 14 are formed on the outer wall of the combustion chamber body 1. The heat dissipation grooves 14 are arranged along the length direction of the combustion chamber body 1, and the plurality of heat dissipation grooves 14 are spaced apart along the circumference of the combustion chamber body 1.

[0096] The implementation principle of Embodiment 5 of this application is as follows: When the detonation wave returns, the shielding ring 13 reduces the amount of detonation wave returning to the flow channel 32, allowing the detonation wave to enter the gas collecting chamber 91 from the air inlet 92 at the outlet end of the flow channel 32, thereby reducing the resistance of the detonation wave to the air entering the flow channel 32. At the same time, the tilt of the shielding ring 13 facilitates the guidance of air from the flow channel 32 into the annular channel 4, thereby reducing the resistance of the shielding ring 13 to the air.

[0097] When air flows inside the ejector channel 81, it carries away heat from the outer wall of the combustion chamber body 1, thus facilitating heat dissipation. Simultaneously, the heat dissipation grooves 14 increase the contact area between the outer wall of the combustion chamber body 1 and the air, thereby improving heat dissipation capacity.

[0098] 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 rotating detonation combustion chamber with a pressure regulating structure and an ejector channel, characterized in that: The system includes a duct housing (8), inside which a combustion chamber body (1) and a Tesla valve (3) located at the inlet of the combustion chamber body (1) are disposed. The combustion chamber body (1) has an annular channel (4). The Tesla valve (3) includes a housing (31) and a flow channel (32). One end of the housing (31) is fixedly connected to one end of the duct housing (8), and the other end of the housing (31) is coaxially connected to the combustion chamber body (1). The flow channel (32) is coaxially disposed 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) is connected to the annular channel (4) inside the combustion chamber body (1). An injection channel is formed between the duct shell (8), the shell (31) and the combustion chamber body (1). A pressure regulating structure (9) is provided at both the inlet end and the outlet end of the flow channel (32). The pressure regulating structure (9) includes an air collection chamber (91) and an air inlet (92) for connecting the air collection chamber (91) and the flow channel (32). The injection channel is connected to the air collection chamber (91). The housing (31) is fixedly installed with multiple support blocks (10) at the outlet of the flow channel (32). The multiple support blocks (10) are arranged at intervals along the circumference of the housing (31). An acceleration channel (11) is formed between two adjacent support blocks (10). The side of the support block (10) away from the housing (31) is fixedly connected to the inner wall of the duct housing (8). The air inlet (92) at the outlet end of the flow channel (32) is located between two adjacent support blocks (10).

2. A rotary detonation combustion chamber with a pressure regulating structure and an ejector channel according to claim 1, characterized in that: The ejector channel includes a gas collection channel (811), a pressurization channel (812), and a gas outlet channel (813) connected in sequence. The gas collection channel (811) is connected to each of the gas collection chambers (91), and the end of the gas outlet channel (813) away from the pressurization channel (812) is located at the outlet of the combustion chamber body (1).

3. A rotary detonation combustion chamber with a pressure regulating structure and an ejector channel according to claim 1, characterized in that: The outer wall of the housing (31) is fixedly installed with a shell (5), and a receiving cavity (6) for accommodating fuel is formed between the shell (5) and the housing (31). The housing (31) has a plurality of oil injection holes (7) that connect the receiving cavity (6) and the flow channel (32).

4. A rotating detonation combustion chamber with a pressure regulating structure and an ejector channel according to claim 3, characterized in that: The outer shell (5) is located between the inlet end of the flow channel (32) and the air inlet (92) at the outlet end of the flow channel (32). The outer shell (5) is bent toward the duct shell (8) to reduce the distance between the outer wall of the outer shell (5) and the inner wall of the duct shell (8).

5. A rotary detonation combustion chamber with a pressure regulating structure and an ejector channel according to claim 1, characterized in that: Multiple buffer blocks (12) are fixedly installed on both inner sidewalls of the acceleration channel (11), and the multiple buffer blocks (12) are arranged at radial intervals along the shell (31).

6. A rotating detonation combustion chamber with a pressure regulating structure and an ejector channel according to claim 5, characterized in that: The buffer block (12) is inclined from one side of the combustion chamber body (1) to the other side, gradually approaching the shell (31), and the support block (10) is bent on the side away from the combustion chamber body (1).

7. A rotating detonation combustion chamber with a pressure regulating structure and an ejector channel according to claim 1, characterized in that: The acceleration channel (11) is tilted so that the angle between the transmission direction of the acceleration channel (11) and the axis of the housing (31) is acute.

8. A rotating detonation combustion chamber with a pressure regulating structure and an ejector channel according to claim 1, characterized in that: A shielding ring (13) is fixedly installed at the inlet end of the flow channel (32) near the inner wall of the duct shell (8). The shielding ring (13) is tangent to the edge of the air inlet (92) away from the combustion chamber body (1). The shielding ring (13) is inclined from the outer ring to the inner ring and gradually approaches the combustion chamber body (1).

9. A rotary detonation combustion chamber with a pressure regulating structure and an ejector channel according to claim 1, characterized in that: The outer wall of the combustion chamber body (1) is provided with a plurality of heat dissipation grooves (14), the heat dissipation grooves (14) are arranged along the length direction of the combustion chamber body (1), and the plurality of heat dissipation grooves (14) are arranged at intervals along the circumference of the combustion chamber body (1).

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