Rotary detonation combustion chamber with pressure regulating structure and injection channel

Abstract

The invention relates to the field of aero-engines, in particular to a rotary detonation combustion chamber with a pressure regulating structure and an injection channel, which comprises a duct shell, a combustion chamber body and a Tesla valve positioned at an inlet of the combustion chamber body are arranged in the duct shell, the combustion chamber body is provided with an annular channel, and the Tesla valve comprises a shell and a flow channel. One end of the shell is fixedly connected with one end of the duct shell, the other end of the shell is coaxially connected with the combustion chamber body, the flow channel is coaxially arranged in the shell, the inlet end of the flow channel is used for introducing air, and the outlet end of the flow channel is communicated with an annular channel in the combustion chamber body; an injection channel is formed among the duct shell, the shell and the combustion chamber body, the inlet end and the outlet end of the flow channel are each provided with a pressure adjusting structure, each pressure adjusting structure comprises a gas collecting cavity and a gas inlet hole used for communicating the gas collecting cavity with the flow channel, and the injection channel communicates with the gas collecting cavity. The method has the effect of improving the problem that the total pressure loss of the combustion chamber is large due to pressure return.

Description

Technical Field

[0001] The present application relates to the field of aircraft engines, and in particular to a rotating detonation combustion chamber having a pressure regulating structure and an ejection channel. Background Art

[0002] Detonation combustion is achieved by compressing the explosive mixture with a leading shock wave to cause a high-speed chemical reaction. Because detonation combustion has the advantages of high heat release per unit time, self-pressurization, high combustion efficiency, and low pollutant emissions, propulsion technology based on detonation combustion is an important development trend of future space technology. The rotating detonation combustion chamber is an annular combustion chamber that uses detonation combustion, and the fuel is supplied by multiple nozzles at the head of the combustion chamber.

[0003] like Figure 1 As shown, in the related art, the intake structure of the rotating detonation combustion chamber includes an intake end 2 for communicating with the combustion chamber body 1 and arranged at the entrance of the combustion chamber body 1, the intake end 2 includes an inner wall 21 and an outer wall 22 which are coaxially sleeved, and an intake passage 23 for fuel and air to enter the combustion chamber body 1 is reserved between the inner wall 21 and the outer wall 22, the intake passage 23 includes a straight flow passage 231 and an expansion flow passage 232 which are connected, one end of the straight 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, that is, a convergent-expansion intake scheme.

[0004] With respect to the above-mentioned related technologies, the inventors believe that the fuel and air detonate inside the combustion chamber body 1 , and the detonation pressure will be transmitted back to the intake end 2 of the combustion chamber body 1 , resulting in a large total pressure loss of the combustion chamber body 1 . Summary of the invention

[0005] In order to improve the problem of large total pressure loss in the combustion chamber caused by pressure feedback, the present application provides a rotating detonation combustion chamber with a pressure regulating structure and an ejection channel.

[0006] The present application provides a rotary detonation combustion chamber with a pressure regulating structure and an ejection channel, which adopts the following technical solution: A rotary detonation combustion chamber with a pressure regulating structure and an ejection channel, characterized in that: it comprises a duct shell, a combustion chamber body and a Tesla valve located at the inlet of the combustion chamber body are arranged inside the duct shell, the combustion chamber body has an annular channel, the Tesla valve comprises a shell and a flow channel, one end of the shell is fixedly connected to one end of the duct shell, the other end of the shell is coaxially connected to the combustion chamber body, the flow channel is coaxially arranged in the shell, the inlet end of the flow channel is used to let in air, and the outlet end of the flow channel is communicated with the annular channel inside the combustion chamber body; An ejection 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 includes an air collecting cavity and an air inlet hole for connecting the air collecting cavity and the flow channel. The ejection channel is connected to the air collecting cavity.

[0007] By adopting the above technical solution and utilizing the one-way flow characteristic of the Tesla valve, the forward channel for air and fuel to enter the combustion chamber body is separated from the reverse channel for pressure return and combustion product return, thereby effectively reducing the obstacles of pressure return and combustion product return to the forward-entering air and fuel, so that the detonation boost can make up for the total pressure loss caused by the upper intake, thereby increasing the total pressure gain of the rotating combustion chamber body, and avoiding the high temperature of the combustion product return from igniting the reactants in advance, thereby reducing the impact of the combustion product return on the performance of the rotating combustion chamber body; and the Tesla valve has no moving parts and does not require energy input to achieve one-way flow of airflow. The difference between the forward flow and the reverse flow is large, and no internal mechanical movement is required. The gas flow is driven by the spatial structure alone, and the gas is accelerated by the physical structure.

[0008] When air is output through air supply equipment such as compressors and turbines, the input air pressure is defined as the incoming flow pressure. After the occurrence of rotating detonation, if air is to be input continuously, the incoming flow pressure needs to be increased, that is, the air pressure output by the air supply equipment needs to be increased, which results in a mismatch between the original design parameters of the air supply equipment and the combustion chamber body.

[0009] A pressure regulating structure is added at the outlet of the flow channel, that is, an impedance wall is added at the outlet of the flow channel. When the pressure wave generated by the rotating detonation is transmitted back to the outlet of the flow channel, due to the volume effect, the high-pressure air transmitted back enters the air collecting cavity through the air inlet hole. With this arrangement, the air supply demand can be met by only slightly increasing the incoming flow pressure or without adjusting the incoming flow pressure, making it easy for the air supply equipment to directly match the combustion chamber body.

[0010] When the annular channel is detonated in rotation, the explosive mixture in the flow channel that is axially consistent with the detonation wave is difficult to enter the annular channel due to the huge pressure generated by the detonation wave, and high-pressure air is also difficult to input. By adding a pressure regulating structure at the inlet end of the flow channel, the high-pressure air at this time can enter the air collecting cavity at the inlet end of the flow channel through the air inlet hole of the pressure regulating structure at the inlet end of the flow channel.

[0011] The high-pressure air in each air collecting cavity is collected in the ejection channel and ejected from the ejection channel. Since the outlet of the ejection channel faces the direction opposite to the flow channel inlet, the high-pressure air ejected from the ejection channel can play a propulsive role. Since the outlet of the ejection channel is connected to the outlet of the combustion chamber body, the ejection of high-pressure air can reduce 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. Such a configuration can increase the intake speed of the annular channel. On the one hand, it can improve the mixing effect of air and fuel. On the other hand, it helps the explosive mixture after the air and fuel are mixed to enter the annular channel for rotational detonation. On the third hand, it also enables continuous intake of air in the air collecting cavity, utilizes the high-pressure air in the air collecting cavity, and improves the utilization rate of the high-pressure air.

[0012] Optionally, the ejection channel includes an air collecting channel, a boosting channel and an air outlet channel which are connected in sequence, the air collecting channel is connected to each of the air collecting cavities, and one end of the air outlet channel away from the boosting channel is located at the outlet of the combustion chamber body.

[0013] By adopting the above technical solution, the air in the ejection channel is transmitted to the outlet channel through the boost channel during the transmission process, and finally ejected through the outlet channel. Since the cross-sectional area of ​​the boost channel decreases along the arrangement direction from the boost channel to the outlet channel, the flow rate of the air passing through the boost channel is increased, so as to increase the flow rate of the air ejected from the ejection channel outlet. On the one hand, the propulsion effect is enhanced, and on the other hand, the pressure difference between the incoming flow pressure and the air pressure at the outlet of the combustion chamber body is further increased, thereby improving the mixing effect and the supply speed of the explosive mixture.

[0014] Optionally, an outer shell is fixedly mounted on the outer wall of the shell, a accommodating cavity for accommodating fuel is formed between the outer shell and the shell, and the shell is provided with a plurality of fuel injection holes connecting the accommodating cavity and the flow channel.

[0015] By adopting the above technical solution, the fuel is contained in the accommodating cavity, and the fuel in the accommodating cavity is sprayed into the interior of the flow channel through the injection hole.

[0016] Optionally, the shell is located between the positions of the air inlet holes at the inlet end and the outlet end of the flow channel, and the shell is bent toward the duct shell to reduce the distance between the outer wall of the shell and the inner wall of the duct shell.

[0017] By adopting the above technical solution, air enters the air collecting chamber from the air inlet at the inlet end of the flow channel, and then the air passes between the outer wall of the shell and the inner wall of the duct shell, thereby increasing the air flow rate. After the air flow rate increases, the air passes through the air collecting chamber at the outlet end of the flow channel, thereby increasing the air flow rate of the air collecting chamber at the outlet end of the flow channel, thereby facilitating the detonation wave to enter the air collecting chamber from the air inlet when it is transmitted back.

[0018] Optionally, the shell is fixedly mounted with a plurality of support blocks at the position of the flow channel outlet, the plurality of support blocks are spaced apart along the circumference of the shell, an acceleration channel is formed between two adjacent support blocks, the side of the support block away from the shell is fixedly connected to the inner wall of the duct shell, and the air inlet located at the flow channel outlet end is located between two adjacent support blocks.

[0019] By adopting the above technical solution, the support block supports the duct shell, thereby improving the connection strength between the duct shell and the shell. At the same time, the air velocity increases when flowing through the acceleration channel, thereby increasing the pressure difference at both ends of the air inlet at the outlet of the flow channel, thereby facilitating the detonation wave to enter the air collecting cavity from the air inlet when it is transmitted back.

[0020] Optionally, a plurality of buffer blocks are fixedly mounted on both inner side walls of the acceleration channel, and the plurality of buffer blocks are arranged at intervals along the radial direction of the shell.

[0021] By adopting the above technical solution, after the detonation wave enters the gas collecting cavity 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.

[0022] Optionally, the buffer block is inclined from one side close to the combustion chamber body to the other side gradually close to the shell, and the support block is bent on a side away from the combustion chamber body.

[0023] By adopting the above technical solution, the inclination of the buffer block is conducive to guiding the detonation wave to flow toward the outlet of the injection channel, thereby increasing the thrust provided by the gas ejected from the injection channel. The support block is bent away from the side of the combustion chamber body, thereby facilitating the guidance of air into the acceleration channel.

[0024] Optionally, the acceleration channel is tilted so that the angle between the transmission direction of the acceleration channel and the axis of the shell is an acute angle.

[0025] By adopting the above technical solution, the air is ejected after entering the acceleration channel. The air is guided by the inclination of the acceleration channel, so that the air rotates and flows inside the injection channel, thereby increasing the thrust provided by the air ejected from the injection channel.

[0026] 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 inlet hole away from the combustion chamber body, and the shielding ring is inclined from the outer circle to the inner circle and gradually approaches the combustion chamber body.

[0027] By adopting the above technical solution, the shielding ring can easily block the return of the detonation wave, allowing the detonation wave to enter the air collecting cavity 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. At the same time, the inclination of the shielding ring facilitates the guidance of air from the flow channel into the annular channel, thereby reducing the resistance of the shielding ring to the air.

[0028] Optionally, a plurality of heat dissipation grooves are provided on an outer wall of the combustion chamber body, and the heat dissipation grooves are arranged along the length direction of the combustion chamber body, and the plurality of heat dissipation grooves are arranged at intervals along the circumference of the combustion chamber body.

[0029] By adopting the above technical solution, when air flows inside the injection channel, the air will take away the heat of the outer wall of the combustion chamber body, thereby facilitating the heat dissipation of the combustion chamber body. At the same time, the contact area between the outer wall of the combustion chamber body and the air is increased through the heat dissipation groove, thereby improving the heat dissipation capacity.

[0030] In summary, the present application includes at least one of the following beneficial technical effects: 1. The Tesla valve's one-way flow characteristic is used to separate the forward channel for air and fuel to enter the combustion chamber from the reverse channel for pressure feedback and combustion product feedback, effectively reducing the obstacles to the forward air and fuel caused by pressure feedback and combustion product feedback, so that detonation supercharging can make up for the total pressure loss caused by the upper intake, thereby increasing the total pressure gain of the combustion chamber, while avoiding the high temperature of the combustion product feedback from igniting the reactants in advance, thereby reducing the impact of the combustion product feedback on the performance of the combustion chamber; 2. The 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 to the air is large, the amount of air entering the air collecting chamber from the air inlet hole at the inlet end of the flow channel increases. After that, after the air flows through the air collecting chamber at the outlet end of the flow channel, the air flow rate is fast, thereby increasing the pressure difference at both ends of the air inlet hole at the outlet end of the flow channel, thereby accelerating the detonation wave from the air inlet hole at the outlet end of the flow channel into the air collecting chamber; 3. The air and detonation wave flow inside the ejection channel and then are ejected, thereby playing a propulsion role. At the same time, the outlet of the ejection channel is connected to the outlet of the combustion chamber body. The air ejected from the ejection channel can reduce the air 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 of the combustion chamber body, thereby facilitating the air to enter the annular channel from the flow channel. BRIEF DESCRIPTION OF THE DRAWINGS

[0031] Figure 1 It is a cross-sectional view of the use state of the air intake structure of the rotating detonation combustion chamber in the related art; Figure 2 is a cross-sectional view of the use state of the anti-backflow intake structure of the rotating detonation combustion chamber of Example 1 of the present application; Figure 3 yes Figure 2 Schematic diagram of some structures; Figure 4 yes Figure 2 The overall structural diagram of the Tesla valve in FIG. Figure 5 yes Figure 4 A three-dimensional cross-sectional view of Figure 6 yes Figure 5 Schematic diagram of some structures; Figure 7 yes Figure 4 Exploded view along the axial direction; Figure 8 is a cross-sectional view of the use state of the anti-backflow intake structure of the rotating detonation combustion chamber of Example 2 of the present application; Fig. 9 yes Figure 8 Schematic diagram of some structures; Fig.10 is a three-dimensional cross-sectional view of Example 3 of the present application; Fig.11 yes Fig.10 The enlarged schematic diagram of point A in the middle; Fig.12 is a structural schematic diagram highlighting the guide vane in Example 3 of the present application; Fig.13 It is a structural schematic diagram highlighting the atomizing nozzle in Example 3 of the present application; Fig.14 is an accompanying drawing of Example 4 of the present application, and is Fig.11 Schematic diagram of the structure after adding support blocks; Fig.15 This is a schematic diagram of the structure of Example 4 of the present application after the duct shell is removed; Fig.16 is an accompanying drawing of Example 5 of the present application, and is Fig.11 Schematic diagram of the structure after adding the blocking ring; Fig.17 It is a schematic diagram of the structure of Example 5 of the present application after the duct shell is removed.

[0032] Explanation of reference numerals: 1. combustion chamber body; 2. air inlet end; 21. inner wall; 22. outer wall; 23. air inlet passage; 231. direct flow passage; 232. expansion flow passage; 3. Tesla valve; 31. shell; 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 guide surface; 3133. second straight guide surface Stream surface; 3134, first connecting column; 3135, second connecting column; 32, flow channel; 321, air 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, accommodating cavity; 7, oil injection hole; 8, duct shell; 81, injection channel; 811, air collecting channel; 812, boosting channel; 813, air outlet channel; 9, pressure regulating structure; 91, air collecting cavity; 92, air inlet; 10, support block; 11, acceleration channel; 12, buffer block; 13, shielding ring; 14, heat dissipation groove. DETAILED DESCRIPTION

[0033] The following is combined with Figure 1-17 This application is described in further detail.

[0034] like Figure 1 As shown, the rotating detonation combustion chamber intake structure in the related art 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 which are coaxially sleeved, and an intake passage 23 for fuel and air to enter the combustion chamber body 1 is reserved between the inner wall 21 and the outer wall 22, the intake passage 23 includes a connected straight channel 231 and an expansion channel 232, one end of the straight channel 231 is connected to the outside air and the other end is connected to the expansion channel 232, and the other end of the expansion channel 232 is connected to the combustion chamber body 1, that is, a convergent-expansion intake scheme.

[0035] The detonation wave is a shock wave that causes the chemical reaction zone to rotate 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 turns to a position, pressure feedback will occur, and the pressure feedback will cause the intake end 2 to be blocked. After the intake is blocked, the pressure decays relatively slowly, resulting in a longer intake recovery time. When the detonation wave turns back to its original position again, fresh air and the fuel required for the reaction have not had time to be replenished into the combustion chamber body 1, causing the detonation wave to be extinguished.

[0036] The convergent-divergent intake scheme is actually a supersonic intake scheme. A positive shock wave will be formed in the expansion flow channel 232. This positive shock wave can block the pressure feedback of the detonation wave. The Mach number of the supersonic intake is very high, and fresh air and the fuel required for the reaction can be quickly replenished, solving the problem of slow intake recovery time. However, the total pressure loss of the engine before and after the positive shock wave is large, and the rotating detonation wave cannot make up for the total pressure loss, resulting in a negative total pressure gain for the entire engine.

[0037] The combustion product is the high-temperature exhaust gas after combustion. When the high-temperature exhaust gas in the combustion chamber body 1 accumulates upstream of the intake duct 23, the reactants that were originally going to detonate and burn upstream will be consumed in advance. The combustion method is the isobaric combustion of a conventional engine. The effective fuel is consumed by the isobaric combustion and supercharging cannot be achieved.

[0038] The embodiment of the present application discloses a rotating detonation combustion chamber having a pressure regulating structure and an ejection channel.

[0039] Embodiment 1: like Figure 2 As shown, a rotary detonation combustion chamber with a pressure regulating structure and an ejection channel includes a combustion chamber body 1, and a Tesla valve 3 connected to the combustion chamber body 1 and snap-fitted at the inlet of the combustion chamber body 1. The combustion chamber body 1 has an annular channel 4 inside. The Tesla valve 3 includes a shell 31 and a flow channel 32, the shell 31 is coaxially snap-fitted with the outer wall of the combustion chamber body 1, the flow channel 32 is opened in the shell 31, the inlet end of the flow channel 32 is used to pass air, and the outlet end of the flow channel 32 is connected to the annular channel 4 of the combustion chamber body 1.

[0040] like Figure 2 , Figure 3 As shown, the flow channel 32 includes an intake channel 321, a connecting channel 322, an arcuate reflow channel 323 and an expansion channel 324; one end of the intake channel 321 is used to allow air to enter, and the other end is connected to the connecting channel 322; the arcuate reflow channel 323 includes an arcuate channel 3231 and a straight channel 3232; the straight channel 3232 is connected to the connecting channel 322 in a straight line; the arcuate 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 connected to the connecting channel 322 in a straight line, 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.

[0041] like Figure 2 ,like Figure 3As shown, the one-way flow characteristic of the Tesla valve 3 is utilized to separate the forward channel for air and fuel to enter the rotating detonation combustion chamber from the reverse channel for pressure feedback and combustion product feedback, thereby effectively reducing the obstacles of pressure feedback and combustion product feedback to the forward entering air and fuel, so that the detonation boost can make up for the total pressure loss caused by the upper intake, thereby increasing the total pressure gain of the rotating detonation combustion chamber; at the same time, it is avoided that the high temperature of the combustion product feedback ignites the reactants in advance, thereby reducing the influence of the combustion product feedback on the combustion chamber body 1.

[0042] In addition, the Tesla valve 3 has no moving parts and can achieve one-way airflow without the need for energy input. The difference between the forward flow and the reverse flow is large, and no internal mechanical movement is required. It only uses the spatial structure to promote the flow of gas and accelerates the gas through the physical structure.

[0043] Using the anti-backflow structure of the rotating detonation combustion chamber of the present application, when air and fuel enter the combustion chamber body 1 in the forward direction, the air and fuel enter the combustion chamber body 1 through the intake channel 321, the connecting channel 322 and the expansion channel 324 in sequence, and the pressure waves and / or combustion products generated in the combustion chamber body 1 are diverted through the arc-shaped reflux channel 323 after passing through the expansion channel 324 and the connecting channel 322 in sequence. 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 road 3232, the pressure wave will go straight and pass through the straight road 3232 and the arc road 3231 in sequence. The forward channel for the flow of air and fuel and the pressure wave return channel are two paths, which effectively reduces the obstruction of the pressure return to the forward entering air and fuel, so that the detonation boost can make up for the loss of total pressure; when the combustion products generated in the combustion chamber body 1 are transmitted back, the combustion products are transmitted back through the expansion channel 324, the connecting channel 322, the straight road 3232 and the arc road 3231 in sequence, which effectively reduces the high temperature of the combustion products that are transmitted back and consumes fuel in advance. At the same time, the fresh air introduced through the arc reflux channel 323 and the entrance of the intake channel 321 cools and dilutes the combustion products, reducing their fuel consumption after entering the intake channel 321 again.

[0044] like Figure 3 As shown, the angle between the intake channel 321 and the straight channel 3232 is 30°-45°; as the angle increases, the reverse blocking performance of the Tesla valve 3 is improved, and when the angle is 45°, the one-way flow performance of the Tesla valve 3 is the best, and when the angle is 30°-45°, the forward conduction performance of the Tesla valve 3 does not change much, but when the angle is greater than 60°, the forward conduction performance of the Tesla valve 3 drops sharply.

[0045] like Figure 4 , Figure 5As shown, the shell 31 includes a first connecting tube 311 , a second connecting tube 312 and a guide block 313 . The first connecting tube 311 is coaxially sleeved outside the second connecting tube 312 , and the guide block 313 is coaxially fixed between the first connecting tube 311 and the second connecting tube 312 .

[0046] like Figure 5 , Figure 6 As shown, the first connecting tube 311 includes a first connecting section 3111, a second connecting section 3112 and a third connecting section 3113 connected in sequence, and the first connecting section 3111, the second connecting section 3112 and the third connecting section 3113 are integrally formed; the second connecting tube 312 includes a fourth connecting section 3121, a fifth connecting section 3122 and a sixth connecting section 3123 connected in sequence, and the fourth connecting section 3121, the fifth connecting section 3122 and the sixth connecting section 3123 are integrally formed; the guide block 313 includes a first straight guide surface 3131, a curved guide surface 3132 and a second straight guide surface 3133 connected in sequence, and an end of the first straight guide surface 3131 away from the curved guide surface 3132 is connected to an end of the second straight guide surface 3133 away from the curved 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 toward 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 arranged on the side of the fifth connecting section 3122 close to the first connecting section 3111, and is located 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 channel 3231 is located between the fourth connecting section 3121 and the arc guide surface 3132, and the straight channel 3232 is located between the second straight guide surface 3133 and the fifth connecting section 3122.

[0047] like Figure 6As shown, a shell 5 is provided on the side of the first connecting cylinder 311 away from the second connecting cylinder 312, and the shell 5 and the first connecting cylinder 311 are integrally formed. A accommodating chamber 6 for accommodating fuel is formed between the shell 5 and the first connecting cylinder 311, and a plurality of injection holes 7 are circumferentially spaced between the accommodating chamber 6 and the air intake passage 321. The injection holes 7 are circumferentially evenly spaced on the first connecting section 3111 and are located on the side of the first connecting section 3111 close to the second connecting section 3112; the fuel is held in the accommodating chamber 6, and the fuel in the accommodating chamber 6 is sprayed into the air intake passage 321 through the injection holes 7. The injection holes 7 are closer to the connecting passage 322 than the entrance of the air intake passage 321, that is, the fuel sprayed from the injection holes 7 enters the second connecting section 3112 along with the air, and the air introduced provides power for the flow of the fuel.

[0048] like Figure 6 , Figure 7 As shown, a plurality of first connecting columns 3134 are installed at equal intervals circumferentially on the first straight guide surface 3131 close to the first connecting section 3111, and the other end of the first connecting column 3134 is connected to the first connecting section 3111; a plurality of second connecting columns 3135 are installed at equal intervals circumferentially on the second straight guide surface 3133 close to the fifth connecting section 3122, and the second connecting columns 3135 are connected to the fifth connecting section 3122.

[0049] The implementation principle of the embodiment 1 of the present application is as follows: when the air and fuel enter the combustion chamber body 1 in the forward direction, the air and fuel enter the combustion chamber body 1 through the intake channel 321, the connecting channel 322 and the expansion channel 324 in sequence; When the pressure wave generated in the combustion chamber body 1 is transmitted back, the pressure wave will sequentially pass through the expansion channel 324 and the connecting channel 322, and after reaching the fork of the intake channel 321 and the straight channel 3232, the pressure wave will go straight and sequentially pass through the straight channel 3232 and the curved channel 3231 to be transmitted back; When the combustion products generated in the combustion chamber body 1 are returned, the combustion products are returned through the expansion channel 324 , the connecting channel 322 , the straight channel 3232 and the arc channel 3231 in sequence.

[0050] Embodiment 2: like Figure 8 , Fig. 9 As shown, the difference between this embodiment and embodiment 1 is that the shell 31 includes a first connecting tube 311, a second connecting tube 312 and a guide block 313, the first connecting tube 311 is coaxially sleeved inside the second connecting tube 312, and the guide block 313 is coaxially fixed between the first connecting tube 311 and the second connecting tube 312.

[0051] The implementation principle of Example 2 is the same as that of Example 1, and will not be repeated here.

[0052] Embodiment 3: like Fig.10 , Fig.11 As shown, the difference between this embodiment and the embodiment 1 is that the first connecting tube 311 further includes an extension section 3114 fixed to the first connecting section 3111 away from the second connecting section 3112, a duct shell 8 is arranged outside the outer shell 5, the duct shell 8 is sleeved on the first connecting tube 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 accommodating chamber 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.

[0053] A plurality of pressure regulating structures 9 are disposed on the second connecting section 3112 and the extending section 3114 . The pressure regulating structures 9 on the second connecting section 3112 and the pressure regulating structures 9 on the extending section 3114 are uniformly distributed circumferentially around the axis of the shell 31 .

[0054] like Fig.11 As shown, the pressure regulating structure 9 includes a gas collecting chamber 91 and a plurality of air inlet holes 92 connected to the gas collecting chamber 91. The air inlet holes 92 on the second connecting section 3112 are opened on the surface of the second connecting section 3112 facing the connecting passage 322. The air inlet holes 92 on the second connecting section 3112 are arranged in groups of three, and the air inlet holes 92 in the same group are evenly distributed along the axial direction of the shell 31, and the air inlet holes 92 in each group are evenly distributed circumferentially around the axis of the shell 31. The gas 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 shell 8, and the air inlet holes 92 are connected to the gas collecting chamber 91 on the second connecting section 3112 and the connecting passage 322.

[0055] like Fig.11 As shown, the air collecting chamber 91 of the pressure regulating structure 9 on the extension section 3114 is formed between the extension section 3114 and the duct shell 8, and the air inlet hole 92 on the extension section 3114 is opened on the extension section 3114, and the air inlet hole 92 of the extension section 3114 is connected to the air inlet 23 and the flow channel 32 on the extension section 3114. The air inlet holes 92 on the extension section 3114 are grouped in three, and the air inlet holes 92 in the same group are uniformly distributed along the axial direction of the shell 31, and the air inlet holes 92 in each group are uniformly distributed circumferentially around the axis of the shell 31. Through the pressure regulating structure 9, the second connecting section 3112 and the extension section 3114 become impedance walls.

[0056] like Fig.10 , Fig.11As shown, an ejection channel 81 is formed between the duct shell 8 and the outer shell 5, the first connecting tube 311 and the combustion chamber body 1. The ejection channel 81 includes a gas collecting channel 811, a boosting channel 812 and an outlet channel 813 arranged in sequence along the arrangement direction from the connecting channel 322 to the expansion channel 324. Each gas collecting cavity 91 is connected to the gas collecting channel 811, and the boosting channel 812 connects the gas collecting channel 811 and the outlet channel 813. The cross-sectional area of ​​the boosting channel 812 decreases along the arrangement direction from the boosting channel 812 to the outlet channel 813. The outlet of the outlet channel 813 faces away from the gas collecting channel 811, and the outlet channel 813 is inclined and faces the outlet of the annular channel 4, and the outlet of the outlet channel 813 is connected to the inlet of the combustion chamber body 1, that is, the outlet of the annular channel 4.

[0057] like Fig.10 , Fig.11 As shown, when the detonation wave is transmitted back, the high-pressure air will enter the air collecting cavity 91 located on the second connecting section 3112 through the air inlet hole 92 located on the second connecting section 3112, and then flow into the injection channel 81. Due to the huge pressure generated by the detonation wave, the positive air in the same axial direction as the detonation wave enters the air collecting cavity 91 located on the extending section 3114 through the air inlet hole 92 located on the extending section 3114, and then flows into the injection channel 81. The air enters the hole in the injection channel 81, and finally is ejected from the air outlet channel 813.

[0058] like Fig.11 , Fig.12 As shown, a plurality of guide vanes 325 are provided in the flow channel 32, and the guide vanes 325 are used to pre-swirl the fuel. The guide vanes 325 are arranged circumferentially around the axis of the shell 31 and are located in the connecting channel 322 and the expansion channel 324. The guide vanes 325 are fixed on the second connecting section 3112, the third connecting section 3113, the fifth connecting section 3122 and the sixth connecting section 3123. Through the guiding effect of the guide vanes 325, the explosive mixture formed by the combination of fuel and air rotates when entering the annular channel 4.

[0059] like Fig.11 , Fig.13 As shown, a plurality of atomizing nozzles 3115 are provided on the extension section 3114, and the atomizing nozzles 3115 are arranged in groups of three. The atomizing nozzles 3115 in the same group are uniformly distributed along the axial direction of the housing 31, and each group of atomizing nozzles 3115 is uniformly distributed circumferentially around the axis of the housing 31, and each atomizing nozzle 3115 is connected to the accommodating chamber 6 through a pipeline. The nozzle of the atomizing nozzle 3115 is located on the side of the extension section 3114 close to the flow channel 32, and the atomizing nozzle 3115 is used to spray atomized fuel. After the fuel sprayed by each atomizing nozzle 3115 is mixed with air to form a mixture, the proportion of fuel in the fuel-air mixture is not greater than 20%.

[0060] like Fig.11 , Fig.13 As shown, the fuel injection holes 7 are arranged in groups of multiple, and the fuel injection holes 7 in the same group are uniformly distributed along the axial direction of the housing 31, and the fuel injection holes 7 in each group are uniformly distributed axially around the axis of the housing 31. In the embodiment of the present application, the fuel injection holes 7 are arranged in groups of four, and the fuel concentration of the fuel-air mixture increases by 20% each time it passes through a fuel injection hole 7, until it increases to 100%. In the embodiment of the present application, the fuel injection holes 7 are fine holes, and in other embodiments, the fuel injection holes 7 can also be directly set as atomizing nozzles.

[0061] The implementation principle of Example 3 of the present application is: the influence of the detonation wave can be reduced as much as possible through the pressure regulating structure 9, so that the incoming flow pressure does not need to be adjusted or only needs to be slightly adjusted, which helps the air supply equipment match the detonation combustion chamber. The high-pressure air transmitted back by the detonation wave and the input air that cannot continue to enter the flow channel 32 due to the impact of the detonation wave are collected into the ejection channel 81 through the pressure regulating structure 9, and ejected through the ejection channel 81, which increases the thrust and expands the pressure difference between the incoming flow pressure and the outlet of the annular channel 4, which helps the subsequent mixing of fuel and air and the continuous supply and input of the explosive mixture.

[0062] Embodiment 4: like Fig.14 , Fig.15 As shown, the difference between this embodiment and embodiment 3 is that a plurality of support blocks 10 are fixedly mounted on the outer wall of the shell 31, and the support blocks 10 are located at the outlet end of the flow channel 32. The plurality of support blocks 10 are arranged at intervals along the circumference of the shell 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 shell 31 is fixedly connected to the inner wall 21 of the duct shell 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 close to the combustion chamber body 1.

[0063] The air inlet 92 at the outlet end of the flow channel 32 is located between two adjacent support blocks 10. Multiple buffer blocks 12 are fixedly installed on both inner side walls of the acceleration channel 11, and the multiple buffer blocks 12 are arranged at intervals along the radial direction of the shell 31. The buffer blocks 12 are arranged in an inclined manner from one side close to the combustion chamber body 1 to the other side and gradually approach the shell 31, and the support block 10 is arranged in a curved manner away from the combustion chamber body 1. The inclined arrangement of the acceleration channel 11 allows the angle between the transmission direction of the acceleration channel 11 and the axis of the shell 31 to be an acute angle.

[0064] The implementation principle of Example 4 of the present application is as follows: combustion and air detonate after combustion inside the annular channel 4 to generate a detonation wave. The return of the detonation wave will increase the resistance of air entering the annular channel 4 from the flow channel 32. After the resistance of the detonation wave to the air increases, the amount of air entering the air collecting chamber 91 from the air inlet 92 at the entrance of the flow channel 32 increases. Then the air in the air collecting chamber 91 at the entrance end of the flow channel 32 enters the air 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 flow rate of the air in the air collecting channel 811. After that, the air enters the acceleration channel 11 again, and the cross-sectional area of ​​the acceleration channel 11 is further reduced, thereby further accelerating the flow rate of the air.

[0065] The air flow speed is accelerated, thereby increasing the pressure difference at both ends of the air inlet hole 92 at the outlet end of the flow channel 32, thereby accelerating the return detonation wave to enter the air collecting cavity 91 from the air inlet hole 92 at the outlet end of the flow channel 32. By accelerating the return detonation wave to enter the air collecting cavity 91 from the air inlet hole 92 at the outlet end of the flow channel 32, it is convenient to reduce the resistance of the return detonation wave to the air, thereby facilitating the air to enter the annular channel 4 from the flow channel 32.

[0066] After the detonation wave enters the gas collecting chamber 91 from 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, thereby reducing the occurrence of impact deformation and damage to the duct shell 8. At the same time, the inclination of the buffer block 12 is conducive to guiding the detonation wave to flow toward the outlet of the injection channel 81, thereby increasing the thrust provided by the air ejected from the injection channel 81.

[0067] Embodiment 5: like Fig.16 , Fig.17 As shown, the difference between this embodiment and embodiment 3 is that a shielding ring 13 is fixedly installed near the inner wall 21 of the duct shell 8 at the inlet end of the flow channel 32, and the shielding ring 13 is tangent to the edge of the air inlet hole 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. The outer wall of the combustion chamber body 1 is provided with a plurality of heat dissipation grooves 14, which 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.

[0068] The implementation principle of the embodiment 5 of the present application is as follows: when the detonation wave is transmitted back, the shielding ring 13 reduces the amount of the detonation wave transmitted back to the flow channel 32, allowing the detonation wave to enter the inside of the air collecting cavity 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 inclination of the shielding ring 13 facilitates the guidance of the air from the flow channel 32 into the annular channel 4, thereby reducing the resistance of the shielding ring 13 to the air.

[0069] When the air flows in the injection channel 81, the air will take away the heat of the outer wall of the combustion chamber body 1, thereby facilitating the heat dissipation of the combustion chamber body 1. At the same time, the contact area between the outer wall of the combustion chamber body 1 and the air is increased through the heat dissipation groove 14, thereby improving the heat dissipation capacity.

[0070] The above are all preferred embodiments of the present application, and the protection scope of the present application is not limited thereto. Therefore, any equivalent changes made according to the structure, shape, and principle of the present application should be included in the protection scope of the present application.

Claims

1. A rotating detonation combustion chamber with a pressure regulating structure and an ejection channel, characterized in that: The duct shell (8) comprises a combustion chamber body (1) and a Tesla valve (3) located at the inlet of the combustion chamber body (1), wherein the combustion chamber body (1) has an annular channel (4), and the Tesla valve (3) comprises a shell (31) and a flow channel (32), wherein one end of the shell (31) is fixedly connected to one end of the duct shell (8), and the other end of the shell (31) is coaxially connected to the combustion chamber body (1), and the flow channel (32) is coaxially arranged in the shell (31), and the inlet end of the flow channel (32) is used for introducing air, and the outlet end of the flow channel (32) is communicated with the annular channel (4) inside the combustion chamber body (1); An ejection 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 the inlet end of the flow channel (32) and the outlet end of the flow channel (32); the pressure regulating structure (9) comprises a gas collecting chamber (91) and an air inlet hole (92) for connecting the gas collecting chamber (91) and the flow channel (32); the ejection channel is connected to the gas collecting chamber (91).

2. A rotating detonation combustion chamber with a pressure regulating structure and an ejection channel according to claim 1, characterized in that: The ejection channel comprises an air collecting channel (811), a pressure-boosting channel (812) and an air outlet channel (813) which are connected in sequence; the air collecting channel (811) is connected to each of the air collecting cavities (91); and one end of the air outlet channel (813) away from the pressure-boosting channel (812) is located at the outlet of the combustion chamber body (1).

3. A rotating detonation combustion chamber with a pressure regulating structure and an ejection channel according to claim 1, characterized in that: An outer shell (5) is fixedly mounted on the outer wall of the shell (31), a receiving chamber (6) for receiving fuel is formed between the outer shell (5) and the shell (31), and the shell (31) is provided with a plurality of fuel injection holes (7) communicating with the receiving chamber (6) and the flow channel (32).

4. A rotating detonation combustion chamber with a pressure regulating structure and an ejection 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 hole (92) at the outlet end of the flow channel (32), 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).

5. The rotary detonation combustion chamber with a pressure regulating structure and an ejection channel according to claim 1, characterized in that: A plurality of support blocks (10) are fixedly mounted on the shell (31) at a position at the outlet of the flow channel (32). The plurality of support blocks (10) are arranged at intervals along the circumference of the shell (31), and an acceleration channel (11) is formed between two adjacent support blocks (10). A side of the support block (10) away from the shell (31) is fixedly connected to an inner wall of the duct shell (8), and an air inlet (92) located at the outlet end of the flow channel (32) is located between two adjacent support blocks (10).

6. A rotating detonation combustion chamber with a pressure regulating structure and an ejection channel according to claim 5, characterized in that: A plurality of buffer blocks (12) are fixedly mounted on both inner side walls of the acceleration channel (11), and the plurality of buffer blocks (12) are arranged at intervals along the radial direction of the housing (31).

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

8. The rotating detonation combustion chamber with a pressure regulating structure and an ejection channel according to claim 5, 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 an acute angle.

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

10. The rotating detonation combustion chamber with a pressure regulating structure and an ejection 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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