Pulse detonation turbine engine

Abstract

The invention relates to the technical field of aero-engines, and discloses a pulse detonation turbine engine which comprises an air inlet assembly, a supercharging assembly, a combustion chamber casing, a pulse detonation combustion chamber, a nozzle assembly, a transition assembly and an exhaust assembly. The first end of the pulse detonation combustion chamber is provided with a first channel and a second channel, and the second end is provided with a first exhaust channel and extends outwards from the combustion chamber casing. A two-way channel is formed between the combustion chamber casing and the pulse detonation combustion chamber, and the two-way channel is communicated with the first channel; the transition assembly is arranged at the end, close to the exhaust direction, of the pressurization assembly and communicates with the second channel. The two channels are formed between the pulse detonation combustion chamber and the combustion chamber casing, the intensity of return detonation can be effectively weakened through the cavity effect of the two channels, and then the return pressure faced by the pressurization assembly is reduced; meanwhile, after air enters the two channels through the pressurizing assembly, the wall face of the pulse detonation combustion chamber can be cooled.

Description

Technical Field

[0001] This invention relates to the field of aero-engine technology, specifically to a pulse detonation turbine engine. Background Technology

[0002] The combustion mode of a conventional aero-engine combustor can be approximated as isobaric combustion, with a small pressure difference between the combustor inlet and outlet. Unlike conventional combustor combustion, pulse detonation combustion is a pressurized combustion process, approximating isochoric combustion. The working fluid gains pressure gain after passing through the pulse detonation combustor, resulting in a higher outlet pressure than inlet pressure. Under the same engine inlet parameters, turbine engines based on pulse detonation combustion exhibit higher cycle thermal efficiency and work capacity than conventional turbine engines based on isobaric combustion.

[0003] While pulse detonation turbine engines have significant theoretical advantages, their engineering applications also present some challenges. In addition to the downstream-propagating detonation wave, the detonation chamber also generates an upstream-propagating "return detonation wave." Although the intensity of the "return detonation wave" is less than that of the detonation wave, it still significantly affects the operation of the upstream compressor, thereby impacting engine performance. Summary of the Invention

[0004] This invention provides a pulse detonation turbine engine to solve the problem of the impact of the back-transmitted detonation wave on the operation of the upstream compressor.

[0005] In a first aspect, the present invention provides a pulse detonation turbocharger engine, comprising an intake assembly, a booster assembly, a combustion chamber casing, a pulse detonation combustion chamber, a nozzle assembly, a transition assembly, and an exhaust assembly; one end of the booster assembly is connected to and communicates with the intake assembly; the combustion chamber casing is connected to the other end of the booster assembly; along the engine axial direction, the pulse detonation combustion chamber has a first end and a second end, the first end having a first channel and a second channel, and the second end having a first exhaust channel extending outward from the combustion chamber casing; two channels are formed between the combustion chamber casing and the pulse detonation combustion chamber, and the two channels communicate with the first channel. The combustion chamber housing is connected to the first exhaust channel; the nozzle assembly penetrates the combustion chamber housing, the nozzle assembly has a nozzle orifice disposed within the pulse detonation combustion chamber, and the nozzle assembly is adapted to inject fuel and ignite the pulse detonation combustion chamber; along the engine axial direction, the transition assembly is disposed at one end of the supercharger assembly near the exhaust direction, the transition assembly is connected to the second channel, and the transition assembly is drively connected to the supercharger assembly; the exhaust assembly includes an exhaust housing, the exhaust housing is connected to the combustion chamber housing, the exhaust housing has an exhaust port, the exhaust port is connected to the first exhaust channel, and the exhaust port is connected to the transition assembly.

[0006] Beneficial effects: By forming two channels between the pulse detonation combustion chamber and the combustion chamber casing, the cavity effect of the two channels can effectively weaken the intensity of the back detonation, thereby reducing the back pressure faced by the supercharger assembly; at the same time, after the air enters the two channels from the supercharger assembly, it can cool the wall of the pulse detonation combustion chamber.

[0007] In one optional embodiment, the pulse detonation combustion chamber includes a flow guiding structure and a detonation combustion structure. The detonation combustion structure is connected to the flow guiding structure. The end of the detonation combustion structure away from the flow guiding structure has a first exhaust channel, and the end of the detonation combustion structure close to the flow guiding structure has a first channel. The first channel is a swirling air intake channel. A second channel is formed within the flow guiding structure, and the nozzle is disposed within the detonation combustion structure.

[0008] Beneficial effects: The swirl intake channel generates pre-swirl during intake, enhancing fuel-air mixing, thereby reducing the transition distance from detonation to knock, reducing the length of the knock chamber flow direction (along the flow direction), increasing the operating frequency of the knock chamber, and further reducing the intensity of the return knock wave entering the two channels; the guide structure introduces part of the return knock wave into the transition component and drives the turbine to do work, improving the utilization rate of high-temperature gas.

[0009] In one optional embodiment, the combustion chamber casing includes an inner combustion chamber casing and an outer combustion chamber casing. The outer combustion chamber casing is connected to the supercharging assembly and the detonation combustion structure, respectively. The inner combustion chamber casing is connected to the detonation combustion structure, and the flow guiding structure is disposed through the inner combustion chamber casing.

[0010] In one optional embodiment, the supercharging assembly includes a compressor and a compressor housing. The two ends of the compressor housing are respectively connected to the intake assembly and the combustion chamber housing. The compressor is disposed inside the compressor housing. The inlet of the compressor is connected to the intake assembly, and the outlet of the compressor is connected to the two channels. The compressor is drivenly connected to the transition assembly.

[0011] Beneficial effects: The compressor casing achieves a sealed connection between the intake components and the combustion chamber casing, ensuring airflow boosting efficiency; the compressor is directly connected to the two channels, reducing intake losses, and the transmission of the transition components achieves a stable power cycle.

[0012] In one optional embodiment, the transition assembly includes a transition casing, a radial turbine, and a turbine casing. The radial turbine is disposed within the turbine casing, the turbine casing is connected to the pulse detonation combustion chamber, the turbine casing is connected to the transition casing, the transition casing is connected to the combustion chamber casing, the radial turbine communicates with the second channel, the radial turbine is drivenly connected to the compressor, a transition channel is formed within the transition casing, and the transition channel communicates with the exhaust assembly.

[0013] Beneficial effects: The radial turbine receives the energy of the return detonation wave and drives the turbine to operate, which in turn drives the compressor, improving energy utilization; the transition channel diverts the gas that the radial turbine has worked on to the exhaust assembly for discharge, increasing engine thrust.

[0014] In one optional embodiment, the transition casing includes an inner transition casing and an outer transition casing, the inner transition casing and the outer transition casing being spaced apart to form the transition channel, the outer transition casing being connected to the turbine casing, and the outer transition casing being connected to the combustion chamber casing. The transition assembly further includes a first support plate and a second support plate, the first support plate being disposed between the inner transition casing and the outer transition casing, and the second support plate being disposed between the outer transition casing and the combustion chamber casing.

[0015] Beneficial effects: By setting the first and second support plates, load transfer between the casings is achieved, improving the overall load-bearing capacity of the structure.

[0016] In one alternative embodiment, the exhaust assembly further includes an exhaust cone connected to the transition inner casing, and a second exhaust passage is formed between the exhaust cone and the transition outer casing, the second exhaust passage communicating with the exhaust port.

[0017] Beneficial effects: The second exhaust channel formed by the exhaust cone and the transition outer casing optimizes the airflow discharge path and reduces exhaust resistance; combined with multi-channel airflow mixing, it improves exhaust stability and indirectly enhances engine thrust output.

[0018] In one alternative embodiment, the exhaust assembly further includes a lobe mixer disposed at one end of the transition casing near the exhaust port. The lobe mixer has a first guide surface and a second guide surface, the first guide surface being adapted to guide the airflow of the first exhaust passage and the second guide surface being adapted to guide the airflow of the second exhaust passage.

[0019] Beneficial effect: By setting up a wavelet mixer, the mixing of the airflow at the knock chamber outlet and the airflow at the turbine outlet is enhanced to reduce exhaust losses.

[0020] In one alternative embodiment, the intake assembly includes an intake casing and an intake cone, the intake casing being connected to the booster assembly, the intake cone being disposed within the intake casing, and the intake cone being disposed at the end of the booster assembly away from the transition assembly.

[0021] Beneficial effects: The intake cone optimizes the intake airflow and improves the smoothness of air entering the compressor; the intake casing and the supercharging components are sealed together to reduce intake leakage and ensure the compressor's supercharging efficiency.

[0022] In one alternative embodiment, the nozzle assembly includes a fuel nozzle and an ignition nozzle, both of which penetrate the combustion chamber casing and extend into the pulse detonation combustion chamber, with the ignition nozzle positioned on the side of the fuel nozzle near the exhaust assembly. Attached Figure Description

[0023] To more clearly illustrate the specific embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the specific embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of the present invention. For those skilled in the art, other drawings can be obtained from these drawings without creative effort.

[0024] Figure 1 This is a schematic diagram of the structure of a pulse detonation turbine engine according to an embodiment of the present invention; Figure 2 This is a schematic diagram of the structure of a pulse detonation turbine engine in related technologies.

[0025] Explanation of reference numerals in the attached figures: 10. Intake assembly; 11. Intake casing; 12. Intake cone; 20. Turbocharger assembly; 21. Compressor; 211. Centrifugal impeller; 22. Compressor casing; 30. Combustion chamber casing; 31. Inner combustion chamber casing; 32. Outer combustion chamber casing; 40. Pulse detonation combustion chamber; 41. Flow guide structure; 42. Detonation combustion structure; 43. First passage; 44. Second passage; 45. First exhaust passage; 50. Nozzle assembly; 51. Fuel nozzle; 52. 60. Ignition nozzle; 61. Transition assembly; 62. Transition casing; 63. Transition inner casing; 64. Transition outer casing; 75. Radial turbine; 76. Turbine casing; 77. Exhaust assembly; 78. Exhaust casing; 79. Exhaust port; 70. Exhaust cone; 71. Lobe mixer; 72. First guide surface; 73. Second guide surface; 84. First support plate; 85. Second support plate; 86. Third support plate; 87. Second exhaust passage; 88. Inlet guide vane. Detailed Implementation

[0026] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0027] The following is combined with Figure 1 The following describes embodiments of the present invention.

[0028] According to an embodiment of the present invention, a pulse detonation turbocharger engine is provided, comprising an intake assembly 10, a booster assembly 20, a combustion chamber housing 30, a pulse detonation combustion chamber 40, a nozzle assembly 50, a transition assembly 60, and an exhaust assembly 70; one end of the booster assembly 20 is connected to and communicates with the intake assembly 10; the combustion chamber housing 30 is connected to the other end of the booster assembly 20; along the engine axial direction, the pulse detonation combustion chamber 40 has a first end and a second end, the first end having a first channel 43 and a second channel 44, and the second end having a first exhaust channel 45 extending outward from the combustion chamber housing 30; two channels are formed between the combustion chamber housing 30 and the pulse detonation combustion chamber 40, and the two channels communicate with... The first channel 43 is connected; the nozzle assembly 50 penetrates the combustion chamber casing 30, and the nozzle assembly 50 has a nozzle orifice disposed within the pulse detonation combustion chamber 40. The nozzle assembly 50 is adapted to inject fuel and ignite into the pulse detonation combustion chamber 40; along the engine axial direction, the transition assembly 60 is disposed at one end of the supercharger assembly 20 near the exhaust direction, the transition assembly 60 is connected to the second channel 44, and the transition assembly 60 is drively connected to the supercharger assembly 20; the exhaust assembly 70 includes an exhaust casing 71, the exhaust casing 71 is connected to the combustion chamber casing 30, the exhaust casing 71 has an exhaust port 711, the exhaust port 711 is connected to the first exhaust channel 45, and the exhaust port 711 is connected to the transition assembly 60.

[0029] The pulse detonation turbine engine of this embodiment forms two channels between the pulse detonation combustion chamber 40 and the combustion chamber casing 30. The cavity effect of the two channels can effectively weaken the intensity of the back-transmission detonation, thereby reducing the back-transmission pressure faced by the booster assembly 20. At the same time, after the air enters the two channels from the booster assembly 20, it can cool the wall of the pulse detonation combustion chamber 40.

[0030] Specifically, such as Figure 1 As shown, a third support plate 83 is also provided between the exhaust casing 71 and the combustion chamber casing 30 to realize load transfer between the structures and improve structural stability.

[0031] Specifically, air enters the supercharger assembly 20 through the intake assembly 10, and after being pressurized by the supercharger assembly 20, it enters the two channels. The airflow from the two channels enters the pulse detonation combustion chamber 40 through the first channel 43. The airflow entering the pulse detonation combustion chamber 40 mixes with the fuel injected by the nozzle assembly 50 to form a combustible mixture, which then fills the combustion chamber. The combustible mixture is ignited by the nozzle assembly 50 to form a slow combustion wave. As the slow combustion wave develops, when the pressure and temperature increase to a certain level, local explosion centers are formed. These local explosion centers develop downstream and eventually form a detonation wave. The shock wave is discharged backward through the first exhaust channel 45 from the pulse detonation combustion chamber 40. On the other hand, it forms a return detonation wave that propagates upstream. The return detonation wave enters the transition component 60 through the second channel 44. During the upstream propagation of the return detonation wave, a small portion will enter the two channels in reverse through the first channel 43. The buffering effect of the two channels reduces the pressure peak and propagation distance of the return detonation wave, thereby reducing its impact on the upstream booster component 20. At the same time, when the pulse detonation combustion chamber 40 is in the filling process, the airflow in the two channels can cool the wall of the pulse detonation combustion chamber 40.

[0032] When the engine is running, the detonation wave from the pulse detonation combustion chamber 40 forms an intermittent high-speed exhaust. Outside air, under the ejector effect of the exhaust from the pulse detonation combustion chamber 40, enters the engine through the channel formed by the combustion chamber casing 30 and the exhaust casing 71. Simultaneously, the combustion gas flowing through the transition assembly 60 flows towards the engine's rear. The ejected air, the combustion gas from the pulse detonation combustion chamber 40, and the combustion gas from the transition assembly 60 mix and are ultimately expelled from the engine to generate thrust.

[0033] It should be noted that, as Figure 2 The image shows a pulse detonation turbine engine in the related art. To distinguish it from the related art, when describing the structure of the related art, 1' is used as the designation for the compressor, 2' as the designation for the radial diffuser, 3' as the designation for the axial diffuser, 4' as the designation for the detonation combustion chamber, 5' as the designation for the turbine, and 6' as the designation for the shaft.

[0034] In related technologies, such as Figure 2As shown, a radial diffuser 2' and an axial diffuser 3' are installed between the outlet of compressor 1' and the detonation combustion chamber 4'. Typically, a dedicated back pressure suppression structure is installed within the flow channel between the axial diffuser 3' and the detonation combustion chamber 4' to reduce the back pressure peak and propagation distance. However, this design makes the back pressure suppression structure very difficult, resulting in poor engineering practicality and making it difficult to effectively suppress back pressure under all engine operating conditions. Furthermore, the complex back pressure suppression structure leads to significant intake losses in the detonation combustion chamber 4', which greatly affects the overall engine performance. In addition, in related technologies, the outlet airflow of compressor 1' flows directly into the detonation combustion chamber 4', where combustion and mixing occur inside the chamber, without dedicated cooling air to cool the walls of the detonation combustion chamber 4'.

[0035] In this application, a dual-channel system is formed between the combustion chamber casing 30 and the pulse detonation combustion chamber 40. The cavity effect of the dual-channel system effectively weakens the back-transmission detonation intensity and reduces the back-transmission pressure faced by the compressor 21. At the same time, when the supercharger 20 pressurizes the air and inputs it into the dual-channel system, the cavity of the dual-channel system can be used to cool the wall of the pulse detonation combustion chamber 40, thereby improving the engine temperature control capability and reducing the impact of prolonged high combustion chamber temperature on engine performance.

[0036] It should be noted that the pulse detonation turbine engine structure in related technologies, such as Figure 2 As shown, in related technologies, the outlet of the detonation combustion chamber 4' is directly connected to the inlet of the turbine 5', and the strong unsteady characteristics of the outlet of the detonation combustion chamber 4' make it difficult to guarantee the efficiency of the turbine 5'.

[0037] In this application, the return detonation wave generated by the pulse detonation combustion chamber 40 is transmitted back to the transition component 60 through the second channel 44. Compared with the related technology that directly uses the detonation wave to drive the turbine, the unsteady characteristics of the return detonation wave are significantly reduced. The degree of change of key parameters such as pressure, temperature, and speed within a working cycle is significantly weaker than that of the detonation wave. The time proportion of the pressure plateau region within a working cycle is significantly increased. This is beneficial to improving the working efficiency of the turbine in the transition component 60 and reducing the aerodynamic design difficulty of the turbine.

[0038] In one embodiment, such as Figure 1 As shown, the pulse detonation combustion chamber 40 includes a flow guiding structure 41 and a detonation combustion structure 42. The detonation combustion structure 42 is connected to the flow guiding structure 41. The end of the detonation combustion structure 42 away from the flow guiding structure 41 has a first exhaust passage 45, and the end of the detonation combustion structure 42 close to the flow guiding structure 41 has a first channel 43. The first channel 43 is a swirling air intake channel. A second channel 44 is formed inside the flow guiding structure 41, and the nozzle is disposed inside the detonation combustion structure 42.

[0039] Specifically, the flow guiding structure 41 is provided with an inlet guide vane 85 on the side near the transition component 60 to rectify the airflow.

[0040] In one embodiment, such as Figure 1 As shown, the combustion chamber casing 30 includes an inner combustion chamber casing 31 and an outer combustion chamber casing 32. The outer combustion chamber casing 32 is connected to the booster assembly 20 and the detonation combustion structure 42, respectively. The inner combustion chamber casing 31 is connected to the detonation combustion structure 42, respectively. The flow guiding structure 41 is disposed through the inner combustion chamber casing 31.

[0041] It should be noted that in the pulse detonation turbine engine of the relevant technology, the airflow direction entering the detonation combustion chamber is generally parallel to the axial direction of the detonation tube. The mixing and filling of airflow and fuel inside the detonation chamber requires a long time and distance, which results in a long detonation distance and detonation chamber length.

[0042] It is worth noting that the swirl intake channel generates pre-swirl during intake, which enhances the mixing of fuel and air, thereby reducing the distance of the transition from detonation to knock, reducing the length of the knock chamber flow direction (along the flow direction), increasing the operating frequency of the knock chamber, and further reducing the intensity of the return knock wave entering the two channels; the flow guiding structure 41 introduces part of the return knock wave into the transition component 60 and drives the turbine to do work, improving the utilization rate of high-temperature gas.

[0043] In one embodiment, such as Figure 1 As shown, the supercharger assembly 20 includes a compressor 21 and a compressor housing 22. The two ends of the compressor housing 22 are connected to the intake assembly 10 and the combustion chamber housing 30, respectively. The compressor 21 is disposed inside the compressor housing 22. The inlet of the compressor 21 is connected to the intake assembly 10, and the outlet of the compressor 21 is connected to the two channels. The compressor 21 is drivenly connected to the transition assembly 60.

[0044] Specifically, air enters the compressor 21, and after being pressurized by the centrifugal impeller 211 of the compressor 21, it flows out of the compressor 21, and the airflow at the outlet of the compressor 21 enters the two channels.

[0045] Specifically, the compressor casing 22 is sealed to the combustion chamber casing 32; furthermore, an inlet guide vane 85 is provided at the outlet of the compressor 21 to rectify the airflow.

[0046] It is worth noting that the compressor casing 22 achieves a sealed connection between the intake assembly 10 and the combustion chamber casing 30, ensuring airflow boosting efficiency; the compressor 21 is directly connected to the two channels, reducing intake losses, and works with the transition assembly 60 to achieve a stable power cycle.

[0047] In one embodiment, such as Figure 1As shown, the transition assembly 60 includes a transition casing 61, a radial turbine 62, and a turbine casing 63. The radial turbine 62 is disposed within the turbine casing 63. The turbine casing 63 is connected to the pulse detonation combustion chamber 40. The turbine casing 63 is connected to the transition casing 61. The transition casing 61 is connected to the combustion chamber casing 30. The radial turbine 62 communicates with the second channel 44 and is drivenly connected to the compressor 21. A transition channel is formed within the transition casing 61, and the transition channel communicates with the exhaust assembly 70.

[0048] Specifically, such as Figure 1 As shown, the transition casing 61 includes an inner transition casing 611 and an outer transition casing 612. The inner transition casing 611 and the outer transition casing 612 are spaced apart to form a transition channel. The outer transition casing 612 is connected to the turbine casing 63 and the combustion chamber casing 30. The transition assembly 60 also includes a first support plate 81 and a second support plate 82. The first support plate 81 is disposed between the inner transition casing 611 and the outer transition casing 612, and the second support plate 82 is disposed between the outer transition casing 612 and the combustion chamber casing 30.

[0049] Specifically, such as Figure 1 As shown, the two ends of the turbine casing 63 are connected to the flow guide structure 41 and the transition outer casing 612, respectively, and the transition outer casing 612 is connected to the combustion chamber casing 31.

[0050] It is worth noting that the radial turbine 62 receives the energy of the return detonation wave and drives the turbine to operate, which in turn drives the compressor 21, improving energy utilization. The transition channel diverts the gas produced by the radial turbine 62 to the exhaust assembly 70 for discharge, increasing engine thrust. By setting the first support plate 81 and the second support plate 82, load transfer between the casings is realized, improving the overall structure's load resistance.

[0051] In one embodiment, such as Figure 1 As shown, the exhaust assembly 70 also includes an exhaust cone 72, which is connected to the transition inner casing 611. A second exhaust passage 84 is formed between the exhaust cone 72 and the transition outer casing 612, and the second exhaust passage 84 is connected to the exhaust port 711.

[0052] It is worth noting that the second exhaust channel 84 formed by the exhaust cone 72 and the transition outer casing 612 optimizes the airflow discharge path and reduces exhaust resistance; in conjunction with multi-channel airflow mixing, it improves exhaust stability and indirectly enhances engine thrust output.

[0053] In one embodiment, such as Figure 1As shown, the exhaust assembly 70 also includes a lobe mixer 73, which is disposed at one end of the transition casing 61 near the exhaust port 711. The lobe mixer 73 has a first guide surface 731 and a second guide surface 732. The first guide surface 731 is adapted to guide the airflow of the first exhaust passage 45, and the second guide surface 732 is adapted to guide the airflow of the second exhaust passage 84.

[0054] Specifically, the ejector air, the combustion gas discharged from the pulse detonation combustion chamber 40, and the combustion gas discharged from the second exhaust passage 84 are mixed at the lobe mixer 73 and finally discharged from the engine to generate thrust.

[0055] It is worth noting that by setting up the wavelet mixer 73, the mixing of the airflow at the knock chamber outlet and the airflow at the turbine outlet is enhanced to reduce exhaust losses.

[0056] In one embodiment, such as Figure 1 As shown, the intake assembly 10 includes an intake casing 11 and an intake cone 12. The intake casing 11 is connected to the supercharger assembly 20. The intake cone 12 is disposed inside the intake casing 11 and is located at the end of the supercharger assembly 20 away from the transition assembly 60.

[0057] It is worth noting that the intake cone 12 optimizes the intake airflow and improves the smoothness of air entering the compressor 21; the intake casing 11 is sealed to the booster assembly 20 to reduce intake leakage and ensure the boosting efficiency of the compressor 21.

[0058] In one embodiment, such as Figure 1 As shown, the nozzle assembly 50 includes a fuel nozzle 51 and an ignition nozzle 52. Both the fuel nozzle 51 and the ignition nozzle 52 penetrate the combustion chamber casing 30 and extend into the pulse detonation combustion chamber 40. The ignition nozzle 52 is located on the side of the fuel nozzle 51 near the exhaust assembly 70.

[0059] The working principle of the pulse detonation turbine engine in this embodiment is as follows: Air enters the compressor 21 through the intake channel formed by the intake cone 12 and the intake casing 11, and then flows out of the compressor 21 after being pressurized by the centrifugal impeller 211. The airflow from the compressor 21 outlet enters the two channels, and the airflow in the two channels rotates through the first channel 43 (swirling intake channel) and enters the pulse detonation combustion chamber 40. The rotating airflow entering the pulse detonation combustion chamber 40 mixes with the fuel injected through the fuel nozzle 51 to form a combustible mixture and fills the combustion chamber. The combustible mixture is ignited by the ignition electrode to form a slow combustion wave. As the slow combustion wave develops, when the pressure and temperature increase to a certain level, local explosion centers are formed. These local explosion centers, on the one hand, flow downstream... The detonation wave develops and eventually forms, and is discharged backward from the pulse detonation combustion chamber 40. On the other hand, a return detonation wave is formed and propagates upstream. The return detonation wave enters the centripetal turbine 62 through the return detonation channel formed by the guide structure 41 and the turbine casing 63 and drives the centripetal turbine 62 to do work, thereby driving the centrifugal compressor 21. During the upstream propagation of the return detonation wave, a small portion will enter the second channel in reverse through the first channel 43 (swirl inlet channel). The buffering effect of the cavity of the second channel is used to reduce the pressure peak and propagation distance of the return detonation wave, thereby reducing its impact on the upstream compressor 21. At the same time, when the pulse detonation combustion chamber 40 is in the filling process, the airflow in the second channel can cool the wall surface of the pulse detonation combustion chamber 40.

[0060] When the engine is running, the detonation wave from the pulse detonation combustion chamber 40 forms an intermittent high-speed exhaust. Outside air, under the ejector effect of the exhaust from the pulse detonation combustion chamber 40, enters the engine through the passage between the outer casing 32 and the exhaust casing 71. Simultaneously, the combustion gases flowing through the radial turbine 62 enter the second exhaust passage 84 and flow towards the engine's rear. The ejected air, the combustion gases from the pulse detonation combustion chamber 40, and the combustion gases from the transition assembly 60 mix and are ultimately expelled from the engine to generate thrust.

[0061] Although embodiments of the invention have been described in conjunction with the accompanying drawings, those skilled in the art can make various modifications and variations without departing from the spirit and scope of the invention, and such modifications and variations all fall within the scope defined by the appended claims.

Claims

1. A pulse detonation turbine engine, characterized in that, include: Intake assembly (10); A booster assembly (20), one end of which is connected to and communicates with the intake assembly (10); Combustion chamber housing (30), which is connected to the other end of the supercharger assembly (20); The pulse detonation combustion chamber (40) is located along the engine axis. The pulse detonation combustion chamber (40) has a first end and a second end. The first end has a first channel (43) and a second channel (44). The second end has a first exhaust channel (45) and extends outward from the combustion chamber casing (30). Two channels are formed between the combustion chamber casing (30) and the pulse detonation combustion chamber (40). The two channels are connected to the first channel (43). The nozzle assembly (50) extends through the combustion chamber casing (30) and has a nozzle orifice disposed within the pulse detonation combustion chamber (40). The nozzle assembly (50) is adapted to inject fuel and ignite the pulse detonation combustion chamber (40). A transition assembly (60) is located along the engine axis and is disposed at one end of the booster assembly (20) near the exhaust direction. The transition assembly (60) is connected to the second channel (44) and is drively connected to the booster assembly (20). An exhaust assembly (70) includes an exhaust casing (71) connected to the combustion chamber casing (30), the exhaust casing (71) having an exhaust port (711) connected to the first exhaust passage (45) and the exhaust port (711) connected to the transition assembly (60).

2. The pulse detonation turbine engine according to claim 1, characterized in that, The pulse detonation combustion chamber (40) includes a flow guiding structure (41) and a detonation combustion structure (42). The detonation combustion structure (42) is connected to the flow guiding structure (41). The end of the detonation combustion structure (42) away from the flow guiding structure (41) has a first exhaust channel (45). The end of the detonation combustion structure (42) close to the flow guiding structure (41) has a first channel (43). The first channel (43) is a swirling air intake channel. The second channel (44) is formed inside the flow guiding structure (41). The nozzle is disposed inside the detonation combustion structure (42).

3. The pulse detonation turbine engine according to claim 2, characterized in that, The combustion chamber casing (30) includes an inner combustion chamber casing (31) and an outer combustion chamber casing (32). The outer combustion chamber casing (32) is connected to the booster assembly (20) and the detonation combustion structure (42) respectively. The inner combustion chamber casing (31) is connected to the detonation combustion structure (42) respectively. The flow guiding structure (41) is disposed through the inner combustion chamber casing (31).

4. The pulse detonation turbine engine according to any one of claims 1-3, characterized in that, The booster assembly (20) includes a compressor (21) and a compressor housing (22). The two ends of the compressor housing (22) are connected to the intake assembly (10) and the combustion chamber housing (30) respectively. The compressor (21) is disposed in the compressor housing (22). The inlet of the compressor (21) is connected to the intake assembly (10), and the outlet of the compressor (21) is connected to the two channels. The compressor (21) is drivenly connected to the transition assembly (60).

5. The pulse detonation turbine engine according to claim 4, characterized in that, The transition assembly (60) includes a transition casing (61), a radial turbine (62), and a turbine casing (63). The radial turbine (62) is disposed within the turbine casing (63). The turbine casing (63) is connected to the pulse detonation combustion chamber (40). The turbine casing (63) is connected to the transition casing (61). The transition casing (61) is connected to the combustion chamber casing (30). The radial turbine (62) communicates with the second channel (44). The radial turbine (62) is drivenly connected to the compressor (21). A transition channel is formed within the transition casing (61). The transition channel communicates with the exhaust assembly (70).

6. The pulse detonation turbine engine according to claim 5, characterized in that, The transition casing (61) includes an inner transition casing (611) and an outer transition casing (612), which are spaced apart to form the transition channel. The outer transition casing (612) is connected to the turbine casing (63) and the combustion chamber casing (30). The transition assembly (60) also includes a first support plate (81) and a second support plate (82), which are disposed between the inner transition casing (611) and the outer transition casing (612) and between the outer transition casing (612) and the combustion chamber casing (30).

7. The pulse detonation turbine engine according to claim 6, characterized in that, The exhaust assembly (70) further includes an exhaust cone (72) connected to the transition inner casing (611), and a second exhaust passage (84) is formed between the exhaust cone (72) and the transition outer casing (612), and the second exhaust passage (84) is connected to the exhaust port (711).

8. The pulse detonation turbine engine according to claim 7, characterized in that, The exhaust assembly (70) further includes a beam mixer (73) disposed at one end of the transition casing (61) near the exhaust port (711). The beam mixer (73) has a first guide surface (731) and a second guide surface (732). The first guide surface (731) is adapted to guide the airflow of the first exhaust passage (45), and the second guide surface (732) is adapted to guide the airflow of the second exhaust passage (84).

9. The pulse detonation turbine engine according to any one of claims 1-3, characterized in that, The intake assembly (10) includes an intake casing (11) and an intake cone (12). The intake casing (11) is connected to the booster assembly (20). The intake cone (12) is disposed inside the intake casing (11) and is disposed at the end of the booster assembly (20) away from the transition assembly (60).

10. The pulse detonation turbine engine according to any one of claims 1-3, characterized in that, The nozzle assembly (50) includes a fuel nozzle (51) and an ignition nozzle (52), both of which penetrate the combustion chamber housing (30) and extend into the pulse detonation combustion chamber (40). The ignition nozzle (52) is located on the side of the fuel nozzle (51) near the exhaust assembly (70).

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