Wave rotor turbine and aircraft engine

Abstract

The application relates to the technical field of turbine structure design, and discloses a wave rotor turbine and an aero-engine. The wave rotor turbine comprises a hub cylinder, turbine blades, end plates and igniters. The hub cylinder is suitable for being rotatably arranged around a first output shaft; the turbine blades are arranged in a plurality of groups; the turbine blades are arranged on the hub cylinder at intervals; two adjacent turbine blades and the hub cylinder form a combustion chamber; the end plates are arranged at two ends of the hub cylinder; the end plates are fixedly arranged; at least one opening is arranged on the end plate; the opening is periodically and communicatively arranged with each combustion chamber; and the igniter is arranged on the end plate and is arranged at intervals with the opening. The wave rotor turbine integration technology is adopted; the combustion chamber and the turbine of a conventional engine are integrated into one component; the double-rotor structure is simplified into a single-rotor structure; the system complexity can be greatly reduced; the power-to-weight ratio and the energy utilization rate can be improved; and the wave rotor turbine has good potential for shortening the axial length of the engine.

Description

Technical Field

[0001] This invention relates to the field of turbine structure design technology, specifically to wave rotor turbines and aero engines. Background Technology

[0002] Turbines play an important role as a component of aircraft engines. Their main function is to convert most of the energy of the high-temperature, high-pressure gas flowing out of the combustion chamber into mechanical work, providing power for the overall operation of the aircraft engine.

[0003] In existing technologies, a conventional combustion chamber is replaced with a wave rotor combustion chamber, and a wave rotor drive motor is added. The remaining structure is basically the same as that of a conventional turbine engine, in order to improve the engine's thermal cycle efficiency and power-to-weight ratio. However, such engines are more complex, which is not conducive to improving the engine's power-to-weight ratio and reduces energy utilization. Summary of the Invention

[0004] In view of this, the present invention provides a wave rotor turbine and an aero engine to solve the problems of high engine complexity and low energy utilization.

[0005] In a first aspect, the present invention provides a wave rotor turbine, comprising: a hub adapted to be rotatably disposed around a first output shaft; turbine blades, wherein a plurality of turbine blades are disposed at intervals on the hub, and two adjacent turbine blades and the hub enclose a combustion chamber; end plates, wherein two end plates are disposed at opposite ends of the hub, the end plates are fixedly disposed, and at least one opening is provided on the end plates, the opening being periodically connected to each combustion chamber; and an igniter disposed on the end plates and on the side close to the turbine blades, the igniter being spaced apart from the opening along the rotation direction of the hub.

[0006] Beneficial effects: The opening periodically connects and closes with each combustion chamber. During the rotation of the hub, the combustible mixture generates compression waves in the channel, thereby achieving a pre-compression process within the wave rotor. When both ends of the combustion chamber are closed, as the hub continues to rotate, the shock wave continuously reflects between the two ends of the channel, and the pressure and temperature of the combustible mixture in the channel continuously increase. Under the action of the igniter, the combustible mixture completes combustion in the combustion chamber, and the airflow pressure and temperature in the combustion chamber further increase until the combustion chamber connects with the opening. The high-temperature and high-pressure gas is discharged from the wave rotor turbine, thus completing one cycle of the wave rotor. This invention adopts wave rotor turbine integration technology, integrating the combustion chamber and turbine components of a conventional engine into one component. At the same time, it simplifies the dual-rotor structure into a single-rotor structure, eliminating some lubrication and sealing systems, significantly reducing system complexity, improving power-to-weight ratio and energy utilization, and possessing good potential for shortening the axial length of the engine.

[0007] In one optional embodiment, the hub includes a cylinder and guide plates. The cylinder is adapted to be rotatably disposed around a first output shaft. A plurality of guide plates are provided, spaced apart on the cylinder. Both ends of the turbine blade are connected to the guide plates to form baffles. Two adjacent baffles and the cylinder enclose the combustion chamber.

[0008] Beneficial effects: By setting up guide plates, the length of the combustion chamber is increased, which can improve combustion stability and enhance the smoothness and reliability of the turbine.

[0009] Secondly, the present invention also provides an aircraft engine, comprising: the aforementioned wave rotor turbine; an air intake assembly disposed upstream of the wave rotor turbine, the air intake assembly having an inlet and an outlet, the inlet being adapted to collect ambient air, and the outlet communicating with the opening located upstream of the wave rotor turbine.

[0010] Beneficial effects: The aero-engine adopts wave rotor technology, which is based on isochoric combustion and has self-pressurization characteristics. It can reduce the number of compressor stages and significantly improve cycle thermal efficiency and power-to-weight ratio.

[0011] In one alternative embodiment, the air intake assembly includes an air intake duct and a compressor, with the inlet formed at a first end of the air intake duct, the second end of the air intake duct communicating with the first end of the compressor, and the outlet formed at the second end of the compressor.

[0012] Beneficial effects: By using an air compressor to compress outside air, the temperature and pressure of the airflow increase.

[0013] In one alternative implementation, the aircraft engine is a turboshaft engine or a turboprop engine.

[0014] In one optional embodiment, the aero-engine further includes: a power shaft, the power shaft including a first output shaft and a second output shaft, the hub being sleeved on the first output shaft and rotatably disposed with the first output shaft, the compressor being sleeved on the second output shaft and rotatably disposed with the second output shaft; and a connecting assembly, the two ends of the connecting assembly being drively connected to the first output shaft and the second output shaft respectively.

[0015] Beneficial effect: By setting up the connecting components, the rotational speeds between the first and second output shafts can be matched.

[0016] In one optional embodiment, the connecting assembly includes a first connecting shaft, a second connecting shaft, and a gearbox. The two ends of the gearbox are respectively connected to the first connecting shaft and the second connecting shaft. The first connecting shaft is connected to the second output shaft, and the second connecting shaft is connected to the first output shaft.

[0017] In one alternative embodiment, the aircraft engine further includes an accessory drive that is drive-connected to the end of the second output shaft away from the connecting assembly.

[0018] Beneficial effects: Power is generated by the rotation of turbine blades in the wave rotor turbine. This power is transmitted through the first output shaft, the second output shaft and the connecting assembly to drive the compressor and accessory drive.

[0019] In one alternative implementation, the aircraft engine is a turbojet engine or a turbofan engine.

[0020] In one alternative embodiment, the aircraft engine further includes an exhaust system that communicates with the opening located downstream of the wave rotor turbine.

[0021] Beneficial effect: By setting up an exhaust device, the high-temperature and high-pressure gas generated by the wave rotor turbine is discharged through the exhaust device. Attached Figure Description

[0022] 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.

[0023] Figure 1 This is a schematic diagram of a wave rotor turbine according to Embodiment 1 of the present invention;

[0024] Figure 2 This is a half-sectional schematic diagram of the wave rotor turbine of Embodiment 1 of the present invention;

[0025] Figure 3 This is a schematic diagram of the full cross-sectional structure of the wave rotor turbine of Embodiment 1 of the present invention;

[0026] Figure 4 This is a two-dimensional schematic diagram of the wave rotor turbine of Embodiment 1 of the present invention;

[0027] Figure 5 This is a schematic diagram of a single working cycle of a wave rotor turbine with a single combustion chamber according to Embodiment 1 of the present invention;

[0028] Figure 6 This is a schematic diagram of the structure of the aero-engine according to Embodiment 2 of the present invention;

[0029] Figure 7 This is a schematic diagram comparing the TS cycles of the wave rotor cycle, constant volume cycle, and constant pressure cycle.

[0030] Explanation of reference numerals in the attached figures:

[0031] 10. Hub; 11. Cylinder; 12. Guide plate; 20. Turbine blade; 30. End plate; 31. Opening; 40. Baffle; 50. Intake assembly; 51. Intake duct; 52. Compressor; 53. Inlet; 54. Outlet; 60. Power shaft; 61. First output shaft; 62. Second output shaft; 70. Connecting assembly; 71. First connecting shaft; 72. Second connecting shaft; 73. Gearbox; 80. Accessory transmission device; 90. Combustion chamber; 100. Exhaust device. Detailed Implementation

[0032] 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.

[0033] The following is combined with Figures 1 to 7 The following describes embodiments of the present invention.

[0034] Example 1

[0035] like Figures 1 to 4 As shown, the wave rotor turbine of this embodiment includes a hub 10, turbine blades 20, end plates 30, and an igniter. The hub 10 is rotatably arranged around a first output shaft 61; twenty turbine blades 20 are provided, and the twenty turbine blades 20 are spaced apart on the hub 10, with two adjacent turbine blades 20 and the hub 10 forming a combustion chamber 90; two end plates 30 are provided, and the two end plates 30 are respectively provided at both ends of the hub 10. The end plates 30 are fixedly arranged, and two openings 31 are provided on the end plates 30. Each opening 31 is periodically connected to each combustion chamber 90; the igniter (not shown in the figure) is provided on the end plate 30 and is located on the side close to the turbine blades 20. Along the rotation direction of the hub 10, the igniter and the openings 31 are spaced apart.

[0036] In this embodiment, the wave rotor turbine has its opening 31 periodically connected to and closed with each combustion chamber 90. During the rotation of the hub 10, the combustible mixture generates a compression wave in the channel, thereby achieving a pre-compression process within the wave rotor. When both ends of the combustion chamber 90 are closed, as the hub 10 rotates continuously, the shock wave is continuously reflected between the two ends of the channel, and the pressure and temperature of the combustible mixture in the channel continuously increase. Under the action of the igniter, the combustible mixture completes combustion in the combustion chamber 90, and the airflow pressure and temperature in the combustion chamber 90 further increase until the combustion chamber 90 connects with the opening 31. The high-temperature and high-pressure gas is discharged from the wave rotor turbine, thus completing one cycle of the wave rotor. This invention adopts wave rotor turbine integration technology, integrating the combustion chamber 90 and turbine of a conventional engine into one component. At the same time, it simplifies the dual-rotor structure into a single-rotor structure, which can omit some lubrication and sealing systems, significantly reducing system complexity, improving power-to-weight ratio and energy utilization, and has good potential to shorten the axial length of the engine.

[0037] It should be noted that, as Figure 7 As shown, Figure 7 A comparison of temperature-entropy diagrams (TS diagrams) for wave rotor cycle, constant volume cycle, and Brayton cycle (constant pressure cycle).

[0038] To further explain, the thermodynamic cycle process of the wave rotor cycle is as follows: the process from 0 to 1 is the isentropic compression process in the intake duct 51 and compressor 52; the process from 1 to 2 is the pre-compression process in the wave rotor channel; the process from 2 to 3 is the wave rotor combustion heat absorption process; the process from 3 to 4 is the pre-expansion process in the wave rotor channel; the process from 4 to 5 is the isentropic expansion process in the turbine and nozzle; and the process from 5 to 0 is the gas heat release process.

[0039] To further explain, the absolute isobaric cycle is a cyclic process from 0 to 1a to 4a to 5a. It can be understood that after isentropic expansion through the turbine and nozzle, the entropy value at section 5 in the wave rotor cycle is less than the entropy value at section 5a in the isobaric cycle. Therefore, the wave rotor cycle generates less heat release during the gas exothermic process (the heat release during the cycle is the area enclosed by the projection of the heat release curves 5 to 0 onto the entropy coordinate on the TS diagram). When the heating amount during the cycle is the same, the heat absorption of the wave rotor cycle is greater than that of the isobaric cycle, meaning it has greater cycle work and higher cycle thermal efficiency.

[0040] However, in existing technologies, adding wave rotor technology to conventional turbine engines requires an additional rotor system, namely a separate starter-generator system for driving and transmitting power. Furthermore, bearings are installed between the wave rotor and the end plate 30, requiring lubrication and sealing. This increases system complexity, and the additional equipment is detrimental to improving the engine's power-to-weight ratio. Moreover, the power generated by the wave rotor is not fully utilized, reducing energy efficiency.

[0041] It is worth noting that in this embodiment, the wave rotor and turbine are combined, and the dual rotor structure (gas generator rotor composed of turbine and wave rotor rotor) is changed to a single rotor structure (rotor formed by the combination of wave rotor and turbine). Therefore, only the bearings of the wave rotor turbine component need to be lubricated and sealed, without having to separate the wave rotor and turbine, which greatly reduces the complexity of the system.

[0042] It should be noted that those skilled in the art can adjust the structure of the wave rotor according to actual needs, such as a flow-through wave rotor or a return-flow wave rotor.

[0043] Specifically, the end plate 30 is an annular plate, and two end plates 30 are provided, respectively located at both ends of the hub 10. Two openings 31 are formed on the end plate 30; that is, in this embodiment, the wave rotor turbine has two intake ports and two exhaust ports. The wave rotor turbine includes two complete wave rotor cycles. (See reference...) Figure 1 In the figure, the opening 31 on the left end plate 30 is the air intake port, and the opening 31 on the right end plate 30 is the exhaust port. Along the rotation direction of the hub 10, the igniter is spaced apart from the opening 31 so as to ignite the gas in the combustion chamber 90 when the opening 31 is closed to the combustion chamber 90.

[0044] It should be noted that those skilled in the art can flexibly select the number of turbine blades 20 according to the airflow requirements of the aero-engine.

[0045] It should be noted that you should refer to [link / reference]. Figure 5 , Figure 5 A schematic diagram of a single working cycle of a wave rotor turbine single combustion chamber 90 is shown. Figure 5 With time as the vertical axis, the thermal state inside the combustion chamber 90 at the bottom and top of the vertical axis is the same. The circulation process of the single combustion chamber 90 of the wave rotor turbine starts from the bottom of the vertical axis. At this time, both ends of the combustion chamber 90 are closed. There is a low-speed flow inside the combustion chamber 90, which is filled with high-temperature and high-pressure combustible gas.

[0046] To further explain, as the single combustion chamber 90 moves upward, the combustion chamber 90 and the exhaust port gradually open, at t a At a certain moment, an expansion wave sector is generated at the lower edge of the exhaust port. The expansion wave enters the combustion chamber 90 and propagates upstream. At this time, high-temperature combustion gas is discharged from the exhaust port, and the combustion gas pressure in the combustion chamber 90 gradually decreases. When the expansion wave is reflected back from the wall of the left end plate 30, it further reduces the total pressure and total temperature in the combustion chamber 90. bAt a certain moment, the intake port is connected to the combustion chamber 90. At this time, the intake pressure is greater than the gas pressure inside the combustion chamber 90, and the combustible mixture enters the combustion chamber 90 of the rotor turbine. The filling process continues until the exhaust port gradually closes; at t c At a certain moment, the exhaust port closes, the scavenging process ends, and the expansion wave emitted from the intake port reaches the exhaust port, slowing down the outflow velocity. Simultaneously, the airflow within combustion chamber 90 encounters the gradually closing exhaust port, generating a series of compression waves and interrupting the airflow within combustion chamber 90. These compression waves gradually superimpose to form a shock wave that propagates upstream, compressing the combustible mixture within combustion chamber 90. When the shock wave reaches the upper edge of the intake port, the intake port gradually closes. At t d At this moment, both the intake and exhaust ports are closed, and the fluid inside the combustion chamber 90 is in a relatively static state. This completes the intake and exhaust cycle of the wave rotor, whose main function is to drive the high-temperature, high-pressure combustion gas into the turbine for expansion and work, scavenging the existing combustion gas in the combustion chamber 90 and drawing in fresh combustible mixture. As the wave rotor channel continuously moves upward (i.e., the turbine blades 20 continuously rotate), the shock wave is continuously reflected between the walls of the end plates 30 at the left and right ends of the combustion chamber 90, causing the pressure and temperature of the combustible mixture inside the combustion chamber 90 to continuously increase. e At a certain moment, the igniter ignites the combustible mixture in the combustion chamber 90 of the wave rotor. At this time, the combustion chamber 90 continues to move upward, and the combustible mixture is burned in the combustion chamber 90. Its combustion mode is isochoric combustion mode. The airflow pressure and temperature in the combustion chamber 90 further increase. As the turbine blades 20 of the wave rotor rotate, the wave rotor enters the next cycle when the combustion chamber 90 gradually contacts the lower edge of the exhaust port. This completes the entire working process of a single cycle of the wave rotor turbine single combustion chamber 90.

[0047] It should be noted that, Figures 1 to 3 The dashed lines in the diagram are cross-sectional lines. Figure 1 and Figure 3 The solid lines with arrows in the diagram represent schematic lines of gas flow.

[0048] like Figure 1 As shown, the hub 10 includes a cylinder 11 and guide plates 12. The cylinder 11 is rotatably arranged around the first output shaft 61. Forty guide plates 12 are provided, and the forty guide plates 12 are spaced apart on the cylinder 11. Both ends of each turbine blade 20 are connected to the guide plate 12 to form a baffle 40. Two adjacent baffles 40 and the cylinder 11 enclose a combustion chamber 90.

[0049] It should be noted that in this embodiment, each turbine blade 20 is connected to two guide plates 12 to form a baffle 40.

[0050] It should be noted that the front end of the turbine blade 20 is also the intake end of the turbine blade 20, and the rear end of the turbine blade 20 is also the exhaust end of the turbine blade 20.

[0051] It is worth noting that by setting the guide plate 12, the length of the combustion chamber 90 is increased, which can improve the stability of combustion and enhance the smoothness and reliability of the turbine.

[0052] Example 2

[0053] like Figure 6 As shown, the aero engine of this embodiment includes the wave rotor turbine and the intake assembly 50 of Embodiment 1. The intake assembly 50 is disposed upstream of the wave rotor turbine, and the intake assembly 50 has an inlet 53 and an outlet 54. The inlet 53 is adapted to collect outside air, and the outlet 54 communicates with an opening 31 near the upstream of the wave rotor turbine.

[0054] The aero-engine using this embodiment employs wave rotor technology, is based on isochoric combustion, has self-pressurization characteristics, can reduce the number of compressor stages by 52, and can significantly improve cycle thermal efficiency and power-to-weight ratio.

[0055] Specifically, the aircraft engine in this embodiment is a turboshaft engine.

[0056] It should be noted that, Figure 6 The solid arrow in the image indicates the direction of gas flow.

[0057] Specifically, the outlet 54 of the intake assembly 50 is connected to the wave rotor turbine through the ventilation channel. The wave rotor turbine is embedded in the ventilation channel, and the combustion chamber of the wave rotor turbine and the interior of the ventilation channel are enclosed to form a closed space.

[0058] like Figure 6 As shown, the intake assembly 50 includes an intake duct 51 and a compressor 52. The first end of the intake duct 51 has an inlet 53, the second end of the intake duct 51 is connected to the first end of the compressor 52, and the second end of the compressor 52 has an outlet 54.

[0059] It should be noted that those skilled in the art can select compressor 52 as an axial compressor or a combined compressor, etc., as needed.

[0060] It should be noted that a transition section is provided between the compressor 52 and the wave rotor turbine. Fuel and air from the outlet 54 of the compressor 52 are atomized and mixed in the transition section to form a combustible mixture, which then enters the wave rotor turbine.

[0061] It is worth noting that the compressor 52 compresses the outside air, causing the air temperature and pressure to rise.

[0062] like Figure 6As shown, the aero-engine also includes a power shaft 60 and a connecting assembly 70. The power shaft 60 includes a first output shaft 61 and a second output shaft 62. The hub 10 is sleeved on the first output shaft 61 and the first output shaft 61 is rotatably mounted. The compressor 52 is sleeved on the second output shaft 62 and is rotatably mounted with the second output shaft 62. The two ends of the connecting assembly 70 are respectively connected to the first output shaft 61 and the second output shaft 62 for transmission.

[0063] Specifically, in this embodiment, the rotational speeds of the hub 10 of the wave rotor turbine and the compressor 52 are not equal. By setting the connecting component 70, the rotational speeds between the first output shaft 61 and the second output shaft 62 are matched.

[0064] like Figure 6 As shown, the connecting assembly 70 includes a first connecting shaft 71, a second connecting shaft 72, and a gearbox 73. The two ends of the gearbox 73 are respectively connected to the first connecting shaft 71 and the second connecting shaft 72. The first connecting shaft 71 is connected to the second output shaft 62, and the second connecting shaft 72 is connected to the first output shaft 61.

[0065] Specifically, the first connecting shaft 71 is driven by the second output shaft 62, that is, the first connecting shaft 71 is driven by the compressor 52; the second connecting shaft 72 is driven by the first output shaft 61, that is, the second connecting shaft 72 is driven by the wave rotor turbine; the two ends of the gearbox 73 are driven by the first connecting shaft 71 and the second connecting shaft 72 respectively, that is, the hub 10 of the wave rotor turbine and the compressor 52 are driven by the gearbox 73. By reasonably designing the gear transmission ratio, the rotational speed between the first output shaft 61 and the second output shaft 62 is matched.

[0066] It should be noted that those skilled in the art can change the type of gearbox 73 as needed, or replace gearbox 73 with other devices that can achieve different speed matching.

[0067] like Figure 6 As shown, the aero-engine also includes an accessory drive 80, which is driven to the end of the second output shaft 62 away from the connecting assembly 70.

[0068] It is worth noting that the power generated by the rotation of the turbine blades 20 inside the wave rotor turbine is transmitted through the first output shaft 61, the second output shaft 62 and the connecting assembly 70 to drive the compressor 52 and the accessory drive device 80.

[0069] In one embodiment, the aircraft engine also includes an exhaust system 100, which communicates with an opening 31 located downstream of the wave rotor turbine.

[0070] It is worth noting that by setting up an exhaust device 100, the high-temperature and high-pressure gas generated by the wave rotor turbine is discharged through the exhaust device 100.

[0071] It should be noted that, in this embodiment, the working principle of the aero engine is as follows: fresh air from the outside flows in through the intake duct 51, is compressed by the compressor 52, and the airflow temperature and pressure rise. Fuel and air at the compressor outlet 54 are atomized and mixed in the transition section to form a combustible mixture. Then, it flows through the opening 31 on the end plate 30 and enters the wave rotor turbine. After pre-compression, ignition and combustion, and pre-expansion, it impacts the turbine blades 20 to generate power. This power is transmitted through the gearbox 73 and the power shaft 60 to drive the compressor 52 and the accessory transmission device 80. Finally, the high-temperature and high-pressure gas is discharged through the exhaust device 100.

[0072] Example 3

[0073] The difference between Example 3 and Example 2 is that the aircraft engine in Example 3 is a turboprop engine. Apart from that, the rest of the structure and connection method are the same as in Example 2, so they will not be described again.

[0074] Example 4

[0075] The difference between Example 4 and Example 2 is that the aircraft engine in Example 4 is a turbojet engine, Example 4 does not have a power shaft 60, and Example 4 includes two drive shafts. The compressor 52 and hub 10 are respectively mounted on the two drive shafts, and the two ends of the connecting assembly 70 are respectively connected to the two drive shafts. Apart from this, the rest of the structure and the matching method are the same as in Example 2, so they will not be described again.

[0076] Example 5

[0077] The difference between Example 5 and Example 2 is that the aircraft engine in Example 5 is a turbofan engine, and Example 5 does not have a power shaft 60. Example 4 includes two drive shafts, and the compressor 52 and hub 10 are respectively mounted on the two drive shafts. The two ends of the connecting assembly 70 are respectively connected to the two drive shafts. Apart from this, the rest of the structure and the matching method are the same as in Example 2, so they will not be described again.

[0078] 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 all such modifications and variations fall within the scope defined by the invention.

Claims

1. A wave rotor turbine characterized by, The utility model relates to a turbine engine, and more particularly to a turbine engine with a wave rotor. The turbine engine comprises: a hub cylinder (10) adapted to be rotatably arranged around a first output shaft (61); a plurality of turbine blades (20) arranged on the hub cylinder (10) at intervals, and two adjacent turbine blades (20) and the hub cylinder (10) form a combustion chamber (90); two end plates (30) arranged at two ends of the hub cylinder (10) respectively, and the end plates (30) are fixedly arranged, and at least one opening (31) is formed in each end plate (30) and periodically communicated with each combustion chamber (90); an igniter arranged on one side of the end plate (30) close to the turbine blade (20) and spaced apart from the opening (31) in the direction of rotation of the hub cylinder (10).

2. An aeroengine characterised in that, The hub cylinder (10) comprises a cylinder body (11) and a plurality of guide plates (12), the cylinder body (11) is adapted to be rotatably arranged around the first output shaft (61), the guide plates (12) are arranged on the cylinder body (11) at intervals, and the turbine blades (20) are connected to the guide plates (12) at both ends to form a baffle plate (40), and two adjacent baffle plates (40) and the cylinder body (11) form the combustion chamber (90). The utility model relates to a turbine engine, and more particularly to a turbine engine with a wave rotor. The turbine engine comprises:

3. The aeroengine of claim 2, wherein, a wave rotor turbine according to claim 1; 4. The aeroengine of claim 3, wherein, an air inlet assembly (50) arranged upstream of the wave rotor turbine, the air inlet assembly (50) having an inlet (53) and an outlet (54), the inlet (53) being adapted to collect external air, and the outlet (54) being communicated with the opening (31) close to the upstream of the wave rotor turbine.

5. The aeroengine of claim 4, wherein, The air inlet assembly (50) comprises an air inlet channel (51) and a compressor (52), the first end of the air inlet channel (51) forms the inlet (53), the second end of the air inlet channel (51) is communicated with the first end of the compressor (52), and the second end of the compressor (52) forms the outlet (54). The turbine engine is a turboshaft engine or a turboprop engine. The turbine engine further comprises: a power shaft (60) comprising a first output shaft (61) and a second output shaft (62), the hub cylinder (10) is sleeved on the first output shaft (61) and rotatably arranged, and the compressor (52) is sleeved on the second output shaft (62) and rotatably arranged; a connecting assembly (70) having two ends respectively drivingly connected with the first output shaft (61) and the second output shaft (62).

6. The aeroengine of claim 5, wherein, The connecting assembly (70) comprises a first connecting shaft (71), a second connecting shaft (72) and a gear box (73), two ends of the gear box (73) are respectively in driving connection with the first connecting shaft (71) and the second connecting shaft (72), the first connecting shaft (71) is in driving connection with the second output shaft (62), and the second connecting shaft (72) is in driving connection with the first output shaft (61).

7. The aeroengine of claim 5, wherein, The aero-engine further comprises an accessory drive (80), which is in driving connection with one end of the second output shaft (62) away from the connecting assembly (70).

8. The aeroengine of claim 3, wherein, The aero-engine is a turbojet engine or a turbofan engine.

9. The aeroengine of claim 2, wherein, The aero-engine further comprises an exhaust device (100), which is in communication with the opening (31) downstream close to the wave rotor turbine.

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