High-power-density axial-flow type turbine disc shaft structure

Abstract

The invention relates to a high-power-density axial-flow type turbine disc shaft structure. The turbine disc shaft structure comprises an axial-flow turbine blade disc, a rotating shaft, a pressing end cover and a bolt. The turbine blade disc is made of light high-temperature-resistant materials, polygonal prism bosses are arranged on the end faces of the two sides of the axial-flow turbine blade disc, and through holes are evenly distributed in the polygonal prism bosses of the section of the air inlet side in the circumferential direction. A connecting disc is arranged at one end of the rotating shaft, a polygonal torque transmission counter bore is formed in the connecting disc, and threaded blind holes are evenly distributed in the bottom of the polygonal torque transmission counter bore in the circumferential direction. A polygonal counter bore is formed in the end face of one side of the pressing end cover, and through holes are evenly distributed in the bottom of the polygonal counter bore in the circumferential direction. The bolt sequentially penetrates through the through holes evenly distributed in the circumferential direction of the pressing end cover and the through hole of the axial-flow type turbine blade disc and is assembled with the threaded blind hole of the rotating shaft, locking of the assembling structure of the axial-flow type turbine blade disc, the rotating shaft and the pressing end cover is achieved, and a complete turbine disc shaft structure is formed. The axial-flow type turbine disc shaft structure is high in reliability and good in manufacturability.

Description

Technical Field

[0001] The invention belongs to the field of turbine engine structure design, and in particular relates to a high power density axial flow turbine disk-shaft structure. Background Art

[0002] Small turbine engines are one of the main power forms for small aircraft such as drones and target drones. The engine converts fuel thermal energy into shaft work or thrust through processes such as compressor air compression, combustion chamber heating, turbine expansion, and nozzle discharge, thereby meeting the thrust requirements of small aircraft.

[0003] The turbine rotor is one of the key components of the turbine engine. It is subjected to multiple loads such as mechanical load, aerodynamic load, thermal load, etc. during operation. The working load and environment are harsh. It is one of the main components that affect the performance and structural reliability of the turbine engine, and it is also a key component that restricts the life of the turbine engine. Reasonable design of the turbine disk-shaft structure is of great significance to improving the performance and reliability of the engine.

[0004] In order to improve the thrust-to-weight ratio and other performance of turbine engines, increasing the operating temperature of the turbine and reducing the weight of the engine components are one of the effective technical approaches. For example, the turbine blades in the axial-flow turbine rotor can be made of ceramic materials, which can increase the operating temperature of the turbine rotor on the one hand, and reduce the weight of the turbine rotor on the other hand, thereby achieving the purpose of lightweighting. For traditional high-temperature alloy turbine blades, the integration of the axial-flow turbine blades and the turbine shaft can be achieved by welding, but for turbine impellers made of ceramic materials, it is impossible to achieve the connection between the turbine blades and the turbine shaft by welding or other methods. To this end, it is necessary to solve the problem of the integration of the ceramic turbine blades with the turbine shaft to ensure the reliability of the axial-flow turbine rotor.

[0005] Aiming at the problem of reliable connection between turbine disk and shaft of turbine engine, reliable connection between turbine disk and shaft is achieved by rationally designing the structure of turbine blade disk and shaft. Meanwhile, the working stress of turbine rotor structure, especially the working stress of turbine blade disk, is reduced, the reliability of turbine rotor structure is improved, the service life of engine is ensured, and the turbine rotor has good processability and maintainability. Summary of the invention

[0006] The present invention aims at the design problem of turbine disc shaft structure of turbine engine, and proposes a high power density axial flow turbine disc shaft structure, which includes an axial flow turbine blade disc, a rotating shaft, a clamping end cover and bolts. The turbine blade disc is made of homogeneous silicon nitride ceramic material or titanium aluminum alloy material. The two side end faces of the axial flow turbine blade disc are provided with polygonal prism bosses, and the upper edge of the polygonal prism bosses is uniformly distributed with through holes in the circumferential direction; one end of the rotating shaft is provided with a connecting disc, and the connecting disc is provided with a polygonal torque transmission countersunk hole, and the bottom of the polygonal torque transmission countersunk hole is uniformly distributed with threaded blind holes in the circumferential direction; the end face of one side of the clamping end cover is provided with a polygonal countersunk hole, and the bottom of the polygonal countersunk hole is uniformly distributed with through holes in the circumferential direction; the bolts pass through the uniformly distributed through holes in the clamping end cover and the through holes of the turbine blade disc in turn, and are assembled with the threaded blind holes of the rotating shaft to realize the thread locking of the assembly structure of the axial flow turbine blade disc, the rotating shaft and the clamping end cover, and form a complete turbine disc shaft structure.

[0007] The technical solution of the present invention:

[0008] A high power density axial flow turbine disk-shaft structure comprises an axial flow turbine blade disk, a rotating shaft, a clamping end cover and bolts.

[0009] The axial flow turbine blade disc is made of homogeneous silicon nitride ceramic material or titanium aluminum alloy material. The air inlet side end face of the axial flow turbine blade disc close to the rotating shaft is provided with a polygonal prismatic boss assembled with the polygonal torque transmission countersunk hole of the rotating shaft. The exhaust end face of the axial flow turbine blade disc is provided with a polygonal prismatic boss assembled with the clamping end cover. The upper edge of the polygonal prismatic boss of the axial flow turbine blade disc is evenly distributed with through holes in the circumferential direction.

[0010] The rotating shaft has a connecting disc at one end close to the axial flow turbine blade disk, and the connecting disc of the rotating shaft has a polygonal torque transmission countersunk hole assembled with the polygonal prismatic boss of the axial flow turbine blade disk. The polygonal torque transmission countersunk hole of the rotating shaft and the polygonal prismatic boss of the axial flow turbine blade disk are assembled with interference fit, and the bottom of the polygonal torque transmission countersunk hole of the rotating shaft has threaded blind holes evenly distributed along the circumferential direction.

[0011] A polygonal countersunk hole is provided on one end face of the clamping end cover and is assembled with the polygonal prismatic boss on the exhaust side of the coaxial flow turbine blade disk. The bottom of the polygonal countersunk hole of the clamping end cover is evenly distributed along the circumference with through holes assembled with bolts. The polygonal countersunk hole of the clamping end cover and the polygonal prismatic boss on the exhaust side of the coaxial flow turbine blade disk are interference fitted.

[0012] The bolt passes through the through hole of the clamping end cover and the through hole of the axial flow turbine blade disk, and is assembled with the threaded blind hole of the rotating shaft.

[0013] The polygonal prismatic boss of the axial-flow turbine blade disk is interference-fitted with the polygonal torque transmission countersunk hole of the rotating shaft, and the polygonal prismatic boss on the exhaust side of the axial-flow turbine blade disk is interference-fitted with the polygonal countersunk hole of the clamping end cover. The bolts pass through the circumferentially uniform through holes of the clamping end cover and the through holes of the axial-flow turbine blade disk in sequence, and are assembled with the threaded blind holes of the rotating shaft, thereby locking the assembly structure of the axial-flow turbine blade disk, the rotating shaft and the clamping end cover to form a complete turbine disk-shaft structure.

[0014] The beneficial effects of the present invention are:

[0015] The present invention proposes a high power density axial flow turbine disc shaft structure. The axial flow turbine blade disc adopts homogeneous silicon nitride ceramic material or titanium aluminum alloy material, which can not only meet the high temperature resistance requirements of the high temperature part of the turbine disc shaft, but also effectively reduce the weight of the turbine disc shaft components, which is helpful to improve the engine performance. The end face of the axial flow turbine blade disc close to the rotating shaft has a polygonal prism boss assembled with the polygonal torque transmission countersunk hole of the rotating shaft, which can realize the high power transmission of the axial flow turbine blade disc and the rotating shaft. The end face of the exhaust side of the axial flow turbine blade disc has a polygonal prism boss assembled with the clamping end cover, which reduces the stress in the center of the turbine blade disc. At the same time, through the cooperation of the polygonal prism boss with the polygonal countersunk hole of the clamping end cover, the load borne by the turbine blade disc is transmitted to the clamping end cover, which greatly reduces the stress in the center of the turbine blade disc and improves the structural reliability of the turbine blade disc; the upper edge of the polygonal prism boss of the axial flow turbine blade disc is uniformly distributed with through holes in the circumferential direction, which realizes the distributed load-bearing of the turbine blade disc structure, which is beneficial to improve the reliability of the turbine blade disc and the connection strength of the blade disc with the rotating shaft. The bolts pass through the circumferentially uniform through holes of the clamping end cover and the through holes of the turbine blade disk in sequence, and are assembled with the threaded blind holes of the rotating shaft. This not only realizes the thread locking of the assembly structure of the axial-flow turbine blade disk, the rotating shaft and the clamping end cover, but also facilitates the disassembly and assembly of the turbine disk shaft, making it have good processability. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] Figure 1 It is a schematic diagram of the high power density axial flow turbine disk-shaft structure.

[0017] Figure 2 It is a schematic diagram of the structure of an axial flow turbine blade disk.

[0018] Figure 3 It is a schematic diagram of the shaft structure.

[0019] 1Axial flow turbine blade 2Rotating shaft 3Tighten end cover 4Bolt

[0020] 5. Polygonal prismatic boss for axial flow turbine blades

[0021] 6Polygonal prismatic boss on the exhaust side of an axial flow turbine blade disk

[0022] 7 through hole of axial flow turbine blade disk 8 connecting disk of rotating shaft

[0023] 9-axis polygonal torque transmission countersunk hole

[0024] 10 Threaded blind hole for shaft DETAILED DESCRIPTION

[0025] A high power density axial flow turbine disk-shaft structure comprises an axial flow turbine blade disk 1, a rotating shaft 2, a clamping end cover 3 and bolts 4.

[0026] The axial-flow turbine blade disk 1 is made of homogeneous silicon nitride ceramic material or titanium-aluminum alloy material. The inlet side end face of the axial-flow turbine blade disk 1 close to the rotating shaft 2 has a polygonal prismatic boss 5 assembled with the polygonal torque transmission countersunk hole 9 of the rotating shaft 2. The exhaust side end face of the axial-flow turbine blade disk 4 has a polygonal prismatic boss 6 assembled with the clamping end cover 3. The polygonal prismatic boss 5 on the inlet side end face of the axial-flow turbine blade disk 1 is evenly distributed with through holes 7 along the circumferential direction.

[0027] The shaft 2 has a connecting disc 8 at one end close to the axial-flow turbine blade disk 1, and the connecting disc 8 of the shaft 2 has a polygonal torque transmission countersunk hole 9 assembled with the polygonal prismatic boss 5 of the axial-flow turbine blade disk 1. The polygonal torque transmission countersunk hole 9 of the shaft 2 and the polygonal prismatic boss 5 of the axial-flow turbine blade disk 1 are fitted with interference fit, and the bottom of the polygonal torque transmission countersunk hole 9 of the shaft 5 has threaded blind holes 10 evenly distributed along the circumferential direction.

[0028] A polygonal countersunk hole is provided on one end face of the clamping end cover 3 and is assembled with the polygonal prismatic boss 6 on the exhaust side of the coaxial flow turbine blade disk 1. The bottom of the polygonal countersunk hole of the clamping end cover 3 is evenly distributed along the circumference with through holes assembled with the bolts 4. The polygonal countersunk hole of the clamping end cover 3 and the polygonal prismatic boss 6 on the exhaust side of the coaxial flow turbine blade disk 1 are interference fitted.

[0029] The bolt 4 passes through the through hole of the clamping end cover 3 and the through hole 7 of the axial flow turbine blade disk 1 , and is assembled with the threaded blind hole 10 of the rotating shaft 2 .

[0030] The polygonal prismatic boss 5 of the axial-flow turbine blade disk 1 is interference-fitted with the polygonal torque transmission countersunk hole 9 of the rotating shaft 2, and the polygonal prismatic boss 6 on the exhaust side of the axial-flow turbine blade disk 1 is interference-fitted with the polygonal countersunk hole of the clamping end cover 3. The bolts 4 pass through the circumferentially uniform through holes of the clamping end cover 3 and the through holes 7 of the axial-flow turbine blade disk 1 in sequence, and are assembled with the threaded blind holes 10 of the rotating shaft 2, so as to lock the assembly structure of the axial-flow turbine blade disk 1, the rotating shaft 2 and the clamping end cover 3 to form a complete turbine disk-shaft structure.

[0031] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.

Claims

1. A high power density axial flow turbine disk-shaft structure, characterized in that: It comprises an axial flow turbine blade disk (1), a rotating shaft (2), a clamping end cover (3) and bolts (4); The end face of the axial flow turbine blade disk (1) on the air intake side close to the rotating shaft (2) has a polygonal prism boss (5) assembled with the polygonal torque transmission countersunk hole (9) of the rotating shaft (2); the end face of the axial flow turbine blade disk (4) on the air exhaust side has a polygonal prism boss (6) assembled with the clamping end cover (3); and through holes (7) are evenly distributed along the circumferential direction on the polygonal prism boss (5) on the air intake side end face of the axial flow turbine blade disk (1); The rotating shaft (2) has a connecting disc (8) at one end close to the axial flow turbine blade disk (1), and the connecting disc (8) of the rotating shaft (2) has a polygonal torque transmission countersunk hole (9) assembled with the polygonal prism boss (5) of the axial flow turbine blade disk (1), and the bottom of the polygonal torque transmission countersunk hole (9) of the rotating shaft (5) has threaded blind holes (10) evenly distributed along the circumferential direction; A polygonal countersunk hole is provided on one end surface of the clamping end cover (3) and is assembled with a polygonal prismatic boss (6) on the exhaust side of the axial flow turbine blade disk (1); and through holes assembled with bolts (4) are evenly distributed at the bottom of the polygonal countersunk hole of the clamping end cover (3) along the circumferential direction; The bolt (4) passes through the through hole of the clamping end cover (3) and the through hole (7) of the axial flow turbine blade disk (1), and is assembled with the threaded blind hole (10) of the rotating shaft (2).

2. A high power density axial flow turbine disk-shaft structure according to claim 1, characterized in that: The axial flow turbine blade disk (1) is made of homogeneous silicon nitride ceramic material or titanium aluminum alloy material.

3. The high power density axial flow turbine disk-shaft structure according to claim 1, characterized in that: The polygonal torque transmission counterbore (9) of the rotating shaft (2) and the polygonal prism boss (5) of the axial flow turbine blade disk (1) are assembled together by interference fit.

4. The high power density axial flow turbine disk-shaft structure according to claim 1, characterized in that: The polygonal countersunk hole of the clamping end cover (3) and the polygonal prism boss (6) on the exhaust side of the axial flow turbine blade disk (1) are assembled by interference fit.

5. The high power density axial flow turbine disk-shaft structure according to claim 1, characterized in that: The polygonal prismatic boss (5) of the axial-flow turbine blade disk (1) is interference-fitted with the polygonal torque transmission countersunk hole (9) of the rotating shaft (2); the polygonal prismatic boss (6) on the exhaust side of the axial-flow turbine blade disk (1) is interference-fitted with the polygonal countersunk hole of the clamping end cover (3); the bolts (4) pass through the circumferentially uniform through holes of the clamping end cover (3) and the through holes (7) of the axial-flow turbine blade disk (1) in sequence, and are assembled with the threaded blind holes (10) of the rotating shaft (2), thereby locking the assembly structure of the axial-flow turbine blade disk (1), the rotating shaft (2) and the clamping end cover (3) to form a complete turbine disk-shaft structure.

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