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CN-122014667-A - Radial positioning, torque transmission and locking structure for turbine side rotor of liquid rocket engine

CN122014667ACN 122014667 ACN122014667 ACN 122014667ACN-122014667-A

Abstract

The invention discloses a radial positioning, torque transmission and locking structure of a turbine side rotor of a liquid rocket engine, and relates to the technical field of liquid rocket engines. The radial positioning, torque transmission and locking structure of the turbine side rotor of the liquid rocket engine comprises a turbine disc, a main shaft, a bushing and a shaft end nut. The turbine side rotor structure transmits torque through flat keys, rectangular splines or involute splines, the turbine disc is radially positioned at two sides, shaft end nuts and a main shaft are screwed in place to load torque, the flange punching points of the shaft end nuts are riveted and embedded into the grooves of the turbine disc, and the turbine disc and the bushing are axially positioned and locked. According to the radial positioning, torque transmission and locking structure of the turbine side rotor of the liquid rocket engine, the turbine disc is adopted for bilateral positioning, so that the radial positioning precision of the turbine rotor is effectively improved, the processing procedure is simplified, the interchangeability and the universality of the turbine rotor are enhanced, the production and assembly efficiency is remarkably improved, and the operation reliability of the turbine side rotor is improved.

Inventors

  • WANG FENGMEI
  • DU CHANGHE
  • ZHANG JIANHUA
  • WU GUANYING
  • LU WEIDONG
  • HE YONG

Assignees

  • 北京往返九霄航空航天科技有限公司

Dates

Publication Date
20260512
Application Date
20260331

Claims (9)

  1. 1. The radial positioning, torque transmission and locking structure of the turbine side rotor of the liquid rocket engine is characterized by comprising a turbine disc (1), a main shaft (2), a bushing (3) and a shaft end nut (4); The turbine disc (1) is provided with a radial positioning surface at 2, namely a turbine disc first radial positioning surface (11) and a turbine disc second radial positioning surface (12), the spindle (2) is provided with a radial positioning surface at 2, namely a spindle first radial positioning surface (21) and a spindle second radial positioning surface (22), the turbine disc first radial positioning surface (11) is directly contacted with the spindle first radial positioning surface (21), and the turbine disc second radial positioning surface (12) is indirectly contacted with the spindle second radial positioning surface (22) through the bushing (3); The turbine side rotor structure is provided with a flat key, a rectangular spline or an involute spline and is used for transmitting torque; the turbine disc (1) and the bushing (3) are axially positioned and locked through the shaft end nut (4).
  2. 2. The radial positioning, torque transmission and locking structure of the turbine side rotor of the liquid rocket engine according to claim 1, wherein the turbine disc (1) and the main shaft (2), the turbine disc (2) and the bushing (3), and the bushing (3) and the main shaft (2) are in clearance fit in the radial direction.
  3. 3. The radial positioning, torque transmission and locking structure of a turbine side rotor of a liquid rocket engine according to claim 1, wherein the turbine disc (1) is provided with an outer end face (13) of the turbine disc, the shaft end nut (4) is provided with an inner end face (44) of the shaft end nut, and an axial gap is arranged between the outer end face (13) of the turbine disc and the inner end face (44) of the shaft end nut.
  4. 4. The radial positioning, torque transmission and locking structure of the turbine side rotor of the liquid rocket engine according to claim 1, wherein 2 or more than 2 turbine disc grooves (14) are arranged on the turbine disc (1) for matching locking.
  5. 5. The radial positioning, torque transmission and locking structure of the turbine side rotor of the liquid rocket engine according to claim 1, wherein the spindle (2) is provided with 1 spindle thread (23), the spindle end nut (4) is provided with 1 spindle end nut thread (41), and the spindle thread (23) and the spindle end nut thread (41) are screwed and screwed to a specified position for axially fixing the turbine disc (1) and the bushing (3).
  6. 6. The radial positioning, torque transmission and locking structure of the turbine side rotor of the liquid rocket engine according to claim 1, wherein the shaft end nut (4) is provided with 1 shaft end nut flange (42) and is used for riveting a punching point of the shaft end nut flange (42) after the turbine disc (1), the main shaft (2) and the bushing (3) are assembled in place, so that the shaft end nut flange (42) is locally deformed and embedded into a turbine disc groove (14), and the axial positioning and locking of the turbine disc (1) and the bushing (3) are realized.
  7. 7. The radial positioning, torque transmission and locking structure of a turbine side rotor of a liquid rocket engine according to claim 6, wherein the thickness of the shaft end nut flange (42) is 0.3-2mm.
  8. 8. The radial positioning, torque transmission and locking structure of the turbine-side rotor of the liquid rocket engine according to claim 1, wherein 2 or more than 2 shaft end nut grooves (43) are arranged on the shaft end nut (4) and serve as process grooves for loading torque on the shaft end nut threads (41).
  9. 9. The radial positioning, torque transmission and locking structure of the turbine side rotor of the liquid rocket engine according to claim 1, wherein the bushing (3) is made of copper alloy material.

Description

Radial positioning, torque transmission and locking structure for turbine side rotor of liquid rocket engine Technical Field The invention relates to the technical field of liquid rocket engines, in particular to a radial positioning, torque transmission and locking structure of a turbine side rotor of a liquid rocket engine. Background The turbo pump is one of the core components of a pump-type liquid rocket engine, and is the "power heart" of the liquid rocket engine. Structural layout, assembly precision and operation reliability of the turbine pump rotor system directly determine thrust stability, working efficiency and service life of the engine. In a rotor system, the working condition of a turbine rotor is particularly severe, and the turbine rotor needs to stably operate under the working conditions of high rotation speed, high temperature and high load, so that strict requirements are provided for the positioning precision, torque transmission mode, locking structure and assembly manufacturability of the turbine rotor. At present, the turbine side rotor of the turbine pump of the liquid rocket engine is used at home and abroad in active service and in research, and the problems of poor single-side positioning precision, complex processing procedures, poor interchangeability among different turbine rotors and the like exist due to the fact that the turbine disc and the main shaft are generally adopted for single-side radial positioning, pins are used for transmitting torque, axial bolt connection and spot welding locking. Disclosure of Invention The invention aims to solve the defects in the prior art, and provides a radial positioning, torque transmission and locking structure for a turbine side rotor of a liquid rocket engine, which further improves radial positioning accuracy, simplifies processing procedures, optimizes the locking structure and improves interchangeability of turbine rotor parts, thereby improving operational reliability of the turbine side rotor. The technical scheme adopted for solving the technical problems is as follows: A radial positioning, torque transmission and locking structure for a turbine side rotor of a liquid rocket engine comprises a turbine disc, a main shaft, a bushing and a shaft end nut. The turbine disk is provided with a radial positioning surface at the position 2, which is a first radial positioning surface of the turbine disk and a second radial positioning surface of the turbine disk respectively. The radial positioning surfaces at the position 2 of the spindle are respectively a first radial positioning surface of the spindle and a second radial positioning surface of the spindle. The first radial positioning surface of the turbine disc is in direct contact with the first radial positioning surface of the main shaft, and the second radial positioning surface of the turbine disc is in indirect contact with the second radial positioning surface of the main shaft through the bushing. The turbine side rotor structure is provided with a flat key, a rectangular spline or an involute spline and is used for transmitting torque. The turbine disc and the bushing are axially positioned and locked through the shaft end nut. Preferably, the turbine disc and the main shaft, the turbine disc and the bushing, and the bushing and the main shaft are in clearance fit in the radial direction. Preferably, the turbine disc is provided with an outer end face of the turbine disc, the shaft end nut is provided with an inner end face of the shaft end nut, and an axial gap is arranged between the outer end face of the turbine disc and the inner end face of the shaft end nut. Preferably, the turbine disc is provided with 2 or more than 2 turbine disc grooves for matching locking. Preferably, the spindle is provided with 1 spindle thread, the spindle end nut is provided with 1 spindle end nut thread, and the spindle thread and the spindle end nut thread are screwed and screwed to a specified position for axially fixing the turbine disc and the bushing. Preferably, the shaft end nut is provided with a shaft end nut flange at 1 position, and is used for riveting the punching point of the shaft end nut flange after the turbine disc, the main shaft and the bushing are assembled in place, so that the shaft end nut flange is locally deformed and embedded into the groove of the turbine disc, and the turbine disc and the bushing are axially positioned and locked. Preferably, the thickness of the flange of the shaft end nut is 0.3-2mm. Preferably, the shaft end nut is provided with 2 or more shaft end nut grooves which are used as process grooves for loading torque by the threads of the shaft end nut. Preferably, the bushing is made of copper alloy material. Compared with the prior art, the invention has the following advantages: (1) According to the radial positioning, torque transmission and locking structure of the turbine side rotor of the liquid rocket engine, 2 radial positioning sect