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CN-122007318-A - Turbine rotor balance weight assembly system of aviation power plant

CN122007318ACN 122007318 ACN122007318 ACN 122007318ACN-122007318-A

Abstract

The invention relates to an assembling system for a turbine rotor balance weight of an aviation power device, which solves the problems of low product assembling quality, low production efficiency, waste of engine maintenance cost and the like in the traditional assembling method. The hydraulic riveting clamp mainly comprises a handle, an oil inlet and return switch, a hydraulic pump, a piston, a dowel bar, a main supporting beam, a die and the like, necessary driving force is provided for an assembly system, the die is customized according to different rotor types, and the die is arranged at the tail end of a fixing clamp through a nut, so that the radial positioning function of the hydraulic riveting clamp and a turbine rotor in the assembly process is realized. The rivet assembling function is realized by converting hydraulic pressure into linear motion of the dowel bar, and the adjustable support shows supporting and horizontal height adjusting functions for the working position of the hydraulic riveting clamp in the assembling process. The invention effectively reduces labor intensity, improves production efficiency and improves assembly quality.

Inventors

  • WANG YOUJIN
  • ZHONG QING
  • ZENG SHULIN
  • LUO PENGCHENG
  • ZHU YE
  • SONG YU
  • LIU SHENG
  • LI NING
  • QIN XIAN
  • ZHOU YING

Assignees

  • 国营川西机器厂

Dates

Publication Date
20260512
Application Date
20251228

Claims (8)

  1. 1. The turbine rotor balance weight assembly system of the aviation power device is characterized by comprising a hydraulic riveting clamp, an adjustable support and a support backing ring; The support backing ring supports and positions the turbine rotor and is provided with an annular support surface matched with the turbine rotor and a central cylindrical positioning surface, a cylindrical support surface or a round hole support surface; The adjustable support comprises a V-shaped block (21), a bottom plate (27), a vertical cylinder (26) and a screw rod (22), wherein the vertical cylinder (26) is fixedly connected to the bottom plate (27), the upper part of the screw rod (22) is fixedly connected with the V-shaped block (21), and the lower part of the screw rod is in threaded connection with the vertical cylinder (26); The hydraulic riveting pliers comprise a positioning mechanism, a hydraulic driving mechanism and an executing mechanism; the positioning mechanism comprises a compression screw (1), a spring (5), a fixing clamp (6) and a die (17), wherein the fixing clamp (6) is slidably installed in a cavity of a main support beam (8) of the actuating mechanism, the left end of the cavity of the main support beam (8) is connected with a baffle plate (3), the compression screw (1) is in threaded connection with the baffle plate (3), the end head is in contact with a spring baffle plate (4) connected to the end part of the fixing clamp (6), the spring (5) is installed between the spring baffle plate (4) and the fixing clamp (6), the die (17) is fixedly connected to the other end of the fixing clamp (6), and the die (17) can be tightly attached to the circular arc surface of a turbine rotor counterweight installation ring; The hydraulic driving mechanism comprises a handle, a hydraulic pump (18), a piston (19) and an oil inlet and return valve switch, wherein the handle is arranged beside the oil inlet and return valve switch, the handle is repeatedly pressed to provide input force for the hydraulic pump, the hydraulic pump provides pressure for the assembly system, the piston (19) is pushed to move in a linear motion, the oil inlet and return valve switch controls the oil path switch of the hydraulic pump (18), and the piston (19) realizes reciprocating motion; The actuating mechanism comprises a dowel bar (9), a pressing head (15), a guide rail (10), a compression spring (13) and a main support beam (8), wherein the main support beam (8) is connected with a hydraulic driving mechanism, a piston (19) of the hydraulic driving mechanism pushes the dowel bar (9) to reciprocate on the guide rail (10) in a linear mode, the pressing head (15) is fixed at the end head of the dowel bar (9), the guide rail (10) is fixedly connected to the main support beam (8), a stop block I (12) is arranged on the surface, matched with the guide rail (10), of the dowel bar (9), a stop block II (14) is arranged on the surface, matched with the guide rail (10), of the main support beam (8), and the compression spring (13) is connected between the stop block I (12) and the stop block II (14).
  2. 2. The turbine rotor balance weight assembly system of an aerodynamic device according to claim 1, wherein the die (17) is provided with a notch capable of avoiding rivets.
  3. 3. The assembly system of the balance weight of the turbine rotor of the aero-power device is characterized in that the left end of the cavity of the main support beam (8) is connected with a baffle plate (3) through a slotted pan head screw (2).
  4. 4. The assembly system of the balance weight of the turbine rotor of the aero-power device according to claim 1, wherein the other end of the fixing clamp (6) is fixedly connected with a die (17) through a nut.
  5. 5. The assembly system of the balance weight of the turbine rotor of the aero-power device according to claim 1, wherein one end, close to the die (17), of the fixing clamp (6) is sleeved with a bushing (11).
  6. 6. An aero-power plant turbine rotor balance weight assembly system according to claim 1, wherein the main support (8) is connected to a hydraulic drive mechanism by means of a screw thread.
  7. 7. The assembly system for balancing the turbine rotor weight of the aero-power device according to claim 1, wherein a stop block II (14) is arranged on the surface of the main support beam (8) matched with the guide rail (10) through a cross-shaped countersunk head screw (7).
  8. 8. The assembly system of the balance weight of the turbine rotor of the aero-power device according to claim 1, wherein a slotted headless shaft position screw (16) is arranged at one end of the main support beam (8) close to the die (17) and is used for limiting the axial movement of the fixing clamp (6).

Description

Turbine rotor balance weight assembly system of aviation power plant Technical Field The invention relates to the technical field of maintenance of aviation power devices, in particular to an assembly system for assembling and fixing a turbine rotor balance weight in the maintenance process of an aviation power device. Background During maintenance of an aero power plant, a worker is required to fix a balance weight to a turbine rotor weight mounting ring by rivet assembly after performing three-stage turbine rotor balancing. The assembly requirement precision is high, and the method has definite limit requirements on the size states of the rivet, such as diameter, height and the like after assembly. The traditional assembly method is adopted for assembly, the labor intensity of operators is high, the rivet riveting end is easy to skew in the assembly process, the rivet cannot be effectively upset, the specified parameters are difficult to guarantee, the assembly qualification rate is low, the reworking is more, a large amount of engine maintenance spare parts are wasted, the production efficiency is low, and the normal complete set delivery of engine maintenance is restricted. Disclosure of Invention The invention aims to solve the technical problem of how to realize high-efficiency and high-quality assembly of a balance weight on a turbine rotor after the balance of a three-stage turbine rotor of an aviation power device is completed. The assembly system can solve the problems of high labor intensity, low product assembly quality, high reworking rate, low qualification rate, low production efficiency, waste of engine maintenance cost and the like in the traditional assembly method. The invention is realized by the following technical scheme: An assembly system for a balance weight of a turbine rotor of an aviation power device comprises a hydraulic riveting clamp, an adjustable support and a support backing ring; The support backing ring supports and positions the turbine rotor and is provided with an annular support surface matched with the turbine rotor and a central cylindrical positioning surface, a cylindrical support surface or a round hole support surface; the adjustable support comprises a V-shaped block 21, a bottom plate 27, a vertical cylinder 26 and a screw rod 22, wherein the vertical cylinder 26 is fixedly connected to the bottom plate 27, the upper part of the screw rod 22 is fixedly connected with the V-shaped block 21, and the lower part of the screw rod 22 is in threaded connection with the vertical cylinder 26; The hydraulic riveting pliers comprise a positioning mechanism, a hydraulic driving mechanism and an executing mechanism; The positioning mechanism comprises a compression screw 1, a spring 5, a fixing clamp 6 and a die 17, wherein the fixing clamp 6 is slidably arranged in a cavity of a main supporting beam 8 of the actuating mechanism, the left end of the cavity of the main supporting beam 8 is connected with a baffle 3 through a slotted pan head screw 2, the compression screw 1 is in threaded connection with the baffle 3, the end head is in contact with a spring baffle 4 connected with the end part of the fixing clamp 6, the spring 5 is arranged between the spring baffle 4 and the fixing clamp 6, the other end of the fixing clamp 6 is fixedly connected with the die 17 through a nut, the die 17 can be clung to the circular arc surface of a turbine rotor counterweight mounting ring, and one end, close to the die 17, of the fixing clamp 6 is sleeved with a bushing 11; The hydraulic driving mechanism comprises a handle, a hydraulic pump 18, a piston 19 and an oil inlet and return valve switch, wherein the handle is arranged beside the oil inlet and return valve switch, the handle is repeatedly pressed to provide input force for the hydraulic pump, the hydraulic pump provides pressure for the assembly system, the piston 19 is pushed to move in a linear motion, the oil inlet and return valve switch controls the oil path switch of the hydraulic pump 18, and the piston 19 realizes reciprocating motion; The actuating mechanism comprises a dowel bar 9, a pressure head 15, a guide rail 10, a compression spring 13 and a main supporting beam 8, wherein the main supporting beam 8 is connected with a hydraulic driving mechanism through threads, a piston 19 of the hydraulic driving mechanism pushes the dowel bar 9 to reciprocate on the guide rail 10 in a linear manner, the pressure head 15 is fixed at the end of the dowel bar 9, the guide rail 10 is fixedly connected to the main supporting beam 8, a stop block I12 is arranged on the surface of the dowel bar 9 matched with the guide rail 10, a stop block II14 is arranged on the surface of the main supporting beam 8 matched with the guide rail 10 (through a cross groove countersunk head screw 7), the compression spring 13 is connected between the stop block I12 and the stop block II14, and a slotted headless shaft position screw 16 is arranged