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CN-121141049-B - Dynamic stability adjusting device based on aeroengine core machine

CN121141049BCN 121141049 BCN121141049 BCN 121141049BCN-121141049-B

Abstract

The invention discloses a dynamic stability adjusting device based on an aeroengine core machine, which comprises a fixed base body, a rotor system, a standard supporting end and a measuring supporting end, wherein the fixed base body comprises a casing and supporting switching tools fixed on two sides of the casing, the rotor system comprises a rotating shaft accommodated in the casing, a high-pressure rotor and a high-vortex rotor are fixedly arranged on the rotating shaft, one end of the rotating shaft is rotatably connected with the casing through a front bearing and a front support, and the measuring supporting end belongs to the technical field of aeroengine and gas turbine manufacturing and assembling.

Inventors

  • LIU CHAO
  • LIN DACHAO
  • WANG ZHENGWAN
  • GUO XIAOWEI

Assignees

  • 上海衡望智能科技有限公司

Dates

Publication Date
20260512
Application Date
20251014

Claims (8)

  1. 1. Dynamic stability adjusting device based on aeroengine core machine, characterized by comprising: The fixed matrix comprises a casing (1) and support switching tools (2) fixed on two sides of the casing; The rotor system comprises a rotating shaft (3) accommodated in the casing (1), and a high-pressure rotor (302) and a high-vortex rotor (303) are fixedly arranged on the rotating shaft (3); the standard support end, one end of the rotating shaft (3) is rotationally connected with the casing (1) through a front bearing (401) and a front bracket (402); the measuring support end, the other end of pivot (3) pass through rear bearing (403) with receiver (1) is connected, the measuring support end includes: a rear bracket (404) fixed on the casing (1); A detecting bearing seat fixture (5) detachably mounted on the rear bracket (404) through a fastener, wherein a cylindrical cavity for accommodating and clamping the rear bearing (403) is arranged in the detecting bearing seat fixture and is provided with a plurality of fixing holes for fixing the rear bearing (403) The integrated measurement system comprises a piezoelectric force sensor group (601) arranged between the detection bearing seat tool (5) and the rear bracket (404), and a key phase sensor (602) for detecting key phase marks of the rotating shaft (3); the structure of the appearance installation dimension, the connection interface and the internal fixing cavity (502) of the detection bearing seat tool (5) is completely the same as the corresponding structure of the formal bearing seat tool; The inside of back support (404) is established to the cavity structure, and telescopic link (701) are installed to its inner wall, output fixedly connected with link (702) of telescopic link (701), all rotate on both sides of link (702) one end and be connected with gyro wheel (703), the outer wall of gyro wheel (703) is connected with the outer wall roll of roller bearing (301).
  2. 2. The dynamic stability adjusting device based on the aircraft engine core machine according to claim 1, wherein the detecting bearing seat tool (5) comprises two symmetrical shells (501), and arc-shaped fixing cavities (502) are symmetrically formed on the inner sides of the two shells (501).
  3. 3. The dynamic stability adjusting device based on the aeroengine core machine according to claim 2, wherein the two fixing cavities (502) are combined together to form the cylindrical cavity, connecting pieces (503) are arranged on two sides of the two shells (501), and the two shells (501) are fastened together through fixing holes (505) in the connecting pieces (503) by fasteners.
  4. 4. The dynamic stability adjusting device based on the aircraft engine core machine according to claim 1, wherein a window (101) is formed in the position, facing the rotor correction plane, of the casing (1).
  5. 5. A dynamic stability adjustment device based on an aircraft engine core machine according to claim 4, characterized in that the window (101) is sealed by a removable closing plate (102).
  6. 6. The dynamic stability adjustment device based on an aircraft engine core machine according to claim 1, wherein a counterweight structure is provided on the rotor system.
  7. 7. The dynamic stability adjusting device based on the aeroengine core machine according to claim 6, wherein the counterweight structure comprises counterweight plates with uniformly distributed threaded holes or T-shaped grooves arranged at two ends of a roller (301) of the rotating shaft (3).
  8. 8. The dynamic stability adjusting device based on the aircraft engine core machine according to claim 7, wherein the counterweight structure comprises uniformly distributed mounting holes formed in a last-stage compressor disk of the high-pressure rotor (302) and a turbine disk of the Gao Guo rotor (303).

Description

Dynamic stability adjusting device based on aeroengine core machine Technical Field The invention relates to the technical field of manufacturing and assembling of aeroengines and gas turbines, in particular to a dynamic stability adjusting device based on an aeroengine core machine. Background The rotor of an aircraft engine core machine (typically comprising a high pressure compressor, a combustion chamber and a high pressure turbine) has inherent drawbacks in conventional processes when dynamic balancing is performed. The traditional method is that the rotor (comprising a rotating shaft, a high-pressure rotor and a high-pressure turbine rotor) is independently placed on an external balancing machine for adjustment, the rotor is disassembled after the balance reaches the standard, the rotor is installed into a casing, and the high-pressure turbine rotor is finally reinstalled; Therefore, the existing requirements are not met, and for this reason we propose a dynamic stability adjusting device based on an aeroengine core machine. Disclosure of Invention Therefore, the invention provides a dynamic stability adjusting device based on an aeroengine core machine, so as to solve the problems in the prior art. In order to achieve the above object, the present invention provides the following technical solutions: according to a first aspect of the invention, a dynamic stability adjusting device based on an aeroengine core machine comprises a fixed matrix, a fixed base body and a support transfer tool, wherein the fixed matrix comprises a casing and support transfer tools fixed on two sides of the casing; The rotor system comprises a rotating shaft accommodated in the casing, and a high-pressure rotor and a high-vortex rotor are fixedly arranged on the rotating shaft; The standard support end, one end of the said spindle is connected with said casing rotation through front bearing and front support; the measurement support end, the other end of pivot through the rear bearing with the receiver is connected, the measurement support end includes: The rear bracket is fixed on the casing; The detection bearing seat tool is detachably arranged on the rear bracket through a fastener, a cylindrical cavity for accommodating and clamping the rear bearing is arranged in the detection bearing seat tool, and The integrated measurement system comprises a piezoelectric force sensor set arranged between the detection bearing seat tool and the rear bracket, and a key phase sensor for detecting the key phase mark of the rotating shaft. Further, the detection bearing seat tool comprises two symmetrical shells, and arc-shaped fixing cavities are symmetrically formed in the inner sides of the two shells. Furthermore, the two fixing cavities are combined together to form the cylindrical cavity, connecting pieces are arranged on two sides of the two shells, and the two shells are fastened together through fastening pieces penetrating through fixing holes in the connecting pieces. Further, the structure of the appearance installation dimension, the connection interface and the internal fixing cavity of the detection bearing seat tool is identical to the corresponding structure of the formal bearing seat tool. Further, a window is formed in the position, facing the rotor correction plane, of the casing, and the window is sealed by a detachable sealing plate. Further, the counterweight structure comprises counterweight plates with uniformly distributed threaded holes or T-shaped grooves at two ends of a roller of the rotating shaft. Further, the counterweight structure comprises mounting holes which are uniformly distributed on a final-stage compressor disk of the high-pressure rotor and a turbine disk of the Gao Guo rotor. The invention has the following advantages: 1. According to the dynamic stability adjusting device based on the aeroengine core machine, by adopting the detection bearing seat tool which is provided with the identical installation interface and the internal cavity structure as the formal bearing seat tool, the mechanical supporting environment of the rotor in the balance test is ensured to be completely consistent with the real working environment, so that the perfect balance state debugged in the test state can be maintained nondestructively and completely after the formal tool is replaced, error sources such as reference change, bolt pretightening force difference and the like caused by secondary assembly in the traditional process are fundamentally eliminated, and the ultimate balance precision is realized; 2. According to the dynamic stability adjusting device based on the aeroengine core machine, the split type shell is designed to realize safe and reliable clamping of the bearing outside the casing through the matching of the two shells and the connecting piece, a stable bearing-tool module is formed, and then the bearing is integrally installed, so that the high-risk operation of press fitting or impact disassemb