CN-119508284-B - Multi-correction-surface progressive balancing method for rotor drum of high-pressure compressor of aero-engine

CN119508284BCN 119508284 BCN119508284 BCN 119508284BCN-119508284-B

Abstract

The invention discloses a progressive balancing method for multiple correction surfaces of a rotor drum of an aeroengine, which comprises the steps of lifting a high-pressure rotor to a dynamic balancing machine, assembling a counterweight, measuring initial unbalance, removing the counterweight, measuring real-time unbalance again, balancing the difference between the real-time unbalance of the three-stage correction surface of the drum, the four-stage correction surface of the drum or the six-stage correction surface of the drum to be less than or equal to 50g.mm according to the phase difference of the real-time unbalance of the three-stage correction surface of the drum and the real-time unbalance of the four-stage correction surface of the drum and the real-time unbalance of the three-stage correction surface of the drum, and balancing the difference between the real-time unbalance of the three-stage correction surface of the drum, the four-stage correction surface of the drum or the six-stage correction surface of the drum and the corresponding initial unbalance of the six-stage correction surface of the drum to be less than or equal to 10g.mm, removing the high-pressure rotor, assembling rotor discs and shafts, and balancing the real-time unbalance of the front end correction surface of the rotor to be less than or equal to 10g.mm. The invention eliminates unbalanced moment in the rotor step by step, and reduces the bending deformation of the flexible rotor under unbalanced excitation at high rotation speed.

Inventors

YANG BIN
LUO ZHANG
YAN LE
SUN TONG
HU LEI
TAN KUN
Zou Saiqun
ZHANG HUAIQING
SHEN KUI
SU XINWEN
LONG YIXIN
JIA YANFEI
LI LIANGHUI
LIU QIWEN
TONG MING
HUANG XIANGRONG
YUAN ZHONGWEI

Assignees

国营川西机器厂

Dates

Publication Date: 20260505
Application Date: 20241129

Claims (9)

1. The progressive balancing method for the multiple correction surfaces of the rotor drum of the high-pressure compressor of the aeroengine is characterized by comprising the following steps of: Fixing the front journal end of the high-voltage rotor by adopting a fixing bracket, and fixing the six-stage rotor on a pressing plate of the fixing bracket; Assembling a balancing device on the high-pressure rotor; After the high-pressure rotor is hoisted to the dynamic balancing machine, the factory balance weight is assembled on each correction surface, and then the initial unbalance amounts of the three-level correction surface of the drum, the four-level correction surface of the drum, the one-level correction surface of the drum and the six-level correction surface of the drum are measured; Measuring the real-time unbalance amount of the three-stage correction surface of the drum, the four-stage correction surface of the drum, the one-stage correction surface of the drum and the six-stage correction surface of the drum again after the factory balance weights assembled on the correction surfaces are taken down in situ; according to the real-time unbalance phase differences of the three-stage correction surface and the four-stage correction surface of the drum and the real-time unbalance values of the four-stage correction surface and the three-stage correction surface of the drum, the real-time unbalance values of the three-stage correction surface of the drum or the four-stage correction surface of the drum or the one-stage correction surface and the six-stage correction surface of the drum and the corresponding initial unbalance values are balanced to be less than or equal to 50g.mm; Removing the high-pressure rotor from the balancing machine, and assembling a rotor disc and a shaft on the high-pressure rotor; and hoisting the high-pressure rotor to a dynamic balancing machine, and balancing the real-time unbalance values of the front-end correcting face and the rear-end correcting face of the rotor to be less than or equal to 10g.mm.
2. A method of progressive balancing multiple correction surfaces of a rotor drum of an aircraft engine high pressure compressor according to claim 1, wherein said assembling balancing means on the high pressure rotor comprises: Operating the fixed support to enable the front journal end of the high-pressure rotor to be upward, and assembling a process bearing at the front journal end; a balancing device is assembled on the process bearing, and a fixing bracket is operated to enable the six-stage rotor end to be upward; and a six-stage locating plate of the heating balance device is used for fixing the six-stage locating plate and the six-stage rotor end.
3. The method for progressively balancing multiple correction surfaces of a rotor drum of an aircraft engine according to claim 1, wherein balancing the difference between the real-time unbalance of the three-stage correction surface, the four-stage correction surface, or the one-stage correction surface, the six-stage correction surface of the drum and the initial unbalance corresponding to the three-stage correction surface, the four-stage correction surface, and the three-stage correction surface to 50g.mm or less according to the phase difference of the real-time unbalance of the three-stage correction surface, the four-stage correction surface, and the real-time unbalance of the three-stage correction surface, comprises: Calculating the phase difference of the initial unbalance amount of the three-stage correction surface and the four-stage correction surface of the drum; When the phase difference of the real-time unbalance amounts of the three-stage correction surface and the four-stage correction surface of the drum is larger than 100 degrees and the magnitude of the real-time unbalance amount of the three-stage correction surface of the drum is larger than the magnitude of the real-time unbalance amount of the four-stage correction surface of the drum, firstly balancing the one-stage correction surface of the drum, reducing the real-time unbalance amount of the three-stage correction surface of the drum by 1/3, then balancing the six-stage correction surface of the drum, reducing the real-time unbalance amount of the four-stage correction surface of the drum by 1/3, and finally balancing the three-stage correction surface of the drum and the four-stage correction surface of the drum until the actual unbalance amount and the corresponding initial unbalance amount are respectively smaller than 50g.mm; when the phase difference of the real-time unbalance amounts of the drum three-stage correction surface and the drum four-stage correction surface is larger than 100 degrees and the real-time unbalance amount of the drum three-stage correction surface is smaller than the real-time unbalance amount of the drum four-stage correction surface, firstly balancing the drum six-stage correction surface, reducing the real-time unbalance amount of the drum four-stage correction surface by 1/3, then balancing the drum one-stage correction surface, reducing the real-time unbalance amount of the drum three-stage correction surface by 1/3, and finally balancing the drum three-stage correction surface and the drum four-stage correction surface until the real-time unbalance amount and the corresponding initial unbalance amount are respectively smaller than 50g.mm.
4. A method of progressive balancing of multiple correction surfaces of a rotor drum of an aircraft engine according to claim 3, wherein said calculating the phase difference of the initial unbalance amounts of the three correction surfaces of the drum and the four correction surfaces of the drum further comprises: When the phase difference of the real-time unbalance amounts of the three-stage correction surface and the four-stage correction surface of the drum is smaller than or equal to 100 DEG and the real-time unbalance amount of the three-stage correction surface of the drum is larger than the real-time unbalance amount of the four-stage correction surface of the drum, firstly balancing the three-stage correction surface of the drum to ensure that the unbalance amount of the three-stage correction surface of the drum is equal to the unbalance amount of the four-stage correction surface of the drum in opposite directions, and then respectively balancing the first-stage correction surface of the drum and the six-stage correction surface of the drum until the actual unbalance amount is smaller than 50g.mm with the corresponding initial unbalance amount; When the phase difference of the real-time unbalance amounts of the drum three-stage correction surface and the drum four-stage correction surface is smaller than or equal to 100 degrees and the real-time unbalance amount of the drum three-stage correction surface is smaller than the real-time unbalance amount of the drum four-stage correction surface, the drum four-stage correction surface is balanced firstly to ensure that the unbalance amount is equal to the unbalance amount of the drum three-stage correction surface in opposite directions, and then the drum one-stage correction surface and the drum six-stage correction surface are balanced until the actual unbalance amount is smaller than 50g.mm than the corresponding initial unbalance amount.
5. The method for progressively balancing multiple correction surfaces of a rotor drum of an aircraft engine high pressure compressor according to claim 1, wherein the balancing device comprises a balancing device body, a six-stage locating plate arranged at one end of the balancing device body, and a flange locating plate arranged at the other end of the balancing device body.
6. A method of progressive balancing of multiple correction surfaces of a rotor drum of an aeroengine high pressure compressor according to claim 1, wherein said fixed support comprises a support frame (11), a high pressure rotor holder rotatably arranged on said support frame (11) and a control member (12) for controlling the rotation of said high pressure rotor holder; the high-voltage rotor fixing frame comprises at least two connecting rods (13), a supporting rod (14) fixed at one end of each connecting rod (13) and arranged on the same plane for supporting the front shaft neck end, a fixing plate (16) fixed at the other end of each connecting rod (13), a pressing plate (15) arranged between the supporting rod (14) and the fixing plate (16), and an adjusting screw (17) connected between the pressing plate (15) and the fixing plate (16) and used for adjusting the distance between the supporting rod (14) and the pressing plate (15).
7. The progressive balancing method for multiple correction surfaces of a rotor drum of an aeroengine high-pressure compressor according to claim 6, characterized in that rollers (18) are arranged at the bottom of the supporting frame (11).
8. Method for progressive balancing of multiple correction surfaces of a rotor drum of an aeroengine high-pressure compressor according to claim 6, characterized in that said connecting rods (13) are 3 and are arranged parallel to each other, wherein two connecting rods (13) are rotatably arranged on said support frame (11).
9. Method for progressive balancing of multiple correction surfaces of a rotor drum of an aeroengine high-pressure compressor according to claim 6, characterized in that said presser plate (15) has a semicircular arc shape.

Description

Multi-correction-surface progressive balancing method for rotor drum of high-pressure compressor of aero-engine Technical Field The invention belongs to the technical field of rotor drum correction surface balance, and particularly relates to a multi-correction surface progressive balancing method for a rotor drum of a high-pressure compressor of an aero-engine. Background The vibration faults ‌ of the aero-engine refer to abnormal vibration phenomena of the aero-engine in the running process, and the faults not only affect the normal operation of the engine, but also can seriously affect the service life and the flight safety of the engine. The reasons for vibration failure are various and mainly include rotor imbalance, rotor-stator rub, misalignment, thermal bending, blade vibration, etc ‌. The existing rotor balancing adopts a step-by-step balancing method for reinforcing a rotor of a disc-type compressor with the application number of CN202311036176.8, and comprises the following steps: S101, performing static balance adjustment on the rotating shaft to be within an allowable range, and marking mass emphasis of the rotating shaft; S102, mounting a middle-stage impeller on the rotating shaft by taking the mass key point obtained in the step S101 as a reference; S103, performing static balance adjustment on the intermediate rotor obtained in the S102, adjusting to an allowable range and marking mass emphasis; s104, mounting two impellers of a middle stage impeller on the rotating shaft along the two sides of the axial direction of the rotating shaft by taking the mass key point obtained in the step S103 as a reference; S105, performing dynamic balance adjustment on the finally obtained intermediate rotor, adjusting the final rotor to be within an allowable range and marking mass emphasis; S106, mounting two impellers of a middle stage impeller on the rotating shaft along the two axial sides of the rotating shaft by taking the final obtained mass key as a reference; And S107, repeating the steps S105-S106 until all impellers are installed, and adjusting the dynamic balance of the compressor rotor to be within an allowable range. Because the rotor body of the high-pressure compressor of the aero-engine is an elastic flexible rotor and has the property of crossing multi-order critical rotating speeds in the working process, the balance of the installed balanced rotor is poor by adopting the method. Disclosure of Invention The invention provides a method for gradually balancing multiple correction surfaces of a rotor drum of a high-pressure compressor of an aeroengine, which aims to solve the problem that an existing method is poor in rotor balance of installation balance of an elastic flexible rotor. The aim of the invention is realized by the following technical scheme: The invention discloses a multi-correction-surface progressive balancing method for a rotor drum of a high-pressure compressor of an aeroengine, which comprises the following steps of: Fixing the front journal end of the high-voltage rotor by adopting a fixing bracket, and fixing the six-stage rotor on a pressing plate of the fixing bracket; Assembling a balancing device on the high-pressure rotor; After the high-pressure rotor is hoisted to the dynamic balancing machine, the factory balance weight is assembled on each correction surface, and then the initial unbalance amounts of the three-level correction surface of the drum, the four-level correction surface of the drum, the one-level correction surface of the drum and the six-level correction surface of the drum are measured; Measuring the real-time unbalance amount of the three-stage correction surface of the drum, the four-stage correction surface of the drum, the one-stage correction surface of the drum and the six-stage correction surface of the drum again after the factory balance weights are assembled on the correction surfaces in situ; according to the real-time unbalance phase differences of the three-stage correction surface and the four-stage correction surface of the drum and the real-time unbalance values of the four-stage correction surface and the three-stage correction surface of the drum, the real-time unbalance values of the three-stage correction surface of the drum or the four-stage correction surface of the drum or the one-stage correction surface and the six-stage correction surface of the drum and the corresponding initial unbalance values are balanced to be less than or equal to 50g.mm; Removing the high-pressure rotor from the balancing machine, and assembling a rotor disc and a shaft on the high-pressure rotor; and hoisting the high-pressure rotor to a dynamic balancing machine, and balancing the real-time unbalance values of the front-end correcting face and the rear-end correcting face of the rotor to be less than or equal to 10g.mm. The beneficial effects of the invention are as follows: the invention eliminates unbalanced moment in the rotor step by a multi-c