CN-115655693-B - Method and structure for detecting angle swing of main pump regulator of aero-engine

CN115655693BCN 115655693 BCN115655693 BCN 115655693BCN-115655693-B

Abstract

The invention relates to the field of aero-engine maintenance technology, in particular to an aero-engine main pump regulator angle swing detection method and a detection structure meeting the performance requirement of an engine high-pressure guide, comprising the following steps that a, a main pump regulator to be detected is connected with a fixing mechanism on a detection device; the method comprises the steps of (a) installing a high-pressure compressor actuator cylinder of an aeroengine on a high-pressure bracket corresponding to a detection device, installing a low-pressure compressor actuator cylinder of the aeroengine on a low-pressure bracket corresponding to the detection device, installing feedback mechanisms of the high-pressure compressor and the low-pressure compressor on the detection device, d, checking linearity and swinging conditions of a guide angle, e, repeating the step d again, f, returning to a repair procedure or an assembly procedure for fault elimination if linearity and swinging conditions of the guide angle are not qualified, and delivering a main pump regulator to an engine assembly and test procedure if linearity and swinging conditions of the guide angle are qualified.

Inventors

ZHANG YOU
WANG DUAN
YANG HONG
LIU XINGZHI
HU PING
LI QIANG
ZHENG JIE

Assignees

国营川西机器厂

Dates

Publication Date: 20260505
Application Date: 20221028

Claims (10)

1. The method for detecting the angle swing of the main pump regulator of the aero-engine is characterized by comprising the following steps of: a. firstly, fixedly arranging a detection device on the ground, and connecting a main pump regulator to be detected with a fixing mechanism on the detection device after all components of the main pump regulator are repaired; b. Installing a high-pressure compressor actuator cylinder of the aero-engine on a high-pressure bracket corresponding to the detection device, installing a low-pressure compressor actuator cylinder of the aero-engine on a low-pressure bracket corresponding to the detection device, and installing a corresponding sensor; c. The method comprises the steps that respective feedback mechanisms of a high-pressure compressor and a low-pressure compressor are arranged on a detection device, a high-pressure feedback dial and a low-pressure feedback dial of a main pump regulator are correspondingly connected respectively, and the movement of the feedback mechanism is ensured to be the same as the actual operation of an engine; d. starting an engine, adjusting inlet air pressure, setting the temperature of aviation kerosene in the engine to be the detection environment temperature, simultaneously setting the air inlet temperature of the engine to be within the range of-60 ℃ to 220 ℃, then adjusting the rotating speed of the engine, and checking the linearity and swing condition of the angle of a high-pressure compressor guider of a main pump regulator; e. setting the temperature of aviation kerosene in an engine to be 115+/-5 ℃, and repeating the step d again; f. if the linearity and swing condition of the angle of the guide are not qualified, returning to a repairing process or an assembling process for fault removal, and if the linearity and swing condition of the angle of the guide are qualified, delivering the main pump regulator to an engine assembling and test run process.
2. The method for detecting the angle swing of the main pump regulator of the aero-engine according to claim 1, wherein in the step b, two high-pressure compressor actuating cylinders of the aero-engine are provided, two high-pressure brackets of the detecting device are provided, and the high-pressure compressor actuating cylinders and the high-pressure brackets are arranged in a one-to-one correspondence.
3. The method for detecting the angle swing of the main pump regulator of the aero-engine according to claim 1, wherein in the step b, two low-pressure compressor actuating cylinders of the aero-engine are provided, two low-pressure brackets of the detecting device are provided, and the high-pressure compressor actuating cylinders and the low-pressure brackets are arranged in a one-to-one correspondence.
4. The method for detecting the angle swing of the main pump regulator of the aeroengine as claimed in claim 1, 2 or 3, wherein in the step c, the feedback mechanism is a feedback steel rope.
5. The method for detecting the angular oscillation of a main pump regulator of an aircraft engine according to claim 1,2 or 3, wherein in the step d, the inlet air pressure of the engine is p=1.57 MPa.
6. The method for detecting the angular oscillation of the main pump regulator of the aeroengine as claimed in claim 1,2 or 3, wherein in the step d, the engine intake temperature is adjusted at-60 ℃,45 ℃, 0 ℃,15 ℃,45 ℃, 80 ℃, 185 ℃ and 220 ℃ respectively, and then the linearity and the oscillation condition of the angle of the high-pressure compressor guide of the main pump regulator under corresponding conditions are checked.
7. The detection structure for realizing the method for detecting the angle swing of the main pump regulator of the aeroengine according to any one of claims 1 to 6, wherein the detection device comprises a bottom plate (1) and a mounting plate (2) arranged on the bottom plate (1), and is characterized in that a fixing structure for fixing the main pump regulator is arranged on the mounting plate (2), a high-pressure bracket and a low-pressure bracket are arranged on the mounting plate (2), the high-pressure bracket and the low-pressure bracket are respectively connected with a high-pressure compressor actuator cylinder and a low-pressure compressor actuator cylinder in a matching way, and respective feedback mechanisms of the high-pressure compressor and the low-pressure compressor are arranged on the detection device, and the feedback mechanisms are respectively connected with a high-pressure feedback dial and a low-pressure feedback dial of the main pump regulator in a corresponding way.
8. The detecting structure for detecting the angle swing of the main pump regulator of the aeroengine according to claim 7, wherein the feedback mechanism is a feedback steel rope or a feedback pull rod.
9. The detection structure for realizing the method for detecting the angle swing of the main pump regulator of the aeroengine according to claim 7, wherein the rotating shaft (18) is arranged on the bottom plate (1), and the mounting plate (2) is rotatably arranged on the rotating shaft (18) through the shaft sleeve (17).
10. The detection structure for realizing the method for detecting the angle swing of the main pump regulator of the aeroengine according to claim 9, wherein the side edge of the bottom plate (1) is provided with a mounting plate locking plate (101), a limiting chute (103) is arranged in the mounting plate locking plate (101), a mounting plate limiting bolt on the mounting plate (2) is slidably arranged in the limiting chute (103), and a limiting nut (102) is matched and arranged on the mounting plate limiting bolt.

Description

Method and structure for detecting angle swing of main pump regulator of aero-engine Technical Field The invention relates to the field of aeroengine maintenance technology, in particular to an aeroengine main pump regulator angle swing detection method and a detection structure. Background The parameter swing fault is a large repair quality problem for the aero-engine, other parameters such as n2 (high-pressure rotor rotating speed), T4 (low-pressure turbine rear temperature) and the like can be caused to swing in the use process, the engine cannot participate in the flight training of the aero-engine if the engine is light, and the engine vibration is large if the engine is heavy. When the device is used for repairing, the swing fault of the angle swing (alpha 2 for short) of the adjustable guide vane of the high-pressure compressor of the main pump regulator frequently occurs, and part of the swing fault is a new engine which is not used, which indicates that related researches are not developed at home and abroad. Therefore, in order to ensure the safety and reliability of the aircraft and the engine and improve the repair quality of the aviation equipment, it is necessary to develop research on the inhibition of the alpha 2 swing fault of the main pump regulator of the aircraft engine, and prevent the alpha 2 swing fault, so as to prevent the property loss of the engine, the aircraft and the like caused by the fact that the repair method is not in place, and influence the use of the aircraft. Disclosure of Invention The invention aims to solve the technical problem of providing a main pump regulator high-pressure guide device angle swing detection device, so that the main pump regulator is ensured to be in a follow-up state. The method and the structure for detecting the angle swing of the main pump regulator of the aeroengine can meet the performance requirement of the high-pressure guider of the engine. The technical scheme includes that a detection device is fixedly arranged on the ground, after all components of the main pump regulator are repaired, the main pump regulator to be detected is connected with a fixing mechanism on the detection device, b, a high-pressure air compressor actuator of an aeroengine is installed on a high-pressure support corresponding to the detection device, a low-pressure air compressor actuator of the aeroengine is installed on a low-pressure support corresponding to the detection device and is provided with a corresponding sensor, C, feedback mechanisms of the high-pressure air compressor and the low-pressure air compressor are installed on the detection device, the feedback mechanisms are respectively connected with the high-pressure feedback and the low-pressure feedback of the main pump regulator, the movement of the feedback mechanisms is identical to the actual work of the engine, d, starting the engine, adjusting inlet air pressure, setting the temperature of aviation kerosene in the engine to be the detection environment temperature, simultaneously adjusting the air inlet temperature of the engine to be within a range of-60 ℃ to 220 ℃, then adjusting the rotating speed of the engine, checking the high-pressure air compressor and the low-pressure air compressor actuator to be the linear guide angle of the main pump regulator to be equal to the actual work of the engine, and the engine to the actual work of the engine, and the linear guide angle of the main pump regulator to be equal to the actual work of the engine is guaranteed, and the linear angle of the engine is not equal to the actual work is guaranteed, and if the working procedure is finished, and the working procedure is repeated, and the working procedure of the working procedure is finished after the step is finished, and the working procedure is finished, and if the working procedure is finished. In the step b, two high-pressure compressor actuating cylinders of the aero-engine are arranged, two high-pressure brackets of the detection device are arranged, and the high-pressure compressor actuating cylinders and the high-pressure brackets are arranged in a one-to-one correspondence. In the step b, two low-pressure compressor actuating cylinders of the aero-engine are arranged, two low-pressure brackets of the detection device are arranged, and the high-pressure compressor actuating cylinders and the low-pressure brackets are arranged in a one-to-one correspondence. Further, in step c, the feedback mechanism is a feedback wire rope. Further, in step d, the inlet air pressure of the engine is p=1.57 MPa. Further, in step d, the engine speed is adjusted at-60 ℃, 45 ℃,0 ℃, 15 ℃, 45 ℃, 80 ℃, 185 ℃ and 220 ℃ respectively, and then the linearity and swing condition of the angle of the high-pressure compressor guide of the main pump regulator under corresponding conditions are checked. Further, the detection device comprises a bottom plate and a mounting plate arranged on the bottom plate, a fixing structure f