An experimental platform for aero-engine vibration control

A technology of aero-engine and experimental platform, applied in the direction of engine test, vibration test, machine/structural component test, etc., can solve the problem of not being able to meet the further requirements, achieve less difficulty in transformation, avoid the failure of experimental results, and the cost of transformation low effect

Inactive Publication Date: 2018-10-02
SUZHOU DONGLING VIBRATION TEST INSTR +1
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The existing experimental platform for research on vibration control of aero-engines simplifies aero-engines into different forms of rotor systems, which are used to study the dynamic response characteristics of aero-engines under various single or these few factors, and play a role in promoting the development of high-performance aero-engine technology. It plays an important role and has accumulated a large number of excellent results, but it can no longer meet the further research needs of multi-factor coupling vibration response characteristics that are more consistent with the actual operation of aero-engines.

Method used

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  • An experimental platform for aero-engine vibration control
  • An experimental platform for aero-engine vibration control
  • An experimental platform for aero-engine vibration control

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0040] Example 1. Research on vibration characteristics of aero-engine high-pressure rotor:

[0041] Start the second drive motor 22, and the power output by the second drive motor 22 is transmitted to the high-voltage rotor through the output shaft and the transmission system near the aero-engine of the second coupling 7, thereby driving the rotation of the high-pressure rotor system 12 to simulate the high-pressure rotor of the aero-engine Operation; The capacitive displacement sensor 8 installed on the output shaft of the second drive motor 22 and the connecting shaft of the outer rotor of the aeroengine is used to measure the axial runout and radial runout of the rotating shaft. It is installed on the 2-3 level of the aeroengine The three-way acceleration sensor on box Ⅱ, 6-level receiver Ⅴ, combustion chamber receiver VI and high-pressure turbine receiver VII collects vibration acceleration signals, connects the sensor output line to the data acquisition system, and the data ...

Embodiment 2

[0042] Example 2: Research on vibration characteristics of aero-engine low-pressure rotor:

[0043] Start the first drive motor 21, the power output by the first drive motor 21 is transmitted to the low-pressure rotor system 11 through the output shaft and the first coupling 6, thereby driving the low-pressure rotor system 11 to rotate, simulating the operation of the low-pressure rotor of an aero engine, The working speed is 300r / min; the capacitive displacement sensor 8 installed on the connecting shaft between the output shaft of the first drive motor 21 and the inner rotor of the aero-engine is used to measure the axial and radial runout of the rotating shaft; it is installed on the aero-engine The three-way acceleration sensor on the 2-3 level receiver II, level 6 receiver V, combustion chamber receiver VI, and high-pressure turbine receiver VII corresponding to the 5 support bearings, collect vibration acceleration signals, and connect the sensor output line to data acquisit...

Embodiment 3

[0044] Example 3 Research on the vibration characteristics of the aero engine:

[0045] The first and second motors are started at the same time, and the two motors rotate forward synchronously to simulate the operation of the dual-rotor system of an aero-engine; the speed of the low-pressure rotor is 0~300r / min, and the speed of the high-pressure rotor is 0~1500r / min. A capacitive displacement sensor 8 on the output shaft of the drive motor 21, the inner rotor connecting shaft and the outer rotor connecting shaft of the aeroengine, used to measure the axial runout and radial runout of the rotating shaft; corresponding to the 5 support bearings installed in the aeroengine The three-way acceleration sensor on the 2-3-level receiver II, the sixth-level receiver V, the combustion chamber receiver VI and the high-pressure turbine receiver VII collects vibration acceleration signals; connect the sensor output line to the data acquisition system, and the data acquisition system will Af...

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Abstract

A vibration control experiment platform for an aero-engine comprises the components of an experiment platform base, an aero-engine body, a driving system, a testing control system and a security protecting device. A first driving motor of the driving system transmits a power to a low-pressure rotor system of the aero-engine body. A second driving motor transmits the power to a high-pressure rotor system of the aero-engine body through a second coupling and an accessory transmission system of the aero-engine body. A motor output shaft, the low-pressure rotor system and the high-pressure rotor system are provided with capacitive displacement sensors. A second-stage case, a third-stage case, a six-stage case, a combustion chamber case and a high-pressure turbo case which correspond with five supporting bearings of the aero-engine are provided with three-dimensional vibration acceleration sensors. The vibration control experiment platform can be used testing and analyzing a multi-factor coupled vibration problem of the aero-engine. The vibration control experiment platform can be widely used for researching vibration characteristic and vibration control strategy of an aero-engine double-rotor system.

Description

Technical field [0001] The invention relates to an engine experiment device, in particular to an aero engine experiment platform. Background technique [0002] As the power unit of an aircraft, aero engines are the key to measuring the level of power research and development and manufacturing of a country, and an important indicator of the strength of a large country. The research on related technologies has extremely high political, economic and military value. In recent years, the requirements for engine performance have been continuously improved, and the load of engine components has increased significantly, resulting in a very prominent vibration problem. Vibration control has become one of the important research projects of aeroengines. [0003] The research of aero-engine vibration control technology needs the support of corresponding experimental platforms. The existing experimental platforms are generally oriented to the local construction of aero-engines and are suitable ...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G01M15/00G01M7/02
CPCG01M7/02G01M7/025G01M15/00
Inventor 蒋玲莉韩清凯王孝忠徐曼冯和英陈广飞
Owner SUZHOU DONGLING VIBRATION TEST INSTR
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