System, device and method for testing service life of aero-engine blade

A technology of aero-engine and test system, applied in the direction of engine test, jet engine test, gas turbine engine test, etc., can solve the problems of complicated operation, long test time, affecting the service life of parts, etc.

Pending Publication Date: 2021-04-30
成都成发泰达航空科技股份有限公司
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, there are usually 32 blades installed on the turbine disc rotor, each blade needs to be measured, the detection time is long, the operation is complicated, and the surface of the part is easily scratched during the operation, which affects the service life of the part

Method used

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  • System, device and method for testing service life of aero-engine blade
  • System, device and method for testing service life of aero-engine blade
  • System, device and method for testing service life of aero-engine blade

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Experimental program
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Embodiment 1

[0034] According to an embodiment of the present application, an aeroengine blade life testing system is provided, which is used for testing and confirming the blade life of the aeroengine blade.

[0035] see figure 1 , the test system for the life of the aero-engine blade includes a reference standard pipeline, a test part pipeline, an air supply pipeline and a differential pressure gauge; among them, the air supply pipeline is used for the air supply of the entire system; the differential pressure gauge is used for measuring and testing The pressure difference between the air source standard pipeline and the test part pipeline.

[0036] In actual operation, the lasting life of the blades can be confirmed indirectly by comparing the pressure difference between the gas passing through the turbine disk and the reference standard pipeline, which can improve the efficiency of detection, stabilize the quality of the assembled turbine disk, and ensure the reliable operation of the ...

Embodiment 2

[0056] According to an embodiment of the present application, on the basis of the above-mentioned embodiments, an aero-engine blade life testing device is further provided, which includes the aero-engine blade life testing system involved in the above-mentioned embodiment.

[0057] In this embodiment, the specific installation structure of the test system for the blade life of the aeroengine is improved.

[0058] see Figure 2 ~ Figure 4 According to the invention, the test device for the life of the aero-engine blade includes an installation stand, on which the test system for the life of the aero-engine blade is installed.

[0059] The table top of the installation platform is a thin plate, which is specifically selected as a stainless steel sheet; the thin plate is fixed on the angle steel by screws to form the overall structure of the installation platform.

[0060] Mounting holes are opened on the thin plate, and correspondingly, instruments such as pressure gauge a, pre...

Embodiment 3

[0066] In the application of the present invention, a test method for the life of an aeroengine blade is also provided, based on the above-mentioned embodiments.

[0067] The specific method steps for the life test of aero-engine blades are as follows:

[0068] 1. Blockage of each blade cooling air intake of the turbine rotor assembly.

[0069] Plug each blade cooling air intake of the turbine rotor with a plug of rubber or equivalent material to prevent galling of the parts.

[0070] 2. Lubricate the test tool interface, and fasten the turbine rotor assembly to the test tool interface.

[0071] Among them, apply lubricating oil to the test tool interface of the aero-engine blade life test device. The lubricating oil can be MIL-PRF-7808 or other similar equivalent lubricating oil, and the turbine rotor assembly is placed on the test tool interface, see Figure 5 , so that the leading edge 22 of the blade faces to the left, that is, toward the upper direction of the test fixt...

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Abstract

The invention discloses a system, device and method for testing the service life of an aero-engine blade, and the system, device and method enable the whole part to be detected during the testing of the service life of the aero-engine blade through the improved design of the structural method of the system, device and method for testing the service life of the aero-engine blade. Confirmation can be carried out by determining the pointing direction of the pointer of the differential pressure gauge, the service life of the blade is guaranteed, meanwhile, the situation that in the prior art, lots of detection devices are used, lots of manpower and time are consumed is avoided, and detection efficiency is improved. Meanwhile, due to the fact that the number of operation steps is small, the part surface damage probability is greatly reduced, and manufacturing and maintenance cost is low.

Description

technical field [0001] The invention relates to the field of engine blade testing, in particular to an aeroengine blade life testing system, device and method. Background technique [0002] The auxiliary power unit is a power unit on the aircraft except the main engine. Its function is to independently provide air-conditioning bleed air and power supply for the aircraft, and at the same time provide compressed air to assist the engine to start. It is an important and indispensable system on the aircraft. It is the most complex and precise device on the aircraft except the main engine. [0003] At present, the turbine rotor is mainly composed of turbine disks and blades; blade grooves are evenly distributed in the circumferential direction of the turbine disks for the installation of blades. Since the turbine rotor works in a high-temperature and high-pressure gas environment for a long time, the assembly condition of the turbine disc and the blade will directly affect the s...

Claims

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Application Information

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IPC IPC(8): G01M13/00G01M3/02G01M3/26G01M15/02G01M15/14
CPCG01M13/00G01M3/025G01M3/26G01M15/02G01M15/14
Inventor 胡敏赵俊伟罗啸
Owner 成都成发泰达航空科技股份有限公司
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