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Testing device and testing method of integral-impeller blade vibration fatigue

An integrated impeller and vibration fatigue technology, which is applied in vibration testing, measuring devices, testing of machine/structural components, etc., can solve the problems of difficult cutting of blades and low efficiency of blade vibration fatigue tests, so as to avoid changes, ensure reliability, The effect of improving test efficiency

Active Publication Date: 2013-07-10
CHINA AVIATION POWER MACHINE INST
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0006] The purpose of the present invention is to provide an impeller blade vibration fatigue test device and test method to solve the technical problems that the blades of the existing integrated impeller are difficult to cut and the efficiency of the blade vibration fatigue test is low

Method used

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  • Testing device and testing method of integral-impeller blade vibration fatigue
  • Testing device and testing method of integral-impeller blade vibration fatigue

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Embodiment Construction

[0031] The embodiments of the present invention will be described in detail below with reference to the accompanying drawings, but the present invention can be implemented in many different ways defined and covered by the claims.

[0032] refer to figure 1 , the preferred embodiment of the present invention provides a vibration fatigue test device for an integral impeller blade, comprising a vibration test bench 10 and an integral impeller 20, the integral impeller 20 is axially compressed and fixed on the vibration test bench 10 through a clamp 30;

[0033] The vibration test bench 10 is connected with a vibration device for initiating vibration; the integral impeller 20 is connected with a detection device for detecting and recording test parameters;

[0034] Rubber damping blocks 22 are provided between adjacent blades on the integral impeller 20 to damp the adjacent blades. Specifically, the tested blade on the integral impeller 20 is set as a free blade 21 that can vibra...

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Abstract

The invention discloses a testing device and a testing method of integral-impeller blade vibration fatigue. The testing device comprises a vibration testing platform and an integral impeller, wherein the integral impeller is axially pressed through a fixture and is fixed on the vibration testing platform; the vibration testing platform is connected with a vibration device used for starting oscillation; the integral impeller is connected with a detection device used for detecting and recording testing parameters; and a rubber damping block enabling adjacent blades to be mutually damped is installed between the adjacent blades of the integral impeller. According to the testing device and the testing method, each rubber damping block is installed between the adjacent blades of the integral impeller to enable the adjacent blades to be mutually damped, the fact that other blades cannot vibrate freely when vibration fatigue testing is conducted on a single blade of the integral impeller is guaranteed, troubles caused by equal division of the integral impeller are avoided, rigidity change of a wheel disc supporting the blades is prevented from leading to change of inherent frequency of the blades, and therefore reliability of vibration fatigue testing results is guaranteed.

Description

technical field [0001] The invention relates to the field of aero-engine tests, in particular to an aero-engine impeller blade vibration fatigue test device and a test method. Background technique [0002] Aeroengine blades are one of the most critical parts in aeroengines. Due to the vibration fatigue failure of the blades, it may cause the engine to stop in the air, and sometimes even cause serious accidents. Therefore, in the development stage of aero-engines, it is very necessary and meaningful to conduct blade vibration fatigue tests to find out various defects in blade design and manufacture. [0003] The rotor blades and discs of most aero-engines are designed separately, and the tenons of the rotor blades must be installed in the tenon grooves of the discs to connect the blades and the discs together. The vibration fatigue test method for this single rotor blade that is not integrated with the disc is: design a special fixture (or transition section) that can simul...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01M7/02
Inventor 王平侯明
Owner CHINA AVIATION POWER MACHINE INST
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