Cyclic test device for fatigue of aeroengine compressor blade

Abstract

The invention relates to a cyclic test device for fatigue of an aeroengine compressor blade. The cyclic test device comprises a centrifugal force loading assembly for simulating cyclic loading of centrifugal force on the aeroengine compressor blade during working; the test device also comprises a high-frequency vibration loading assembly for simulating high-frequency loads on the aeroengine compressor blade during working; the high-frequency vibration loading assembly comprises vibrating table, a support A for fixing a compressor blade test piece and a support B for fixing the centrifugal force loading assembly, wherein the vibrating table is used for applying high-frequency vibration on the compressor blade test piece. The cyclic test device for the fatigue of the aeroengine compressor blade is simple in structure and convenient to operate; the cyclic test device is capable of simulating the low cyclic loading of the centrifugal force and the high-frequency loads on the aeroengine compressor blade during working so that the test state is completely consistent with the actual working state, and therefore, the centrifugal force loading test and the high-frequency load test of the compressor blade are realized, completely trustable predetermined safe cycle life is provided and then potential safety hazards in use can be avoided.

Description

technical field [0001] The invention relates to the field of aero-generator tests, in particular to a test device for testing the performance of an aero-engine compressor blade. Background technique [0002] As one of the key and important components of an aero-engine, the compressor blade plays a vital role in the structural integrity and reliability of the engine. Usually, the failure of the compressor blade will cause a major safety accident, or even crash the aircraft. Therefore, in order to ensure the safe use of compressor blades, it is necessary to give the predetermined safe cycle life of its assessment parts through experiments. However, due to the relatively complex loads on the compressor blades, the engine not only has to bear centrifugal force and low cycle loads, but also high-frequency vibration loads when the engine is actually working. Under the experimental conditions of the existing test equipment, only the low cycle load of centrifugal force can be simul...

AI Technical Summary

Problems solved by technology

[0003] The object of the present invention is to aim at the above-mentioned problem that existing aeronautical engine compressor blade fatigue cycle test device exists, and a kind of aeroengine compressor blade fatigue cycle test device is provided, and this test device can be used for simulating Centrifugal low cycle load and high frequency load provide test means to solve the problems of low reliability of predetermined safe cycle life given by existing test devices and test methods and potential safety hazards in use

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