Vibratory fatigue testing method of aviation-engine blades based on electrodynamics vibration generator

Abstract

The invention belongs to the technical field of testing of vibratory fatigue and in particular relates to a vibratory fatigue testing method of aviation-engine blades based on an electrodynamics vibration generator; the method aims at solving over-testing or insufficient testing problem in the prior art and comprises the steps: calibrating a maximum vibratory stress response point, choosing auxiliary monitoring points, choosing sine constant-frequency stabilization and simulation blades, judging the fatigue destruction of the blades and analyzing testing results. By adopting the steps of choosing the auxiliary monitoring points and choosing the sine constant-frequency stabilization and simulation blades, the vibratory stress level (the fluctuation error is within 2%) of the blades in the testing process is stabilized effectively, the testing precision is guaranteed and the full-process monitoring of the vibratory stress level of the blades at the maximum stress point is realized.

Description

technical field [0001] The invention belongs to the technical field of vibration fatigue tests, in particular to an aeroengine blade vibration fatigue test method based on an electrodynamic vibration table. Background technique [0002] The aero-engine is regarded as the "heart" of a fighter plane, and the engine blade is the part with the worst working environment and the most complex structure of the aero-engine, and it is also the main failure-prone part of the engine. The reliability of aeroengine blades restricts the requirements of high thrust-to-weight ratio, high applicability, high reliability, durability and low cost of modern high-performance aeroengines. [0003] During the working process, the blades of aero-engines will bear heavy alternating loads for a long time. When the magnitude of the alternating load exceeds the corresponding fatigue limit, fatigue cracks will appear on the blade within the design life, and gradually develop to fatigue fracture, and eng...

AI Technical Summary

Problems solved by technology

This is often accompanied by the following problems: due to the small-scale drift (0-2Hz) of the resonant frequency of the blade, the amplitude of the vibration response also drifts, making the stress at the point of the maximum response stress of the blade unstable, and there are often overtests or undertests. The test results have a great impact; a

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