Fatigue Mechanism Experiment Method of Blade Fracture Failure in Aero-engine

doi:10.3901/JME.2019.13.072

Abstract

Abstract: Aiming at the blade fracture failure of the aero-engine, a testing methodology for researching the fatigue mechanism is proposed, in which the square plate specimen is designed by FEM (finite element modal) analysis, as the simulation of the blade, is driven into the high order composite bending-torsional mode by base excitation. The results show that the high order composite bending-torsional mode which causes the blade fracture failure can be effectively simulated by the composite double-torsional and bending mode of the specimen in the resonant test. At the resonant fatigue test, complex nonlinearity is appeared in the vibration of the specimen, which significantly affects the progress of the experiment. The data of the resonant fatigue experiment results can be accurately determined by the crack criterion developed for the specimen, which confirms that it's feasible to simulate the blade fracture failure with the specimen.

Key words: blade fracture failure, composited bending-torsion resonance, crack criterion, fatigue strength, specimen simulating blade

CLC Number:

V232

CHENG Li, CHEN Lishun, LI Silu, LIU Jingyuan. Fatigue Mechanism Experiment Method of Blade Fracture Failure in Aero-engine[J]. Journal of Mechanical Engineering, 2019, 55(13): 72-79.

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