Abstract
The vibration frequency of the aero-engine blade is affected by its own mass characteristics and steady-state centrifugal force, which can be used to adjust the blade resonance frequency to avoid the exciting source and prolong the fatigue life of the blade, and can also be used to approach the exciting source frequency and guide the design of ultrasonic fatigue specimens. Through the combination of mechanical analysis and finite element simulation, the influence mechanism of geometric parameters and axial tension on modal frequency is analyzed from the point of view of vibration and energy, the influence law is obtained, and the optimal design of two kinds of three-point bending specimens is completed. The resonant frequency error calculated by finite element method is controlled within ±5Hz, and the frequency is 20.03 kHz verified by ultrasonic fatigue test, which meets the accuracy requirements, which provides a reliable theoretical support for the design of simulated blade ultrasonic fatigue specimens.
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