Experimental investigation on fatigue of blade specimen subjected to resonance and effect of a damping hard coating treatment

Abstract

Failures due to high-cycle fatigue have led to a high cost in aerospace engineering over the past few decades. In this paper, the experimental results of the fatigue behavior of compressor blade specimen subjected to resonance and the effects of a damping hard coating on relieving the fatigue progress are presented. The crack initiation and propagation processes were observed under resonance of the first bending mode by using the resonant frequencies as the indicator. Significant nonlinear features were observed in the spectrum of the blade with a fatigue crack. The finite element model considering the breathing crack was established with nonlinear contact based on the crack localization and size, which was obtained by ultrasonic phased array technology. The simulation results of the vibration behavior of the cracked blade were obtained and consistent with the experimental results. A NiCrAlY coating was deposited on the blade, and increases in the fatigue life were observed under the same condition. The results of this paper can help to better understand the fatigue of a compressor blade subjected to resonance and provide a preference for the application of a damping hard coating on compressor blades.

Keywords

blade vibration / high-cycle fatigue / fatigue test / damping hard coating

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