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.

在过去的几十年中，由于高周疲劳而导致的故障导致了航空航天工程的高昂成本。本文给出了压气机叶片试样在共振条件下的疲劳行为的实验结果，以及阻尼硬质涂层对缓解疲劳过程的影响。以共振频率为指标，在第一弯曲模式的共振下观察到裂纹的萌生和扩展过程。在具有疲劳裂纹的叶片光谱中观察到了明显的非线性特征。基于裂纹的位置和大小，通过非线性接触建立了考虑呼吸裂纹的有限元模型，该模型是通过超声相控阵技术获得的。获得了裂纹叶片振动行为的仿真结果，与实验结果吻合。NiCrAlY涂层沉积在叶片上，在相同条件下观察到疲劳寿命的增加。本文的结果可以帮助更好地理解遭受共振的压气机叶片的疲劳度，并优先考虑在压气机叶片上使用阻尼硬质涂层。