Abstract Fan blade is one of the key parts used in aircraft engine and its failure is mainly caused by fatigue fracture. This paper aims to predict fatigue life of fan blade during its service operation. First, the effective load and stress of fan blade are obtained by using finite element analysis and simulation. Second, the fatigue notch factor of fan blade is determined by using the nominal stress method. Then, the material properties of fan blade are used to correct and obtain the S−N $S - N$ curve of fan blade. Finally, according to the actual load spectrum of three working loading cycles in 900h, the Miner’s damage accumulation rule is employed to predict the fatigue life of fan blade.

中文翻译：

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用名义应力法和累积疲劳损伤理论预测风扇叶片的疲劳寿命

摘要 风扇叶片是飞机发动机的关键部件之一，其失效主要是由疲劳断裂引起的。本文旨在预测风机叶片在服役期间的疲劳寿命。首先，通过有限元分析和仿真得到风扇叶片的有效载荷和应力。其次，采用名义应力法确定风扇叶片的疲劳缺口系数。然后，利用扇叶的材料特性进行修正，得到扇叶的 S−N$S-N$ 曲线。最后，根据900h内三个工作载荷循环的实际载荷谱，采用Miner损伤累积规律预测风扇叶片的疲劳寿命。