Thermal barrier coatings (TBCs) are widely used on turbine guide vanes (TGVs) in aero engines. The construction of a reasonable TBC fatigue life prediction model is of great significance to the development of aero engines. A 2D axisymmetric finite element model (FEM) is established, based on experimental data from a tube with a TBC. Then, a reasonable TBC life fatigue prediction model is established by combining the Manson–Coffin equation, linear cumulative damage theory, and growth characteristics of the oxide layer. The fitting problem is transformed into an optimization problem in the process of establishing the TBC fatigue life prediction model, and the coefficients of the model are solved by a genetic algorithm (GA). Finally, a strain analysis FEM for TGVs with a TBC is established, based on the master–slave model method, and TGVs coating fatigue life is predicted by a fatigue life prediction model. The results show that the maximum fatigue life prediction error for tubes with a TBC is 104.7%, which is 114.4% lower than that obtained in previous studies, and most of the coating fatigue life prediction values are distributed within 50% confidence bounds. The coating fatigue life of the TGV on the trailing edge is 1948 cycles, which is a reasonable result. The efforts of this study provide a framework to predict the coating fatigue life of aero engine hot components.

热障涂层 (TBC) 广泛用于航空发动机的涡轮导向叶片 (TGV)。构建合理的TBC疲劳寿命预测模型对航空发动机的发展具有重要意义。基于来自带有 TBC 的管的实验数据，建立了 2D 轴对称有限元模型 (FEM)。然后，结合Manson-Coffin方程、线性累积损伤理论和氧化层生长特性，建立了合理的TBC寿命疲劳预测模型。在建立TBC疲劳寿命预测模型的过程中，将拟合问题转化为优化问题，并通过遗传算法（GA）求解模型的系数。最后，基于主从模型方法，建立了带有TBC的TGV的应变分析有限元法，TGVs涂层疲劳寿命通过疲劳寿命预测模型进行预测。结果表明，TBC管材的最大疲劳寿命预测误差为104.7%，比以往研究得到的低114.4%，并且大部分涂层疲劳寿命预测值分布在50%的置信区间内。TGV后缘涂层疲劳寿命为1948个循环，这是一个合理的结果。这项研究的工作为预测航空发动机热部件的涂层疲劳寿命提供了一个框架。大部分涂层疲劳寿命预测值分布在 50% 的置信区间内。TGV后缘涂层疲劳寿命为1948个循环，这是一个合理的结果。这项研究的工作为预测航空发动机热部件的涂层疲劳寿命提供了一个框架。大部分涂层疲劳寿命预测值分布在 50% 的置信区间内。TGV后缘涂层疲劳寿命为1948个循环，这是一个合理的结果。这项研究的工作为预测航空发动机热部件的涂层疲劳寿命提供了一个框架。