Modeling the residual stress of TBCs near the interfacial asperity on turbine component tends to encounter numerical cumbersomeness ordinarily due to huge computational scale and complex mechanical behavior. This paper proposed a numerical method named submodeling method to simulate the local stress near the asperity by a partition model (named submodel) of a coated vane, based on the submodeling technique of ABAQUS code. First a global mechanical analysis about the coated vane was carried lasting three thermal cycles without considering interface asperities. Then a submodel was established with asperity and divided into three unique zones with proper mesh density according to their functions. Finally the local mechanical analysis was separately processed by submodeling method, based on interpolation of the solution from the global analysis onto the outer zone of the submodel. The results show that the stress level of TC near the asperity is relatively low after 3 thermal cycles. The normal stress and the shear stress of BC near the asperity are concentrated in the peak and nearby the trough, respectively. These stress concentrations may lead to TGO/BC interfacial crack. The stress values and distribution feature of BC near the asperity is quite agreement with former results. These may prove that submodeling method can be applicable for local stress modeling and failure prediction.

由于巨大的计算规模和复杂的机械性能，通常在涡轮部件的界面粗糙附近对TBC的残余应力进行建模往往会遇到数值麻烦。基于ABAQUS代码的子建模技术，提出了一种基于子叶片的分区模型（称为子模型）的数值模型，称为子模型方法，用于模拟粗糙表面附近的局部应力。首先，在不考虑界面粗糙的情况下，进行了连续三个热循环有关涂层叶片的整体机械分析。然后，建立具有粗糙性的子模型，并根据其功能将其划分为三个具有适当网格密度的独特区域。最后，通过子建模方法分别处理局部力学分析，基于从全局分析到子模型外部区域的解的插值。结果表明，在3个热循环后，粗糙附近的TC应力水平相对较低。粗糙附近的BC的正应力和剪应力分别集中在波峰处和波谷附近。这些应力集中可能导致TGO / BC界面裂纹。BC粗糙附近的应力值和分布特征与以前的结果非常吻合。这些可以证明子建模方法可以适用于局部应力建模和破坏预测。粗糙附近的BC的正应力和剪应力分别集中在波峰处和波谷附近。这些应力集中可能导致TGO / BC界面裂纹。BC粗糙附近的应力值和分布特征与以前的结果非常吻合。这些可以证明子建模方法可以适用于局部应力建模和破坏预测。粗糙附近的BC的正应力和剪应力分别集中在波峰处和波谷附近。这些应力集中可能导致TGO / BC界面裂纹。BC粗糙附近的应力值和分布特征与以前的结果非常吻合。这些可以证明子建模方法可以适用于局部应力建模和破坏预测。