The efficient boundary element method is improved in this paper to deal with open multi - layer structures , and used to analyze thermal barrier coated components of aero - engine , which further enrich the former research 本文将薄体多层结构边界元法分析推广用于开环型多层结构分析，进一步丰富了以前的研究成果，并利用它分析航空发动机带热障涂层叶片热应力。
Many typical examples of 2 - d multi - layer thin structures with only one interface crack under temperature and mechanical loads are analyzed numerically by the bem given in this paper to demonstrate the efficiency and accuracy of this method . finally , the analysis for a thermal barrier coated blade by the method in this paper has been performed successfully 最后，利用本文提出的边界元方法对某热障涂层涡轮叶片温度场、热应力及层间裂纹应力强度因子进行数值分析，得到一些可供热障涂层叶片设计借鉴的结果和建议，为今后带热障涂层叶片设计提供了有益的数据及经验。
At the same time , bem formulae for interface crack analysis of thermal barrier coated structures are given in this paper . the method to evaluate nearly - singular integrals over crack tip elements and the formulae for calculating stress intensity factors ( sif ) using open and slip displacements on crack faces are presented too 基于边界元法、断裂力学等基本理论，本文导出了带热障涂层构件界面裂纹的断裂特性分析边界元法公式；结合先进的近奇异积分技术处理裂尖元的近奇异积分，利用位移法计算层间界面裂纹的应力强度因子。
