中文摘要：

到在不同服务的温度分发和热压力的地上演的学习，有热障碍涂层的汽轮机片的一个二维的模型被开发，在哪个 conjugate 热转移分析和 decoupled 热压力的计算方法被采用。基于模拟结果，温度的不一致的分布出现在片表面的不同位置，这被发现，它直接影响了应力领域。有 1030  °C 的价值的最大的温度发生在前缘。在稳定的阶段期间，热地成年的氧化物(TGO ) 的最大的压力出现在吸方面的中间，到达 3.75  GPa。在冷却的结束阶段，有 −3.5 GPa 的价值的 TGO 的最大的压缩压力发生在前缘。因此，在稳定的阶段期间，危险区域可以在吸方面定位，这能被预言，当前缘可以是对冷却上的失败敏感的更多时。

英文摘要：

To study the temperature distribution and thermal-stress field in different service stages, a two-dimensional model of a turbine blade with thermal barrier coatings is developed, in which the conjugate heat transfer analysis and the decoupled thermal-stress calculation method are adopted. Based on the simulation results, it is found that a non-uniform distribution of temperature appears in different positions of the blade surface, which has directly impacted on stress field. The maximum temperature with a value of 1030 ℃ occurs at the leading edge. During the steady stage, the maximum stress of thermally grown oxide （TGO） appears in the middle of the suction side, reaching 3.75 GPa. At the end stage of cooling, the maximum compressive stress of TGO with a value of-3.5 GPa occurs at the leading edge. Thus, it can be predicted that during the steady stage the dangerous regions may locate at the suction side, while the leadine edge mav be more Drone to failure on cooling.