Thermal barrier coatings are a promising concept to improve the lifetime of the copper liner of a rocket engine. Due to the high heat fluxes and the large thermal conductivity of copper, coatings have to be designed especially for this application. In this paper, we perform fully thermo-mechanically coupled finite element analyses of a small section of a combustion chamber with a coating system comprising a NiCuCrAl bond coat and a NiCrAlY top coat. Heat fluxes are calculated to determine reasonable coating thickness values. Elastic and plastic deformation in the materials is considered to study the stress evolution. A crack model serves to estimate the possibility of vertical cracks propagating through the coating system. Several design guidelines are developed from these results that will aid future development of thermal barrier coatings.

中文翻译：

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火箭发动机应用的热障涂层中的应力演变

隔热涂层是提高火箭发动机铜衬套使用寿命的有前途的概念。由于铜的高热通量和高导热率，必须为此应用专门设计涂层。在本文中，我们对一个燃烧室的一小部分进行了完全热机械耦合的有限元分析，其涂层系统包括NiCuCrAl粘结涂层和NiCrAlY面涂层。计算热通量以确定合理的涂层厚度值。考虑材料中的弹性和塑性变形来研究应力演化。裂纹模型用于估计垂直裂纹传播通过涂层系统的可能性。从这些结果中得出了一些设计准则，这些准则将有助于热障涂层的未来发展。