Abstract
Reliability of environmental barrier coatings for ceramics (EBC) is essential for improving performance of high-pressure turbine materials for aircraft engines. The aim of this study is to prescribe theoretical guidelines for structural design of EBC with better mechanical reliability. We propose a simple theoretical method to predict the condition of interface crack initiation in multi-layered EBC coatings (ceramics/Si-based bond coat/Mullite/Yb-silicate) due to thermal stress in fabrication processes. The method is validated by comparing energy release rates between finite element method analysis and the proposed method. The results reveal that the condition of Si-based bond coat/ceramics interface crack initiation can be estimated by the method introducing factors independent of the thickness of layers. On the other hand, the conditions of crack initiation at Mullite/Si-based bond coat and Yb-silicate/Mullite interfaces are dependent on the thickness of the Si-based bond coat.
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