With　the　development　of　high　temperature　protective　material,　thermal　barrier　coatings　are　used　in　the　field　of　aircraft　and　industrial　steam　turbine.　They　have　characteristics　of　complex　structure　and　long-term　work　in　high　temperature　environment,　etc.　Because　of　multilayer　material　physical　properties　mismatch,　oxidation,　interface　roughness,　creep　stress　and　so　on,　the　coatings　system　is　easy　to　produce　cracks,　expand　and　link　near　the　interface　of　coating　during　thermal　cycling.　By　establishing　I,　II,　III,　IV　four　numerical　models　of　crack　fracture　mechanisms,　assuming　that　the　thickness　of　oxidation　layer　is　constant,　considering　the　influence　of　interface　roughness　and　material　properties　mismatch　in　the　process　of　thermal　cycling,　it　gets　the　results　of　residual　stress　field　near　the　crack　and　the　influence　of　the　interface.　Compared　to　the　presence　of　defects,　four　kinds　of　crack　failure　mechanisms　are　analyzed.　Energy　release　rate　is　calculated　by　the　virtual　crack　closure　method,　which　can　conclude　the　cracks　of　I,　IV　tip　stress　concentration　phenomena　are　obvious,　crack　II　is　easy　to　expand,　due　to　the　temperature　load,　crack　III　does　not　appear　stress　concentration　phenomenon　at　the　tip.　©　(2014)　Trans　Tech　Publications,　Switzerland.