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发明公开
EP3162917A1 METHODS OF REPAIRING A THERMAL BARRIER COATING OF A GAS TURBINE COMPONENT AND THE RESULTING COMPONENTS 审中-公开
方法修复用燃气涡轮机部件和热层RESULTING成分的

METHODS OF REPAIRING A THERMAL BARRIER COATING OF A GAS TURBINE COMPONENT AND THE RESULTING COMPONENTS
摘要：
Turbine engine components (300) are provided that have a repaired thermal barrier coating (520), along with their methods of formation and repair. The turbine engine component (300) includes a thermal barrier coating (504) on a first portion (512) of a surface (303) of a substrate (302); a repaired thermal barrier coating (308) on a second portion of the surface (303) of the substrate (302); and a ceramic coat (308) on the outer bond coat (306). The thermal barrier coating (504) includes an inner bonding layer (502) and a first ceramic layer (504), with the inner bonding layer (502) is positioned between the substrate (302) and the first ceramic layer (504). The repaired thermal barrier coating (308) generally includes an inner bond coat (304) on the surface (303) of the substrate (302) and an outer bond coat (306) on the inner bond coat (304). The inner bond coat (304) is formed from a cobalt-containing material, while the outer bond coat (306) is substantially free from cobalt.
摘要（中）：

提供涡轮发动机部件（300）thathave修复的热障涂层（520），以及它们的形成和修复的方法。 该涡轮发动机部件（300）包括在衬底（302）的表面（303）的第一部分（512）的热障涂层（504）; 在基板（302）的表面（303）的第二部分的修理热障涂层（308）; 并且在外粘合涂层（306）的陶瓷涂层（308）。 热障涂层（504）包括在内部粘合层（502）和第一陶瓷层（504）与所述内部粘合层（502）在基板（302）和第一陶瓷层（504）之间定位。 修复的热障涂层（308）基因的反弹包括内粘合涂层（304）在基板（302）的表面（303）上和外粘合涂层（306）上的内粘结涂层（304）。 内粘合涂层（304）由含钴材料形成，而外层粘合涂层（306）是从钴基本上不含。

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