コーティング設計と高耐久性遮熱コーティングの開発

抄録

Thermal barrier coatings (TBC_s) had been already applied to hot section parts of gas turbines, such as a bucket and a combustor. It is thought that the TBC_s are indispensable for the gas turbines in company with a cooling technology. Nowadays, it is desired the higher durability to TBC_s with increasing the combustion temperature. For the sake of this situation, it is necessary to introduce a design concept into the coating technology.
In this paper, the coating design concept makes clear for gas turbines. And, the coating design system, that consists of a thermal stress analysis and a reaction diffusion analysis, and its application is showed. For developing the high-durable TBC_s, the coating design was conducted for a gas turbine nozzle. This study led to the conclusion that the improved TBCs could be obtained by introducing the oxidation resistant layer by aluminizing. The developed TBC system was applied to the gas turbine nozzle.