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정규익(Kyu Ick Jung),김태우(Tae Woo Kim),백운규(Unkyu Paik),이기성(Kee Sung Lee) 대한기계학회 2006 대한기계학회 춘추학술대회 Vol.2006 No.11
A gas turbine blade is operated at high temperature to increase engine efficiency and improve blade performance. For this purpose, TBCs(Thermal barrier coatings) are used on advanced turbine blade. Due to severe operation conditions, the evaluation of creep, fatigue, corrosion and indentation stress are important. In this study, we prepared multi-layered system for TBCs, which protects inside metallic component from external damage such as collision of fine particle. The difference of CTE between the coating layer and the substrate causes residual stress in the coating layer. Therefore, we designed that the outer layer of the multi-layered system has a good resistance from contact damage and inner layer has similar CTE to lower bond-coat layer. Especially we investigated the indentation behavior using Hertzian and Vickers indentation technique.