| 摘要 |
A gas turbine component is provided. The gas turbine component includes an airfoil having a leading edge 222,230, a trailing edge 224,232, a suction side 226,234 extending from the leading edge to the trailing edge, and a pressure side 228,236 extending from the leading edge to the trailing edge opposite the suction side. The gas turbine component also includes a thermal barrier coating 240 applied to the airfoil pressure side such that an uncoated margin 278 is defined on the pressure side at the trailing edge. |
