GAS TURBINE COMPONENT, INTERMEDIATE STRUCTURE OF GAS TURBINE COMPONENT, GAS TURBINE, METHOD OF MANUFACTURING GAS TURBINE COMPONENT, AND METHOD OF REPAIRING GAS TURBINE COMPONENT

摘要

PROBLEM TO BE SOLVED: To inhibit peeling-off of a ceramic layer in a gas turbine component exposed to high-temperature combustion gas.SOLUTION: A gas turbine component has a metal intermediate structure 110 and a ceramic layer 130. The intermediate structure 110 is formed with a gas path surface 102 facing a combustion gas flow passage GP side in the radial direction Dr, and a pair of side surface 103 opposed to each other in the circumferential direction Dc. The ceramic layer 130 is formed thereon with the gas path surface 102 of the intermediate structure 110. However, the ceramic layer 130 is not formed on a rotation upstream corner 115u between, in the pair of side surfaces 103, the rotation upstream side surface 103u on the upstream side in the rotation direction of a rotor and the gas path surface 102 .SELECTED DRAWING: Figure 3