GAS TURBINE BLADE

摘要

PROBLEM TO BE SOLVED: To provide a turbine blade improved in reliability. SOLUTION: This gas turbine blade has a base material formed of a heat resisting alloy, a bond layer consisting of an alloy for coating the surface of this base material and having the high-temperature corrosion resistance higher than that of the base material and a ceramic layer for coating the surface of this bond layer in a segment to be exposed to combustion gases. This ceramic layer is a porous structure which consists essentially of ZrO2, contains >=5 to <=10 wt.% Sc2O3 and has porosity of >=2 to <=20%.