Patent ID: 9617867
Date: 2017-04-11
CPC Classifications: F01D,F05D

Claim:
1. A gas turbine comprising: disk wheels of which a rotor is formed; a rotor blade including a shank and a rotor blade profile portion, the shank being mounted on the outer circumference of each of the disk wheels; a first-stage stator blade including a stator blade profile portion and an inner circumferential end wall provided at the stator blade profile portion on the side of the inner circumference of the stator blade profile portion; and a seal fin provided on the shank of the rotor blade in such a manner that the seal fin faces an inside-diameter surface lying on the inner circumferential end wall of the stator blade; wherein an abradable coating is applied to a portion of the inside-diameter surface of the first-stage stator blade lying on the inner circumferential end wall of the first-stage stator blade and facing the seal fin on the shank; the abradable coating is a ceramic abradable coating applied to the portion of the inside-diameter surface of the first-stage stator blade, to which high-temperature and high-pressure combustion gas is led from a combustor; and the ceramic abradable coating has an underlying layer provided on an inside-diameter side portion of the inner circumferential end wall of the first-stage stator blade, a cellular ceramic heat barrier and a ceramic layer with cellular structure being provided on the heat barrier.