Patent ID: 9297267
Filing Date: 2016-03-29
CPC Classification: F01D,F05D

Claim Text:
1. A stationary vane for a turbine of a gas turbine, the stationary vane comprising: an inner flange radially spaced from an outer flange; an airfoil that extends radially between the inner flange and the outer flange, wherein the airfoil is at least partially formed from a substrate and a coating applied to an outer surface of the substrate, wherein the coating has an interior surface facing the outer surface of the substrate and an exterior surface opposed to the interior surface, wherein the airfoil defines a first cavity and a second cavity within the substrate; a supply plenum that extends through the outer flange, wherein the supply plenum is in fluid communication with the first cavity; a return plenum that extends through the outer flange, wherein the return plenum is in fluid communication with the second cavity; a first fluid channel defined between the outer surface of the airfoil substrate and the exterior surface of the coating, wherein the supply plenum, the first cavity, the first fluid channel, the second cavity and the return plenum define a flow path for routing a cooling media into and hack out of the airfoil through the outer flange.