Patent ID: 7220103

Claim:
A gas turbine engine component comprising: a fir tree for mounting the component to a rotatable disk; a platform connected to said fir tree and extending in a first plane between a leading edge and a trailing edge; an airfoil interconnected to said platform by a fillet extending at an acute angle from said platform first plane to a leading edge of the airfoil extending along a second plane substantially orthogonal to said first plane, said fillet being so formed so as to curve forwardly as it extends radially inwardly and having an inner wall surface; an impingement rib disposed adjacent to said fillet inner wall surface to jointly form a fillet cavity therebetween, said impingement rib being so formed as to curve forwardly as it extends radially inwardly in close proximity to said fillet and having a plurality of impingement holes formed therein for conducting the flow of cooling air to impinge on said fillet inner wall surface; and a generally radially extending supply air passage formed in said fir tree for conducting the flow of cooling air to one side of said impingement rib, so as to pass through said plurality of impingement holes and impinge on said fillet inner wall surface.