Patent ID: 7217094

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 to form a fillet cavity within said airfoil; and cooling means within said component to provide cooling air to said fillet cavity wherein the extent of said fillet is defined by an offset distance defined by the distance between a first point in which the fillet intersects with said first plane and a second point in which the fillet intersects with said second plane as measured along a plane parallel the said first plane, and further wherein the offset distance is in the range of 0.080″ to 0.375″.