Patent ID: 8231349

Claim:
A gas turbine engine component comprising: a root and a tip separated along a longitudinal axis; an airfoil portion having a leading edge, a trailing edge, an external suction side wall, and an external pressure side wall, the external walls extending between said leading edge and said trailing edge, said external walls enclosing a central cavity for the passage of cooling air between the root and the tip; at least one longitudinally extending first web connecting said suction side wall with said pressure side wall, said at least one first web partitioning said cavity into a leading edge region and a trailing edge region and defining a leading edge chamber in the leading edge region; a second longitudinally extending web connecting said at least one first web with the suction side wall and defining a first entry chamber on the suction side of the second web and a second entry chamber for cooling air in the trailing edge region; wherein said at least one first web comprises at least one cross-over hole between the first entry chamber and the leading edge chamber, and wherein the second web is devoid of openings; wherein the at least one cross-over hole in the at least one first web between the first entry chamber and the leading edge chamber comprises a longitudinally extending row of holes, and wherein the cross-sectional area of the holes of said row is larger in a region of the tip than in a region of the root.