Abstract: A turbine airfoil for a gas turbine engine including an outer peripheral wall having an external surface, the outer peripheral wall enclosing an interior space and including a concave pressure sidewall and a convex suction sidewall joined together at a leading edge and at a trailing edge; wherein the outer peripheral wall has a varying wall thickness which incorporates a locally-thickened wall portion; and a film cooling hole having a shaped diffuser exit passing through the outer peripheral wall within the locally-thickened wall portion.

Abstract: A turbine airfoil for a gas turbine engine including an outer peripheral wall having an external surface, the outer peripheral wall enclosing an interior space and including a concave pressure sidewall and a convex suction sidewall joined together at a leading edge and at a trailing edge; wherein the outer peripheral wall has a varying wall thickness which incorporates a locally-thickened wall portion; and a film cooling hole having a shaped diffuser exit passing through the outer peripheral wall within the locally-thickened wall portion.

Abstract: A method for manufacturing a turbine damper by a metal injection molding process is disclosed. The damper includes a base section and a wire section, and is formed of a nickel-base or cobalt base superalloy.

Abstract: A turbine blade damper includes an outer part for damping vibration of the blade airfoil and a supporting inner part. The two parts are formed of different materials for the different performance required thereof in the blade.

Abstract: A turbine rotor blade includes a hollow airfoil joined to a platform and dovetail. A main flow channel extends longitudinally in span through the blade and is bound chordally by opposite partitions transversely bridging opposite sidewalls of the airfoil. A damper rib and transversely opposite damper pad are arranged together in a plurality of pairs spaced longitudinally apart in the airfoil and chordally positioned intermediate to the partitions to provide unobstructed forward and aft portions of the flow channel for channeling a coolant therethrough. The damper ribs and pads are configured to receive a wire damper through the channel to locally dampen vibration while minimizing obstruction of the coolant flow therethrough.

Abstract: A method for manufacturing a turbine damper by a metal injection molding process is disclosed. The damper includes a base section and a wire section, and is formed of a nickel-base or cobalt base superalloy.

Abstract: A turbine blade damper includes an outer part for damping vibration of the blade airfoil and a supporting inner part. The two parts are formed of different materials for the different performance required thereof in the blade.

Abstract: A turbine rotor blade includes a hollow airfoil joined to a platform and dovetail. A main flow channel extends longitudinally in span through the blade and is bound chordally by opposite partitions transversely bridging opposite sidewalls of the airfoil. A damper rib and transversely opposite damper pad are arranged together in a plurality of pairs spaced longitudinally apart in the airfoil and chordally positioned intermediate to the partitions to provide unobstructed forward and aft portions of the flow channel for channeling a coolant therethrough. The damper ribs and pads are configured to receive a wire damper through the channel to locally dampen vibration while minimizing obstruction of the coolant flow therethrough.