Patent ID: 9273561
Filing Date: 2016-03-01
CPC Classification: F01D,F05D

Claim Text:
1. A rotor blade for a turbine of a combustion turbine engine, the rotor blade comprising an airfoil that includes a pressure sidewall and a suction sidewall defining an outer periphery and a tip portion defining an outer radial end, the tip portion including a rail that defines a tip cavity, wherein the airfoil includes an interior cooling passage configured to circulate coolant through the airfoil during operation, the rotor blade comprising: a slotted portion of the rail; and at least one film cooling outlet disposed within at least one of the pressure sidewall and the suction sidewall of the airfoil, the film cooling outlet comprising a position that is adjacent to the tip portion and in proximity to the slotted portion of the rail; wherein: wherein: wherein: wherein: wherein the slotted portion of the rail comprises a plurality of regularly spaced slots; and wherein the plurality of slots are disposed in parallel on the pressure side rail.