Patent ID: 7997865

Claim:
A turbine blade for use in a gas turbine engine, the blade comprising: a pressure side wall with a pressure side tip rail; a suction side wall with a suction side tip rail; a squealer pocket formed by a tip floor and the pressure side tip rail and the suction side tip rail; at least one cooling supply cavity formed within the blade; a pressure side vortex cooling channel extending along the pressure side wall between the pressure side tip rail and the cooling supply cavity; a suction side vortex cooling channel extending along the suction side wall between the suction side tip rail and the cooling supply cavity; a pressure side cooling hole connecting the cooling supply cavity to the pressure side vortex cooling channel and opening onto the pressure side wall near to the pressure side tip rail; a suction side cooling hole connecting the cooling supply cavity to the suction side vortex cooling channel and opening onto the squealer pocket side wall of the suction side tip rail; and, the inlets and the outlets of the pressure side cooling hole and suction side cooling hole are offset to produce a vortex flow within the vortex cooling channels.