Patent ID: 8801377

Claim:
A turbine rotor blade for a gas turbine engine comprising: an airfoil section having a pressure side wall and a suction side wall with a leading edge region and a trailing edge region; a blade tip region with a pressure side tip rail and a suction side tip rail forming a squealer pocket; a pressure side pocket channel and a suction side pocket channel separated by a partition rib; the pressure side and suction side pocket channels extend from the leading edge region to the trailing edge region; the pressure side and suction side pocket channels have inlets that open to a flow of a hot gas stream passing over the blade tip region; a first row of film cooling holes connected to the pressure side pocket channel and opening onto the pressure side wall of the blade tip region; and, a second row of film cooling holes connected to the suction side pocket channel and opening onto the suction side wall of the blade tip region.