Patent ID: 7597539

Claim:
A turbine rotor blade for use in a gas turbine engine, the blade comprising: an airfoil section having a leading edge and a trailing edge with a pressure side wall and a suction side wall extending between the two edges; a blade tip rail having a pressure side wall and a suction side wall; the pressure side tip rail and the suction side tip rail merging into the trailing edge tip rail; a first vortex pocket formed on the pressure side tip rail; and, a first row of pressure side tip cooling holes connected to a cooling air supply channel formed within the airfoil and opening onto a trailing edge cap surface on the pressure side and aligned to discharge cooling air to form a vortex flow within the first vortex pocket and to push a hot gas leakage flow up over the trailing edge tip rail; and, a second vortex pocket formed on the suction side tip rail; and, a second row of suction side tip cooling holes connected to the cooling air supply channel formed within the airfoil and opening onto a trailing edge cap surface on the suction side and aligned to discharge cooling air to form a second vortex flow within the second vortex pocket and to push a hot gas leakage flow up over a suction side tip corner.