Patent ID: 7985050

Claim:
A turbine airfoil for use in a gas turbine engine comprising: A leading edge and a trailing edge; A pressure side wall and a suction side wall both extending between the leading edge and the trailing edge; An internal airfoil cooling circuit to provide cooling for the airfoil; A row of pressure side bleed channels connected to the internal airfoil cooling circuit to provide cooling for the trailing edge region of the airfoil; An exit slot connected to each of the bleed channels and opening onto the pressure side wall of the trailing edge region of the airfoil; A vortex chamber extending along the trailing edge tip of the airfoil; A row of inlet holes connecting the vortex chamber to the pressure side wall of the airfoil at a location downstream from the exit slots; and, A row of exit holes connecting the vortex chamber to the trailing edge tip to discharge cooling air from the vortex chamber.