Patent ID: 8079813

Claim:
A turbine airfoil, comprising: a generally elongated, hollow airfoil formed by an outer wall extending chord wise from a forward leading edge to a rearward trailing edge, a tip section at a first span wise end, a root coupled to the airfoil at an end generally opposite the first end span wise for supporting the airfoil and for coupling the airfoil to a disc, and a cooling system formed from at least one cavity in the elongated, hollow airfoil positioned in internal aspects of the generally elongated, hollow airfoil; said outer wall having a concave pressure side and a convex suction side separated rearwardly by the trailing edge, said trailing edge having a central camber line with the pressure side on one side of the camber line and the suction side on the other; at least two submerged suction side cooling slots spaced span wise and each extending chord wise to provide an opening beginning at a front edge on the suction side and extending to a terminal location at the trailing edge; at least one trailing edge cooling channel positioned within the generally elongated, hollow airfoil and extending toward the trailing edge, but terminating in a pressure side cooling slot having a curving rearward side that curves to a pressure side outlet forward of the trailing edge, said pressure side outlet having a pressure side lip at its forward junction with the pressure side, said front edges of the suction side cooling openings being no further forward chord-wise than the pressure side lip; and at least one boundary layer bleed hole fluidly connecting the pressure side cooling slot to at least one of the suction side cooling slots, said at least one boundary layer bleed hole being no further forward chord-wise than the pressure side lip.