Patent ID: 7520723
Filing Date: 2009-04-21
Classification: F01D,F05D

Abstract:
1. A turbine airfoil, comprising: a generally elongated, hollow airfoil having a leading edge, a trailing edge, a tip section at a first end, a root coupled to the airfoil at an end generally opposite the first end 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; an outer wail forming the generally elongated airfoil, wherein a portion of the outer wall proximate to a suction side of the generally elongated airfoil includes a plurality of vortex cooling chambers extending in a generally spanwise direction; wherein at least one row of the vortex cooling chambers is positioned in close proximity to the leading edge of the generally elongated, hollow airfoil; at least one vortex cooling chamber bleed slot positioned between each row of vortex cooling chambers and in communication with the adjacent vortex cooling chambers; at least one trailing edge bleed slot extending from one of the vortex cooling chambers through the trailing edge for exhausting cooling fluids from the generally elongated airfoil; wherein the vortex cooling chambers, the at least one vortex cooling chamber bleed slot, and the at least one trailing edge bleed slot form a continuous cooling circuit in the outer wall of the generally elongated, hollow airfoil from close proximity of the leading edge, along the suction side and through the trailing edge; and a leading edge cooling channel positioned proximate to the leading edge and extending generally spanwise and at least one leading edge bleed slot positioned in the outer wall and extending between the leading edge cooling channel and at least one of the plurality of vortex cooling chambers.