Patent ID: 6612811
Filing Date: 2003-09-02
Classification: F01D,F05D,Y10T

Abstract:
An airfoil for a turbine nozzle assembly of a gas turbine engine, comprising:(a) an outer side wall; (b) an inner side wall; (c) a leading edge extending from said outer side wall to said inner side wall; (d) a trailing edge extending from said outer side wall to said inner side wall; (e) a concave surface extending from said leading edge to said trailing edge on a pressure side of said airfoil; (f) a convex surface extending from said leading edge to said trailing edge on a suction side of said airfoil; (g) an outer cooling slot, an inner cooling slot, and at least one middle cooling slot formed in said concave side of said airfoil adjacent said trailing edge, each of said cooling slots further including: (1) a recessed wall; (2) an inner slot side wall; (3) an outer slot side wall; (4) an inner corner fillet located between said inner slot side wall and said recessed wall; and, (5) an outer corner fillet located between said outer slot side wall and said recessed wall; wherein one of said inner and outer corner fillets for at least one of said inner and outer cooling slots forms a variable contour from an opening in said concave surface to an exit plane of said trailing edge cooling slots.