| 摘要 |
An airfoil (32) for a turbine nozzle assembly of a gas turbine engine includes an outer side wall, an inner side wall, a leading edge extending from the outer side wall to said inner side wall, a trailing edge (44) extending from the outer side wall to the inner side wall a concave surface (46) extending from the leading edge to the trailing edge (44) on a pressure side of the airfoil (32), a convex surface extending from the leading edge to the trailing edge (44) on a suction side of said airfoil (32), an outer cooling slot, an inner cooling slot (52), and at least one middle cooling slot (54) formed in the concave side (46) of the airfoil (32) adjacent the trailing edge (44). Each of the cooling slots (52,54) further includes a recessed wall (56), an inner slot side wall, an outer slot side wall (60), an inner corner fillet (62) located between the inner slot side wall and the recessed wall (56), and an outer corner fillet (64) located between the outer slot side wall (60) and the recessed wall (56), wherein one of the inner and outer corner fillets (62,64) for at least one of the inner (52) and outer cooling slots forms a variable contour (66) from an opening (68) in the concave surface (46) to an exit plane (70) of the trailing edge cooling slots (52,54). <IMAGE> <IMAGE> |
