Patent ID: 7503749
Filing Date: 2009-03-17
Classification: F01D,F05D,Y02T

Abstract:
1. An airfoil for a gas turbine engine, said airfoil having opposed pressure and suction sidewalls extending between a leading edge and a trailing edge, and comprising: an array of radially-spaced apart longitudinally-extending lands, said lands defining a plurality of trailing edge slots therebetween, each of said trailing edge slots having an inlet in fluid communication with an interior of said airfoil and an exit in fluid communication with said trailing edge; wherein at least one of said lands is tapered linearly such that a width of said land measured in a radial direction decreases from said suction sidewall to said pressure sidewall; and wherein said land comprises a base adiacent said suction sidewall, a ton adiacent said pressure sidewall and spaced-apart longitudinally extending side faces extending between said suction sidewall and said pressure sidewall with a concave fillet extending between each of said side faces and said suction sidewall, said fillet including a radius that varies from said exit to said trailing edge.