Patent ID: 6022188
Filing Date: 2000-02-08
Classification: F01D,F05D

Abstract:
A turbine section of a combustion turbine comprising an airfoil having a leading edge and a trailing edge defining an axial chord length therebetween, said airfoil further comprising a convex suction surface and a concave pressure surface intersecting at said leading edge and said trailing edge, said suction surface comprising an accelerating flow section and a decelerating flow section downstream of said accelerating flow section, said accelerating flow section formed such that a gas flow through said turbine section over said airfoil continues to accelerate over more than one half of said axial chord length, further comprising a film cooling perforations, formed in said accelerating flow section substantially upstream of said trailing edge including at least one of said film cooling perforations located downstream of a midpoint of said axial chord length, said perforation operable to enable a cooling film to be ejected into an accelerating gas flow stream.