Patent attributes
A cooling system for a turbine airfoil of a turbine engine having at least one diffusion film cooling hole positioned in an outer wall defining the turbine airfoil is disclosed. The diffusion film cooling hole includes a first sidewall having a first radius of curvature about an axis generally orthogonal to a centerline of cooling fluid flow through the diffusion film cooling hole and a second sidewall having a second radius of curvature about an axis generally orthogonal to the centerline of cooling fluid flow through the at least one diffusion film cooling hole. The radii of curvature of the first and second sidewalls are different such that the diffusion film cooling hole includes an ever increasing cross-sectional area moving from an inlet to an outlet, thereby diffusing and reducing the velocity of cooling fluids flowing there through.
