Curved film cooling holes for gas turbine engine vanes

Details Curved film cooling holes for gas turbine engine vanes Curved film cooling holes for gas turbine engine vanes

F - Mech Eng,Light,Heat,Weapons

01

D

F01D 5/18 (2006.01)

Patent

CA 2042266

13DV-9902 ABSTRACT OF THE DISCLOSURE A method and apparatus for film cooling of an aerodynamically shaped airfoil uses a plurality of curved slots extending through the airfoil in an area upstream of the high curvature region of the airfoil, i.e., in an area of low Mach number of the gas stream passing over the airfoil surface. The curved slots are configured to inject cooling air at an angle of about 16.5 degrees. The cooling air is injected at a blowing ratio in excess of 1.0 and yet is effective to form a film on the vane surface.

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