High efficiency fan cooling holes for turbine airfoil

Details High efficiency fan cooling holes for turbine airfoil High efficiency fan cooling holes for turbine airfoil

F - Mech Eng,Light,Heat,Weapons

01

D

F01D 5/18 (2006.01) F01D 5/14 (2006.01)

Patent

CA 2534061

A turbine airfoil (32) includes a leading edge (36) and an axially spaced-part trailing edge (38), the leading edge (36) having an axially-extending external surface curvature. A cooling circuit (50) in the airfoil includes cooling holes (60) formed in the leading edge (36) along the span axis of the airfoil. The cooling holes (60) have a diffuser section communicating with the leading edge (36) surface. The diffuser section has four opposed walls defining a generally quadralinear exit opening on the surface of the leading edge (36). One of the diffuser walls has a convex curvature that approximates the external surface curvature of the leading edge (36) whereby fluid flow from the cooling hole exits is evenly dispersed and spread along land portions of the leading edge (36) adjacent the cooling holes (60).

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