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

1990-07-13

1994-01-25

Look, Edward K.

Rotary kinetic fluid motors or pumps

With passage in blade, vane, shaft or rotary distributor...

F01D 904

Patent

active

052810844

ABSTRACT:
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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S. Stephen Papell et al.; "Influence of Coolant Tube Curvature on Film Cooling Effectiveness as Detected by Infrared Imagery"; NASA Technical Paper No. 1546; 1979; pp. 3-16.

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