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METHOD AND STRUCTURE FOR COOLING AIRFOIL SURFACES USING ASYMMETRIC CHEVRON FILM HOLES

United States Patent Application

20110097191
A1
View the Complete Application at the US Patent & Trademark Office
A film-cooled turbine structure is configured with one or more asymmetric chevron film cooling holes for improving film cooling for a variety of airfoil surfaces or airfoil regions, particularly in regions and applications where the surface fluid streamline curvature is significant.
Bunker, Ronald Scott (Niskayuna, NY)
GENERAL ELECTRIC COMPANY (SCHENECTADY NY)
12/ 607,586
October 28, 2009
STATEMENT REGARDING FEDERALLY SPONSORED RESEARCH & DEVELOPMENT [0001] This invention was made with U.S. Government Department of Energy support under contract number DE-FC26-05NT42643. The Government has certain rights in the invention.