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Near-wall serpentine cooled turbine airfoil

United States Patent

September 17, 2013
View the Complete Patent at the US Patent & Trademark Office
U.S. Department of Energy - Visit the Office of the Assistant General Counsel for Technology Transfer & Intellectual Property Website
A serpentine coolant flow path (54A-54G) formed by inner walls (50, 52) in a cavity (49) between pressure and suction side walls (22, 24) of a turbine airfoil (20A). A coolant flow (58) enters (56) an end of the airfoil, flows into a span-wise channel (54A), then flows forward (54B) over the inner surface of the pressure side wall, then turns behind the leading edge (26), and flows back along a forward part of the suction side wall, then follows a loop (54E) forward and back around an inner wall (52), then flows along an intermediate part of the suction side wall, then flows into an aft channel (54G) between the pressure and suction side walls, then exits the trailing edge (28). This provides cooling matched to the heating topography of the airfoil, minimizes differential thermal expansion, revives the coolant, and minimizes the flow volume needed.
Lee; Ching-Pang (Cincinnati, OH)
Siemens Energy, Inc. (Orlando, FL)
12/ 836,060
July 14, 2010
STATEMENT REGARDING FEDERALLY SPONSORED DEVELOPMENT Development for this invention was supported in part by Contract Number DE-FC26-05NT42644, awarded by the United States Department of Energy. Accordingly, the United States Government may have certain rights in this invention.