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Integrated axial and tangential serpentine cooling circuit in a turbine airfoil

United States Patent

May 5, 2015
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 continuous serpentine cooling circuit forming a progression of radial passages (44, 45, 46, 47A, 48A) between pressure and suction side walls (52, 54) in a MID region of a turbine airfoil (24). The circuit progresses first axially, then tangentially, ending in a last radial passage (48A) adjacent to the suction side (54) and not adjacent to the pressure side (52). The passages of the axial progression (44, 45, 46) may be adjacent to both the pressure and suction side walls of the airfoil. The next to last radial passage (47A) may be adjacent to the pressure side wall and not adjacent to the suction side wall. The last two radial passages (47A, 48A) may be longer along the pressure and suction side walls respectively than they are in a width direction, providing increased direct cooling surface area on the interiors of these hot walls.
Lee; Ching-Pang (Cincinnati, OH), Jiang; Nan (Jupiter, FL), Marra; John J. (Winter Springs, FL), Rudolph; Ronald J. (Jensen Beach, FL), Dalton; John P. (Wellington, FL)
Siemens Energy, Inc. (Orlando, FL), Mikro Systems, Inc. (Charlottesville, VA)
13/ 027,333
February 15, 2011
STATEMENT REGARDING FEDERALLY SPONSORED DEVELOPMENT Development for this invention was supported in part by Contract No. DE-FC26-05NT42644, awarded by the United States Department of Energy. Accordingly, the United States Government may have certain rights in this invention.