Near-wall serpentine cooled turbine airfoil [electronic resource].

Published:: Washington, D.C. : United States. Dept. of Energy, 2013.
Oak Ridge, Tenn. : Distributed by the Office of Scientific and Technical Information, U.S. Dept. of Energy
Additional Creators:: United States. Department of Energy and United States. Department of Energy. Office of Scientific and Technical Information

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Summary:

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.

Report Numbers:

E 1.99:8,535,006
8,535,006

Subject(s):

Engineering

Note:

Published through SciTech Connect.
09/17/2013.
"8,535,006"
"12/836,060"
Lee, Ching-Pang.
Siemens Energy, Inc. (Orlando, FL)

Funding Information:

FC26-05NT42644

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