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INTEGRATED CIRCUIT COOLED TURBINE BLADE

United States Patent Application

*** PATENT GRANTED ***
20170058678
9,745,853
A1
View the Complete Application at the US Patent & Trademark Office
A turbine rotor blade includes at least two integrated cooling circuits that are formed within the blade that include a leading edge circuit having a first cavity and a second cavity and a trailing edge circuit that includes at least a third cavity located aft of the second cavity. The trailing edge circuit flows aft with at least two substantially 180-degree turns at the tip end and the root end of the blade providing at least a penultimate cavity and a last cavity. The last cavity is located along a trailing edge of the blade. A tip axial cooling channel connects to the first cavity of the leading edge circuit and the penultimate cavity of the trailing edge circuit. At least one crossover hole connects the penultimate cavity to the last cavity substantially near the tip end of the blade.
Lee, Ching-Pang (Cincinnati, OH), Jiang, Nan (Charlotte, NC), Um, Jae Y. (Winter Garden, FL), Holloman, Harry (Cincinnati, OH), Koester, Steven (Sharonville, OH)
14/ 840,572
August 31, 2015
STATEMENT REGARDING FEDERALLY SPONSORED RESEARCH [0001] Development of this invention was supported in part by the United States Department of Energy, Contract No. DE-FC26-05NT42644. Accordingly, the United States Government may have certain rights in this invention.