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Air cooled turbine rotor blade for closed loop cooling

United States Patent Application

View the Complete Application at the US Patent & Trademark Office
A turbine rotor blade with a closed loop cooling circuit for an industrial gas turbine engine in which cooling air for the rotor blade is supplied and carried away to and from the rotor blade through the rotor shaft, and where the rotor blade includes a serpentine flow cooling circuit with an even number of legs or channels in which the cooling air is supplied to and discharge from the blade in the blade root. The closed loop rotor blade cooling circuit can be two four-pass serpentine flow cooling circuits or one six-pass serpentine flow cooling circuit.
Downs, James P. (Hobe Sound, FL), Rawlings, Christopher K. (Stuart, FL)
15/ 255,227
September 2, 2016
GOVERNMENT LICENSE RIGHTS [0001] This invention was made with Government support under contract number DE-FE0023975 awarded by Department of Energy. The Government has certain rights in the invention.