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Cooling circuit for a gas turbine bucket and tip shroud

United States Patent

6,761,534
July 13, 2004
View the Complete Patent at the US Patent & Trademark Office
An open cooling circuit for a gas turbine airfoil and associated tip shroud includes a first group of cooling holes internal to the airfoil and extending in a radially outward direction generally along a leading edge of the airfoil; a second group of cooling holes internal to the airfoil and extending in a radially outward direction generally along a trailing edge of the airfoil. A common plenum is formed in the tip shroud in direct communication with the first and second group of cooling holes, but a second plenum may be provided for the second group of radial holes. A plurality of exhaust holes extends from the plenum(s), through the tip shroud and opening along a peripheral edge of the tip shroud.
Willett; Fred Thomas (Burnt Hills, NY)
General Electric Company (Schenectady, NY)
09/ 286,151
April 5, 1999
This invention was made with Government support under Contract No. DEFC21-95MC31176 awarded by the Department of Energy. The Government has certain rights in this invention.