Cooling circuit for a gas turbine bucket and tip shroud

Patent · Tue Jul 13 00:00:00 EDT 2004

OSTI ID:1174937

Willett, Fred Thomas

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.

• Research Organization: General Electric Co., Schenectady, NY (United States)
• Sponsoring Organization: USDOE
• DOE Contract Number: FC21-95MC31176
• Assignee: General Electric Company (Schenectady, NY)
• Patent Number(s): 6,761,534
• Application Number: 09/286,151
• OSTI ID: 1174937
• Country of Publication: United States
• Language: English

Related Subjects

33 ADVANCED PROPULSION SYSTEMS
42 ENGINEERING