Cooling circuit for a gas turbine bucket and tip shroud
Abstract
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.
- Inventors:
- Issue Date:
- Research Org.:
- General Electric Co., Schenectady, NY (United States)
- Sponsoring Org.:
- USDOE
- OSTI Identifier:
- 1174937
- Patent Number(s):
- 6761534
- Application Number:
- 09/286,151
- Assignee:
- General Electric Company (Schenectady, NY)
- Patent Classifications (CPCs):
-
F - MECHANICAL ENGINEERING F01 - MACHINES OR ENGINES IN GENERAL F01D - NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- DOE Contract Number:
- FC21-95MC31176
- Resource Type:
- Patent
- Country of Publication:
- United States
- Language:
- English
- Subject:
- 33 ADVANCED PROPULSION SYSTEMS; 42 ENGINEERING
Citation Formats
Willett, Fred Thomas. Cooling circuit for a gas turbine bucket and tip shroud. United States: N. p., 2004.
Web.
Willett, Fred Thomas. Cooling circuit for a gas turbine bucket and tip shroud. United States.
Willett, Fred Thomas. Tue .
"Cooling circuit for a gas turbine bucket and tip shroud". United States. https://www.osti.gov/servlets/purl/1174937.
@article{osti_1174937,
title = {Cooling circuit for a gas turbine bucket and tip shroud},
author = {Willett, Fred Thomas},
abstractNote = {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.},
doi = {},
journal = {},
number = ,
volume = ,
place = {United States},
year = {Tue Jul 13 00:00:00 EDT 2004},
month = {Tue Jul 13 00:00:00 EDT 2004}
}
Works referenced in this record:
Rayleigh/Raman/LIF measurements in a turbulent lean premixed combustor
conference, February 2013
- Nandula, S.; Pitz, R.; Barlow, R.
- 34th Aerospace Sciences Meeting and Exhibit
Advances in Steam Path Technology
journal, April 1996
- Cofer, J. I.
- Journal of Engineering for Gas Turbines and Power, Vol. 118, Issue 2