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Title: 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 = {2004},
month = {7}
}

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Works referenced in this record:

Rayleigh/Raman/LIF measurements in a turbulent lean premixed combustor
conference, February 2013


Advances in Steam Path Technology
journal, April 1996