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Title: Cooling circuit for and method of cooling a gas turbine bucket

Abstract

A closed internal cooling circuit for a gas turbine bucket includes axial supply and return passages in the dovetail of the bucket. A first radial outward supply passage provides cooling medium to and along a passageway adjacent the leading edge and then through serpentine arranged passageways within the airfoil to a chamber adjacent the airfoil tip. A second radial passage crosses over the radial return passage for supplying cooling medium to and along a pair of passageways along the trailing edge of the airfoil section. The last passageway of the serpentine passageways and the pair of passageways communicate one with the other in the chamber for returning spent cooling medium radially inwardly along divided return passageways to the return passage. In this manner, both the leading and trailing edges are cooled using the highest pressure, lowest temperature cooling medium.

Inventors:
 [1]
  1. Simpsonville, SC
Issue Date:
Research Org.:
General Electric Co., Schenectady, NY (United States)
OSTI Identifier:
874606
Patent Number(s):
6422817
Assignee:
General Electric Company (Schenectady, NY)
Patent Classifications (CPCs):
F - MECHANICAL ENGINEERING F05 - INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04 F05D - INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
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:
cooling; circuit; method; gas; turbine; bucket; closed; internal; axial; supply; return; passages; dovetail; radial; outward; passage; provides; medium; passageway; adjacent; leading; edge; serpentine; arranged; passageways; airfoil; chamber; tip; crosses; supplying; pair; trailing; section; communicate; returning; spent; radially; inwardly; divided; manner; edges; cooled; pressure; lowest; temperature; gas turbine; cooling circuit; /416/415/

Citation Formats

Jacala, Ariel C. P.. Cooling circuit for and method of cooling a gas turbine bucket. United States: N. p., 2002. Web.
Jacala, Ariel C. P.. Cooling circuit for and method of cooling a gas turbine bucket. United States.
Jacala, Ariel C. P.. Tue . "Cooling circuit for and method of cooling a gas turbine bucket". United States. https://www.osti.gov/servlets/purl/874606.
@article{osti_874606,
title = {Cooling circuit for and method of cooling a gas turbine bucket},
author = {Jacala, Ariel C. P.},
abstractNote = {A closed internal cooling circuit for a gas turbine bucket includes axial supply and return passages in the dovetail of the bucket. A first radial outward supply passage provides cooling medium to and along a passageway adjacent the leading edge and then through serpentine arranged passageways within the airfoil to a chamber adjacent the airfoil tip. A second radial passage crosses over the radial return passage for supplying cooling medium to and along a pair of passageways along the trailing edge of the airfoil section. The last passageway of the serpentine passageways and the pair of passageways communicate one with the other in the chamber for returning spent cooling medium radially inwardly along divided return passageways to the return passage. In this manner, both the leading and trailing edges are cooled using the highest pressure, lowest temperature cooling medium.},
doi = {},
journal = {},
number = ,
volume = ,
place = {United States},
year = {2002},
month = {1}
}

Patent:

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Works referenced in this record:

Development Requirements for an Advanced Gas Turbine System
journal, October 1995


Advances in Steam Path Technology
journal, April 1996