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Title: System for tuning a combustor of a gas turbine

Abstract

A system for tuning a combustor of a gas turbine includes a flow sleeve having an annular main body. The main body includes an upstream end, a downstream end, an inner surface and an outer surface. A cooling channel extends along the inner surface of the main body. The cooling channel extends at least partially between the downstream end and the upstream end of the main body.

Inventors:
Publication Date:
Research Org.:
General Electric Co., Schenectady, NY (United States)
Sponsoring Org.:
USDOE
OSTI Identifier:
1337666
Patent Number(s):
9,528,701
Application Number:
13/833,878
Assignee:
GENERAL ELECTRIC COMPANY (Schenectady, NY
DOE Contract Number:  
FC26-05NT42643
Resource Type:
Patent
Resource Relation:
Patent File Date: 2013 Mar 15
Country of Publication:
United States
Language:
English
Subject:
33 ADVANCED PROPULSION SYSTEMS; 42 ENGINEERING

Citation Formats

Hughes, Michael John. System for tuning a combustor of a gas turbine. United States: N. p., 2016. Web.
Hughes, Michael John. System for tuning a combustor of a gas turbine. United States.
Hughes, Michael John. 2016. "System for tuning a combustor of a gas turbine". United States. https://www.osti.gov/servlets/purl/1337666.
@article{osti_1337666,
title = {System for tuning a combustor of a gas turbine},
author = {Hughes, Michael John},
abstractNote = {A system for tuning a combustor of a gas turbine includes a flow sleeve having an annular main body. The main body includes an upstream end, a downstream end, an inner surface and an outer surface. A cooling channel extends along the inner surface of the main body. The cooling channel extends at least partially between the downstream end and the upstream end of the main body.},
doi = {},
url = {https://www.osti.gov/biblio/1337666}, journal = {},
number = ,
volume = ,
place = {United States},
year = {Tue Dec 27 00:00:00 EST 2016},
month = {Tue Dec 27 00:00:00 EST 2016}
}

Works referenced in this record:

Combustor liner cooling thimbles and related method
patent, November 2002


Method and apparatus for cooling combustor liner and transition piece of a gas turbine
patent, February 2009


Combustor liner helical cooling apparatus
patent, November 2013