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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:
Issue Date:
Research Org.:
General Electric Co., Schenectady, NY (United States)
Sponsoring Org.:
USDOE
OSTI Identifier:
1337666
Patent Number(s):
9528701
Application Number:
13/833,878
Assignee:
GENERAL ELECTRIC COMPANY (Schenectady, NY
Patent Classifications (CPCs):
F - MECHANICAL ENGINEERING F23 - COMBUSTION APPARATUS F23R - GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
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. Tue . "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 = {},
journal = {},
number = ,
volume = ,
place = {United States},
year = {2016},
month = {12}
}

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


Axial flow sleeve for a turbine combustor and methods of introducing flow sleeve air
patent, May 2010


Combustor liner helical cooling apparatus
patent, November 2013