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Title: Combustor assembly in a gas turbine engine

Abstract

A combustor assembly in a gas turbine engine. The combustor assembly includes a combustor device coupled to a main engine casing, a first fuel injection system, a transition duct, and an intermediate duct. The combustor device includes a flow sleeve for receiving pressurized air and a liner disposed radially inwardly from the flow sleeve. The first fuel injection system provides fuel that is ignited with the pressurized air creating first working gases. The intermediate duct is disposed between the liner and the transition duct and defines a path for the first working gases to flow from the liner to the transition duct. An intermediate duct inlet portion is associated with a liner outlet and allows movement between the intermediate duct and the liner. An intermediate duct outlet portion is associated with a transition duct inlet section and allows movement between the intermediate duct and the transition duct.

Inventors:
;
Issue Date:
Research Org.:
Siemens Energy, Inc. (Orlando, FL)
Sponsoring Org.:
USDOE
OSTI Identifier:
1082947
Patent Number(s):
8375726
Application Number:
12/431,302
Assignee:
Siemens Energy, Inc. (Orlando, FL)
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:  
FC26-05NT42644
Resource Type:
Patent
Country of Publication:
United States
Language:
English
Subject:
42 ENGINEERING

Citation Formats

Wiebe, David J, and Fox, Timothy A. Combustor assembly in a gas turbine engine. United States: N. p., 2013. Web.
Wiebe, David J, & Fox, Timothy A. Combustor assembly in a gas turbine engine. United States.
Wiebe, David J, and Fox, Timothy A. Tue . "Combustor assembly in a gas turbine engine". United States. https://www.osti.gov/servlets/purl/1082947.
@article{osti_1082947,
title = {Combustor assembly in a gas turbine engine},
author = {Wiebe, David J and Fox, Timothy A},
abstractNote = {A combustor assembly in a gas turbine engine. The combustor assembly includes a combustor device coupled to a main engine casing, a first fuel injection system, a transition duct, and an intermediate duct. The combustor device includes a flow sleeve for receiving pressurized air and a liner disposed radially inwardly from the flow sleeve. The first fuel injection system provides fuel that is ignited with the pressurized air creating first working gases. The intermediate duct is disposed between the liner and the transition duct and defines a path for the first working gases to flow from the liner to the transition duct. An intermediate duct inlet portion is associated with a liner outlet and allows movement between the intermediate duct and the liner. An intermediate duct outlet portion is associated with a transition duct inlet section and allows movement between the intermediate duct and the transition duct.},
doi = {},
journal = {},
number = ,
volume = ,
place = {United States},
year = {Tue Feb 19 00:00:00 EST 2013},
month = {Tue Feb 19 00:00:00 EST 2013}
}

Works referenced in this record:

Turbine spring clip seal
patent, March 2005


Non-catalytic combustor for reducing NOx emissions
patent, November 2005


Flow sleeve for a low NOx combustor
patent, August 2006


Turbine fuel ring assembly
patent, July 2007


Gas turbine combustor barrier structures for spring clips
patent, May 2008


Liner stop assembly for a combustor
patent, June 1994


Gas turbine combustor and gas turbine
patent, May 1997