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}
}
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