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Title: Lean-rich axial stage combustion in a can-annular gas turbine engine

Abstract

An apparatus and method for lean/rich combustion in a gas turbine engine (10), which includes a combustor (12), a transition (14) and a combustor extender (16) that is positioned between the combustor (12) and the transition (14) to connect the combustor (12) to the transition (14). Openings (18) are formed along an outer surface (20) of the combustor extender (16). The gas turbine (10) also includes a fuel manifold (28) to extend along the outer surface (20) of the combustor extender (16), with fuel nozzles (30) to align with the respective openings (18). A method (200) for axial stage combustion in the gas turbine engine (10) is also presented.

Inventors:
;
Issue Date:
Research Org.:
SIEMENS ENERGY, INC., Orlando, FL (United States)
Sponsoring Org.:
USDOE
OSTI Identifier:
1257245
Patent Number(s):
9366443
Application Number:
13/739,316
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
Resource Relation:
Patent File Date: 2013 Jan 11
Country of Publication:
United States
Language:
English
Subject:
42 ENGINEERING; 33 ADVANCED PROPULSION SYSTEMS

Citation Formats

Laster, Walter R., and Szedlacsek, Peter. Lean-rich axial stage combustion in a can-annular gas turbine engine. United States: N. p., 2016. Web.
Laster, Walter R., & Szedlacsek, Peter. Lean-rich axial stage combustion in a can-annular gas turbine engine. United States.
Laster, Walter R., and Szedlacsek, Peter. Tue . "Lean-rich axial stage combustion in a can-annular gas turbine engine". United States. https://www.osti.gov/servlets/purl/1257245.
@article{osti_1257245,
title = {Lean-rich axial stage combustion in a can-annular gas turbine engine},
author = {Laster, Walter R. and Szedlacsek, Peter},
abstractNote = {An apparatus and method for lean/rich combustion in a gas turbine engine (10), which includes a combustor (12), a transition (14) and a combustor extender (16) that is positioned between the combustor (12) and the transition (14) to connect the combustor (12) to the transition (14). Openings (18) are formed along an outer surface (20) of the combustor extender (16). The gas turbine (10) also includes a fuel manifold (28) to extend along the outer surface (20) of the combustor extender (16), with fuel nozzles (30) to align with the respective openings (18). A method (200) for axial stage combustion in the gas turbine engine (10) is also presented.},
doi = {},
journal = {},
number = ,
volume = ,
place = {United States},
year = {Tue Jun 14 00:00:00 EDT 2016},
month = {Tue Jun 14 00:00:00 EDT 2016}
}

Works referenced in this record:

Combustion chamber for gas turbines
patent, March 1980


Watertube boiler and its method of combustion
patent, June 1991


Lean staged combustion assembly
patent, March 1992


Inspirated staged combustion burner
patent, December 1993


Method and apparatus for staged combustion of air and fuel
patent, August 2010


Fuel Nozzle Assembly for Use in a Combustor of a Gas Turbine Engine
patent-application, March 2011


Air/Fuel Supply System for use in a Gas Turbine Engine
patent-application, December 2011