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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:
;
Publication Date:
Research Org.:
SIEMENS ENERGY, INC., Orlando, FL (United States)
Sponsoring Org.:
USDOE
OSTI Identifier:
1257245
Patent Number(s):
9,366,443
Application Number:
13/739,316
Assignee:
SIEMENS ENERGY, INC. (Orlando, FL) NETL
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. doi:. 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}
}

Patent:

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