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):
- 9,366,443
- Application Number:
- 13/739,316
- Assignee:
- SIEMENS ENERGY, INC. (Orlando, FL)
- 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 = {2016},
month = {6}
}
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