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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. 2016. "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 = 2016,
month = 6
}

Patent:

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  • A method is described of learning control for air/fuel ratio of an internal combustion engine operated with fuel injection to maintain the air/fuel ratio at the stoichiometric value, comprising the steps of: determining a basic fuel injection time duration according to engine load and engine revolution speed; determining an air/fuel ratio feedback complementing factor which is changed over between a constantly increasing mode which continues as long as the air/fuel ratio is on the lean side of the stoichiometric value and a constantly decreasing mode which continues as long as the air/fuel ratio is on the rich side of themore » stoichiometric value; determining a learning control factor; multiplying the basic fuel injection time duration by the air/fuel ratio feedback complementing factor and further modifying the basic fuel injection time duration by the learning control factor so as to change in the same direction as the learning control factor changes to provide an actual fuel injection time duration.« less
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  • An internal combustion engine of lean air-fuel mixture combustion type comprises a subsidiary combustion chamber opening into a main combustion chamber via a connecting passage. A raised portion is formed on the top surface of the piston. The raised portion extends from the peripheral end of the inner surface of the cylinder head to the vicinity of the opening of the subsidiary combustion chamber for creating a squish flow along the inner surface of the cylinder head. The connecting passage is arranged so that a high velocity burning jet injected from the subsidiary combustion chamber meets with the squish flowmore » at an angle of less 90/sup 0/.« less