Ducting arrangement with injector assemblies arranged in an expanding cross-sectional area of a downstream combustion stage in a gas turbine engine

Chen, Yuntao; Portillo Bilbao, Juan Enrique; North, Andrew J.; Tran, Lucky; Meadows, Joseph; Laster, Walter Ray

Title: Ducting arrangement with injector assemblies arranged in an expanding cross-sectional area of a downstream combustion stage in a gas turbine engine

Abstract

A ducting arrangement (10) in a combustion stage downstream of a main combustion stage of a gas turbine engine is provided. A duct (18) is fluidly coupled to receive a cross-flow of combustion gases from the main combustion stage. Duct (18) includes a duct segment (23) with an expanding cross-sectional area (24) where one or more injector assemblies (26) are disposed. Injector assembly (26) includes one or more reactant-guiding structures (27) arranged to deliver a flow of reactants into the downstream combustion stage to be mixed with the cross-flow of combustion gases. Disclosed injector assemblies are arranged in expanding cross-sectional area (24) to reduce total pressure loss while providing an effective level of mixing of the injected reactants with the passing cross-flow. Respective duct components or the entire ducting arrangement may be formed as a unitized structure, such as a single piece using a rapid manufacturing technology, such as 3D Printing/Additive Manufacturing (AM) technologies.

Inventors:: Chen, Yuntao; Portillo Bilbao, Juan Enrique; North, Andrew J.; Tran, Lucky; Meadows, Joseph; Laster, Walter Ray

Issue Date:: 2019-03-05

Research Org.:: Siemens Energy, Inc., Orlando, FL (United States)

Sponsoring Org.:: USDOE

OSTI Identifier:: 1525025

Patent Number(s):: 10222066

Application Number:: 15/165,195

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

F - MECHANICAL ENGINEERING F02 - COMBUSTION ENGINES F02C - GAS-TURBINE PLANTS

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F - MECHANICAL ENGINEERING F23 - COMBUSTION APPARATUS F23R - GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
F23R3/02 - characterised by the air-flow or gas-flow configuration

F - MECHANICAL ENGINEERING F02 - COMBUSTION ENGINES F02C - GAS-TURBINE PLANTS
F02C7/222 - {Fuel flow conduits, e.g. manifolds}

F - MECHANICAL ENGINEERING F23 - COMBUSTION APPARATUS F23R - GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
F23R2900/03341 - Sequential combustion chambers or burners
F23R3/04 - Air inlet arrangements
F23R3/045 - {using pipes}
F23R3/42 - characterised by the arrangement or form of the flame tubes or combustion chambers
F23R3/346 - {for staged combustion}
F23R3/18 - Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants
F23R3/286 - {having fuel-air premixing devices
F23R3/002 - {Wall structures
F23R3/06 - Arrangement of apertures along the flame tube

F - MECHANICAL ENGINEERING F01 - MACHINES OR ENGINES IN GENERAL F01D - NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
F01D9/023 - {Transition ducts between combustor cans and first stage of the turbine in gas-turbine engines

F - MECHANICAL ENGINEERING F23 - COMBUSTION APPARATUS F23R - GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
F23R3/16 - with devices inside the flame tube or the combustion chamber to influence the air or gas flow

F - MECHANICAL ENGINEERING F02 - COMBUSTION ENGINES F02C - GAS-TURBINE PLANTS
F02C6/003 - {Gas-turbine plants with heaters between turbine stages}

F - MECHANICAL ENGINEERING F05 - INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04 F05D - INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
F05D2240/35 - Combustors or associated equipment

F - MECHANICAL ENGINEERING F23 - COMBUSTION APPARATUS F23R - GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
F23R3/34 - Feeding into different combustion zones
F23R3/20 - incorporating fuel injection means
F23R3/10 - for primary air

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DOE Contract Number:: FE0023968

Resource Type:: Patent

Resource Relation:: Patent File Date: 2016-05-26

Country of Publication:: United States

Language:: English

Subject:: 33 ADVANCED PROPULSION SYSTEMS

Citation Formats


                    Chen, Yuntao, Portillo Bilbao, Juan Enrique, North, Andrew J., Tran, Lucky, Meadows, Joseph, and Laster, Walter Ray. Ducting arrangement with injector assemblies arranged in an expanding cross-sectional area of a downstream combustion stage in a gas turbine engine.  United States: N. p., 2019. 
        Web.

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                    Chen, Yuntao, Portillo Bilbao, Juan Enrique, North, Andrew J., Tran, Lucky, Meadows, Joseph, & Laster, Walter Ray. Ducting arrangement with injector assemblies arranged in an expanding cross-sectional area of a downstream combustion stage in a gas turbine engine.  United States.

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                    Chen, Yuntao, Portillo Bilbao, Juan Enrique, North, Andrew J., Tran, Lucky, Meadows, Joseph, and Laster, Walter Ray. Tue .  
        "Ducting arrangement with injector assemblies arranged in an expanding cross-sectional area of a downstream combustion stage in a gas turbine engine".  United States.  https://www.osti.gov/servlets/purl/1525025.

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@article{osti_1525025,

  title        = {Ducting arrangement with injector assemblies arranged in an expanding cross-sectional area of a downstream combustion stage in a gas turbine engine},

  author       = {Chen, Yuntao and Portillo Bilbao, Juan Enrique and North, Andrew J. and Tran, Lucky and Meadows, Joseph and Laster, Walter Ray},

  abstractNote = {A ducting arrangement (10) in a combustion stage downstream of a main combustion stage of a gas turbine engine is provided. A duct (18) is fluidly coupled to receive a cross-flow of combustion gases from the main combustion stage. Duct (18) includes a duct segment (23) with an expanding cross-sectional area (24) where one or more injector assemblies (26) are disposed. Injector assembly (26) includes one or more reactant-guiding structures (27) arranged to deliver a flow of reactants into the downstream combustion stage to be mixed with the cross-flow of combustion gases. Disclosed injector assemblies are arranged in expanding cross-sectional area (24) to reduce total pressure loss while providing an effective level of mixing of the injected reactants with the passing cross-flow. Respective duct components or the entire ducting arrangement may be formed as a unitized structure, such as a single piece using a rapid manufacturing technology, such as 3D Printing/Additive Manufacturing (AM) technologies.},

  doi          = {},

  journal      = {},
number       = ,

  volume       = ,

  place        = {United States},

  year         = {2019},

  month        = {3}

}

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Works referenced in this record:

Combustion transition duct providing stage 1 tangential turning for turbine engines
patent, May 2010

Bancalari, Eduardo E.; Wilson, Jody; Little, David A.
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Fox, Timothy A.; Schilp, Reinhard; Gambacorta, Domenico
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McMasters, Marie Ann; Lohmueller, Steven Joseph; Boehm, Randall Charles
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Combustor and method of operating same
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Similar Records

Title: Ducting arrangement with injector assemblies arranged in an expanding cross-sectional area of a downstream combustion stage in a gas turbine engine

Abstract

Citation Formats

Combustion transition duct providing stage 1 tangential turning for turbine engines patent, May 2010

Forming structures from CAD solid models patent, November 2004

Assembly for directing combustion gas patent, October 2012

Dual stage-dual mode low emission gas turbine combustion system patent, December 1983

Combustor assembly in a gas turbine engine patent, February 2013

Air/fuel supply system for use in a gas turbine engine patent, June 2014

Gas turbine engine combustion chamber patent, December 1995

Late lean injection with adjustable air splits patent, February 2012

Method and apparatus for sequentially staged combustion using a catalyst patent, April 1997

Fuel nozzle patent, November 2015

Combustor and method of operating same patent, April 1993

Combustion transition duct providing stage 1 tangential turning for turbine engines
patent, May 2010

Forming structures from CAD solid models
patent, November 2004

Assembly for directing combustion gas
patent, October 2012

Dual stage-dual mode low emission gas turbine combustion system
patent, December 1983

Combustor assembly in a gas turbine engine
patent, February 2013

Air/fuel supply system for use in a gas turbine engine
patent, June 2014

Gas turbine engine combustion chamber
patent, December 1995

Late lean injection with adjustable air splits
patent, February 2012

Method and apparatus for sequentially staged combustion using a catalyst
patent, April 1997

Fuel nozzle
patent, November 2015

Combustor and method of operating same
patent, April 1993