Method and computer-readable model for additively manufacturing ducting arrangement for a gas turbine engine

Title: Method and computer-readable model for additively manufacturing ducting arrangement for a gas turbine engine

Abstract

Method and computer-readable model for additively manufacturing a ducting arrangement (10) for a gas turbine engine are provided. Ducting arrangement (10) may include a duct (18) to be fluidly coupled to receive a cross-flow of combustion gases from a 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 to be mixed with the cross-flow of combustion gases. The ducting arrangement is effective 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:: 2019-02-26

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

Sponsoring Org.:: USDOE

OSTI Identifier:: 1524998

Patent Number(s):: 10215038

Application Number:: 15/165,210

Assignee:: Siemens Energy, Inc. (Orlando, FL)

Patent Classifications (CPCs):: G - PHYSICS G06 - COMPUTING G06F - ELECTRIC DIGITAL DATA PROCESSING

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

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G - PHYSICS G06 - COMPUTING G06F - ELECTRIC DIGITAL DATA PROCESSING
G06F2119/18 - Manufacturability analysis or optimisation for manufacturability

F - MECHANICAL ENGINEERING F02 - COMBUSTION ENGINES F02C - GAS-TURBINE PLANTS
F02C3/14 - characterised by the arrangement of the combustion chamber in the plant

B - PERFORMING OPERATIONS B33 - ADDITIVE MANUFACTURING TECHNOLOGY B33Y - ADDITIVE MANUFACTURING, i.e. MANUFACTURING OF THREE-DIMENSIONAL [3-D] OBJECTS BY ADDITIVE DEPOSITION, ADDITIVE AGGLOMERATION OR ADDITIVE LAYERING, e.g. BY 3-D PRINTING, STEREOLITHOGRAPHY OR SELECTIVE LASER SINTERING
B33Y80/00 - Products made by additive manufacturing

F - MECHANICAL ENGINEERING F02 - COMBUSTION ENGINES F02C - GAS-TURBINE PLANTS
F02C7/222 - {Fuel flow conduits, e.g. manifolds}
F02C7/04 - Air intakes for gas-turbine plants or jet-propulsion plants

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
F05D2260/601 - using an ejector or a jet pump

Y - NEW / CROSS SECTIONAL TECHNOLOGIES Y02 - TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE Y02E - REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
Y02E20/16 - Combined cycle power plant [CCPP], or combined cycle gas turbine [CCGT]

G - PHYSICS G05 - CONTROLLING G05B - CONTROL OR REGULATING SYSTEMS IN GENERAL
G05B2219/35134 - 3-D cad-cam
G05B2219/49007 - Making, forming 3-D object, model, surface

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 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
F05D2260/81 - Modelling or simulation
F05D2240/35 - Combustors or associated equipment
F05D2230/50 - Building or constructing in particular ways

Y - NEW / CROSS SECTIONAL TECHNOLOGIES Y02 - TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE Y02P - CLIMATE CHANGE MITIGATION TECHNOLOGIES IN THE PRODUCTION OR PROCESSING OF GOODS
Y02P90/02 - Total factory control, e.g. smart factories, flexible manufacturing systems [FMS] or integrated manufacturing systems [IMS]

G - PHYSICS G05 - CONTROLLING G05B - CONTROL OR REGULATING SYSTEMS IN GENERAL
G05B19/4099 - Surface or curve machining, making 3D objects, e.g. desktop manufacturing

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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

Citation Formats


                    Chen, Yuntao, Portillo Bilbao, Juan Enrique, North, Andrew J., Tran, Lucky, Meadows, Joseph, and Laster, Walter Ray. Method and computer-readable model for additively manufacturing ducting arrangement for 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. Method and computer-readable model for additively manufacturing ducting arrangement for 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 .  
        "Method and computer-readable model for additively manufacturing ducting arrangement for a gas turbine engine".  United States.  https://www.osti.gov/servlets/purl/1524998.

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@article{osti_1524998,

  title        = {Method and computer-readable model for additively manufacturing ducting arrangement for 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 = {Method and computer-readable model for additively manufacturing a ducting arrangement (10) for a gas turbine engine are provided. Ducting arrangement (10) may include a duct (18) to be fluidly coupled to receive a cross-flow of combustion gases from a 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 to be mixed with the cross-flow of combustion gases. The ducting arrangement is effective 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        = {2}

}

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Rodgers, Colin; Shekleton, Jack R.; Jones, Anthony C.
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Combustion transition duct providing stage 1 tangential turning for turbine engines
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Title: Method and computer-readable model for additively manufacturing ducting arrangement for a gas turbine engine

Abstract

Citation Formats

Small diameter gas turbine engine patent, May 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

Method and apparatus for total energy systems patent, September 1986

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

Fuel nozzle patent, November 2015

Injector for turbine engines patent, August 1997

Small diameter gas turbine engine
patent, May 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

Method and apparatus for total energy systems
patent, September 1986

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

Fuel nozzle
patent, November 2015

Injector for turbine engines
patent, August 1997