Method of making an aero-derivative gas turbine engine

Wiebe, David J.

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A01 - agriculture
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Title: Method of making an aero-derivative gas turbine engine

Abstract

A method of making an aero-derivative gas turbine engine (100) is provided. A combustor outer casing (68) is removed from an existing aero gas turbine engine (60). An annular combustor (84) is removed from the existing aero gas turbine engine. A first row of turbine vanes (38) is removed from the existing aero gas turbine engine. A can annular combustor assembly (122) is installed within the existing aero gas turbine engine. The can annular combustor assembly is configured to accelerate and orient combustion gasses directly onto a first row of turbine blades of the existing aero gas turbine engine. A can annular combustor assembly outer casing (108) is installed to produce the aero-derivative gas turbine engine (100). The can annular combustor assembly is installed within an axial span (85) of the existing aero gas turbine engine vacated by the annular combustor and the first row of turbine vanes.

Inventors:: Wiebe, David J.

Issue Date:: Tue Feb 06 00:00:00 EST 2018

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

Sponsoring Org.:: USDOE

OSTI Identifier:: 1419776

Patent Number(s):: 9885482

Application Number:: 15/355,665

Assignee:: SIEMENS ENERGY, INC. (Orlando, FL)

Patent Classifications (CPCs):: F - MECHANICAL ENGINEERING F01 - MACHINES OR ENGINES IN GENERAL F01D - NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES

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

Show more

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 F02 - COMBUSTION ENGINES F02C - GAS-TURBINE PLANTS
F02C3/04 - having a turbine driving a compressor
F02C3/14 - characterised by the arrangement of the combustion chamber in the plant

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
F05D2230/80 - Repairing, retrofitting or upgrading methods
F05D2250/314 - the axes being inclined in relation to each other

F - MECHANICAL ENGINEERING F23 - COMBUSTION APPARATUS F23R - GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
F23R3/46 - Combustion chambers comprising an annular arrangement of {several essentially tubular} flame tubes within a common annular casing or within individual casings

Y - NEW / CROSS SECTIONAL TECHNOLOGIES Y10 - TECHNICAL SUBJECTS COVERED BY FORMER USPC Y10T - TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
Y10T29/49229 - Prime mover or fluid pump making

Show less

DOE Contract Number:: FC26-05NT42644

Resource Type:: Patent

Resource Relation:: Patent File Date: 2016 Nov 18

Country of Publication:: United States

Language:: English

Subject:: 42 ENGINEERING

Citation Formats


                    Wiebe, David J. Method of making an aero-derivative gas turbine engine.  United States: N. p., 2018. 
        Web.

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                    Wiebe, David J. Method of making an aero-derivative gas turbine engine.  United States.

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                    Wiebe, David J. Tue .  
        "Method of making an aero-derivative gas turbine engine".  United States.  https://www.osti.gov/servlets/purl/1419776.

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@article{osti_1419776,

  title        = {Method of making an aero-derivative gas turbine engine},

  author       = {Wiebe, David J.},

  abstractNote = {A method of making an aero-derivative gas turbine engine (100) is provided. A combustor outer casing (68) is removed from an existing aero gas turbine engine (60). An annular combustor (84) is removed from the existing aero gas turbine engine. A first row of turbine vanes (38) is removed from the existing aero gas turbine engine. A can annular combustor assembly (122) is installed within the existing aero gas turbine engine. The can annular combustor assembly is configured to accelerate and orient combustion gasses directly onto a first row of turbine blades of the existing aero gas turbine engine. A can annular combustor assembly outer casing (108) is installed to produce the aero-derivative gas turbine engine (100). The can annular combustor assembly is installed within an axial span (85) of the existing aero gas turbine engine vacated by the annular combustor and the first row of turbine vanes.},

  doi          = {},

  journal      = {},
number       = ,

  volume       = ,

  place        = {United States},

  year         = {Tue Feb 06 00:00:00 EST 2018},

  month        = {Tue Feb 06 00:00:00 EST 2018}

}

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Works referenced in this record:

Cleaning gas turbine compressors
patent, February 1989

Woodson, Jeffrey; Cooper, Lance A.; White, Helen M.
US Patent Document 4,808,235
URL: https://image-ppubs.uspto.gov/dirsearch-public/print/downloadPdf/4808235

Chemically recuperated gas turbine
patent, July 1992

Horner, Michael W.; Hines, William R.
US Patent Document 5,133,180
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Convectively cooled, single stage, fully premixed controllable fuel/air combustor
patent, April 2001

Mowill, R. Jan
US Patent Document 6,220,034
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Silo/can-annular low emissions combustor
patent, April 2002

Kraft, Robert J.; Martling, Vincent C.; Mack, Brian R.
US Patent Document 6,374,594
URL: https://image-ppubs.uspto.gov/dirsearch-public/print/downloadPdf/6374594

Hybrid combined cycle power generation facility
patent, August 2003

Steinway, Paul
US Patent Document 6,608,395
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Heat-tolerated vortex-disrupting fluid guide component
patent, April 2005

Beeck, Alexander
US Patent Document 6,884,029
URL: https://image-ppubs.uspto.gov/dirsearch-public/print/downloadPdf/6884029

Multi-spool turbogenerator system and control method
patent, August 2005

Belokon, Alexander; Senkevich, Mikhail; Touchton, George L.
US Patent Document 6,931,856
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Combustion transition duct providing stage 1 tangential turning for turbine engines
patent, May 2010

Bancalari, Eduardo; Wilson, Jody W.; Little, David A.
US Patent Document 7,721,547
URL: https://image-ppubs.uspto.gov/dirsearch-public/print/downloadPdf/7721547

Gas turbine engine with radial diffuser and shortened mid section
patent, September 2015

Charron, Richard C.; Montgomery, Matthew
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Gas turbine with combined can-type and annular combustor and method of operating a gas turbine
patent-application, October 2002

Schulten, Wilhelm; Simon, Gerhard; Tiemann, Peter
US Patent Application 09/842881; 20020157400
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Premixing device for low emission combustion process
patent-application, May 2007

Evulet, Andrei Tristan
US Patent Application 11/273212; 20070107436
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Low emission combustion and method of operation
patent-application, May 2007

Evulet, Andrei Tristan; Varatharajan, Balachandar; Fritz, Jassin Marcel
US Patent Application 11/280664; 20070107437
URL: https://image-ppubs.uspto.gov/dirsearch-public/print/downloadPdf/20070107437

Transition with a linear flow path with exhaust mouths for use in a gas turbine engine
patent-application, February 2010

Charron, Richard; Snyder, Gary
US Patent Application 12/190060; 20100037617
URL: https://image-ppubs.uspto.gov/dirsearch-public/print/downloadPdf/20100037617

Modular Transvane Assembly
patent-application, April 2010

Wilson, Jody; Nordlund, Raymond; Charron, Richard
US Patent Application 12/420149; 20100077719
URL: https://image-ppubs.uspto.gov/dirsearch-public/print/downloadPdf/20100077719

Structural Attachment System for Transition Duct Outlet
patent-application, July 2010

Charron, Richard
US Patent Application 12/357607; 20100180605
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Method of Starting A Turbomachine
patent-application, June 2011

Vernet, Valerie S.; Alexander, Michael J.; Maters, John C.
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Assembly for directing combustion gas
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Charron, Richard; Nordlund, Raymond; Morrison, Jay
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Aero-Derivative Gas Turbine Engine With An Advanced Transition Duct Combustion Assembly
patent-application, April 2013

Wiebe, David J.
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patent-application, March 2014

Beeck, Alexander R.
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Similar Records

Title: Method of making an aero-derivative gas turbine engine

Abstract

Citation Formats

Cleaning gas turbine compressors patent, February 1989

Chemically recuperated gas turbine patent, July 1992

Convectively cooled, single stage, fully premixed controllable fuel/air combustor patent, April 2001

Silo/can-annular low emissions combustor patent, April 2002

Hybrid combined cycle power generation facility patent, August 2003

Heat-tolerated vortex-disrupting fluid guide component patent, April 2005

Multi-spool turbogenerator system and control method patent, August 2005

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

Gas turbine engine with radial diffuser and shortened mid section patent, September 2015

Gas turbine with combined can-type and annular combustor and method of operating a gas turbine patent-application, October 2002

Premixing device for low emission combustion process patent-application, May 2007

Low emission combustion and method of operation patent-application, May 2007

Transition with a linear flow path with exhaust mouths for use in a gas turbine engine patent-application, February 2010

Modular Transvane Assembly patent-application, April 2010

Structural Attachment System for Transition Duct Outlet patent-application, July 2010

Method of Starting A Turbomachine patent-application, June 2011

Assembly for directing combustion gas patent-application, August 2011

Aero-Derivative Gas Turbine Engine With An Advanced Transition Duct Combustion Assembly patent-application, April 2013

Gas Turbine Engine With Shortened Mid Section patent-application, March 2014

Cleaning gas turbine compressors
patent, February 1989

Chemically recuperated gas turbine
patent, July 1992

Convectively cooled, single stage, fully premixed controllable fuel/air combustor
patent, April 2001

Silo/can-annular low emissions combustor
patent, April 2002

Hybrid combined cycle power generation facility
patent, August 2003

Heat-tolerated vortex-disrupting fluid guide component
patent, April 2005

Multi-spool turbogenerator system and control method
patent, August 2005

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

Gas turbine engine with radial diffuser and shortened mid section
patent, September 2015

Gas turbine with combined can-type and annular combustor and method of operating a gas turbine
patent-application, October 2002

Premixing device for low emission combustion process
patent-application, May 2007

Low emission combustion and method of operation
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Transition with a linear flow path with exhaust mouths for use in a gas turbine engine
patent-application, February 2010

Modular Transvane Assembly
patent-application, April 2010

Structural Attachment System for Transition Duct Outlet
patent-application, July 2010

Method of Starting A Turbomachine
patent-application, June 2011

Assembly for directing combustion gas
patent-application, August 2011

Aero-Derivative Gas Turbine Engine With An Advanced Transition Duct Combustion Assembly
patent-application, April 2013

Gas Turbine Engine With Shortened Mid Section
patent-application, March 2014