Segmented annular combustion system

Berry, Jonathan Dwight; Hughes, Michael John

Title: Segmented annular combustion system

Abstract

An annular combustion system includes a fuel nozzle, a panel fuel injector including a fuel plenum and at least one premixing channel therein, an inner liner including an inner band radially spaced from an outer band and an inner flow annulus formed therebetween, and an outer liner radially spaced from the inner liner and comprising an inner band radially spaced from an outer band and an outer flow annulus formed therebetween. The fuel nozzle is positioned radially between the inner liner and the outer liner, and the panel fuel injector extends radially between the inner liner and the outer liner. At least one of the inner flow passage and the outer flow passage is in fluid communication with at least one of a premix air plenum, a cooling air cavity and a cooling air plenum defined within the panel fuel injector.

Inventors:: Berry, Jonathan Dwight; Hughes, Michael John

Issue Date:: 2020-07-28

Research Org.:: General Electric Co., Schenectady, NY (United States)

Sponsoring Org.:: USDOE

OSTI Identifier:: 1735071

Patent Number(s):: 10724441

Application Number:: 15/442,171

Assignee:: General Electric Company (Schenectady, NY)

Patent Classifications (CPCs):: F - MECHANICAL ENGINEERING F02 - COMBUSTION ENGINES F02C - GAS-TURBINE 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

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F - MECHANICAL ENGINEERING F02 - COMBUSTION ENGINES F02C - GAS-TURBINE PLANTS
F02C3/04 - having a turbine driving a compressor
F02C7/18 - the medium being gaseous, e.g. air {
F02C7/22 - Fuel supply systems
F02C7/222 - {Fuel flow conduits, e.g. manifolds}

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
F05D2220/32 - in gas turbines
F05D2240/35 - Combustors or associated equipment
F05D2260/201 - by impingement of a fluid
F05D2260/202 - by film cooling

F - MECHANICAL ENGINEERING F23 - COMBUSTION APPARATUS F23R - GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
F23R3/002 - {Wall structures
F23R3/005 - {Combined with pressure or heat exchangers}
F23R3/06 - Arrangement of apertures along the flame tube
F23R3/10 - for primary air
F23R3/28 - characterised by the fuel supply
F23R3/283 - {Attaching or cooling of fuel injecting means including supports for fuel injectors, stems, or lances}
F23R3/286 - {having fuel-air premixing devices
F23R3/34 - Feeding into different combustion zones
F23R3/346 - {for staged combustion}

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DOE Contract Number:: FE0023965

Resource Type:: Patent

Resource Relation:: Patent File Date: 02/24/2017

Country of Publication:: United States

Language:: English

Subject:: 42 ENGINEERING

Citation Formats


                    Berry, Jonathan Dwight, and Hughes, Michael John. Segmented annular combustion system.  United States: N. p., 2020. 
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                    Berry, Jonathan Dwight, & Hughes, Michael John. Segmented annular combustion system.  United States.

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                    Berry, Jonathan Dwight, and Hughes, Michael John. Tue .  
        "Segmented annular combustion system".  United States.  https://www.osti.gov/servlets/purl/1735071.

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@article{osti_1735071,

  title        = {Segmented annular combustion system},

  author       = {Berry, Jonathan Dwight and Hughes, Michael John},

  abstractNote = {An annular combustion system includes a fuel nozzle, a panel fuel injector including a fuel plenum and at least one premixing channel therein, an inner liner including an inner band radially spaced from an outer band and an inner flow annulus formed therebetween, and an outer liner radially spaced from the inner liner and comprising an inner band radially spaced from an outer band and an outer flow annulus formed therebetween. The fuel nozzle is positioned radially between the inner liner and the outer liner, and the panel fuel injector extends radially between the inner liner and the outer liner. At least one of the inner flow passage and the outer flow passage is in fluid communication with at least one of a premix air plenum, a cooling air cavity and a cooling air plenum defined within the panel fuel injector.},

  doi          = {},

  journal      = {},
number       = ,

  volume       = ,

  place        = {United States},

  year         = {2020},

  month        = {7}

}

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Integrated combustor nozzle for a segmented annular combustion system

Patent Berry, Jonathan Dwight; Widener, Stanley Kevin; Hughes, Michael John; ...

The present disclosure is directed to an integrated combustor nozzle for a segmented annular combustion system. The integrated combustor nozzle includes an outer liner segment, an inner liner segment, and a fuel injection panel extending radially between the outer liner segment and the inner liner segment. The fuel injection panel includes a first side wall, a second side wall, and a plurality of premixing channels between the first and second side walls, each of the premixing channels having an outlet on one of the first and second side walls. The aft end of the fuel injection panel defines a turbinemore » nozzle. « less
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Segmented annular combustion system with axial fuel staging

Patent Berry, Jonathan Dwight; Widener, Stanley Kevin; Hughes, Michael John; ...

A segmented annular combustion system includes an alternating arrangement of fuel nozzles and integrated combustor nozzles. The fuel nozzles deliver fuel to the primary combustion zones. The integrated combustor nozzles include an inner liner segment, an outer liner segment, and a fuel injection panel extending between the liner segments. The fuel injection panel includes injection outlets on one or both side walls to deliver a combustible mixture to the secondary combustion zones. Each fuel injection panel, which provides a boundary between adjacent primary and secondary combustion zones, includes an aft end that defines a turbine nozzle. The segmented annular combustionmore » system is part of a gas turbine. « less
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Segmented annular combustion system

Patent Berry, Jonathan Dwight; Hughes, Michael John

The present disclosure is directed to a segmented annular combustion system including a first panel fuel injector including a premix air plenum, a fuel plenum, and a plurality of first side premixing channels, where each first side premixing channel is in fluid communication with the premix air plenum, the fuel plenum, and a respective first side injection aperture of a plurality of first side injection apertures. A second panel fuel injector is circumferentially spaced from the first panel fuel injector and includes a premix air plenum, a fuel plenum, and a plurality of second side premixing channels where each secondmore » « less
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Cooling of integrated combustor nozzle of segmented annular combustion system

Patent Berry, Jonathan Dwight; Widener, Stanley Kevin; Hughes, Michael John

A segmented annular combustion system includes integrated combustor nozzles, each of which has a fuel injection panel disposed radially between an inner liner segment and an outer liner segment. The fuel injection panel includes an aft end portion, a first side wall, a second side wall, premixing channels defined between the first side wall and the side wall, and injection outlets defined along at least one of the first side wall and the second side wall. The aft end portion defines a turbine nozzle portion. An interior portion between the first side wall and the second side wall includes wallsmore » « less
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Operation and turndown of a segmented annular combustion system

Patent Berry, Jonathan Dwight; Hughes, Michael John

The present disclosure is directed to the operation and turndown of a segmented annular combustion system. The method includes injecting, via a fuel nozzle, a combustible mixture into a primary combustion zone between an adjacent pair of integrated combustor nozzles and burning the combustible mixture. The method further includes flowing air and injecting fuel into a premixing channel defined within a first integrated combustor nozzle to produce a second combustible mixture. The second combustible mixture is injected into a secondary combustion zone where it is combusted. The flow of combustion gases is accelerated, via turbine nozzles of the integrated combustormore » « less
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Title: Segmented annular combustion system

Abstract

Citation Formats

Aft mounting system for combustion transition duct members patent, December 1983

Cooling air recycling for gas turbine transition duct end frame and related method patent, July 2002

Methods and apparatus for cooling gas turbine nozzles patent, March 2009

Gas turbine and operating method thereof patent, February 2016

Transition duct with enhanced profile optimization patent, November 2003

Annular combustor with outer transition liner cooling patent, August 1993

Cooling structure for recovery-type air-cooled gas turbine combustor patent, December 2016

Spiral cooled fuel nozzle patent, September 2012

Fuel injection for gas turbine combustors patent, October 2014

Lean Direct Injection Atomizer for Gas Turbine Engines patent-application, November 2006

Secondary fuel delivery system patent, February 2010

Communicating structure between adjacent combustors and turbine portion and gas turbine patent, July 2016

Gas turbine combustor transition duct forced convection cooling patent, February 1990

Gas turbine combustor transition patent, May 1999

Fuel nozzle for combustor patent, June 2013

Annular premix section for dry low-NO.sub.x combustors patent, July 2000

Segmented annular combustor patent, June 1979

Combustor assembly in a gas turbine engine patent, February 2013

Gas turbine steam-cooled combustor with alternately counter-flowing steam passages patent, October 2002

Cooled gas turbine transition duct patent, December 2007

Annular Wall of a Combustion Chamber with Improved Cooling at the Level of Primary and/or Dilution Holes patent-application, September 2014

Combustor assembly in a gas turbine engine patent, April 2015

Static Seal Structure patent, August 1973

Combustor liner cooling system patent, August 2013

One-piece combustor cowl patent, July 1999

Combustion Apparatus patent, April 1972

Fuel Atomization Dual Orifice Fuel Nozzle patent-application, June 2012

Cooled transition duct for a gas turbine engine patent, September 2011

Thermal spreading combustion liner patent, October 1999

Combustion Chamber Clustering Structure patent, April 1972

Cooled heat shield for gas turbine combustor patent, August 2001

Cooling Flowpath Dirt Deflector in Fuel Nozzle patent-application, June 2012

Annular one-piece corrugated liner for combustor of a gas turbine engine patent-application, October 2003

Aerodynamically Enhanced Fuel Nozzle patent-application, June 2012

Combustor dome heat shield patent, July 1989

Combustor of gas turbine with features for vibration reduction and increased cooling patent, November 1981

Transition piece external frame support patent, June 1998

Transition duct cooling feed tubes patent, April 2012

Combustor for a low-emissions gas turbine engine patent, August 2000

Combustor patent, March 1994

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

Gas turbine engine having an improved transition duct support patent, April 1977

Repair method for a gas turbine patent, April 2003

Lean Direct Injection Atomizer for Gas Turbine Engines patent-application, November 2010

Catalytic combustion system for a stationary combustion turbine having a transition duct mounted catalytic element patent, November 1983

Fuel injector for use in a gas turbine engine patent, October 2012

Combustion Chamber of a Combustor for a Gas Turbine patent-application, December 2014

Steam cooled rich-burn combustor liner patent, April 1989

Integral aft seal for turbine applications patent, September 2002

Cooling scheme for an increased gas turbine efficiency patent, November 2013

Gas turbine system having premixed injector vanes patent, August 2015

Impingement jets coupled to cooling channels for transition cooling patent, February 2011

Steam cooled gas turbine system patent, August 2000

Segmented annular combustor patent, January 2011

Modular Transvane Assembly patent-application, April 2010

Protection of an Integrated Circuit and Method Thereof patent-application, August 2008

Compressed air steam generator for cooling combustion turbine transition section patent, October 2001

Gas turbine plant with combustor cooling system patent, September 2000

Tangential Combustor with Vaneless Turbine for Use on Gas Turbine Engines patent-application,

Burner and method for reducing combustion humming during operation patent, April 2002

Effusion cooled transition duct patent, May 2003

Aerodynamically enhanced fuel nozzle patent, March 2013

Bolted gas turbine combustor transition coupling patent, September 2000

Combustor cap with cooling passage patent, May 2017

Fuel heating system used in conjunction with steam cooled combustors and transitions patent, October 1998

Power Plant Combustion Apparatus Having Apertured Combustion Chamber Walls patent, May 1952

Side seal for combustor transitions patent, February 2002

Impingement cooled transition duct patent, January 1988

Hollow Structure with Flange patent-application, July 2003

Attachment device for removable components in hot gas paths in a turbine engine patent, February 2008

Combustion chamber construction patent, September 1986

Combustor heat shield patent, April 2019

Thermally free aft frame for a transition duct patent, September 2003

Liquid-cooled transition member to turbine inlet patent, April 1980

Transition piece for non-annular gas turbine combustion chambers patent-application, September 2003

Method and apparatus to enhance transition duct cooling in a gas turbine engine patent, October 2013

Gas turbine aerofoil patent, June 2006

Aft mounting system for combustion transition duct members
patent, December 1983

Cooling air recycling for gas turbine transition duct end frame and related method
patent, July 2002

Methods and apparatus for cooling gas turbine nozzles
patent, March 2009

Gas turbine and operating method thereof
patent, February 2016

Transition duct with enhanced profile optimization
patent, November 2003

Annular combustor with outer transition liner cooling
patent, August 1993

Cooling structure for recovery-type air-cooled gas turbine combustor
patent, December 2016

Spiral cooled fuel nozzle
patent, September 2012

Fuel injection for gas turbine combustors
patent, October 2014

Lean Direct Injection Atomizer for Gas Turbine Engines
patent-application, November 2006

Secondary fuel delivery system
patent, February 2010

Communicating structure between adjacent combustors and turbine portion and gas turbine
patent, July 2016

Gas turbine combustor transition duct forced convection cooling
patent, February 1990

Gas turbine combustor transition
patent, May 1999

Fuel nozzle for combustor
patent, June 2013

Annular premix section for dry low-NO.sub.x combustors
patent, July 2000

Segmented annular combustor
patent, June 1979

Combustor assembly in a gas turbine engine
patent, February 2013

Gas turbine steam-cooled combustor with alternately counter-flowing steam passages
patent, October 2002

Cooled gas turbine transition duct
patent, December 2007

Annular Wall of a Combustion Chamber with Improved Cooling at the Level of Primary and/or Dilution Holes
patent-application, September 2014

Combustor assembly in a gas turbine engine
patent, April 2015

Static Seal Structure
patent, August 1973

Combustor liner cooling system
patent, August 2013

One-piece combustor cowl
patent, July 1999

Combustion Apparatus
patent, April 1972

Fuel Atomization Dual Orifice Fuel Nozzle
patent-application, June 2012

Cooled transition duct for a gas turbine engine
patent, September 2011

Thermal spreading combustion liner
patent, October 1999

Combustion Chamber Clustering Structure
patent, April 1972

Cooled heat shield for gas turbine combustor
patent, August 2001

Cooling Flowpath Dirt Deflector in Fuel Nozzle
patent-application, June 2012

Annular one-piece corrugated liner for combustor of a gas turbine engine
patent-application, October 2003

Aerodynamically Enhanced Fuel Nozzle
patent-application, June 2012

Combustor dome heat shield
patent, July 1989

Combustor of gas turbine with features for vibration reduction and increased cooling
patent, November 1981

Transition piece external frame support
patent, June 1998

Transition duct cooling feed tubes
patent, April 2012

Combustor for a low-emissions gas turbine engine
patent, August 2000

Combustor
patent, March 1994

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

Gas turbine engine having an improved transition duct support
patent, April 1977

Repair method for a gas turbine
patent, April 2003

Lean Direct Injection Atomizer for Gas Turbine Engines
patent-application, November 2010

Catalytic combustion system for a stationary combustion turbine having a transition duct mounted catalytic element
patent, November 1983

Fuel injector for use in a gas turbine engine
patent, October 2012

Combustion Chamber of a Combustor for a Gas Turbine
patent-application, December 2014

Steam cooled rich-burn combustor liner
patent, April 1989

Integral aft seal for turbine applications
patent, September 2002

Cooling scheme for an increased gas turbine efficiency
patent, November 2013

Gas turbine system having premixed injector vanes
patent, August 2015

Impingement jets coupled to cooling channels for transition cooling
patent, February 2011

Steam cooled gas turbine system
patent, August 2000

Segmented annular combustor
patent, January 2011

Modular Transvane Assembly
patent-application, April 2010

Protection of an Integrated Circuit and Method Thereof
patent-application, August 2008

Compressed air steam generator for cooling combustion turbine transition section
patent, October 2001

Gas turbine plant with combustor cooling system
patent, September 2000

Tangential Combustor with Vaneless Turbine for Use on Gas Turbine Engines
patent-application,

Burner and method for reducing combustion humming during operation
patent, April 2002

Effusion cooled transition duct
patent, May 2003

Aerodynamically enhanced fuel nozzle
patent, March 2013

Bolted gas turbine combustor transition coupling
patent, September 2000

Combustor cap with cooling passage
patent, May 2017

Fuel heating system used in conjunction with steam cooled combustors and transitions
patent, October 1998

Power Plant Combustion Apparatus Having Apertured Combustion Chamber Walls
patent, May 1952

Side seal for combustor transitions
patent, February 2002

Impingement cooled transition duct
patent, January 1988

Hollow Structure with Flange
patent-application, July 2003

Attachment device for removable components in hot gas paths in a turbine engine
patent, February 2008

Combustion chamber construction
patent, September 1986

Combustor heat shield
patent, April 2019

Thermally free aft frame for a transition duct
patent, September 2003

Liquid-cooled transition member to turbine inlet
patent, April 1980

Transition piece for non-annular gas turbine combustion chambers
patent-application, September 2003

Method and apparatus to enhance transition duct cooling in a gas turbine engine
patent, October 2013

Gas turbine aerofoil
patent, June 2006

Flame Tube Having Telescoping Walls with Fluted Ends to Admit Air
patent, January 1953

Dilution pole combustor and method
patent, August 1993

Piping support of gas turbine steam cooled combustor
patent, February 2003