Patents by Inventor Geoffrey David Myers
Geoffrey David Myers has filed for patents to protect the following inventions. This listing includes patent applications that are pending as well as patents that have already been granted by the United States Patent and Trademark Office (USPTO).
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Patent number: 8457861Abstract: A gas turbine engine is provided and includes a combustor having a first interior in which a first fuel is combustible, a turbine into which products of at least the combustion of the first fuel are receivable, a transition zone, including a second interior in which a second fuel and the products of the combustion of the first fuel are combustible, a plurality of fuel injectors which are configured to supply the second fuel to the second interior in any one of a single axial stage, multiple axial stages, a single axial circumferential stage and multiple axial circumferential stages, a compressor, by which air is supplied to the first and second interiors for the combustion therein, and a control system configured to control relative amounts of the air to the first and second interiors and relative amounts of the first and second fuels supplied to the first and second interiors.Type: GrantFiled: August 24, 2012Date of Patent: June 4, 2013Assignee: General Electric CompanyInventors: Lewis Berkley Davis, Jr., Krishna Kumar Venkataraman, Willy Steve Ziminsky, Geoffrey David Myers
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Publication number: 20130098040Abstract: A system includes a gas turbine engine having a combustor, a liquid fuel supply coupled to the combustor, and a water supply coupled to the liquid fuel supply. The water supply is configured to flow water through the liquid fuel supply while the liquid fuel supply is not in use to flow a liquid fuel.Type: ApplicationFiled: October 24, 2011Publication date: April 25, 2013Applicant: General Electric CompanyInventors: Hua Zhang, Douglas Frank Beadie, Geoffrey David Myers, Fabien Thibault Codron, Gregory Allen Boardman
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Publication number: 20130098056Abstract: A system includes a turbine fuel supply system. The turbine fuel supply system includes a first turbine fuel mixer configured to mix a first liquid fuel and a first deaerated water to generate a first fuel mixture. The first fuel mixture is configured to combust in a combustor of a gas turbine engine. The turbine fuel supply system also includes a deaerated water flow path configured to route the first deaerated water to the first turbine fuel mixer and a liquid fuel flow path configured to route the first liquid fuel to the first turbine fuel mixer.Type: ApplicationFiled: October 24, 2011Publication date: April 25, 2013Applicant: GENERAL ELECTRIC COMPANYInventors: Hua Zhang, Douglas Frank Beadie, Geoffrey David Myers, Fabien Thibault Codron, William Thomas Ross
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Patent number: 8418469Abstract: A fuel nozzle assembly is disclosed. The fuel nozzle assembly comprises an outer burner tube and an inner burner tube defining a pre-mixing annulus therebetween. The fuel nozzle assembly further comprises a swirler assembly, the swirler assembly comprising a plurality of swirler vanes disposed in an annular array about the inner burner tube and configured to interact with primary air upstream of the pre-mixing annulus. The fuel nozzle assembly further comprises an air injection feature configured to flow secondary air into the pre-mixing annulus downstream of the swirler assembly such that the secondary air flows in a generally linear path longitudinally with respect to the pre-mixing annulus and adjacent at least one of the outer burner tube and the inner burner tube.Type: GrantFiled: September 27, 2010Date of Patent: April 16, 2013Assignee: General Electric CompanyInventors: Geoffrey David Myers, Nishant Govindbhai Parsania, Gregory Allen Boardman
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Publication number: 20130067921Abstract: A fuel injector is provided and includes a member defining a flowpath through which a first fluid flows, the flowpath having a cross-section with transverse elongate and short axes, a head defining a plenum storing a supply of a second fluid and a system fluidly coupled to the flowpath and the plenum to inject the second fluid from the plenum and into the flowpath at first and second locations along the elongate axis. The injected second fluid is formed into jets at the first and second locations, the first fluid entrains the jets such that the injected second fluid flows through the flowpath and mixes with the first fluid, and the short axis has a sufficient dimension such that the jets remain spaced from a sidewall of the member.Type: ApplicationFiled: September 15, 2011Publication date: March 21, 2013Applicant: General Electric CompanyInventors: Mark Allan Hadley, Jun Cai, Lucas John Stoia, Geoffrey David Myers, Jayaprakash Natarajan
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Patent number: 8387396Abstract: A method for assembling a combustor assembly is provided. The method includes providing at least one sleeve having a plurality of inlets, and coupling at least one airfoil to at least one of the plurality of inlets defined in the at least one sleeve. The airfoil includes a pair of opposing sidewalls coupled together at a leading edge and at a trailing edge and at least one channel is formed between the airfoil sidewalls for channeling cooling air. The cooling air is directed to flow substantially perpendicularly to a direction of air flowing around the airfoil in a portion of the combustor assembly that is to be cooled. The method also includes coupling the at least one sleeve around the portion of the combustor assembly to be cooled. Also provided are a sleeve and an airfoil for use in a combustor assembly.Type: GrantFiled: January 9, 2007Date of Patent: March 5, 2013Assignee: General Electric CompanyInventors: Wei Chen, Stephen Robert Thomas, Geoffrey David Myers, Vijay Kumar Turaga
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Patent number: 8377232Abstract: A method for removing hot gas deposits from a system via pressure pulses is provided. The method includes regulating a flow of a mixture of detonation fluid and oxidizer into an expansion chamber; and generating a detonation within the expansion chamber by igniting the mixture of detonation fluid and oxidizer in the expansion chamber producing a high-pressure wave, the high-pressure wave propagating along a fluid path of the system in a supersonic rate removing hot gas deposits in the fluid path while the system is in fired operation, the expansion chamber directing the high-pressure wave towards the fluid path of the system.Type: GrantFiled: May 4, 2009Date of Patent: February 19, 2013Assignee: General Electric CompanyInventors: Geoffrey David Myers, Michael John Hughes, Atul Kumar Vij
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Publication number: 20120312024Abstract: A gas turbine engine is provided and includes a combustor having a first interior in which a first fuel is combustible, a turbine into which products of at least the combustion of the first fuel are receivable, a transition zone, including a second interior in which a second fuel and the products of the combustion of the first fuel are combustible, a plurality of fuel injectors which are configured to supply the second fuel to the second interior in any one of a single axial stage, multiple axial stages, a single axial circumferential stage and multiple axial circumferential stages, a compressor, by which air is supplied to the first and second interiors for the combustion therein, and a control system configured to control relative amounts of the air to the first and second interiors and relative amounts of the first and second fuels supplied to the first and second interiors.Type: ApplicationFiled: August 24, 2012Publication date: December 13, 2012Applicant: GENERAL ELECTRIC COMPANYInventors: Lewis Berkley Davis, JR., Krishna Kumar Venkataraman, Willy Steve Ziminsky, Geoffrey David Myers
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Publication number: 20120305086Abstract: A system for supplying fuel includes a fuel manifold, a water manifold, and a fluid junction between the fuel manifold and the water manifold. A turbulator downstream from the fluid junction receives a fluid flow from the fluid junction. A method for supplying fuel includes flowing fuel through a fuel manifold, flowing water through a water manifold, and combining a portion of the water from the water manifold with the fuel from the fuel manifold to create emulsion fuel. The method further includes flowing the emulsion fuel through a turbulator.Type: ApplicationFiled: June 6, 2011Publication date: December 6, 2012Applicant: GENERAL ELECTRIC COMPANYInventors: Hua Zhang, Douglas Frank Beadie, Gregory Allen Boardman, Geoffrey David Myers, William Thomas Ross
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Publication number: 20120291447Abstract: A combustor nozzle includes a first and second liquid fuel passages that terminate at first and second fuel ports. A first diluent passage terminates at a first diluent outlet radially surrounding the second fuel ports. A second diluent passage terminates at a second diluent outlet between the first diluent outlet and the second fuel ports. A third diluent passage surrounds at least a portion of the first and second diluent passages. A method for supplying fuel to a combustor includes flowing a liquid fuel through a first fuel passage and flowing an emulsified liquid fuel through a second fuel passage. The method further includes flowing a first diluent through a shroud surrounding the second fuel passage to a first diluent passage surrounding at least a portion of the second fuel passage and flowing a second diluent through a second diluent passage radially disposed between the first diluent passage and the second fuel passage.Type: ApplicationFiled: May 18, 2011Publication date: November 22, 2012Applicant: GENERAL ELECTRIC COMPANYInventors: Gregory Allen Boardman, Geoffrey David Myers, William Thomas Ross
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Publication number: 20120272655Abstract: A system and a method of generating energy in a power plant using a turbine are provided. The system includes an air separation unit providing an oxygen output; a plasma generator that is capable of generating plasma; and a combustor configured to receive oxygen and to combust a fuel stream in the presence of the plasma, so as to maintain a stable flame, generating an exhaust gas. The system can further include a water condensation system, fluidly-coupled to the combustor, that is capable of producing a high-content carbon dioxide stream that is substantially free of oxygen. The method of generating energy in a power plant includes the steps of operating an air separation unit to separate oxygen from air, combusting a fuel stream in a combustor in the presence of oxygen, and generating an exhaust gas from the combustion. The exhaust gas can be used in a turbine to generate electricity. A plasma is generated inside the combustor, and a stable flame is maintained in the combustor.Type: ApplicationFiled: April 29, 2011Publication date: November 1, 2012Applicant: GENERAL ELECTRIC COMPANYInventors: Ahmed Mostafa ELKady, Uyigue Omoma Idahosa, Matthew Patrick Boespflug, Grover Andrew Bennett, John Thomas Herbon, Hasan Karim, Geoffrey David Myers, Seyed Gholamali Saddoughi
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Patent number: 8281600Abstract: A method for cooling a combustor assembly having a cooling passage. The method includes providing at least one thimble including an inner surface that defines a first opening, a second opening that is downstream from the first opening, and a flow channel that extends between the first opening and the second opening. The flow channel has a converging portion and a recovery portion that is downstream from the converging portion. The method also includes inserting the at least one thimble into at least one inlet that is defined in at least one sleeve such that cooling air is discharged from the flow channel into the cooling passage.Type: GrantFiled: January 9, 2007Date of Patent: October 9, 2012Assignee: General Electric CompanyInventors: Wei Chen, Stephen Robert Thomas, Geoffrey David Myers, Vijay Kumar Turaga
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Patent number: 8275533Abstract: A gas turbine engine is provided and includes a combustor having a first interior in which a first fuel is combustible, a turbine into which products of at least the combustion of the first fuel are receivable, a transition zone, including a second interior in which a second fuel and the products of the combustion of the first fuel are combustible, a plurality of fuel injectors which are configured to supply the second fuel to the second interior in any one of a single axial stage, multiple axial stages, a single axial circumferential stage and multiple axial circumferential stages, a compressor, by which air is supplied to the first and second interiors for the combustion therein, and a control system configured to control relative amounts of the air to the first and second interiors and relative amounts of the first and second fuels supplied to the first and second interiors.Type: GrantFiled: January 6, 2012Date of Patent: September 25, 2012Assignee: General Electric CompanyInventors: Lewis Berkley Davis, Jr., Krishna Kumar Venkataraman, Willy Steve Ziminsky, Geoffrey David Myers
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Publication number: 20120198857Abstract: A condition measurement apparatus is provided and includes a gas turbine engine combustor having an end cover, a liner defining a liner interior and a fuel nozzle communicative with the liner interior, the end cover being formed to separate a cold side thereof, which is a relatively low temperature environment, from a hot side thereof, which is a relatively high temperature environment in which the liner and the fuel nozzle are disposed, the combustor being formed to define a fuel flow path extending through piping disposed at the cold side of the end cover by which fuel is deliverable to the fuel nozzle, and a condition sensing device operably mounted on the piping.Type: ApplicationFiled: February 8, 2011Publication date: August 9, 2012Applicant: GENERAL ELECTRIC COMPANYInventors: KWANWOO KIM, GEOFFREY DAVID MYERS, VENKATESWARLU NARRA, SHIVA KUMAR SRINIVASAN
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Publication number: 20120125004Abstract: A combustor premixer is provided and includes a burner tube having a bell mouth-shaped opening, a plurality of tubular bodies telescopically disposed within the burner tube to deliver combustible materials to a premixing passage defined between the burner tube and an outermost one of the plurality of tubular bodies and a plurality of swirler vanes arrayed circumferentially in the opening, each one of the plurality of swirler vanes including a body extending along a radial dimension from the burner tube to the outermost tubular body and a leading edge protruding upstream from the opening.Type: ApplicationFiled: November 19, 2010Publication date: May 24, 2012Applicant: GENERAL ELECTRIC COMPANYInventors: Nishant Govindbhai Parsania, Geoffrey David Myers, Ajay Pratap Singh
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Publication number: 20120117976Abstract: A nozzle includes a center body that defines an axial centerline. A shroud circumferentially surrounds at least a portion of the center body to define an annular passage between the center body and the shroud. A plenum is inside the center body and substantially parallel to the axial centerline, and an igniter is inside the center body and generally adjacent to the plenum. A method for igniting a combustor includes flowing a fuel through a center body axially aligned in a nozzle and flowing a working fluid through an annular passage, wherein the annular passage is substantially parallel to and radially outward of the center body. The method further includes projecting at least one of a beam, spark, or flame from an igniter located inside the center body.Type: ApplicationFiled: November 11, 2010Publication date: May 17, 2012Applicant: GENERAL ELECTRIC COMPANYInventors: Anthony Wayne Krull, Geoffrey David Myers, James Harold Westmoreland, III
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Publication number: 20120110974Abstract: A gas turbine engine is provided and includes a combustor having a first interior in which a first fuel is combustible, a turbine into which products of at least the combustion of the first fuel are receivable, a transition zone, including a second interior in which a second fuel and the products of the combustion of the first fuel are combustible, a plurality of fuel injectors which are configured to supply the second fuel to the second interior in any one of a single axial stage, multiple axial stages, a single axial circumferential stage and multiple axial circumferential stages, a compressor, by which air is supplied to the first and second interiors for the combustion therein, and a control system configured to control relative amounts of the air to the first and second interiors and relative amounts of the first and second fuels supplied to the first and second interiors.Type: ApplicationFiled: January 6, 2012Publication date: May 10, 2012Applicant: GENERAL ELECTRIC COMPANYInventors: Lewis Berkley Davis, JR., Krishna Kumar Venkataraman, Willy Steve Ziminsky, Geoffrey David Myers
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Publication number: 20120102957Abstract: A premixing nozzle of a combustor is provided and includes a gas premixer module, a centerbody, which is breech-loadable into the gas premixer module and a deformable, compliant interface between the gas premixer module and the centerbody.Type: ApplicationFiled: November 3, 2010Publication date: May 3, 2012Applicant: GENERAL ELECTRIC COMPANYInventor: Geoffrey David Myers
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Publication number: 20120073302Abstract: A fuel nozzle assembly is disclosed. The fuel nozzle assembly comprises an outer burner tube and an inner burner tube defining a pre-mixing annulus therebetween. The fuel nozzle assembly further comprises a swirler assembly, the swirler assembly comprising a plurality of swirler vanes disposed in an annular array about the inner burner tube and configured to interact with primary air upstream of the pre-mixing annulus. The fuel nozzle assembly further comprises an air injection feature configured to flow secondary air into the pre-mixing annulus downstream of the swirler assembly such that the secondary air flows in a generally linear path longitudinally with respect to the pre-mixing annulus and adjacent at least one of the outer burner tube and the inner burner tube.Type: ApplicationFiled: September 27, 2010Publication date: March 29, 2012Applicant: GENERAL ELECTRIC COMPANYInventors: Geoffrey David Myers, Nishant Govindbhai Parsania, Gregory Allen Boardman
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Patent number: 8122725Abstract: Methods and systems for delivering fuel in a gas turbine engine are provided. The system includes a plurality of can annular combustors that includes at least a first set of combustors of the plurality of can annular combustors and at least a second set of combustors of the plurality of can annular combustors wherein each set of combustors is supplied by a separately controllable respective fuel delivery system. The method includes supplying fuel at a first fuel schedule to the first set of combustors and supplying fuel at a second fuel schedule to the second set of combustors during a first mode of operation wherein the second fuel schedule is different than the first fuel schedule, and supplying fuel at the second fuel schedule to the first and second sets of combustors during a second mode of operation.Type: GrantFiled: November 1, 2007Date of Patent: February 28, 2012Assignee: General Electric CompanyInventors: Geoffrey David Myers, David August Snider, Eric Motter, Daniel R. Tegel, James Harper, Stephen R. Watts, Joseph Citeno