Patents by Inventor Geoffrey D. Myers
Geoffrey D. 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: 11629642Abstract: A power generation system includes a combustion system, a liquid supply system, and a vapor supply system. The combustion system is configured to generate power by combusting an alternative fuel. The liquid supply system is configured to channel a liquid alternative fuel to the combustion system. The vapor supply system is configured to channel a vapor alternative fuel to the combustion system. The combustion system is ignited by combusting the liquid alternative fuel from the liquid supply system and is operated by combusting the vapor alternative fuel from the vapor supply system.Type: GrantFiled: December 20, 2019Date of Patent: April 18, 2023Assignee: GENERAL ELECTRIC COMPANYInventors: William James Lawson, Keegan Saunders O'Donnell, Geoffrey D. Myers, Paul Burchell Glaser
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Publication number: 20210189965Abstract: A power generation system includes a combustion system, a liquid supply system, and a vapor supply system. The combustion system is configured to generate power by combusting an alternative fuel. The liquid supply system is configured to channel a liquid alternative fuel to the combustion system. The vapor supply system is configured to channel a vapor alternative fuel to the combustion system. The combustion system is ignited by combusting the liquid alternative fuel from the liquid supply system and is operated by combusting the vapor alternative fuel from the vapor supply system.Type: ApplicationFiled: December 20, 2019Publication date: June 24, 2021Inventors: William James Lawson, Keegan Saunders O'Donnell, Geoffrey D. Myers, Paul Burchell Glaser
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Patent number: 9416975Abstract: The present application and the resultant patent provide a dual fuel combustor for a gas turbine engine. The combustor may include a primary premixer positioned within a head end plenum of the combustor, and a dual fuel injection system positioned within the head end plenum and upstream of the premixer. The injection system may be configured to inject a gas fuel about an inlet end of the premixer when the combustor operates on the gas fuel. The injection system also may be configured to vaporize and inject a liquid fuel about the inlet end of the premixer when the combustor operates on the liquid fuel. The present application and the resultant patent also provide a related method of operating a dual fuel combustor.Type: GrantFiled: September 4, 2013Date of Patent: August 16, 2016Assignee: General Electric CompanyInventor: Geoffrey D. Myers
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Patent number: 9217570Abstract: An axial flow fuel nozzle for a gas turbine includes a plurality of annular passages for delivering materials for combustion. An annular air passage receives compressor discharge air, and a plurality of swirler vane slots are positioned adjacent an axial end of the annular air passage. A first next annular passage is disposed radially inward of the annular air passage and includes first openings positioned adjacent an axial end of the first annular passage and downstream of the swirler vane slots. A second next annular passage is disposed radially inward of the first annular passage and includes second openings positioned adjacent an axial end of the second annular passage and downstream of the first openings.Type: GrantFiled: January 20, 2012Date of Patent: December 22, 2015Assignee: General Electric CompanyInventors: Nishant Govindbhai Parsania, Geoffrey D. Myers, Gregory Allen Boardman
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Publication number: 20150059352Abstract: The present application and the resultant patent provide a dual fuel combustor for a gas turbine engine. The combustor may include a primary premixer positioned within a head end plenum of the combustor, and a dual fuel, injection system positioned within the head end plenum and upstream of the premixer. The injection system may be configured to inject a gas fuel about an inlet end of the premixer when the combustor operates on the gas fuel. The injection system also may be configured to vaporize and inject a liquid fuel about the inlet end of the premixer when the combustor operates on the liquid fuel. The present application and the resultant patent also provide a related method of operating a dual fuel combustor.Type: ApplicationFiled: September 4, 2013Publication date: March 5, 2015Applicant: General Electric CompanyInventor: Geoffrey D. Myers
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Patent number: 8752389Abstract: A fuel nozzle configured to channel fluid toward a combustion chamber within a gas turbine engine and a method for assembling the same are provided. The fuel nozzle includes a first hollow tube fabricated from a first material that has a first coefficient of thermal expansion and a second tube fabricated from a second material that has a second coefficient of thermal expansion that is different from the first coefficient of thermal expansion. The second tube is coupled within the first tube such that the first tube substantially circumscribes the second tube, and the second tube thermally expands approximately at a same rate as the first tube during fuel nozzle operation.Type: GrantFiled: November 5, 2008Date of Patent: June 17, 2014Assignee: General Electric CompanyInventors: Geoffrey D. Myers, Scott Simmons, Stephen R. Thomas, Donald Mark Bailey
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Patent number: 8720206Abstract: Methods and systems are provided for inducing combustion dynamics within turbine engines to remove combustion deposits within the turbine engine during operation of the turbine engine.Type: GrantFiled: May 14, 2009Date of Patent: May 13, 2014Assignee: General Electric CompanyInventors: Kevin Weston McMahan, Mark Allan Hadley, Geoffrey D. Myers, Sam D. Draper
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Patent number: 8505304Abstract: A fuel nozzle for use with a combustion chamber defined within a gas turbine engine and a method for assembling the same are provided. The fuel nozzle includes a swirler assembly and a burner tube that is coupled to a support flange in a detachable manner such that an inner surface of the burner tube circumscribes an outer surface of the swirler assembly during fuel nozzle operation.Type: GrantFiled: December 1, 2008Date of Patent: August 13, 2013Assignee: General Electric CompanyInventors: Geoffrey D. Myers, Scott Simmons, Stephen R. Thomas, Donald Mark Bailey, David Martin Johnson
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Publication number: 20130186094Abstract: An axial flow fuel nozzle for a gas turbine includes a plurality of annular passages for delivering materials for combustion. An annular air passage receives compressor discharge air, and a plurality of swirler vane slots are positioned adjacent an axial end of the annular air passage. A first next annular passage is disposed radially inward of the annular air passage and includes first openings positioned adjacent an axial end of the first annular passage and downstream of the swirler vane slots. A second next annular passage is disposed radially inward of the first annular passage and includes second openings positioned adjacent an axial end of the second annular passage and downstream of the first openings.Type: ApplicationFiled: January 20, 2012Publication date: July 25, 2013Inventors: Nishant Govindbhai Parsania, Geoffrey D. Myers, Gregory Allen Boardman
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Patent number: 8490406Abstract: A method and apparatus to determine a first heating value of a low BTU fuel, determine a target fuel quality level based on a state of a turbine system, control a second heating value of a high BTU fuel, and inject the high BTU fuel into the low BTU fuel to achieve the target fuel quality level.Type: GrantFiled: January 7, 2009Date of Patent: July 23, 2013Assignee: General Electric CompanyInventors: Constantin Dinu, Gilbert Kraemer, Geoffrey D Myers
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Patent number: 8316648Abstract: A method and apparatus to determine a first heating value of a low BTU fuel, determine a target fuel quality level based on a state of a turbine system, control a second heating value of a high BTU fuel, and inject the high BTU fuel into the low BTU fuel to achieve the target fuel quality level.Type: GrantFiled: January 7, 2009Date of Patent: November 27, 2012Assignee: General Electric CompanyInventors: Constantin Dinu, Gilbert Kraemer, Geoffrey D Myers
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Patent number: 7861528Abstract: A fuel nozzle having a dedicated circuit to cool the diffusion tip with lower part count and reduced complexity. More specifically, the proposed design uses an independent circuit to cool the tip with diffusion fuel or purge air. An impingement plate may be provided to augment the cooling effect.Type: GrantFiled: August 21, 2007Date of Patent: January 4, 2011Assignee: General Electric CompanyInventors: Geoffrey D. Myers, Scott Simmons, Stephen R. Thomas
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Publication number: 20100287943Abstract: Methods and systems are provided for inducing combustion dynamics within turbine engines to remove combustion deposits within the turbine engine during operation of the turbine engine.Type: ApplicationFiled: May 14, 2009Publication date: November 18, 2010Applicant: GENERAL ELECTRIC COMPANYInventors: Kevin Weston McMahan, Mark Allan Hadley, Geoffrey D. Myers, Sam D. Draper
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Publication number: 20100180599Abstract: A swirl vane is independently connectable to a central hub assembly of a gas turbine. The swirl vane includes a structural body and at least one fuel delivery passage including a corresponding at least one fuel port defined within the structural body. At least one connecting tab is cooperable with the structural body and is connectable to the central hub assembly.Type: ApplicationFiled: January 21, 2009Publication date: July 22, 2010Inventors: Stephen R. Thomas, Geoffrey D. Myers, Scott Simmons
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Publication number: 20100170266Abstract: In an embodiment, a method includes determining a first heating value of a low BTU fuel, determining a target fuel quality level based on a state of a turbine system, controlling a second heating value of a high BTU fuel, and injecting the high BTU fuel into the low BTU fuel to achieve the target fuel quality level.Type: ApplicationFiled: January 7, 2009Publication date: July 8, 2010Applicant: General Electric CompanyInventors: Constantin Dinu, Gilbert Kraemer, Geoffrey D. Myers
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Publication number: 20100132364Abstract: A fuel nozzle for use with a combustion chamber defined within a gas turbine engine and a method for assembling the same are provided. The fuel nozzle includes a swirler assembly and a burner tube that is coupled to a support flange in a detachable manner such that an inner surface of the burner tube circumscribes an outer surface of the swirler assembly during fuel nozzle operation.Type: ApplicationFiled: December 1, 2008Publication date: June 3, 2010Inventors: Geoffrey D. Myers, Scott Simmons, Stephen R. Thomas, Donald Mark Bailey, David Martin Johnson
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Publication number: 20100107639Abstract: A fuel nozzle configured to channel fluid toward a combustion chamber within a gas turbine engine and a method for assembling the same are provided. The fuel nozzle includes a first hollow tube fabricated from a first material that has a first coefficient of thermal expansion and a second tube fabricated from a second material that has a second coefficient of thermal expansion that is different from the first coefficient of thermal expansion. The second tube is coupled within the first tube such that the first tube substantially circumscribes the second tube, and the second tube thermally expands approximately at a same rate as the first tube during fuel nozzle operation.Type: ApplicationFiled: November 5, 2008Publication date: May 6, 2010Inventors: Geoffrey D. Myers, Scott Simmons, Stephen R. Thomas, Donald Mark Bailey
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Publication number: 20090211255Abstract: A gas turbine combustor is presented, which includes a combustion chamber that is positioned downstream of a premixing chamber. The premixing chamber includes at least one opening for ingesting air. At least one primary fuel nozzle is disposed to discharge fuel into the premixing chamber. The fuel discharged from the primary fuel nozzle mixes with the ingested air in the premixing chamber to provide a fuel air mix. A secondary fuel nozzle is disposed proximate the combustion chamber to discharge fuel at the combustion chamber. A stabilizer is disposed at the secondary fuel nozzle so as to be positioned in close proximity to a flame when fuel at the secondary fuel nozzle is ignited. The stabilizer is composed of a material having the ability to absorb heat from a heat flux generated within the combustor and maintaining a temperature sufficient to sustain ignition of the flame. A method of stabilizing a flame in a gas turbine combustor is also presented.Type: ApplicationFiled: February 21, 2008Publication date: August 27, 2009Applicant: GENERAL ELECTRIC COMPANYInventors: Derrick Walter Simons, Geoffrey D. Myers, Larry L. Thomas, Jeffrey Lebegue
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Publication number: 20090050710Abstract: A fuel nozzle having a dedicated circuit to cool the diffusion tip with lower part count and reduced complexity. More specifically, the proposed design uses an independent circuit to cool the tip with diffusion fuel or purge air. An impingement plate may be provided to augment the cooling effect.Type: ApplicationFiled: August 21, 2007Publication date: February 26, 2009Applicant: General Electric CompanyInventors: Geoffrey D. Myers, Scott Simmons, Stephen R. Thomas
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Patent number: 6286300Abstract: An annular combustor having fuel preparation chambers mounted in the dome of the combustor. The fuel preparation chamber comprises an annular wall extending axially from an inlet to an exit that defines a mixing chamber. Mounted to the inlet are an air swirler and a fuel atomizer. The air swirler provides swirled air to the mixing chamber while the atomizer provides a fuel spray. On the downstream side of the exit, the fuel preparation chamber has an inwardly extending conical wall that compresses the swirling mixture of fuel and air exiting the mixing chamber.Type: GrantFiled: January 27, 2000Date of Patent: September 11, 2001Assignee: Honeywell International Inc.Inventors: Joseph Zelina, Geoffrey D. Myers, Ram Srinivasan, Robert S. Reynolds