Patents by Inventor Mark Allan Hadley
Mark Allan Hadley 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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Publication number: 20130091846Abstract: A fuel injector is provided, including a fuel injector body, a plurality of fuel vanes, and a plurality of fuel pegs. The injector body includes a manifold and an inlet. The manifold is configured for receiving fuel, and the inlet is configured for receiving air. The fuel vanes are located within the injector body and are positioned in a direction that is generally parallel with a longitudinal axis of the injector body to orient the air flowing from the inlet. The plurality of fuel pegs are fluidly connected to the manifold and are arranged within the plurality of fuel vanes. The plurality of fuel pegs are each spaced at a distance that is about equal between each of the plurality of fuel pegs.Type: ApplicationFiled: October 17, 2011Publication date: April 18, 2013Applicant: GENERAL ELECTRIC COMPANYInventors: Mark Allan Hadley, David Kenton Felling
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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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Publication number: 20120204573Abstract: A system for producing a hydrogen enriched fuel includes a gas turbine comprising a compressor, a combustor, and a turbine. A fuel reformer is connected between the compressor and the combustor. The fuel reformer comprises an inlet connected to the compressor and an outlet connected to the combustor, and the fuel reformer produces the hydrogen enriched fuel. A method for producing a hydrogen enriched fuel includes compressing a working fluid with a compressor to produce a compressed working fluid and diverting a first portion of the compressed working fluid to a fuel reformer.Type: ApplicationFiled: February 14, 2011Publication date: August 16, 2012Applicant: GENERAL ELECTRIC COMPANYInventors: Samuel David Draper, Raub Warfield Smith, Stanley Frank Simpson, Mark Allan Hadley, Amit Surendra Toprani
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Publication number: 20120180489Abstract: A fuel injector is provided and includes a first tube connectable with a vessel and second and third tubes to deliver fuel to an interior of the vessel, the second and third tubes being supported within the first tube such that the second and third tubes are offset in first and second opposing directions from a first plane of the first tube, respectively, and in a third direction from a second plane of the first tube, the first tube defining an annulus about the second and third tubes through which gas is deliverable to the vessel interior.Type: ApplicationFiled: January 14, 2011Publication date: July 19, 2012Applicant: GENERAL ELECTRIC COMPANYInventors: Mark Allan Hadley, Jayaprakash Natarajan
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Publication number: 20120180491Abstract: A fuel injector is provided and includes a first tube, having first and second opposing ends, which is supplied with fuel, and one or more second tubes disposed within the first tube, each of the one or more second tubes being supplied with air and having sidewalls defining injection holes through which the fuel enters the one or more second tubes to mix with the air, and an outlet end of the sidewalls corresponding to the second end of the first tube.Type: ApplicationFiled: January 14, 2011Publication date: July 19, 2012Applicant: GENERAL ELECTRIC COMPANYInventors: Mark Allan Hadley, Rajani Kumar Akula, Jayaprakash Natarajan, Chetan Babu Velkur
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Publication number: 20110296844Abstract: A gas turbine engine system, comprising a compressor, a combustor, and a turbine; a fuel system comprising one or more fuel circuits configured to provide fuel to the combustor; a non-catalytic fuel reformer in fluid communication with the one or more fuel circuits, wherein the non-catalytic fuel reformer is configured to receive an oxidant and a fraction of the fuel in the one or more fuel circuits in a fuel-rich ratio and reform the fraction of the fuel to produce a reformate; and a control system configured to regulate at least one of fuel flow and oxidizer flow to the non-catalytic fuel reformer to control a Modified Wobbe Index of the fuel entering the combustor.Type: ApplicationFiled: June 2, 2010Publication date: December 8, 2011Applicant: GENERAL ELECTRIC COMPANYInventors: Stanley Kevin Widener, Mark Allan Hadley
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Patent number: 8037689Abstract: A fuel nozzle for a turbine is disclosed. The fuel nozzle includes a housing, a plurality of fuel passages disposed within the housing, and a plurality of air passages disposed within the housing. A total flow area of the plurality of fuel passages is substantially equal to a total flow area of the plurality of air passages.Type: GrantFiled: August 21, 2007Date of Patent: October 18, 2011Assignee: General Electric CompanyInventors: Sergey Adolfovich Oskin, Mark Allan Hadley, Joel Meador Hall, Sergey Konstantinovich Yerokhin, Sergey Anatolievich Meshkov
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Publication number: 20110023494Abstract: A gas turbine includes a compressor and at least one combustor downstream from the compressor. The combustor includes a burner having an inner shroud extending axially along at least a portion of the burner, an outer shroud radially separated from the inner shroud and extending axially along at least a portion of the burner, and a plurality of stator vanes extending radially between the inner shroud and the outer shroud. The stator vanes have an inner end proximate the inner shroud and an outer end proximate the outer shroud. The burner further includes a vortex tip at one of either the inner end or the outer end of the stator vanes. The vortex tip provides a gap between the inner end and the inner shroud or the outer end and the outer shroud, and the vortex tip includes a plurality of fuel ports. The gas turbine further includes a turbine downstream from the combustor.Type: ApplicationFiled: July 28, 2009Publication date: February 3, 2011Applicant: GENERAL ELECTRIC COMPANYInventors: JESSE BLAIR BUTLER, DAVID LEACH, KEVIN WESTON MCMAHAN, MARK ALLAN HADLEY, GEOFFREY DAVID MYERS
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Publication number: 20100300107Abstract: A gas turbine includes a combustor liner having at least one hole formed therein. The gas turbine also includes a flow sleeve that at least partially surrounds the liner thereby forming a plenum between the flow sleeve and the liner, the plenum having an airflow therethrough, a portion of the airflow passing through the at least one hole in the liner and into the liner thereby reducing the mass of the airflow in the plenum. The flow sleeve has an axial profile that is reduced in cross section dimension at a predetermined axial location of the flow sleeve, thereby reducing a width of the plenum at the predetermined axial location. The reduction at the cross section dimension in the flow sleeve increases a velocity of the airflow in the plenum at the predetermined axial location, the increased velocity airflow increasing transfer of heat away from the liner.Type: ApplicationFiled: May 29, 2009Publication date: December 2, 2010Applicant: GENERAL ELECTRIC COMPANYInventors: Jesse Ellis Barton, Jonathan Dwight Berry, James Thomas Brown, Mark Allan Hadley, Patrick Benedict Melton, Svetlana Yakubova
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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: 20100281871Abstract: A fuel nozzle tip for use with a combustor and a method of assembling the fuel nozzle tip are provided. The fuel nozzle tip includes a fuel tube and an air collar coupled to the fuel tube. The fuel tube includes a first plurality of circumferentially-spaced fuel openings and a second plurality of circumferentially-spaced fuel openings. The fuel tube is configured to channel fuel into a mixing zone defined within the combustor. The air collar includes a plurality of circumferentially-spaced air openings configured to discharge air into the mixing zone.Type: ApplicationFiled: May 6, 2009Publication date: November 11, 2010Inventors: Mark Allan Hadley, John Lipinski, Jesse Ellis Barton
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Publication number: 20100281872Abstract: A fuel nozzle tip for use with a combustor and a method of assembling the fuel nozzle tip are provided. The fuel nozzle tip includes a fuel tube and an air collar coupled to the fuel tube. The fuel tube includes a first plurality of circumferentially-spaced fuel openings and a second plurality of circumferentially-spaced fuel openings. The fuel tube is configured to channel fuel into a mixing zone defined within the combustor. The air collar includes a plurality of circumferentially-spaced air openings configured to discharge air into the mixing zone. At least one of the plurality of air openings is oriented to facilitate generating a swirl number of greater than 0.6 within the mixing zone.Type: ApplicationFiled: May 6, 2009Publication date: November 11, 2010Inventors: Mark Allan Hadley, John Lipinski, Jesse Ellis Barton
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Publication number: 20100281869Abstract: A fuel nozzle tip for use with a combustor and a method of assembling the fuel nozzle tip are provided. The fuel nozzle tip includes a fuel tube and an air collar coupled to the fuel tube. The fuel tube includes a first plurality of circumferentially-spaced fuel openings and a second plurality of circumferentially-spaced fuel openings. The fuel tube is configured to channel fuel into a mixing zone defined within the combustor. The air collar includes a plurality of circumferentially-spaced air openings configured to discharge air into the mixing zone.Type: ApplicationFiled: May 6, 2009Publication date: November 11, 2010Inventors: Mark Allan Hadley, John Lipinski, Jesse Ellis Barton
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Publication number: 20100089022Abstract: Disclosed is a combustor including a baffle plate having at least one through baffle hole and at least one fuel nozzle extending through the at least one baffle hole. A shroud is disposed between the baffle plate and the at least one fuel nozzle and is affixed to the baffle plate. A plurality of openings in the shroud are configured to meter a flow of diluent between the baffle hole and the at least one fuel nozzle. Further disclosed is a method for providing diluent to a combustor including providing a plurality of openings disposed in a shroud affixed to a baffle plate and disposed between the baffle plate and at least one fuel nozzle extending through a through hole in the baffle plate. The diluent is flowed through the plurality of openings toward at least one airflow opening in the at least one fuel nozzle.Type: ApplicationFiled: October 14, 2008Publication date: April 15, 2010Applicant: GENERAL ELECTRIC COMPANYInventors: Jesse Ellis Barton, Jonathan Dwight Berry, Mark Allan Hadley
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Publication number: 20100092896Abstract: Disclosed is a combustor including a baffle plate having at least one through baffle hole and at least one fuel nozzle extending through the at least one baffle hole. At least one shroud is secured to the baffle plate and includes at least one piston ring disposed at the shroud. The at least one piston ring is configured to meter a flow of diluent between the at least one shroud and the at least one fuel nozzle. Further disclosed is a method for providing diluent to a combustor including providing a piston ring gap defined by at least one piston ring disposed at a baffle plate and a fuel nozzle extending through a through hole in the baffle plate. The diluent is flowed through the piston ring gap toward at least one airflow hole in the fuel nozzle.Type: ApplicationFiled: October 14, 2008Publication date: April 15, 2010Applicant: GENERAL ELECTRIC COMPANYInventors: Jesse Ellis Barton, Jonathan Dwight Berry, Mark Allan Hadley, Glenn David Nelson, Robert Joseph Rohrssen, John Drake Vanselow
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Publication number: 20100089020Abstract: Disclosed is a combustor including a baffle plate having at least one through baffle hole and at least one fuel nozzle extending through the at least one baffle hole. A circumferentially adjustable collar is located at the at least one baffle hole between the baffle plate and the at least one fuel nozzle. A plurality of openings at the collar are configured to meter a flow of diluent between the baffle hole and the at least one fuel nozzle. Further disclosed is a method for providing diluent to a combustor including providing a plurality of openings disposed at a circumferentially adjustable collar between a baffle plate and at least one fuel nozzle extending through a through hole in the baffle plate. The diluent is flowed through the plurality of openings toward at least one airflow hole in the at least one fuel nozzle.Type: ApplicationFiled: October 14, 2008Publication date: April 15, 2010Applicant: GENERAL ELECTRIC COMPANYInventors: Jesse Ellis Barton, Jonathan Dwight Berry, Mark Allan Hadley, John Drake Vanselow
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Publication number: 20100089021Abstract: Disclosed is a combustor including a baffle plate having at least one through baffle hole and at least one fuel nozzle extending through the at least one baffle hole. A plurality of injection holes extend through the at least one fuel nozzle and are configured to meter a flow of diluent into the combustor. Further disclosed is a method for providing diluent to a combustor including providing a plurality of openings located at at least one fuel nozzle extending through a through hole in a baffle plate. The diluent is flowed through the plurality of openings toward at least one airflow opening in the at least one fuel nozzle.Type: ApplicationFiled: October 14, 2008Publication date: April 15, 2010Applicant: General Electric CompanyInventors: Jesse Ellis Barton, Jonathan Dwight Berry, Mark Allan Hadley, Patrick Benedict Melton
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Patent number: 7624578Abstract: A method for generating combustion products within a gas turbine engine includes directing an internal air/fuel mixture towards a stagnation point in close proximity to an inner surface of a porous wall defining a combustion chamber. The internal air/fuel mixture is ignited to generate combustion products including a pilot flame. A quantity of air is externally mixed with a quantity of fuel to produce an external air/fuel mixture. The external air/fuel mixture is directed through the porous wall and into the combustion chamber such that the external air/fuel mixture is ignited by the pilot flame. A direction of flow of the combustion products is reversed at the stagnation point.Type: GrantFiled: September 30, 2005Date of Patent: December 1, 2009Assignee: General Electric CompanyInventor: Mark Allan Hadley
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Publication number: 20090229270Abstract: A method for controlling a combustion dynamics level within a combustion device includes defining a high dynamics operating state at a first fuel split ratio. The first fuel split ratio is a ratio of an amount of fuel supplied to the combustion device through a first fuel line to a total amount of fuel supplied to the combustion device. A low dynamics operating state is defined at a second fuel split ratio different from the first fuel split ratio. The second fuel split ratio is a second ratio of an amount of fuel supplied to the combustion device through the first fuel line to a total amount of fuel supplied to the combustion device. The combustion dynamics level within the combustion device is controlled by periodically switching between the first fuel split ratio and the second fuel split ratio.Type: ApplicationFiled: May 27, 2009Publication date: September 17, 2009Inventor: Mark Allan Hadley
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Publication number: 20090193809Abstract: A method of assembling a combustion system includes providing a gas turbine engine that includes a gas turbine section coupled downstream from a combustion chamber and coupling a source of oxygen to the gas turbine engine such that a stream of oxygen discharged from the source facilitates displacing nitrogen in the working fluid of the gas turbine engine and facilitates decreasing emissions generated within the gas turbine engine.Type: ApplicationFiled: February 4, 2008Publication date: August 6, 2009Inventors: Mark Stewart Schroder, Mark Allan Hadley, Richard Anthony DePuy, Todd Stanley Nemec