Patents by Inventor Joel Meador Hall
Joel Meador Hall 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: 11971170Abstract: A system includes a gas turbine having a turbine shaft disposed along a rotational axis, a turbine casing disposed circumferentially about the turbine shaft, a combustion gas path disposed between the turbine shaft and the turbine casing, and a turbine stage disposed in the combustion gas path. The turbine stage includes a plurality of turbine vanes disposed upstream from a plurality of turbine blades. The gas turbine includes an isothermal expansion system coupled to the turbine stage, wherein the isothermal expansion system includes a plurality of flame stabilizers configured to vary axial positions of combustion within a turbine stage expansion of the turbine stage to reduce temperature variations over the turbine stage expansion. The flame stabilizers are disposed in different axial positions over an axial length between leading and trailing edges of the turbine blades, wherein at least one flame stabilizer is coupled to each of the turbine blades.Type: GrantFiled: December 30, 2022Date of Patent: April 30, 2024Assignee: GE INFRASTRUCTURE TECHNOLOGY LLCInventors: Joel Meador Hall, John Farrior Woodall
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Patent number: 11891949Abstract: A system includes a gas turbine having a turbine stage disposed in a combustion gas path, wherein the turbine stage includes turbine vanes disposed upstream from turbine blades. The system includes an isothermal expansion system coupled to the turbine stage. The isothermal expansion system includes multi-fluid injectors configured to vary axial positions of combustion within a turbine stage expansion of the turbine stage to reduce temperature variations over the turbine stage expansion, wherein at least one of the multi-fluid injectors is coupled to each of the turbine vanes. Each of the multi-fluid injectors includes a fuel port configured to inject a fuel, an oxidant port configured to inject an oxidant, and a barrier fluid port configured to inject a barrier fluid between the fuel and the oxidant, wherein the barrier fluid is configured to delay mixing between the fuel and the oxidant.Type: GrantFiled: December 30, 2022Date of Patent: February 6, 2024Assignee: GE Infrastructure Technology LLCInventors: John Farrior Woodall, Joel Meador Hall
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Patent number: 10113747Abstract: The present disclosure generally relates to a system with a gas turbine engine. The gas turbine engine includes a first combustor having a first fuel injector and a second combustor having a second fuel injector. The gas turbine engine further includes a first fuel conduit extending from a first orifice to a first fuel outlet of the first fuel injector. The first fuel conduit has a first acoustic volume between the first orifice and the first fuel outlet. The gas turbine engine further includes a second fuel conduit extending from a second orifice to a second fuel outlet of the second fuel injector. The second fuel conduit has a second acoustic volume between the second orifice and the second fuel outlet, and the first acoustic volume and the second acoustic volume are different from one another.Type: GrantFiled: April 15, 2015Date of Patent: October 30, 2018Assignee: General Electric CompanyInventors: Sarah Lori Crothers, Hasan Karim, Joel Meador Hall
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Publication number: 20160305337Abstract: The present disclosure generally relates to a system with a gas turbine engine. The gas turbine engine includes a first combustor having a first fuel injector and a second combustor having a second fuel injector. The gas turbine engine further includes a first fuel conduit extending from a first orifice to a first fuel outlet of the first fuel injector. The first fuel conduit has a first acoustic volume between the first orifice and the first fuel outlet. The gas turbine engine further includes a second fuel conduit extending from a second orifice to a second fuel outlet of the second fuel injector. The second fuel conduit has a second acoustic volume between the second orifice and the second fuel outlet, and the first acoustic volume and the second acoustic volume are different from one another.Type: ApplicationFiled: April 15, 2015Publication date: October 20, 2016Inventors: Sarah Lori Crothers, Hasan Karim, Joel Meador Hall
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Patent number: 8359870Abstract: A flame-holding control method in a gas turbine having a combustor can and a fuel nozzle disposed in the combustor can. The method can include performing a first scheduled injection of a diluent stream into the nozzle, checking to see if a time period has exceeded a time threshold and in response to the time period being greater than that the time threshold, performing a second scheduled injection of the diluent stream into the nozzle.Type: GrantFiled: May 12, 2009Date of Patent: January 29, 2013Assignee: General Electric CompanyInventors: Robert Thomas Thatcher, Joel Meador Hall, Andrew Mitchell Rodwell
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Publication number: 20120322013Abstract: A combustor housing includes an inlet cover plate having a central inlet configured to receive a supply of one of a high BTU content fuel or air and at least one radially-spaced, peripheral fuel inlet configured to receive a supply of a low BTU content fuel and an outlet cover plate having at least one radially-spaced, peripheral fuel outlet. The combustor housing also includes a peripheral sidewall joining the inlet cover and the outlet cover and enclosing a plenum, the at least one peripheral fuel inlet opening through the inlet cover plate into the plenum and the at least one fuel outlet opening from the plenum through the outlet cover plate. The central inlet opens into at least one conduit which extends away from the central inlet and opens into at least one high BTU content fuel conduit or air supply conduit that is axially aligned with the at least one fuel outlet.Type: ApplicationFiled: June 15, 2012Publication date: December 20, 2012Applicant: GENERAL ELECTRIC COMPANYInventors: Joel Meador Hall, Sergey Adolfovich Oskin, Scott Robert Simmons
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Patent number: 8220272Abstract: A combustor housing includes an inlet cover plate having a central inlet configured to receive a supply of one of a high BTU content fuel or air and at least one radially-spaced, peripheral fuel inlet configured to receive a supply of a low BTU content fuel. It also includes an outlet cover plate having at least one radially-spaced, peripheral fuel outlet. The combustor housing also includes a peripheral sidewall joining the inlet cover and the outlet cover and enclosing a plenum, the at least one peripheral fuel inlet opening through the inlet cover plate into the plenum and the at least one fuel outlet opening from the plenum through the outlet cover plate. The central inlet opens into at least one conduit which extends away from the central inlet and opens into at least one high BTU content fuel conduit or air supply conduit that is axially aligned with the at least one fuel outlet.Type: GrantFiled: December 4, 2008Date of Patent: July 17, 2012Assignee: General Electric CompanyInventors: Joel Meador Hall, Sergey Adolfovich Oskin, Scott Robert Simmons
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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: 20100287937Abstract: A flame-holding control method in a gas turbine having a combustor can and a fuel nozzle disposed in the combustor can. The method can include performing a first scheduled injection of a diluent stream into the nozzle, checking to see if a time period has exceeded a time threshold and in response to the time period being greater than that the time threshold, performing a second scheduled injection of the diluent stream into the nozzle.Type: ApplicationFiled: May 12, 2009Publication date: November 18, 2010Applicant: GENERAL ELECTRIC COMPANYInventors: Robert Thomas Thatcher, Joel Meador Hall, Andrew Mitchell Rodwell
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Publication number: 20100139238Abstract: A combustor housing includes an inlet cover plate having a central inlet configured to receive a supply of one of a high BTU content fuel or air and at least one radially-spaced, peripheral fuel inlet configured to receive a supply of a low BTU content fuel. It also includes an outlet cover plate having at least one radially-spaced, peripheral fuel outlet. The combustor housing also includes a peripheral sidewall joining the inlet cover and the outlet cover and enclosing a plenum, the at least one peripheral fuel inlet opening through the inlet cover plate into the plenum and the at least one fuel outlet opening from the plenum through the outlet cover plate. The central inlet opens into at least one conduit which extends away from the central inlet and opens into at least one high BTU content fuel conduit or air supply conduit that is axially aligned with the at least one fuel outlet.Type: ApplicationFiled: December 4, 2008Publication date: June 10, 2010Applicant: General Electric CompanyInventors: Joel Meador Hall, Sergey Adolfovich Oskin, Scott Robert Simmons
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Publication number: 20090049838Abstract: 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: ApplicationFiled: August 21, 2007Publication date: February 26, 2009Applicant: GENERAL ELECTRIC COMPANYInventors: Sergey Adolfovich Oskin, Mark Allan Hadley, Joel Meador Hall, Sergey Konstantinovich Yerokhin, Sergey Anatolievich Meshkov