Patents by Inventor Donald Lee Gardner
Donald Lee Gardner 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: 20230258407Abstract: A heat exchanger for a gas turbine engine includes a heat exchanger body having a first surface and a second surface oriented at least partially at an oblique angle relative to the first surface. The heat exchanger body defines a plenum extending between the first and second surfaces. Furthermore, the heat exchanger body defines a fluid passage extending through the second surface such that the fluid passage is in fluid communication with the plenum. The fluid passage, in turn, includes first and second portions. The first portion intersects the plenum at an intersection and defines a line of projection extending normal to the second surface. The second portion defines a line of projection extending normal to the first surface. The fluid passage further includes a curved portion extending from the first portion to the second portion.Type: ApplicationFiled: April 19, 2023Publication date: August 17, 2023Applicant: General Electric CompanyInventors: Ramon Martinez, Raymond Floyd Martell, Donald Lee Gardner
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Patent number: 11662150Abstract: A heat exchanger for a gas turbine engine includes a heat exchanger body having a first surface and a second surface oriented at least partially at an oblique angle relative to the first surface. The heat exchanger body defines a plenum extending between the first and second surfaces. Furthermore, the heat exchanger body defines a fluid passage extending through the second surface such that the fluid passage is in fluid communication with the plenum. The fluid passage, in turn, includes first and second portions. The first portion intersects the plenum at an intersection and defines a line of projection extending normal to the second surface. The second portion defines a line of projection extending normal to the first surface. The fluid passage further includes a curved portion extending from the first portion to the second portion.Type: GrantFiled: August 13, 2020Date of Patent: May 30, 2023Assignee: General Electric CompanyInventors: Ramon Martinez, Raymond Floyd Martell, Donald Lee Gardner
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Publication number: 20220325889Abstract: Embodiments of a combustor assembly for a turbine engine are generally provided. The combustor assembly includes a first separable portion defining a dome assembly, and a second separable portion defining a deflector assembly. The first separable portion and the second separable portion are coupled together at a fitted interface.Type: ApplicationFiled: February 18, 2022Publication date: October 13, 2022Inventors: Ryan Christopher Jones, Paul Christopher Schilling, Andrew Scott Bilse, Daniel Endecott Osgood, Donald Lee Gardner
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Publication number: 20220268443Abstract: A combustor assembly for a heat engine is generally provided. The combustor assembly includes a liner wall defining a combustion chamber, and a deflector assembly. The deflector assembly includes a radially extended first wall disposed adjacent to the combustion chamber, and further an axially extended second wall disposed forward of the first wall and adjacent thereto. The second wall is coupled to the liner wall.Type: ApplicationFiled: May 12, 2022Publication date: August 25, 2022Inventors: Andrew Scott Bilse, Craig Alan Gonyou, Paul Christopher Schilling, Hojjat Nasr, Ryan Christopher Jones, Donald Lee Gardner
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Patent number: 11408356Abstract: A system and method for operating a combustion system comprising a fuel nozzle defining at least one main fuel circuit and at least one pilot fuel circuit is generally provided. The method includes determining an overall flow of fuel, the overall flow of fuel defining a sum total fuel through the main fuel circuit and the pilot fuel circuit; determining a plurality of ranges of ratios of main fuel flow through the main fuel circuit versus pilot fuel flow through the pilot circuit from the overall flow of fuel, wherein each range of ratios is based on a combustion criterion different from one another; determining a resultant range of ratios of main fuel flow versus pilot fuel flow based on a hierarchy of combustion criteria, wherein the hierarchy of combustion criteria provides a priority ranking of the combustion criterion; and flowing the overall flow of fuel to the main fuel circuit and the pilot fuel circuit based on the resultant range of ratios of main fuel flow versus pilot fuel flow.Type: GrantFiled: October 3, 2017Date of Patent: August 9, 2022Assignee: GENERAL ELECTRIC COMPANYInventors: Steven Clayton Vise, Duane Douglas Thomsen, Richard Wade Stickles, Clayton Stuart Cooper, Donald Lee Gardner, George ChiaChun Hsiao, Michael Anthony Benjamin, Shai Birmaher
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Patent number: 11339966Abstract: A combustor assembly for a heat engine is generally provided. The combustor assembly includes a liner wall defining a combustion chamber, and a deflector assembly. The deflector assembly includes a radially extended first wall disposed adjacent to the combustion chamber, and further an axially extended second wall disposed forward of the first wall and adjacent thereto. The second wall is coupled to the liner wall.Type: GrantFiled: August 21, 2018Date of Patent: May 24, 2022Assignee: GENERAL ELECTRIC COMPANYInventors: Andrew Scott Bilse, Donald Lee Gardner, Craig Alan Gonyou, Paul Christopher Schilling, Hojjat Nasr, Ryan Christopher Jones
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Patent number: 11280492Abstract: Embodiments of a combustor assembly for a turbine engine are generally provided. The combustor assembly includes a first separable portion defining a dome assembly, and a second separable portion defining a deflector assembly. The first separable portion and the second separable portion are coupled together at a fitted interface.Type: GrantFiled: August 23, 2018Date of Patent: March 22, 2022Assignee: GENERAL ELECTRIC COMPANYInventors: Ryan Christopher Jones, Donald Lee Gardner, Paul Christopher Schilling, Andrew Scott Bilse, Daniel Endecott Osgood
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Publication number: 20220049904Abstract: A heat exchanger for a gas turbine engine includes a heat exchanger body having a first surface and a second surface oriented at least partially at an oblique angle relative to the first surface. The heat exchanger body defines a plenum extending between the first and second surfaces. Furthermore, the heat exchanger body defines a fluid passage extending through the second surface such that the fluid passage is in fluid communication with the plenum. The fluid passage, in turn, includes first and second portions. The first portion intersects the plenum at an intersection and defines a line of projection extending normal to the second surface. The second portion defines a line of projection extending normal to the first surface. The fluid passage further includes a curved portion extending from the first portion to the second portion.Type: ApplicationFiled: August 13, 2020Publication date: February 17, 2022Inventors: Ramon Martinez, Raymond Floyd Martell, Donald Lee Gardner
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Publication number: 20200063583Abstract: A combustor assembly for a heat engine is generally provided. The combustor assembly includes a liner wall defining a combustion chamber, and a deflector assembly. The deflector assembly includes a radially extended first wall disposed adjacent to the combustion chamber, and further an axially extended second wall disposed forward of the first wall and adjacent thereto. The second wall is coupled to the liner wall.Type: ApplicationFiled: August 21, 2018Publication date: February 27, 2020Inventors: Andrew Scott Bilse, Donald Lee Gardner, Craig Alan Gonyou, Paul Christopher Schilling, Hojjat Nasr, Ryan Christopher Jones
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Publication number: 20200063961Abstract: Embodiments of a combustor assembly for a turbine engine are generally provided. The combustor assembly includes a first separable portion defining a dome assembly, and a second separable portion defining a deflector assembly. The first separable portion and the second separable portion are coupled together at a fitted interface.Type: ApplicationFiled: August 23, 2018Publication date: February 27, 2020Inventors: Ryan Christopher Jones, Donald Lee Gardner, Paul Christopher Schilling, Andrew Scott Bilse, Daniel Endecott Osgood
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Publication number: 20190101062Abstract: A system and method for operating a combustion system comprising a fuel nozzle defining at least one main fuel circuit and at least one pilot fuel circuit is generally provided. The method includes determining an overall flow of fuel, the overall flow of fuel defining a sum total fuel through the main fuel circuit and the pilot fuel circuit; determining a plurality of ranges of ratios of main fuel flow through the main fuel circuit versus pilot fuel flow through the pilot circuit from the overall flow of fuel, wherein each range of ratios is based on a combustion criterion different from one another; determining a resultant range of ratios of main fuel flow versus pilot fuel flow based on a hierarchy of combustion criteria, wherein the hierarchy of combustion criteria provides a priority ranking of the combustion criterion; and flowing the overall flow of fuel to the main fuel circuit and the pilot fuel circuit based on the resultant range of ratios of main fuel flow versus pilot fuel flow.Type: ApplicationFiled: October 3, 2017Publication date: April 4, 2019Inventors: Steven Clayton Vise, Duane Douglas Thomsen, Richard Wade Stickles, Clayton Stuart Cooper, Donald Lee Gardner, George ChiaChun Hsiao, Michael Anthony Benjamin, Shai Birmaher
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Patent number: 8893382Abstract: A method of assembling a combustion system for a gas turbine engine includes providing a combustion chamber frame, an inner casing structure, and an outer casing structure. The method also includes mounting the combustion chamber frame between the inner casing structure and the outer casing structure such that the combustion chamber frame is coupled to the inner casing structure and the outer casing structure.Type: GrantFiled: September 30, 2011Date of Patent: November 25, 2014Assignee: General Electric CompanyInventors: David Bruce Patterson, Donald Michael Corsmeier, Craig Douglas Young, Donald Lee Gardner, James Edward Thompson, Daniel Dale Brown, Glenn Edward Wiehe, Donald Scott Yeager, Mark Willard Marusko, Michael Joseph Zerbe
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Patent number: 8876042Abstract: An assembly includes a unitary nacelle structure and an integrated fan housing for a gas turbine engine assembly. The unitary nacelle structure includes an inlet region and a fan cowl region, and is configured to at least partially circumscribe the integrated fan housing. The integrated fan housing comprises an integral composite structure and includes a fan case sized and configured for encircling a fan blade assembly of an associated gas turbine engine, a fan hub, and a plurality of fan outlet guide vanes. The unitary nacelle structure cooperates with the integrated fan housing to transfer static and dynamic loads directly to a support structure, rather than through the engine core, to minimize backbone bending.Type: GrantFiled: June 30, 2010Date of Patent: November 4, 2014Assignee: General Electric CompanyInventors: Donald George LaChapelle, Christopher Charles Glynn, Donald Lee Gardner, Stephen Craig Mitchell, Mullahalli Venkataramaniah Srinivas, Edward Atwood Rainous, David Lance Pennekamp
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Patent number: 8662834Abstract: A method for reducing tip rub loads in a rotor blade is described having the steps of selecting a location of contact between the rotor blade and a static structure; selecting a location on the blade for incorporating a tip-cutter; selecting a cutter-profile for the tip-cutter; and incorporating the tip-cutter on the selected location on the blade such that tip-cutter is capable of removing a portion of the static structure during a tip rub such that tip rub loads are facilitated to be reduced.Type: GrantFiled: June 30, 2009Date of Patent: March 4, 2014Assignee: General Electric CompanyInventors: Nicholas Joseph Kray, David W. Crall, Daniel E. Mollmann, Donald Lee Gardner, Marcia Boyle Johnson, Howard P. Weaver, Max Robert Farson
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Patent number: 8657570Abstract: An airfoil for use in a rotor assembly is disclosed, the airfoil having a tip-cutter located on a sidewall near a tip portion, wherein the tip-cutter is capable of removing a portion of an abradable material during a tip rub. In another embodiment, an airfoil has a tip-grinder located on the tip portion, wherein the tip-grinder capable of removing a portion of an abradable material during a tip rub. In another embodiment, an airfoil has a tip-rake that facilitates reducing loading induced to said airfoil during tip rubs.Type: GrantFiled: June 30, 2009Date of Patent: February 25, 2014Assignee: General Electric CompanyInventors: Nicholas Joseph Kray, David W. Crall, Daniel E. Mollmann, Donald Lee Gardner, Marcia Boyle Johnson, Howard P. Weaver, Max Robert Farson
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Publication number: 20130081270Abstract: A method of assembling a combustion system for a gas turbine engine includes providing a combustion chamber frame, an inner casing structure, and an outer casing structure. The method also includes mounting the combustion chamber frame between the inner casing structure and the outer casing structure such that the combustion chamber frame is coupled to the inner casing structure and the outer casing structure.Type: ApplicationFiled: September 30, 2011Publication date: April 4, 2013Inventors: David Bruce Patterson, Donald Michael Corsmeier, Craig Douglas Young, Donald Lee Gardner, James Edward Thompson, Daniel Dale Brown, Glenn Edward Wiehe
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Patent number: 8126628Abstract: A method and system adjusts blade tip clearance between rotating aircraft gas turbine engine blade tips and a surrounding shroud in anticipation of and before an engine command that changes an engine rotational speed. The method may include determining when to begin adjusting the tip clearance by expanding or contracting the shroud before the engine command and may be based on monitored aircraft and/or aircraft crew data indicative of the engine. The aircraft and/or aircraft crew data may include communications between aircraft crew and air traffic control authorities or air traffic control surrogates. Determining when to begin adjusting the tip clearance may include using learning algorithms which may use the aircraft gas turbine engine's operating experience and/or operating experience of other jet engines on an aircraft containing the aircraft gas turbine engine and/or on other aircraft.Type: GrantFiled: August 3, 2007Date of Patent: February 28, 2012Assignee: General Electric CompanyInventors: John Erik Hershey, Brock Estel Osborn, Donald Lee Gardner, Rafael Jose Ruiz, William Lee Herron
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Publication number: 20110146230Abstract: An assembly includes a unitary nacelle structure and an integrated fan housing for a gas turbine engine assembly. The unitary nacelle structure includes an inlet region and a fan cowl region, and is configured to at least partially circumscribe the integrated fan housing. The integrated fan housing comprises an integral composite structure and includes a fan case sized and configured for encircling a fan blade assembly of an associated gas turbine engine, a fan hub, and a plurality of fan outlet guide vanes. The unitary nacelle structure cooperates with the integrated fan housing to transfer static and dynamic loads directly to a support structure, rather than through the engine core, to minimize backbone bending.Type: ApplicationFiled: June 30, 2010Publication date: June 23, 2011Inventors: Donald George LaChapelle, Christopher Charles Glynn, Donald Lee Gardner, Stephen Craig Mitchell, Mullahalli Venkataramaniah Srinivas, Edward Atwood Rainous, David Lance Pennekamp
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Publication number: 20100329863Abstract: A method for reducing tip rub loads in a rotor blade is described having the steps of selecting a location of contact between the rotor blade and a static structure; selecting a location on the blade for incorporating a tip-cutter; selecting a cutter-profile for the tip-cutter; and incorporating the tip-cutter on the selected location on the blade such that tip-cutter is capable of removing a portion of the static structure during a tip rub such that tip rub loads are facilitated to be reduced.Type: ApplicationFiled: June 30, 2009Publication date: December 30, 2010Inventors: Nicholas Joseph Kray, David W. Crall, Daniel E. Mollmann, Donald Lee Gardner, Marcia Boyle Johnson, Howard P. Weaver, Max Robert Farson
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Publication number: 20100329875Abstract: An airfoil for use in a rotor assembly is disclosed, the airfoil having a tip-cutter located on a sidewall near a tip portion, wherein the tip-cutter is capable of removing a portion of an abradable material during a tip rub. In another embodiment, an airfoil has a tip-grinder located on the tip portion, wherein the tip-grinder capable of removing a portion of an abradable material during a tip rub. In another embodiment, an airfoil has a tip-rake that facilitates reducing loading induced to said airfoil during tip rubs.Type: ApplicationFiled: June 30, 2009Publication date: December 30, 2010Inventors: Nicholas Joseph Kray, David W. Crall, Daniel E. Mollmann, Donald Lee Gardner, Marcia Boyle Johnson, Haward P. Weaver, Max Robert Farson