Patents by Inventor Randall E. Yount
Randall E. Yount 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: 10920983Abstract: An improved system, apparatus and method may comprise an inner liner and an outer liner extending circumferentially around an engine centerline axis thereby forming a combustion chamber therebetween. The system, apparatus, and method may include a front end extending between the inner and outer liners and having a plurality of fuel nozzle ports configured to each receive a fuel nozzle. First and second outer plunged inlet holes may be formed in the outer liner and extending in a first radial direction toward the engine centerline axis and into at least a portion of the combustion chamber. First and second inner plunged inlet holes may be formed in the inner liner and extending in a second radial direction away from the engine centerline axis and into at least a portion of the combustion chamber.Type: GrantFiled: December 10, 2015Date of Patent: February 16, 2021Assignee: Rolls-Royce CorporationInventors: Charles B. Graves, Mindi D. Moore, Afework Woubshet, Randall E. Yount
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Patent number: 10451003Abstract: A nozzle support system for a nozzle of a gas turbine includes an outer ring, an inner ring disposed within the outer ring, and a plurality of links pivotally attaching the outer ring to the inner ring. Each one of the links may have an outer end that is pivotally attached to the outer ring, and each one of the links may have an inner end that is pivotally attached to the inner ring, such that the inner ring moves along a longitudinal axis of the outer ring.Type: GrantFiled: October 27, 2015Date of Patent: October 22, 2019Assignee: Rolls-Royce North American Technologies, Inc.Inventors: David L. Sutterfield, Randall E. Yount
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Publication number: 20160169517Abstract: An improved system, apparatus and method may comprise an inner liner and an outer liner extending circumferentially around an engine centerline axis thereby forming a combustion chamber therebetween. The system, apparatus, and method may include a front end extending between the inner and outer liners and having a plurality of fuel nozzle ports configured to each receive a fuel nozzle. First and second outer plunged inlet holes may be formed in the outer liner and extending in a first radial direction toward the engine centerline axis and into at least a portion of the combustion chamber. First and second inner plunged inlet holes may be formed in the inner liner and extending in a second radial direction away from the engine centerline axis and into at least a portion of the combustion chamber.Type: ApplicationFiled: December 10, 2015Publication date: June 16, 2016Applicant: Rolls-Royce CorporationInventors: Charles B. Graves, Mindi D. Moore, Afework Woubshet, Randall E. Yount
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Publication number: 20160115904Abstract: A nozzle support system for a nozzle of a gas turbine includes an outer ring, an inner ring disposed within the outer ring, and a plurality of links pivotally attaching the outer ring to the inner ring. Each one of the links may have an outer end that is pivotally attached to the outer ring, and each one of the links may have an inner end that is pivotally attached to the inner ring, such that the inner ring moves along a longitudinal axis of the outer ring.Type: ApplicationFiled: October 27, 2015Publication date: April 28, 2016Inventors: David L. Sutterfield, Randall E. Yount
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Patent number: 9162162Abstract: A system for removing oxygen from a fuel is provided including a pressurized gas lumen and a liquid transport lumen having a fuel separation device. The liquid transport lumen is positioned partially within the pressurized gas lumen and includes a plurality of openings formed along its length within said pressurized gas lumen. A shearing feature is formed within the liquid transport lumen and is positioned downstream of the openings and upstream of the fuel separation device. The gas enters the liquid transport lumens through the openings to form a plurality of bubbles removing oxygen from the fuel. The shearing feature collapses the bubbles into larger bubbles prior to flow into the fuel separation device.Type: GrantFiled: December 17, 2013Date of Patent: October 20, 2015Assignee: Rolls-Royce North American Technologies, Inc.Inventor: Randall E. Yount
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Patent number: 9032737Abstract: A gas turbine engine having a ramburner is disclosed. The ramburner is disposed downstream of a gas turbine engine combustor and receives an engine exhaust flow from the gas turbine engine combustor. The ramburner also accepts a bypass air. Fuel is injected into the ramburner and a combustion reaction is auto-initiated based upon local gas temperatures. No mechanical flame holders need be used. A slidable valve may be used to vary the amount of bypass air into the ramburner. A movable cowl and a plug nozzle form an exit flow path of the gas turbine engine. The movable cowl can be positioned to vary a throat area and exit area of the gas turbine engine based upon the operation of the ramburner, which may be influenced by the amount of bypass air entering the ramburner.Type: GrantFiled: December 22, 2010Date of Patent: May 19, 2015Assignee: Rolls-Royce North American Technologies, Inc.Inventors: Robert A. Ress, Jr., Victor L. Oechsle, Randall E. Yount, Stephen A. Bergeron
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Patent number: 8938943Abstract: One embodiment of the present invention is a gas turbine engine with a bypass mixer. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for gas turbine engines and bypass mixers. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith.Type: GrantFiled: August 5, 2011Date of Patent: January 27, 2015Assignee: Rolls-Royce North American Technoloies, Inc.Inventors: Kaare Erickson, Randall E. Yount
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Patent number: 8863527Abstract: A combustor liner for a turbine engine is disclosed herein. The combustor liner includes an inner liner surface operable to define at least part of a combustion chamber in a turbine engine. The inner liner surface extends along a portion of a chordal arc on a first side of the chordal arc. The combustor liner also includes a bearing surface operable to support a floating dome panel. At least part of the bearing surface is spaced from the chordal arc on a second side of the chordal arc opposite the first side.Type: GrantFiled: April 30, 2009Date of Patent: October 21, 2014Assignee: Rolls-Royce CorporationInventors: Marcus Timothy Holcomb, Todd Taylor, Randall E. Yount
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Patent number: 8850823Abstract: One embodiment of the present invention is an integrated aero-engine flowpath structure. Another embodiment is a method of manufacturing integrated aero-engine flowpath structure. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for aero-engine flowpath structures. Further embodiments, forms, features, aspects, benefits, and advantages of the present application shall become apparent from the description and figures provided herewith.Type: GrantFiled: December 27, 2010Date of Patent: October 7, 2014Assignee: Rolls-Royce North American Technologies, Inc.Inventors: Robert A. Ress, Jr., Randall E. Yount, Thomas D. Destefano, Jitendra R. Patel
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Publication number: 20140260980Abstract: A system for removing oxygen from a fuel is provided including a pressurized gas lumen and a liquid transport lumen having a fuel separation device. The liquid transport lumen is positioned partially within the pressurized gas lumen and includes a plurality of openings formed along its length within said pressurized gas lumen. A shearing feature is formed within the liquid transport lumen and is positioned downstream of the openings and upstream of the fuel separation device. The gas enters the liquid transport lumens through the openings to form a plurality of bubbles removing oxygen from the fuel. The shearing feature collapses the bubbles into larger bubbles prior to flow into the fuel separation device.Type: ApplicationFiled: December 17, 2013Publication date: September 18, 2014Applicant: Rolls-Royce North American Technologies, Inc.Inventor: Randall E. Yount
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Patent number: 8800294Abstract: One embodiment of the present invention is an integrated aero-engine flowpath structure. Another embodiment is a method of manufacturing integrated aero-engine flowpath structure. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for aero-engine flowpath structures. Further embodiments, forms, features, aspects, benefits, and advantages of the present application shall become apparent from the description and figures provided herewith.Type: GrantFiled: December 27, 2010Date of Patent: August 12, 2014Assignee: Rolls-Royce North American Technologies, Inc.Inventors: Robert A. Ress, Jr., Randall E. Yount, Thomas D. Destefano, Jitendra R. Patel
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Publication number: 20120279198Abstract: One embodiment of the present invention is a gas turbine engine with a bypass mixer. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for gas turbine engines and bypass mixers. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith.Type: ApplicationFiled: August 5, 2011Publication date: November 8, 2012Inventors: Kaare Erickson, Randall E. Yount
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Publication number: 20120144836Abstract: One embodiment of the present invention is an integrated aero-engine flowpath structure. Another embodiment is a method of manufacturing integrated aero-engine flowpath structure. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for aero-engine flowpath structures. Further embodiments, forms, features, aspects, benefits, and advantages of the present application shall become apparent from the description and figures provided herewith.Type: ApplicationFiled: December 27, 2010Publication date: June 14, 2012Inventors: Robert A. Ress, JR., Randall E. Yount, Thomas D. Destefano, Jitendra R. Patel
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Publication number: 20120067053Abstract: A gas turbine engine having a ramburner is disclosed. The ramburner is disposed downstream of a gas turbine engine combustor and receives an engine exhaust flow from the gas turbine engine combustor. The ramburner also accepts a bypass air. Fuel is injected into the ramburner and a combustion reaction is auto-initiated based upon local gas temperatures. No mechanical flame holders need be used. A slidable valve may be used to vary the amount of bypass air into the ramburner. A movable cowl and a plug nozzle form an exit flow path of the gas turbine engine. The movable cowl can be positioned to vary a throat area and exit area of the gas turbine engine based upon the operation of the ramburner, which may be influenced by the amount of bypass air entering the ramburner.Type: ApplicationFiled: December 22, 2010Publication date: March 22, 2012Inventors: Robert A. Ress, JR., Victor L. Oechsle, Randall E. Yount, Stephen A. Bergeron
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Publication number: 20100275606Abstract: A combustor liner for a turbine engine is disclosed herein. The combustor liner includes an inner liner surface operable to define at least part of a combustion chamber in a turbine engine. The inner liner surface extends along a portion of a chordal arc on a first side of the chordal arc. The combustor liner also includes a bearing surface operable to support a floating dome panel. At least part of the bearing surface is spaced from the chordal arc on a second side of the chordal arc opposite the first side.Type: ApplicationFiled: April 30, 2009Publication date: November 4, 2010Inventors: MARCUS TIMOTHY HOLCOMB, Todd Taylor, Randall E. Yount