Patents by Inventor Justin Paul Smith
Justin Paul Smith 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: 11866182Abstract: A fuel oxygen reduction unit assembly for a fuel system is provided. The fuel oxygen reduction unit assembly includes: a fuel oxygen reduction unit located downstream from the fuel source and defining a stripping gas flowpath and a liquid fuel flowpath, the fuel oxygen reduction unit comprising a means for transferring an amount of oxygen from a liquid fuel flow through the liquid fuel flowpath to a gas flow through the stripping gas flowpath; and an oxygen conversion unit in flow communication with the stripping gas flowpath configured to extract a flow of oxygen from a gas flow through the stripping gas flowpath, the oxygen conversion unit defining an oxygen outlet configured to provide the extracted flow of oxygen to an external system.Type: GrantFiled: May 1, 2020Date of Patent: January 9, 2024Assignee: General Electric CompanyInventors: Daniel Alan Niergarth, Brandon Wayne Miller, John Michael Pyles, Ethan Patrick O'Connor, Justin Paul Smith, William James Mailander
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Patent number: 11674443Abstract: A fuel system for a vehicle having an engine is provided. The fuel system including: a fuel tank for holding a hydrogen fuel in a liquid phase; a fuel delivery assembly extending from the fuel tank to the engine for providing the hydrogen fuel from the fuel tank to the engine; a vaporizer in communication with the fuel delivery assembly for heating the hydrogen fuel in the liquid phase to a gaseous phase, to a supercritical phase, or both; and a high pressure pump in fluid communication with the fuel delivery assembly at a location downstream of the vaporizer for inducing a flow of the hydrogen fuel through the fuel delivery assembly to the engine.Type: GrantFiled: September 14, 2021Date of Patent: June 13, 2023Assignees: General Electric Company, GE Avio S.r.l.Inventors: Nathan Evan McCurdy Gibson, David Justin Brady, Justin Paul Smith, Mirko Gernone
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Patent number: 11671040Abstract: A turbomachine and method for operating a turbomachine comprising a first rotatable component and a second rotatable component each defining a rotatable speed mechanically independent of one another, and an electric machine electrically coupled to the first rotatable component and the second rotatable component such that a load level relative to the first rotatable component and the second rotatable component is adjustable is generally provided.Type: GrantFiled: April 28, 2021Date of Patent: June 6, 2023Assignee: General Electric CompanyInventors: Justin Paul Smith, Kurt David Murrow, Darek Tomasz Zatorski, Patrick Michael Marrinan
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Patent number: 11506131Abstract: A thermal management system includes a first heat source assembly including a first heat source exchanger, a first thermal fluid inlet line extending to the first heat source exchanger, and a first thermal fluid outlet line extending from the first heat source exchanger; a second heat source assembly including a second heat source exchanger, a second thermal fluid inlet line extending to the second heat source exchanger, and second a thermal fluid outlet line extending from the second heat source exchanger; a shared assembly including a thermal fluid line and a heat sink exchanger, the shared assembly defining an upstream junction in fluid communication with the first thermal fluid outlet line and second thermal fluid outlet line and a downstream junction in fluid communication with the first thermal fluid inlet line and second thermal fluid inlet line; and a controller configured to selectively fluidly connect the first heat source assembly or the second heat source assembly to the shared assembly.Type: GrantFiled: April 26, 2021Date of Patent: November 22, 2022Assignee: General Electric CompanyInventors: Justin Paul Smith, Brandon Wayne Miller, Daniel Alan Niergarth
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Patent number: 11428171Abstract: A multi-spool turbomachine having an electric machine that can be controlled to input power to one of the spools of the turbomachine is provided. In one aspect, the multi-spool turbomachine can be a hybrid electric gas turbine engine for an aircraft. The hybrid electric gas turbine engine can include a first spool, a second spool, and an electric machine operatively coupled with the first spool. In response to an increase in thrust demand, the electric motor receives electrical power from an electrical power source. In turn, the electric machine applies a torque to the first spool, causing the first spool to increase in rotational speed. In this manner, the electric machine can electrically assist the turbomachine to meet the increase in thrust demand.Type: GrantFiled: December 6, 2019Date of Patent: August 30, 2022Assignee: GENERAL ELECTRIC COMPANYInventors: Thomas William Brown, Justin Paul Smith, Dominic Barone
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Patent number: 11391211Abstract: A turbine engine includes a compressor section, a combustion section, a turbine section, and an exhaust section in serial flow order and together defining a core air flowpath; a fuel delivery system for providing a flow of fuel to the combustion section; and a waste heat recovery system. The waste heat recovery system includes a heat source exchanger in thermal communication with the turbine section, the exhaust section, or both; a heat sink exchanger in thermal communication with the fuel delivery system, the core air flowpath, or both; a thermal transfer bus including a thermal transfer fluid and extending from the heat source exchanger to the heat sink exchanger; and a pump in fluid communication with the thermal transfer bus downstream of the heat source exchanger and upstream of the heat sink exchanger for increasing a temperature and a pressure of the thermal transfer fluid in the thermal transfer bus.Type: GrantFiled: November 28, 2018Date of Patent: July 19, 2022Assignee: General Electric CompanyInventors: Justin Paul Smith, Brandon Wayne Miller, Thomas Helmut Ripplinger
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Publication number: 20220145801Abstract: A fuel system for a vehicle having an engine is provided. The fuel system including: a fuel tank for holding a hydrogen fuel in a liquid phase; a fuel delivery assembly extending from the fuel tank to the engine for providing the hydrogen fuel from the fuel tank to the engine; a vaporizer in communication with the fuel delivery assembly for heating the hydrogen fuel in the liquid phase to a gaseous phase, to a supercritical phase, or both; and a high pressure pump in fluid communication with the fuel delivery assembly at a location downstream of the vaporizer for inducing a flow of the hydrogen fuel through the fuel delivery assembly to the engine.Type: ApplicationFiled: September 14, 2021Publication date: May 12, 2022Inventors: Nathan Evan McCurdy Gibson, David Justin Brady, Justin Paul Smith, Mirko Gernone
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Patent number: 11261792Abstract: A thermal management system is provided for incorporation into at least one of a gas turbine engine or an aircraft. The thermal management system includes: a thermal transport bus having a heat exchange fluid flowing therethrough, the thermal transport bus further including: a first flow loop comprising at least one first heat source exchanger, at least one first heat sink exchanger, and a first pump to move the heat exchange fluid through the first flow loop; and a second flow loop comprising at least one second heat source exchanger, at least one second heat sink exchanger, and a second pump to move the heat exchange fluid through the second flow loop; wherein the first flow loop is isolated from the second flow loop, and wherein the first heat source exchanger and the second heat source exchanger are configured with a common heat source.Type: GrantFiled: November 15, 2019Date of Patent: March 1, 2022Assignee: General Electric CompanyInventors: Daniel Alan Niergarth, Brandon Wayne Miller, Justin Paul Smith
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Publication number: 20210339878Abstract: A fuel oxygen reduction unit assembly for a fuel system is provided. The fuel oxygen reduction unit assembly includes: a fuel oxygen reduction unit located downstream from the fuel source and defining a stripping gas flowpath and a liquid fuel flowpath, the fuel oxygen reduction unit comprising a means for transferring an amount of oxygen from a liquid fuel flow through the liquid fuel flowpath to a gas flow through the stripping gas flowpath; and an oxygen conversion unit in flow communication with the stripping gas flowpath configured to extract a flow of oxygen from a gas flow through the stripping gas flowpath, the oxygen conversion unit defining an oxygen outlet configured to provide the extracted flow of oxygen to an external system.Type: ApplicationFiled: May 1, 2020Publication date: November 4, 2021Inventors: Daniel Alan Niergarth, Brandon Wayne Miller, John Michael Pyles, Ethan Patrick O'Connor, Justin Paul Smith, William James Mailander
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Publication number: 20210246836Abstract: A thermal management system includes a first heat source assembly including a first heat source exchanger, a first thermal fluid inlet line extending to the first heat source exchanger, and a first thermal fluid outlet line extending from the first heat source exchanger; a second heat source assembly including a second heat source exchanger, a second thermal fluid inlet line extending to the second heat source exchanger, and second a thermal fluid outlet line extending from the second heat source exchanger; a shared assembly including a thermal fluid line and a heat sink exchanger, the shared assembly defining an upstream junction in fluid communication with the first thermal fluid outlet line and second thermal fluid outlet line and a downstream junction in fluid communication with the first thermal fluid inlet line and second thermal fluid inlet line; and a controller configured to selectively fluidly connect the first heat source assembly or the second heat source assembly to the shared assembly.Type: ApplicationFiled: April 26, 2021Publication date: August 12, 2021Inventors: Justin Paul Smith, Brandon Wayne Miller, Daniel Alan Niergarth
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Publication number: 20210249978Abstract: A turbomachine and method for operating a turbomachine comprising a first rotatable component and a second rotatable component each defining a rotatable speed mechanically independent of one another, and an electric machine electrically coupled to the first rotatable component and the second rotatable component such that a load level relative to the first rotatable component and the second rotatable component is adjustable is generally provided.Type: ApplicationFiled: April 28, 2021Publication date: August 12, 2021Inventors: Justin Paul Smith, Kurt David Murrow, Darek Tomasz Zatorski, Patrick Michael Marrinan
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Patent number: 11067000Abstract: A gas turbine engine includes a compressor section, a combustion section, and a turbine section arranged in serial flow order; a casing surrounding the compressor section, the combustion section, and the turbine section; a first system comprising a first system fluid line, the first system fluid line including a first system fluid therein; and a second system including a hydraulic motor, the hydraulic motor positioned within the casing and fluidly coupled to the first system fluid line such that a flow of the first system fluid through the first system fluid line drives the hydraulic motor, the second system further including a fluid pump and a second system fluid line, the hydraulic motor drivingly coupled to the fluid pump, the fluid pump operable with the second system fluid line for providing a flow of a second system fluid through the second system fluid line during operation.Type: GrantFiled: February 13, 2019Date of Patent: July 20, 2021Assignee: General Electric CompanyInventor: Justin Paul Smith
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Publication number: 20210172384Abstract: A multi-spool turbomachine having an electric machine that can be controlled to input power to one of the spools of the turbomachine is provided. In one aspect, the multi-spool turbomachine can be a hybrid electric gas turbine engine for an aircraft. The hybrid electric gas turbine engine can include a first spool, a second spool, and an electric machine operatively coupled with the first spool. In response to an increase in thrust demand, the electric motor receives electrical power from an electrical power source. In turn, the electric machine applies a torque to the first spool, causing the first spool to increase in rotational speed. In this manner, the electric machine can electrically assist the turbomachine to meet the increase in thrust demand.Type: ApplicationFiled: December 6, 2019Publication date: June 10, 2021Inventors: Thomas William Brown, Justin Paul Smith, Dominic Barone
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Patent number: 11021961Abstract: An aspect of the present disclosure is directed to a rotor assembly for a turbine engine. The rotor assembly includes an airfoil assembly and a hub to which the airfoil assembly is attached. A wall assembly defines a first cavity and a second cavity between the airfoil assembly and the hub. The first cavity and the second cavity are at least partially fluidly separated by the wall assembly. The first cavity is in fluid communication with a flow of first cooling fluid and the second cavity is in fluid communication with a flow of second cooling fluid different from the first cooling fluid.Type: GrantFiled: December 5, 2018Date of Patent: June 1, 2021Assignee: General Electric CompanyInventors: Jeffrey Douglas Rambo, Kirk Douglas Gallier, Brandon Wayne Miller, Craig Alan Gonyou, Kevin Robert Feldmann, Justin Paul Smith
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Patent number: 11015534Abstract: A thermal management system includes a first heat source assembly including a first heat source exchanger, a first thermal fluid inlet line extending to the first heat source exchanger, and a first thermal fluid outlet line extending from the first heat source exchanger; a second heat source assembly including a second heat source exchanger, a second thermal fluid inlet line extending to the second heat source exchanger, and second a thermal fluid outlet line extending from the second heat source exchanger; a shared assembly including a thermal fluid line and a heat sink exchanger, the shared assembly defining an upstream junction in fluid communication with the first thermal fluid outlet line and second thermal fluid outlet line and a downstream junction in fluid communication with the first thermal fluid inlet line and second thermal fluid inlet line; and a controller configured to selectively fluidly connect the first heat source assembly or the second heat source assembly to the shared assembly.Type: GrantFiled: November 28, 2018Date of Patent: May 25, 2021Inventors: Justin Paul Smith, Brandon Wayne Miller, Daniel Alan Niergarth
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Publication number: 20210148283Abstract: A thermal management system is provided for incorporation into at least one of a gas turbine engine or an aircraft. The thermal management system includes: a thermal transport bus having a heat exchange fluid flowing therethrough, the thermal transport bus further including: a first flow loop comprising at least one first heat source exchanger, at least one first heat sink exchanger, and a first pump to move the heat exchange fluid through the first flow loop; and a second flow loop comprising at least one second heat source exchanger, at least one second heat sink exchanger, and a second pump to move the heat exchange fluid through the second flow loop; wherein the first flow loop is isolated from the second flow loop, and wherein the first heat source exchanger and the second heat source exchanger are configured with a common heat source.Type: ApplicationFiled: November 15, 2019Publication date: May 20, 2021Inventors: Daniel Alan Niergarth, Brandon Wayne Miller, Justin Paul Smith
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Patent number: 10998837Abstract: A turbomachine and method for operation turbomachine are provided, the method including adjusting a first load at a first electric machine operably coupled to a first rotatable component, in which the first electric machine is operably coupled to the first rotatable component such that a first speed of the first rotatable component is increased or decreased based on an engine condition and the first load; adjusting a second load at a second electric machine operably coupled to a second rotatable component, in which the second electric machine is operably coupled to the second rotatable component such that a second speed of the second rotatable component is decreased or increased based on the engine condition and the second load; and transferring energy generated from at least one of the first electric machine or the second electric machine.Type: GrantFiled: April 2, 2020Date of Patent: May 4, 2021Assignee: General Electric CompanyInventors: Justin Paul Smith, Kurt David Murrow, Darek Tomasz Zatorski, Patrick Michael Marrinan
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Publication number: 20210108573Abstract: A gas turbine engine includes a gas turbine engine core having a high pressure compressor, a combustor, and a high pressure turbine in serial relationship; and a low pressure compressor upstream of the gas turbine engine core; wherein the low pressure compressor driven by a variable speed power source such that the rotational speed of the low pressure compressor is controllable independently from the rotational speed of any turbine of the gas turbine engine.Type: ApplicationFiled: March 6, 2020Publication date: April 15, 2021Inventors: Arthur William Sibbach, Brandon Wayne Miller, Justin Paul Smith, Brian Lewis Devendorf, Carlos Walberto Perez
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Publication number: 20200256252Abstract: A gas turbine engine includes a compressor section, a combustion section, and a turbine section arranged in serial flow order; a casing surrounding the compressor section, the combustion section, and the turbine section; a first system comprising a first system fluid line, the first system fluid line including a first system fluid therein; and a second system including a hydraulic motor, the hydraulic motor positioned within the casing and fluidly coupled to the first system fluid line such that a flow of the first system fluid through the first system fluid line drives the hydraulic motor, the second system further including a fluid pump and a second system fluid line, the hydraulic motor drivingly coupled to the fluid pump, the fluid pump operable with the second system fluid line for providing a flow of a second system fluid through the second system fluid line during operation.Type: ApplicationFiled: February 13, 2019Publication date: August 13, 2020Inventor: Justin Paul Smith
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Publication number: 20200244199Abstract: A turbomachine and method for operating a turbomachine comprising a first rotatable component and a second rotatable component each defining a rotatable speed mechanically independent of one another, and an electric machine electrically coupled to the first rotatable component and the second rotatable component such that a load level relative to the first rotatable component and the second rotatable component is adjustable is generally provided.Type: ApplicationFiled: April 2, 2020Publication date: July 30, 2020Inventors: Justin Paul Smith, Kurt David Murrow, Darek Tomasz Zatorski, Patrick Michael Marrinan