Patents by Inventor Kyle Robert SNOW
Kyle Robert SNOW 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: 11098647Abstract: A system for managing thermal transfer in at least one of an aircraft or a gas turbine engine includes a first engine system utilizing an oil for heat transfer. The oil of the first system has a temperature limit of at least about 500° F. The system additionally includes a fuel system having a deoxygenation unit for deoxygenating fuel in the fuel system, as well as a fuel-oil heat exchanger located downstream of the deoxygenation unit. The fuel-oil heat exchanger is in thermal communication with the oil in the first engine system and the fuel in the fuel system for transferring heat from the oil in the first engine system to the fuel in the fuel system.Type: GrantFiled: January 24, 2019Date of Patent: August 24, 2021Assignee: General Electric CompanyInventors: Brandon Wayne Miller, Duane Howard Anstead, Mohammed El Hacin Sennoun, Ning Fang, Kyle Robert Snow
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Patent number: 10830092Abstract: Rotor thrust balancing systems for turbomachines and methods of using the same are generally disclosed. For example, a rotor thrust balancing system for a turbomachine, wherein the turbomachine defines a centerline extending the length of the turbomachine. The system includes a rotating drive shaft, a thrust bearing, and a first waveguide sensor. The rotating drive shaft couples a turbine section and a compressor section of the turbomachine. The thrust bearing supports the rotating drive shaft of the turbomachine. The thrust bearing includes a plurality of ball bearings, an inner race coupled to the rotating drive shaft, and an outer race coupled to a fixed structure. The first waveguide sensor is coupled to the outer race at a first end of the waveguide sensor. The waveguide sensor communicates a vibrational frequency from the thrust bearing to a second end of the waveguide sensor.Type: GrantFiled: March 7, 2018Date of Patent: November 10, 2020Assignee: General Electric CompanyInventors: Kyle Robert Snow, Andrew Michael Tompkins, Andrew Michael Watson, Philip Joseph Ogston, Christopher Michael Thompson
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Patent number: 10648365Abstract: A gas turbine engine having a core engine. The core engine includes an inlet, a compressor section, a combustion section, a turbine section, and an exhaust. The gas turbine engine also includes a bearing sump arranged in the core engine for containing lubrication, the bearing sump and lubrication having an operational range between at least about 0° F. and about 550° F.Type: GrantFiled: December 8, 2015Date of Patent: May 12, 2020Assignee: General Electric CompanyInventors: Kyle Robert Snow, Brandon Wayne Miller, Duane Howard Anstead, Jonothan Allen Scheetz, Mohammed El Hacin Sennoun, Ning Fang
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Patent number: 10598035Abstract: A seal assembly for use between an inner shaft and an outer shaft rotatable about a common axis within a turbine engine includes a pair of end rings and a plurality of seal elements coupled between the pair of end rings. Each end ring includes a flange extending in an axial direction, and each seal element includes a pair of shoulders extending in opposing axial directions. The seal assembly also includes a pair of retaining rings. Each retaining ring is positioned between one shoulder of the pair of shoulders and a corresponding one end ring flange of the pair of end ring flanges.Type: GrantFiled: May 27, 2016Date of Patent: March 24, 2020Assignee: General Electric CompanyInventors: Kyle Robert Snow, Daniel Scott Tomasic
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Patent number: 10539076Abstract: A self-contained lubrication fluid circulation system for use with a gas turbine engine defining a core air flowpath includes a sump configured to collect lubrication fluid and a heat source coupled in fluid communication with the sump and configured to transfer heat to the lubrication fluid. The system also includes a heat sink positioned within the sump and coupled in fluid communication with the heat source. A lubrication fluid conduit of the system is configured to channel the lubrication fluid between the heat source and the heat sink, wherein the lubrication fluid conduit is positioned entirely within the sump.Type: GrantFiled: November 10, 2015Date of Patent: January 21, 2020Assignee: General Electric CompanyInventors: Daniel Alan Niergarth, Brandon Wayne Miller, Kyle Robert Snow, Christopher James Kroger
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Publication number: 20190277157Abstract: Rotor thrust balancing systems for turbomachines and methods of using the same are generally disclosed. For example, a rotor thrust balancing system for a turbomachine, wherein the turbomachine defines a centerline extending the length of the turbomachine. The system includes a rotating drive shaft, a thrust bearing, and a first waveguide sensor. The rotating drive shaft couples a turbine section and a compressor section of the turbomachine. The thrust bearing supports the rotating drive shaft of the turbomachine. The thrust bearing includes a plurality of ball bearings, an inner race coupled to the rotating drive shaft, and an outer race coupled to a fixed structure. The first waveguide sensor is coupled to the outer race at a first end of the waveguide sensor. The waveguide sensor communicates a vibrational frequency from the thrust bearing to a second end of the waveguide sensor.Type: ApplicationFiled: March 7, 2018Publication date: September 12, 2019Inventors: Kyle Robert Snow, Andrew Michael Tompkins, Andrew Michael Watson, Philip Joseph Ogston, Christopher Michael Thompson
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Publication number: 20190226585Abstract: Sealing assemblies and systems and their assembly methods are provided. For example, a seal assembly is provided for use between an inner shaft and an outer shaft that are rotatable about a common axis. The seal assembly comprises a first end ring having an aft face; a second end ring positioned aft of the first end ring and having a forward face; a first hydrodynamic portion defined on the aft face of the first end ring; a second hydrodynamic portion defined on the forward face of the second end ring. A seal element is disposed between the first end ring and the second end ring such that the seal element is positioned between the first hydrodynamic portion and the second hydrodynamic portion.Type: ApplicationFiled: January 25, 2018Publication date: July 25, 2019Inventors: Kyle Robert Snow, Scott Wolfer, Daniel Scott Tomasic
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Publication number: 20190153954Abstract: A system for managing thermal transfer in at least one of an aircraft or a gas turbine engine includes a first engine system utilizing an oil for heat transfer. The oil of the first system has a temperature limit of at least about 500° F. The system additionally includes a fuel system having a deoxygenation unit for deoxygenating fuel in the fuel system, as well as a fuel-oil heat exchanger located downstream of the deoxygenation unit. The fuel-oil heat exchanger is in thermal communication with the oil in the first engine system and the fuel in the fuel system for transferring heat from the oil in the first engine system to the fuel in the fuel system.Type: ApplicationFiled: January 24, 2019Publication date: May 23, 2019Inventors: Brandon Wayne Miller, Duane Howard Anstead, Mohammed El Hacin Sennoun, Ning Fang, Kyle Robert Snow
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Patent number: 10247106Abstract: An apparatus and method of reducing a flow of fluid and heat between a first space and a second space in a rotatable machine and an integral seal and heat shield device are provided. The device includes an annular flange configured to couple to the rotating member of the rotatable machine and a multi-walled seal shield member extending axially from the flange. The multi-walled seal shield member is formed integrally with the flange. The seal shield member includes a first wall including a plurality of surface features, a second wall spaced radially inwardly with respect to the first wall, and a cavity formed between the first and second walls. The integral seal and heat shield device also includes a cap end integrally formed and configured to seal the first and second walls. Each of the flange, the seal shield member, and the cap end are formed of a sintered metal.Type: GrantFiled: June 15, 2016Date of Patent: April 2, 2019Assignee: General Electric CompanyInventors: Michael Thomas Dansereau, Kyle Robert Snow
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Patent number: 10215097Abstract: A system for managing thermal transfer in at least one of an aircraft or a gas turbine engine includes a first engine system utilizing an oil for heat transfer. The oil of the first system has a temperature limit of at least about 500° F. The system additionally includes a fuel system having a deoxygenation unit for deoxygenating fuel in the fuel system, as well as a fuel-oil heat exchanger located downstream of the deoxygenation unit. The fuel-oil heat exchanger is in thermal communication with the oil in the first engine system and the fuel in the fuel system for transferring heat from the oil in the first engine system to the fuel in the fuel system.Type: GrantFiled: February 11, 2016Date of Patent: February 26, 2019Assignee: General Electric CompanyInventors: Brandon Wayne Miller, Duane Howard Anstead, Mohammed El Hacin Sennoun, Ning Fang, Kyle Robert Snow
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Patent number: 10196986Abstract: In one aspect, the present disclosure is directed to a bearing compartment sealing system including a bearing for supporting a shaft. A housing encloses the bearing and defines a compartment for holding lubricant therein. At least two seals are located between the shaft and the housing. The at least two seals, the housing, and the shaft collectively enclose the compartment. Only one of the at least two seals is a hydrodynamic seal.Type: GrantFiled: September 4, 2015Date of Patent: February 5, 2019Assignee: General Electric CompanyInventors: Ning Fang, Scott Wolfer, Adam Mitchell Record, Jonathan K. Remer, Daryl Scott Schneider, Jacob Patrick Miller, Kyle Robert Snow
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Patent number: 9879720Abstract: One embodiment describes a bearing damper including a housing; a damper with an annular gap and an internal spring, in which the annular gap is formed between an inner rim and an outer rim of the damper, the internal spring circumferentially bounds the annular gap, the outer rim is coupled to the housing, and the annular gap is configured to be filled with fluid used to dampen vibrations produced on a drive shaft; and an external spring coupled to the housing and to the inner rim, in which the external includes an axial stiffness engineered to externally offset axial forces exerted on the inner rim of the and a radial stiffness engineered to externally offset a first portion of radial forces exerted on the inner rim and to permit a second portion of the radial forces to propagate the vibrations from the drive shaft to the inner rim.Type: GrantFiled: May 5, 2016Date of Patent: January 30, 2018Assignee: General Electric CompanyInventors: Bugra Han Ertas, Kyle Robert Snow
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Publication number: 20170363011Abstract: An apparatus and method of reducing a flow of fluid and heat between a first space and a second space in a rotatable machine and an integral seal and heat shield device are provided. The device includes an annular flange configured to couple to the rotating member of the rotatable machine and a multi-walled seal shield member extending axially from the flange. The multi-walled seal shield member is formed integrally with the flange. The seal shield member includes a first wall including a plurality of surface features, a second wall spaced radially inwardly with respect to the first wall, and a cavity formed between the first and second walls. The integral seal and heat shield device also includes a cap end integrally formed and configured to seal the first and second walls. Each of the flange, the seal shield member, and the cap end are formed of a sintered metal.Type: ApplicationFiled: June 15, 2016Publication date: December 21, 2017Inventors: Michael Thomas Dansereau, Kyle Robert Snow
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Patent number: 9841056Abstract: A bearing apparatus includes: a bearing including a first race rotatable relative to a second race, wherein the first race includes one or more drain passages extending therethrough; and a squeeze film damper connected to the first race, the squeeze film damper including first and second squeeze film spaces separated by an oil drain path which communicates with the one or more drain passages of the first race.Type: GrantFiled: October 21, 2015Date of Patent: December 12, 2017Assignee: General Electric CompanyInventors: Kyle Robert Snow, Philip J. Ogston, Christopher Michael Grady
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Publication number: 20170342848Abstract: A seal assembly for use between an inner shaft and an outer shaft rotatable about a common axis within a turbine engine includes a pair of end rings and a plurality of seal elements coupled between the pair of end rings. Each end ring includes a flange extending in an axial direction, and each seal element includes a pair of shoulders extending in opposing axial directions. The seal assembly also includes a pair of retaining rings. Each retaining ring is positioned between one shoulder of the pair of shoulders and a corresponding one end ring flange of the pair of end ring flanges.Type: ApplicationFiled: May 27, 2016Publication date: November 30, 2017Inventors: Kyle Robert Snow, Daniel Scott Tomasic
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Publication number: 20170321747Abstract: One embodiment describes a bearing damper including a housing; a damper with an annular gap and an internal spring, in which the annular gap is formed between an inner rim and an outer rim of the damper, the internal spring circumferentially bounds the annular gap, the outer rim is coupled to the housing, and the annular gap is configured to be filled with fluid used to dampen vibrations produced on a drive shaft; and an external spring coupled to the housing and to the inner rim, in which the external includes an axial stiffness engineered to externally offset axial forces exerted on the inner rim of the and a radial stiffness engineered to externally offset a first portion of radial forces exerted on the inner rim and to permit a second portion of the radial forces to propagate the vibrations from the drive shaft to the inner rim.Type: ApplicationFiled: May 5, 2016Publication date: November 9, 2017Inventors: Bugra Han Ertas, Kyle Robert Snow
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Patent number: 9677424Abstract: A gas turbine engine is provided defining a radial direction. The gas turbine engine generally includes a compressor section and a turbine section, the compressor section and turbine section together defining a core air flowpath. The gas turbine engine also includes a sump positioned inward of the core air flowpath along the radial direction. An air pump is positioned inward of the core air flowpath along the radial direction for providing a flow of air from the sump to lower an internal pressure of the sump and reduce a likelihood of lubrication leaking from the sump.Type: GrantFiled: June 24, 2015Date of Patent: June 13, 2017Assignee: General Electric CompanyInventors: Brandon Wayne Miller, Matthew Timothy Franer, Kyle Robert Snow
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Publication number: 20170159493Abstract: A gas turbine engine having a core engine. The core engine includes an inlet, a compressor section, a combustion section, a turbine section, and an exhaust. The gas turbine engine also includes a bearing sump arranged in the core engine for containing lubrication, the bearing sump and lubrication having an operational range between at least about 0° F. and about 550° F.Type: ApplicationFiled: December 8, 2015Publication date: June 8, 2017Inventors: Kyle Robert Snow, Brandon Wayne Miller, Duane Howard Anstead, Jonothan Allen Scheetz, Mohammed El Hacin Sennoun, Ning Fang
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Publication number: 20170159564Abstract: A system for managing thermal transfer in at least one of an aircraft or a gas turbine engine includes a first engine system utilizing an oil for heat transfer. The oil of the first system has a temperature limit of at least about 500° F. The system additionally includes a fuel system having a deoxygenation unit for deoxygenating fuel in the fuel system, as well as a fuel-oil heat exchanger located downstream of the deoxygenation unit. The fuel-oil heat exchanger is in thermal communication with the oil in the first engine system and the fuel in the fuel system for transferring heat from the oil in the first engine system to the fuel in the fuel system.Type: ApplicationFiled: December 8, 2015Publication date: June 8, 2017Inventors: Brandon Wayne Miller, Duane Howard Anstead, Mohammed El Hacin Sennoun, Ning Fang, Kyle Robert Snow
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Publication number: 20170159569Abstract: A system for managing thermal transfer in at least one of an aircraft or a gas turbine engine includes a first engine system utilizing an oil for heat transfer. The oil of the first system has a temperature limit of at least about 500° F. The system additionally includes a fuel system having a deoxygenation unit for deoxygenating fuel in the fuel system, as well as a fuel-oil heat exchanger located downstream of the deoxygenation unit. The fuel-oil heat exchanger is in thermal communication with the oil in the first engine system and the fuel in the fuel system for transferring heat from the oil in the first engine system to the fuel in the fuel system.Type: ApplicationFiled: February 11, 2016Publication date: June 8, 2017Inventors: Brandon Wayne Miller, Duane Howard Anstead, Mohammed El Hacin Sennoun, Ning Fang, Kyle Robert Snow