Patents by Inventor Thomas Lee Becker
Thomas Lee Becker 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: 20240117770Abstract: A turbomachine engine includes a core engine having one or more compressor sections, one or more turbine sections that includes a power turbine, and a combustion chamber in flow communication with the compressor sections and turbine sections. The turbomachine engine also includes a shaft coupled to the power turbine and characterized by a midshaft rating (MSR) between two hundred (ft/sec)1/2 and three hundred (ft/sec)1/2. In one aspect, the shaft has a redline speed between fifty and two hundred fifty feet per second (ft/sec). In another aspect, the shaft has a length L, an outer diameter D, and a ratio of L/D between twelve and thirty-seven.Type: ApplicationFiled: October 13, 2023Publication date: April 11, 2024Inventors: Narayanan Payyoor, Weize Kang, Thomas Lee Becker, Richard Schmidt
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Publication number: 20240044261Abstract: The present disclosure is directed to a gas turbine engine assembly having a compressor configured to increase pressure of incoming air, a combustion chamber, at least one turbine coupled to a generator, a torsional damper, and a controller. The combustion chamber is configured to receive a pressurized air stream from the compressor. Further, fuel is injected into the pressurized air in the combustion chamber and ignited so as to raise a temperature and energy level of the pressurized air. The turbine is operatively coupled to the combustion chamber so as to receive combustion products that flow from the combustion chamber. The generator is coupled to the turbine via a shaft. Thus, the torsional damper is configured to dampen torsional oscillations of the generator. Moreover, the controller is configured to provide additional damping control to the generator.Type: ApplicationFiled: October 10, 2023Publication date: February 8, 2024Inventors: Paul Robert Gemin, Thomas Lee Becker, Tod Robert Steen
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Patent number: 11802492Abstract: The present disclosure is directed to a gas turbine engine assembly having a compressor configured to increase pressure of incoming air, a combustion chamber, at least one turbine coupled to a generator, a torsional damper, and a controller. The combustion chamber is configured to receive a pressurized air stream from the compressor. Further, fuel is injected into the pressurized air in the combustion chamber and ignited so as to raise a temperature and energy level of the pressurized air. The turbine is operatively coupled to the combustion chamber so as to receive combustion products that flow from the combustion chamber. The generator is coupled to the turbine via a shaft. Thus, the torsional damper is configured to dampen torsional oscillations of the generator. Moreover, the controller is configured to provide additional damping control to the generator.Type: GrantFiled: May 20, 2022Date of Patent: October 31, 2023Assignee: General Electric CompanyInventors: Paul Robert Gemin, Thomas Lee Becker, Tod Robert Steen
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Patent number: 11795882Abstract: A turbomachine engine includes a core engine having one or more compressor sections, one or more turbine sections that includes a power turbine, and a combustion chamber in flow communication with the compressor sections and turbine sections. The turbomachine engine also includes a shaft coupled to the power turbine and characterized by a midshaft rating (MSR) between two hundred (ft/sec)1/2 and three hundred (ft/sec)1/2. In one aspect, the shaft has a redline speed between fifty and two hundred fifty feet per second (ft/sec). In another aspect, the shaft has a length L, an outer diameter D, and a ratio of L/D between twelve and thirty-seven.Type: GrantFiled: January 11, 2023Date of Patent: October 24, 2023Assignee: GENERAL ELECTRIC COMPANYInventors: Narayanan Payyoor, Weize Kang, Thomas Lee Becker, Richard Schmidt
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Publication number: 20230160346Abstract: A turbomachine engine includes a core engine having one or more compressor sections, one or more turbine sections that includes a power turbine, and a combustion chamber in flow communication with the compressor sections and turbine sections. The turbomachine engine also includes a shaft coupled to the power turbine and characterized by a midshaft rating (MSR) between two hundred (ft/sec)1/2 and three hundred (ft/sec)1/2. In one aspect, the shaft has a redline speed between fifty and two hundred fifty feet per second (ft/sec). In another aspect, the shaft has a length L, an outer diameter D, and a ratio of L/D between twelve and thirty-seven.Type: ApplicationFiled: January 11, 2023Publication date: May 25, 2023Inventors: Narayanan Payyoor, Weize Kang, Thomas Lee Becker, Richard Schmidt
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Patent number: 11603801Abstract: A turbomachine engine includes a core engine having one or more compressor sections, one or more turbine sections that includes a power turbine, and a combustion chamber in flow communication with the compressor sections and turbine sections. The turbomachine engine also includes a shaft coupled to the power turbine and characterized by a midshaft rating (MSR) between two hundred (ft/sec)1/2 and three hundred (ft/sec)1/2. In one aspect, the shaft has a redline speed between fifty and two hundred fifty feet per second (ft/sec). In another aspect, the shaft has a length L, an outer diameter D, and a ratio of L/D between twelve and thirty-seven.Type: GrantFiled: May 24, 2021Date of Patent: March 14, 2023Assignee: GENERAL ELECTRIC COMPANYInventors: Narayanan Payyoor, Weize Kang, Thomas Lee Becker, Richard Schmidt
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Patent number: 11585354Abstract: An un-ducted turbofan engine defining a radial direction and an axial direction that includes a core engine, a fan, a plurality of variable outlet guide vanes, and a pitch change mechanism. Each of the plurality of variable outlet guide vanes are attached in a rotatable manner to the core engine of the un-ducted turbofan engine. The pitch change mechanism is positioned radially between the engine air flowpath and the plurality of variable outlet guide vanes and coupled to at least one variable outlet guide vane of the plurality of variable outlet guide vanes for changing a pitch of the at least one variable outlet guide vane.Type: GrantFiled: June 15, 2022Date of Patent: February 21, 2023Assignee: General Electric CompanyInventors: Brandon Wayne Miller, Thomas Lee Becker, Jr.
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Publication number: 20220372917Abstract: A turbomachine engine includes a core engine having one or more compressor sections, one or more turbine sections that includes a power turbine, and a combustion chamber in flow communication with the compressor sections and turbine sections. The turbomachine engine also includes a shaft coupled to the power turbine and characterized by a midshaft rating (MSR) between two hundred (ft/sec)1/2 and three hundred (ft/sec)1/2. In one aspect, the shaft has a redline speed between fifty and two hundred fifty feet per second (ft/sec). In another aspect, the shaft has a length L, an outer diameter D, and a ratio of L/D between twelve and thirty-seven.Type: ApplicationFiled: May 24, 2021Publication date: November 24, 2022Inventors: Narayanan Payyoor, Weize Kang, Thomas Lee Becker, Richard Schmidt
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Publication number: 20220373019Abstract: A turbomachine engine includes a core engine having one or more compressor sections, one or more turbine sections that includes a power turbine, and a combustion chamber in flow communication with the compressor sections and turbine sections. The turbomachine engine also includes a shaft coupled to the power turbine and characterized by a midshaft rating (MSR) between two hundred (ft/sec)1/2 and three hundred (ft/sec)1/2. In one aspect, the shaft has a redline speed between fifty and two hundred fifty feet per second (ft/sec). In another aspect, the shaft has a length L, an outer diameter D, and a ratio of L/D between twelve and thirty-seven.Type: ApplicationFiled: May 24, 2021Publication date: November 24, 2022Inventors: Narayanan Payyoor, Weize Kang, Thomas Lee Becker, Richard Schmidt
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Publication number: 20220325723Abstract: An un-ducted turbofan engine defining a radial direction and an axial direction that includes a core engine, a fan, a plurality of variable outlet guide vanes, and a pitch change mechanism. Each of the plurality of variable outlet guide vanes are attached in a rotatable manner to the core engine of the un-ducted turbofan engine. The pitch change mechanism is positioned radially between the engine air flowpath and the plurality of variable outlet guide vanes and coupled to at least one variable outlet guide vane of the plurality of variable outlet guide vanes for changing a pitch of the at least one variable outlet guide vane.Type: ApplicationFiled: June 15, 2022Publication date: October 13, 2022Inventors: Brandon Wayne Miller, Thomas Lee Becker, JR.
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Patent number: 11447259Abstract: An aircraft including a fuselage and an aft engine is provided. The fuselage extends from a forward end of the aircraft towards an aft end of the aircraft. The aft engine is mounted to the fuselage proximate the aft end of the aircraft and includes a fan and a nacelle. The fan is rotatable about a central axis of the aft engine and includes a plurality of fan blades. The nacelle of the aft engine surrounds the plurality of fan blades and defines a bottom portion having a forward end. Additionally, the nacelle defines a curved surface at the forward end of the bottom portion, the curved surface including a reference point where the curved surface defines the smallest radius of curvature. The nacelle further defines a normal reference line extending normal from the reference point. The normal reference line defines an angle with the central axis of the aft engine greater than zero to, e.g., allow for a maximum amount of airflow into the aft engine.Type: GrantFiled: June 24, 2019Date of Patent: September 20, 2022Assignee: General Electric CompanyInventors: Patrick Michael Marrinan, Thomas Lee Becker, Kurt David Murrow, Jixian Yao
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Publication number: 20220282637Abstract: The present disclosure is directed to a gas turbine engine assembly having a compressor configured to increase pressure of incoming air, a combustion chamber, at least one turbine coupled to a generator, a torsional damper, and a controller. The combustion chamber is configured to receive a pressurized air stream from the compressor. Further, fuel is injected into the pressurized air in the combustion chamber and ignited so as to raise a temperature and energy level of the pressurized air. The turbine is operatively coupled to the combustion chamber so as to receive combustion products that flow from the combustion chamber. The generator is coupled to the turbine via a shaft. Thus, the torsional damper is configured to dampen torsional oscillations of the generator. Moreover, the controller is configured to provide additional damping control to the generator.Type: ApplicationFiled: May 20, 2022Publication date: September 8, 2022Inventors: Paul Robert Gemin, Thomas Lee Becker, Tod Robert Steen
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Patent number: 11391298Abstract: An aeronautical propulsion device including a fan and a plurality of variable guide vanes is provided. The fan includes a plurality of fan blades for providing a flow of air and the plurality of variable guide vanes are configured for directing air to or from the fan in a desired direction. Each of the plurality of guide vanes defines an inner end along the radial direction and is attached to a housing of the portion device at the inner end in a rotatable manner. The propulsion device further includes a pitch change mechanism positioned in the housing and mechanically coupled to at least one of the plurality of guide vanes for changing a pitch of the at least one of the plurality of guide vanes.Type: GrantFiled: October 7, 2015Date of Patent: July 19, 2022Assignee: General Electric CompanyInventors: Brandon Wayne Miller, Thomas Lee Becker, Jr.
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Patent number: 11346243Abstract: The present disclosure is directed to a gas turbine engine assembly having a compressor configured to increase pressure of incoming air, a combustion chamber, at least one turbine coupled to a generator, a torsional damper, and a controller. The combustion chamber is configured to receive a pressurized air stream from the compressor. Further, fuel is injected into the pressurized air in the combustion chamber and ignited so as to raise a temperature and energy level of the pressurized air. The turbine is operatively coupled to the combustion chamber so as to receive combustion products that flow from the combustion chamber. The generator is coupled to the turbine via a shaft. Thus, the torsional damper is configured to dampen torsional oscillations of the generator. Moreover, the controller is configured to provide additional damping control to the generator.Type: GrantFiled: April 19, 2017Date of Patent: May 31, 2022Assignee: General Electric CompanyInventors: Paul Robert Gemin, Thomas Lee Becker, Tod Robert Steen
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Publication number: 20210062728Abstract: An actuation assembly for concentric variable stator vanes of a rotary component of a gas turbine engine. The actuation assembly includes an inner casing and an intermediate casing defining a first concentric flowpath extending between the inner casing and the intermediate casing. The actuation assembly includes an outer casing defining a second concentric flowpath extending between the intermediate casing and the outer casing. The actuation assembly includes a first variable stator vane extending radially inward from the intermediate casing into the first concentric flowpath. The actuation assembly includes a second variable stator vane extending radially within the second concentric flowpath between a distal end at the outer casing and proximate end at the inner casing and defining a cavity extending therebetween. A first trunnion extends radially inward from the outer casing through the cavity of the second variable stator vane and is drivingly coupled to the first variable stator vane.Type: ApplicationFiled: September 4, 2019Publication date: March 4, 2021Inventors: Mark Frisch, Mark Joseph Mielke, Thomas Lee Becker
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Patent number: 10711702Abstract: A gas turbine engine is provided having a compressor section, a combustion section located downstream of the compressor section, and a turbine section located downstream of the combustion section. A structural member extends from the compressor section to the turbine section for strengthening one or more components of the gas turbine engine. The structural member also defines a flowpath extending between an inlet in airflow communication with the compressor section and an outlet in airflow communication with the turbine section. The flowpath is configured to provide bleed air from the compressor section to the turbine section to capture at least a portion of the energy in such bleed air.Type: GrantFiled: August 18, 2015Date of Patent: July 14, 2020Assignee: General Electric CompanyInventor: Thomas Lee Becker, Jr.
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Patent number: 10578028Abstract: A gas turbine engine is provided having a compressor section, a combustion section, and a turbine section. The compressor section includes one or more compressors and the turbine section includes one or more turbines. The one or more compressors and the one or more turbines are each rotatable about a longitudinal centerline of the gas turbine engine. Additionally, a bleed air flowpath is provided extending between an inlet in airflow communication with the compressor section and an outlet. An auxiliary turbine is positioned in airflow communication with the bleed air flowpath for extracting energy from a flow of bleed air through the bleed air flowpath.Type: GrantFiled: August 18, 2015Date of Patent: March 3, 2020Assignee: General Electric CompanyInventor: Thomas Lee Becker, Jr.
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Publication number: 20190329896Abstract: An aircraft including a fuselage and an aft engine is provided. The fuselage extends from a forward end of the aircraft towards an aft end of the aircraft. The aft engine is mounted to the fuselage proximate the aft end of the aircraft and includes a fan and a nacelle. The fan is rotatable about a central axis of the aft engine and includes a plurality of fan blades. The nacelle of the aft engine surrounds the plurality of fan blades and defines a bottom portion having a forward end. Additionally, the nacelle defines a curved surface at the forward end of the bottom portion, the curved surface including a reference point where the curved surface defines the smallest radius of curvature. The nacelle further defines a normal reference line extending normal from the reference point. The normal reference line defines an angle with the central axis of the aft engine greater than zero to, e.g., allow for a maximum amount of airflow into the aft engine.Type: ApplicationFiled: June 24, 2019Publication date: October 31, 2019Inventors: Patrick Michael Marrinan, Thomas Lee Becker, Kurt David Murrow, Jixian Yao
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Patent number: 10358228Abstract: An aircraft is provided including a fuselage and an aft engine. The fuselage defines a top side, a bottom side, and a frustum located proximate an aft end of the aircraft. The frustum defines a top reference line extending along the frustum at a top side of the fuselage, and a bottom reference line extending along the frustum at a bottom side of the fuselage. The top and bottom reference lines meet at a reference point aft of the frustum. The fuselage further defines a recessed portion located aft of the frustum and indented inwardly from the bottom reference line. The aft engine includes a nacelle extending adjacent to the recessed portion of the fuselage such that the aft engine may be included with the aircraft without interfering with, e.g., a takeoff angle of the aircraft.Type: GrantFiled: October 26, 2017Date of Patent: July 23, 2019Assignee: General Electric CompanyInventors: Patrick Michael Marrinan, Thomas Lee Becker, Kurt David Murrow, Jixian Yao
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Patent number: 10247017Abstract: A system includes a gas delivery disk coupled to a second shaft, wherein the second shaft and the gas delivery disk are disposed about an axis. The gas delivery disk includes an inner axial opening configured to facilitate a first axial flow through a first passage within the second shaft, a duct configured to supply a bearing flow in a radial direction toward the axis, and a bearing face disposed within the first passage and radially interior to the inner axial opening. The bearing face is configured to receive the bearing flow, and the bearing face is configured to form a gas bearing between the bearing face and a first shaft disposed about the axis.Type: GrantFiled: June 29, 2016Date of Patent: April 2, 2019Assignee: GENERAL ELECTRIC COMPANYInventors: Brandon Wayne Miller, Thomas Lee Becker, Daniel Alan Niergarth, Bugra Han Ertas