Patents by Inventor Thomas Lee BECKER, JR.
Thomas Lee BECKER, JR. 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: 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: 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: 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: 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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Patent number: 10060290Abstract: The pump includes a first rotatable member including a radially inward facing groove having an edge. The first rotatable member configured to receive a plurality of flows of fluid over the edge. The first rotatable member configured to rotate at a first angular velocity. The pump also includes a second rotatable member including a collector configured to rotate at a second angular velocity. The second rotatable member also includes a plurality of scoop tubes extending radially outwardly from the collector. Each scoop tube of the plurality of scoop tubes includes a first end coupled in flow communication to the collector and a second end including an inlet opening extending into the groove. The second end curved such that the inlet opening is open in a direction of rotation of the second rotatable member. The inlet opening configured to scoop a fluid collected in the groove.Type: GrantFiled: December 30, 2015Date of Patent: August 28, 2018Assignee: General Electric CompanyInventors: Thomas Ory Moniz, Thomas Lee Becker, Jr.
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Publication number: 20170191378Abstract: The pump includes a first rotatable member including a radially inward facing groove having an edge. The first rotatable member configured to receive a plurality of flows of fluid over the edge. The first rotatable member configured to rotate at a first angular velocity. The pump also includes a second rotatable member including a collector configured to rotate at a second angular velocity. The second rotatable member also includes a plurality of scoop tubes extending radially outwardly from the collector. Each scoop tube of the plurality of scoop tubes includes a first end coupled in flow communication to the collector and a second end including an inlet opening extending into the groove. The second end curved such that the inlet opening is open in a direction of rotation of the second rotatable member. The inlet opening configured to scoop a fluid collected in the groove.Type: ApplicationFiled: December 30, 2015Publication date: July 6, 2017Inventors: Thomas Ory Moniz, Thomas Lee Becker, JR.
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Publication number: 20170102006Abstract: 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: ApplicationFiled: October 7, 2015Publication date: April 13, 2017Inventors: Brandon Wayne Miller, Thomas Lee Becker, JR.
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Publication number: 20170051678Abstract: 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: ApplicationFiled: August 18, 2015Publication date: February 23, 2017Inventor: Thomas Lee BECKER, JR.
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Publication number: 20170051680Abstract: An airflow injection nozzle for a stage of airflow injection nozzles located in a turbine section of the gas turbine engine is provided. The airflow injection nozzle includes a leading end positioned opposite of a trailing end, as well as a pressure side positioned opposite of a suction side. The airflow injection nozzle includes an opening positioned on the pressure side oriented generally in a flow direction of the gas turbine engine for injecting a flow of bleed air from a compressor section of the gas turbine engine into the turbine section of the gas turbine engine.Type: ApplicationFiled: August 18, 2015Publication date: February 23, 2017Inventors: Thomas Lee BECKER, JR., Craig Miller KUHNE
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Publication number: 20170051679Abstract: 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: ApplicationFiled: August 18, 2015Publication date: February 23, 2017Inventor: Thomas Lee Becker, JR.