Patents by Inventor Timothy Leo Schelfaut
Timothy Leo Schelfaut 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: 11970279Abstract: A control system and methods for controlling the position of one or more engine-mounting links of an engine-mounting linkage system are provided. In one aspect, an engine-mounting linkage system includes one or more engine-mounting links that each have an adjustable inclination angle. An inclination angle of a link may be adjusted by an actuator of the control system. One or more controllers of the control system can control the actuator and thus the inclination angle of the link by determining a control command based at least in part on an output received from one or more sensors of the control system. The controllers can then cause the actuator to change the inclination angle of the link based at least in part on the determined control command.Type: GrantFiled: February 21, 2020Date of Patent: April 30, 2024Assignee: General Electric CompanyInventors: Timothy Leo Schelfaut, Anthony Michael Metz, Jonathan Edward Coleman, Thomas P. Joseph
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Patent number: 11939070Abstract: Engine-mounting linkage systems may include a plurality of engine mounting links configured to couple an engine frame to an engine support structure of an aircraft. The plurality of engine-mounting links may include a forward link that is connectable to a forward frame portion of the engine frame and the engine support structure, and an aft link that is connectable to an aft frame portion of the engine frame and the engine support structure. The engine mounting linkage system may include an actuator that is connectable to the engine support structure and one of the plurality of engine-mounting links, or to the engine support structure and the engine frame. The actuator, when actuated, changes an inclination angle ? of at least one of the plurality of engine-mounting links.Type: GrantFiled: February 21, 2020Date of Patent: March 26, 2024Assignee: GENERAL ELECTRIC COMPANYInventors: Timothy Leo Schelfaut, Anthony Michael Metz, Jonathan Edward Coleman, Thomas P. Joseph, Michael C. Borner, Mahesh Khandeparker, Kudum Shinde
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Patent number: 11697506Abstract: Methods, apparatus, systems and articles of manufacture are disclosed to methods and apparatus for gas turbine bending isolation. An example mechanical interface to couple a first section of a gas turbine to a second section of the gas turbine, the mechanical interface comprising a first mating surface disposed on the first section, and a second mating surface disposed on the second section and circumferentially around the first mating surface, wherein the coupling of the first mating surface to the second mating surface enables the first section to rotate about the mechanical interface during operation of the gas turbine.Type: GrantFiled: May 15, 2020Date of Patent: July 11, 2023Assignee: GENERAL ELECTRIC COMPANYInventors: Timothy Leo Schelfaut, Thomas P. Joseph, Jonathan E. Coleman, Anthony M. Metz, Stefan K. Fox
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Patent number: 11560840Abstract: Damper engine mount links are disclosed. An example engine assembly includes a core including a fore portion and an aft portion, the fore portion of the core to couple to a fan hub frame, the aft portion of the core to couple to a turbine rear frame or a turbine center frame. The engine assembly further includes a forward mount to couple the fan hub frame to an aircraft, and a damper link to couple the turbine rear frame or the turbine center frame to an aircraft mount.Type: GrantFiled: October 16, 2020Date of Patent: January 24, 2023Assignee: General Electric CompanyInventors: Timothy Leo Schelfaut, Anthony M. Metz, Michael A. Riehle, Jonathan E. Coleman, Illya Emmanuel Arcos Perez, Brian Michael Dixon
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Patent number: 11549554Abstract: Bearings with visually distinct wear indicators are disclosed. An example bearing disclosed herein includes a movable portion, a race to receive the movable portion along a first surface to thereby permit movement of the movable portion within the race, and a liner disposed on the first surface of the race, the liner having a first layer and a second layer, the first layer disposed on top of the second layer, the first layer visually distinctive from the second layer.Type: GrantFiled: April 16, 2020Date of Patent: January 10, 2023Assignee: General Electric CompanyInventors: Timothy Leo Schelfaut, Thomas P. Joseph, Anthony M. Metz, Jonathan E. Coleman
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Patent number: 11407518Abstract: An aircraft and propulsion system are provided. The aircraft includes an airframe including one or more of a fuselage, a wing, or an empennage. The aircraft includes an aircraft propulsion system including a front frame and an aft frame. A front mount link is connected to the airframe and the front frame, and the aft frame is selectively connected to the airframe by an aft mount link.Type: GrantFiled: February 19, 2020Date of Patent: August 9, 2022Assignee: GENERAL ELECTRIC COMPANYInventors: Timothy Leo Schelfaut, Anthony Michael Metz, Jonathan Edward Coleman, Thomas P. Joseph, Brian Michael Dixon
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Publication number: 20220120218Abstract: Damper engine mount links are disclosed. An example engine assembly includes a core including a fore portion and an aft portion, the fore portion of the core to couple to a fan hub frame, the aft portion of the core to couple to a turbine rear frame or a turbine center frame. The engine assembly further includes a forward mount to couple the fan hub frame to an aircraft, and a damper link to couple the turbine rear frame or the turbine center frame to an aircraft mount.Type: ApplicationFiled: October 16, 2020Publication date: April 21, 2022Inventors: Timothy Leo Schelfaut, Anthony M. Metz, Michael A. Riehle, Jonathan E. Coleman, Illya Emmanuel Arcos Perez, Brian Michael Dixon
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Publication number: 20210354838Abstract: Methods, apparatus, systems and articles of manufacture are disclosed to methods and apparatus for gas turbine bending isolation. An example mechanical interface to couple a first section of a gas turbine to a second section of the gas turbine, the mechanical interface comprising a first mating surface disposed on the first section, and a second mating surface disposed on the second section and circumferentially around the first mating surface, wherein the coupling of the first mating surface to the second mating surface enables the first section to rotate about the mechanical interface during operation of the gas turbine.Type: ApplicationFiled: May 15, 2020Publication date: November 18, 2021Inventors: Timothy Leo Schelfaut, Thomas P. Joseph, Jonathan E. Coleman, Anthony M. Metz, Stefan K. Fox
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Publication number: 20210324905Abstract: Bearings with visually distinct wear indicators are disclosed. An example bearing disclosed herein includes a movable portion, a race to receive the movable portion along a first surface to thereby permit movement of the movable portion within the race, and a liner disposed on the first surface of the race, the liner having a first layer and a second layer, the first layer disposed on top of the second layer, the first layer visually distinctive from the second layer.Type: ApplicationFiled: April 16, 2020Publication date: October 21, 2021Inventors: Timothy Leo Schelfaut, Thomas P. Joseph, Anthony M. Metz, Jonathan E. Coleman
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Publication number: 20210261262Abstract: Engine-mounting linkage systems may include a plurality of engine mounting links configured to couple an engine frame to an engine support structure of an aircraft. The plurality of engine-mounting links may include a forward link that is connectable to a forward frame portion of the engine frame and the engine support structure, and an aft link that is connectable to an aft frame portion of the engine frame and the engine support structure. The engine mounting linkage system may include an actuator that is connectable to the engine support structure and one of the plurality of engine-mounting links, or to the engine support structure and the engine frame. The actuator, when actuated, changes an inclination angle ? of at least one of the plurality of engine-mounting links.Type: ApplicationFiled: February 21, 2020Publication date: August 26, 2021Inventors: Timothy Leo Schelfaut, Anthony Michael Metz, Jonathan Edward Coleman, Thomas P. Joseph, Michael C. Borner, Mahesh Khandeparker, Kudum Shinde
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Publication number: 20210261263Abstract: A control system and methods for controlling the position of one or more engine-mounting links of an engine-mounting linkage system are provided. In one aspect, an engine-mounting linkage system includes one or more engine-mounting links that each have an adjustable inclination angle. An inclination angle of a link may be adjusted by an actuator of the control system. One or more controllers of the control system can control the actuator and thus the inclination angle of the link by determining a control command based at least in part on an output received from one or more sensors of the control system. The controllers can then cause the actuator to change the inclination angle of the link based at least in part on the determined control command.Type: ApplicationFiled: February 21, 2020Publication date: August 26, 2021Inventors: Timothy Leo Schelfaut, Anthony Michael Metz, Jonathan Edward Coleman, Thomas P. Joseph
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Publication number: 20210253260Abstract: An aircraft and propulsion system are provided. The aircraft includes an airframe including one or more of a fuselage, a wing, or an empennage. The aircraft includes an aircraft propulsion system including a front frame and an aft frame. A front mount link is connected to the airframe and the front frame, and the aft frame is selectively connected to the airframe by an aft mount link.Type: ApplicationFiled: February 19, 2020Publication date: August 19, 2021Inventors: Timothy Leo Schelfaut, Anthony Michael Metz, Jonathan Edward Coleman, Thomas Peter Joseph, Brian Michael Dixon
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Patent number: 11077954Abstract: A connection assembly for mounting an engine to a mounting structure. The engine is rotatable about an axis of rotation and defines an axial direction extending along the axis of rotation from a forward end to an aft end. The engine has a center of gravity. The connection assembly includes: an engine coupling piece coupled to the engine; and a connection piece connecting the engine coupling piece and the mounting structure, the connection piece being inclined toward the axial direction. A mounting system including the connection assembly is also described.Type: GrantFiled: December 20, 2017Date of Patent: August 3, 2021Assignee: General Electric CompanyInventors: Timothy Leo Schelfaut, Lawrence Jerome Meyer, Anthony Michael Metz, Jonathan Edward Coleman, Thomas Peter Joseph
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Patent number: 10414507Abstract: Systems and methods for adjusting blade tip clearance targets and utilizing the adjusted targets to optimize the clearances between the blade tips and surrounding shrouds of a turbine engine are provided. In one exemplary aspect, one or more engine controllers utilize a machine-learned model to customize blade tip clearance targets based on the way an engine has been uniquely operated in the past for a particular flight mission. Present flight data associated with a present flight of a given flight mission is obtained. A model blade tip clearance target is adjusted based at least in part on the machine-learned model and the present flight data. The machine-learned model is trained at least in part on past flight data indicative of the manner in which the turbine engine has been operated for one or more past flights of the flight mission. An adjusted blade tip clearance target is then generated.Type: GrantFiled: March 9, 2017Date of Patent: September 17, 2019Assignee: General Electric CompanyInventor: Timothy Leo Schelfaut
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Publication number: 20190185170Abstract: A connection assembly for mounting an engine to a mounting structure. The engine is rotatable about an axis of rotation and defines an axial direction extending along the axis of rotation from a forward end to an aft end. The engine has a center of gravity. The connection assembly includes: an engine coupling piece coupled to the engine; and a connection piece connecting the engine coupling piece and the mounting structure, the connection piece being inclined toward the axial direction. A mounting system including the connection assembly is also described.Type: ApplicationFiled: December 20, 2017Publication date: June 20, 2019Inventors: Timothy Leo SCHELFAUT, Lawrence Jerome MEYER, Anthony Michael METZ, Jonathan Edward COLEMAN, Thomas Peter JOSEPH
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Publication number: 20180258785Abstract: Systems and methods for adjusting blade tip clearance targets and utilizing the adjusted targets to optimize the clearances between the blade tips and surrounding shrouds of a turbine engine are provided. In one exemplary aspect, one or more engine controllers utilize a machine-learned model to customize blade tip clearance targets based on the way an engine has been uniquely operated in the past for a particular flight mission. Present flight data associated with a present flight of a given flight mission is obtained. A model blade tip clearance target is adjusted based at least in part on the machine-learned model and the present flight data. The machine-learned model is trained at least in part on past flight data indicative of the manner in which the turbine engine has been operated for one or more past flights of the flight mission. An adjusted blade tip clearance target is then generated.Type: ApplicationFiled: March 9, 2017Publication date: September 13, 2018Inventor: Timothy Leo Schelfaut
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Patent number: 9909441Abstract: A method of operating a clearance control system for a gas turbine engine, includes estimating, in a control module, thermal expansion values of engine components based at least partially on an exhaust gas temperature of the gas turbine engine, determining an estimated clearance value based on the thermal expansion values and ducting airflow for cooling the engine components.Type: GrantFiled: November 11, 2015Date of Patent: March 6, 2018Assignee: General Electric CompanyInventor: Timothy Leo Schelfaut
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Publication number: 20170130602Abstract: A method of operating a clearance control system for a gas turbine engine, includes estimating, in a control module, thermal expansion values of engine components based at least partially on an exhaust gas temperature of the gas turbine engine, determining an estimated clearance value based on the thermal expansion values and ducting airflow for cooling the engine components.Type: ApplicationFiled: November 11, 2015Publication date: May 11, 2017Inventor: Timothy Leo Schelfaut