Patents by Inventor Roy D. Fulayter
Roy D. Fulayter 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: 10697320Abstract: A gas turbine engine assembly includes a static component and a rotatable component configured to rotate about a central axis of the gas turbine engine assembly relative to the static component. The gas turbine engine assembly further includes a vibration-dampening system configured to dampen vibration of the gas turbine engine assembly.Type: GrantFiled: January 10, 2018Date of Patent: June 30, 2020Assignee: Rolls-Royce CorporationInventors: Roy D. Fulayter, Michael G. Meyer
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Patent number: 10612401Abstract: A blisk assembly for vibration dampening includes a disk portion extending circumferentially about a central axis of the blisk, a plurality of blades integrally coupled to the disk, and a piezoelectric damping ring that includes a damping ring and a plurality of piezoelectric elements coupled to the damping ring. The disk portion includes a groove configured to receive the piezoelectric damping ring. As a result of centrifugal forces applied to the piezoelectric damping ring during rotation of the blisk assembly, mechanical energy may be generated at one or more of the plurality of piezoelectric elements, which is converted to electrical energy and transmitted to another one or more of the plurality of piezoelectric elements. Accordingly, the one or more of the piezoelectric elements having received the electricity can convert the electricity to mechanical energy to provide vibration damping.Type: GrantFiled: January 19, 2017Date of Patent: April 7, 2020Assignee: Rolls-Royce CorporationInventors: Roy D. Fulayter, Daniel Hoyniak
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Patent number: 10557352Abstract: A blisk assembly for vibration dampening includes a disk portion extending circumferentially about a central axis of the blisk, a plurality of blades integrally coupled to the disk, and a piezoelectric damping ring that includes a damping ring and a plurality of piezoelectric elements coupled to the damping ring. The disk portion includes a groove configured to receive the piezoelectric damping ring. As a result of centrifugal forces applied to the piezoelectric damping ring during rotation of the blisk assembly, mechanical energy may be generated at one or more of the plurality of piezoelectric elements, which is converted to electrical energy and transmitted to another one or more of the plurality of piezoelectric elements. Accordingly, the one or more of the piezoelectric elements having received the electricity can convert the electricity to mechanical energy to provide vibration damping.Type: GrantFiled: September 4, 2015Date of Patent: February 11, 2020Assignee: Rolls-Royce CorporationInventors: Roy D. Fulayter, Daniel Hoyniak
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Patent number: 10539024Abstract: A gas turbine engine airflow member is disclosed having spherical interface shapes at a tip end and a hub end. In one embodiment, the airflow member is a fan blade. The spherical interface shapes can be convex or concave. In one form, the tip end spherical shape is axially shifted aft relative to a hub end. The tip end can include relatively little forward portion in an expanding flow path with predominant portion of the tip end in a contracting flow path. Such a configuration can occur with a midpoint and trailing edge located in the contracting flow path. A center of gravity of a swept airflow member having spherical end shape can be located on a pivot axis of the airflow member. Divot depressions can be provided to permit concave flow path shapes.Type: GrantFiled: July 7, 2017Date of Patent: January 21, 2020Assignees: Rolls-Royce Corporation, Rolls-Royce North American Technologies Inc.Inventors: Roy D. Fulayter, Daniel K. Vetters, Bronwyn Power
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Patent number: 10273903Abstract: A nacelle for a gas turbine jet engine for an aircraft includes plasma actuators that act as flow disruptors to provide boundary layer turbulence when the engine is exposed to air flow that is obtuse or perpendicular to direction of travel of the engine.Type: GrantFiled: March 21, 2016Date of Patent: April 30, 2019Assignees: Rolls-Royce Corporation, Rolls-Royce North American Technologies Inc.Inventors: Roy D. Fulayter, Crawford F. Smith, III
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Patent number: 10253784Abstract: A fan for a gas turbine engine is disclosed. The fan includes a fan disk and a plurality of fan blades coupled to the fan disk. The fan disk is adapted for rotation about a central axis. The fan blades are coupled to the fan disk for rotation therewith about the central axis.Type: GrantFiled: March 9, 2016Date of Patent: April 9, 2019Assignee: Rolls-Royce CorporationInventor: Roy D. Fulayter
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Patent number: 10156244Abstract: A fan assembly for use in a gas turbine engine includes a fan wheel and a plurality of blades extending radially from the fan wheel away from a central axis of the fan assembly. Each of the blades includes a root coupled with the fan wheel and an airfoil extending radially outwardly from the root. The blades are adapted to rotate about the central axis to push air.Type: GrantFiled: February 12, 2016Date of Patent: December 18, 2018Assignee: Rolls-Royce CorporationInventors: Roy D. Fulayter, Jonathan M. Rivers
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Patent number: 10072511Abstract: A nacelle for a gas turbine jet engine for an aircraft includes flow disruptors to provide boundary layer turbulence when the engine is exposed to air flow that is obtuse to direction of travel of the engine.Type: GrantFiled: August 28, 2015Date of Patent: September 11, 2018Assignees: Rolls-Royce North American Technologies Inc., Rolls-Royce CorporationInventors: Roy D. Fulayter, Crawford F. Smith
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Publication number: 20180209345Abstract: A gas turbine engine assembly includes a static component and a rotatable component configured to rotate about a central axis of the gas turbine engine assembly relative to the static component. The gas turbine engine assembly further includes a vibration-dampening system configured to dampen vibration of the gas turbine engine assembly.Type: ApplicationFiled: January 10, 2018Publication date: July 26, 2018Inventors: Roy D. Fulayter, Michael G. Meyer
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Patent number: 9932840Abstract: A rotor for a gas turbine engine includes a central wheel and a plurality of blades that extend outwardly from the central wheel. The blades are non-uniform to reduce flutter and forced response effects induced during operation of a gas turbine engine including the rotor.Type: GrantFiled: April 28, 2015Date of Patent: April 3, 2018Assignee: Rolls-Royce CorporationInventors: Roy D. Fulayter, Jonathan M. Rivers, Matthew Jordan, Daniel E. Molnar
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Publication number: 20170306762Abstract: A gas turbine engine airflow member is disclosed having spherical interface shapes at a tip end and a hub end. In one embodiment, the airflow member is a fan blade. The spherical interface shapes can be convex or concave. In one form, the tip end spherical shape is axially shifted aft relative to a hub end. The tip end can include relatively little forward portion in an expanding flow path with predominant portion of the tip end in a contracting flow path. Such a configuration can occur with a midpoint and trailing edge located in the contracting flow path. A center of gravity of a swept airflow member having spherical end shape can be located on a pivot axis of the airflow member. Divot depressions can be provided to permit concave flow path shapes.Type: ApplicationFiled: July 7, 2017Publication date: October 26, 2017Inventors: Roy D. Fulayter, Daniel K. Vetters, Bronwyn Power
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Publication number: 20170306772Abstract: A blisk assembly for vibration dampening includes a disk portion extending circumferentially about a central axis of the blisk, a plurality of blades integrally coupled to the disk, and a piezoelectric damping ring that includes a damping ring and a plurality of piezoelectric elements coupled to the damping ring. The disk portion includes a groove configured to receive the piezoelectric damping ring. As a result of centrifugal forces applied to the piezoelectric damping ring during rotation of the blisk assembly, mechanical energy may be generated at one or more of the plurality of piezoelectric elements, which is converted to electrical energy and transmitted to another one or more of the plurality of piezoelectric elements. Accordingly, the one or more of the piezoelectric elements having received the electricity can convert the electricity to mechanical energy to provide vibration damping.Type: ApplicationFiled: January 19, 2017Publication date: October 26, 2017Inventors: Roy D. Fulayter, Daniel Hoyniak
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Patent number: 9759095Abstract: An integrated access panel is disclosed that can be used to assist in adjusting a component like a fan blade of a turbofan engine. in one form the integrated access panel is hinged at one end such that the panel remains attached during adjustment of the fan blade. The access panel can be positioned in an angled flow surface of a nacelle such that the fan blade cannot be removed from a wheel without removal of the nacelle or opening of the access panel. The integrated access panel can be spring-loaded and positioned to allow the fan blade to be removed from a wheel by moving the access panel out of the way. Subsequent blade removal can occur by rotation of the wheel to locate another blade in proximity to the access panel.Type: GrantFiled: December 31, 2013Date of Patent: September 12, 2017Assignee: Rolls-Royce CorporationInventors: Jonathan M. Rivers, Roy D. Fulayter
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Patent number: 9708914Abstract: A gas turbine engine airflow member is disclosed having spherical interface shapes at a tip end and a hub end. In one embodiment, the airflow member is a fan blade. The spherical interface shapes can be convex or concave. In one form, the tip end spherical shape is axially shifted aft relative to a hub end. The tip end can include relatively little forward portion in an expanding flow path with predominant portion of the tip end in a contracting flow path. Such a configuration can occur with a midpoint and trailing edge located in the contracting flow path. A center of gravity of a swept airflow member having spherical end shape can be located on a pivot axis of the airflow member. Divot depressions can be provided to permit concave flow path shapes.Type: GrantFiled: December 6, 2013Date of Patent: July 18, 2017Assignees: Rolls-Royce Corporation, Rolls-Royce North American Technologies, Inc.Inventors: Roy D Fulayter, Daniel K Vetters, Bronwyn Power
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Patent number: 9568009Abstract: A flow path surface of a gas turbine engine at the location of a bladed component is disclosed in which the flow path surface includes a cylindrical upstream side and a conical downstream side. The bladed component is located at the intersection of the cylindrical upstream side and the conical downstream side. The cylindrical upstream side can extend from a leading edge of the bladed component, or a point upstream of it, to a location between the leading edge and trailing edge of the component. The conical downstream side can extend past the trailing edge of the bladed component. The bladed component can be a fan blade or a compressor blade.Type: GrantFiled: November 27, 2013Date of Patent: February 14, 2017Assignee: Rolls-Royce CorporationInventors: Bronwyn Power, Roy D. Fulayter, Jonathan M. Rivers
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Publication number: 20160290282Abstract: A nacelle for a gas turbine jet engine for an aircraft includes plasma actuators that act as flow disruptors to provide boundary layer turbulence when the engine is exposed to air flow that is obtuse or perpendicular to direction of travel of the engine.Type: ApplicationFiled: March 21, 2016Publication date: October 6, 2016Inventors: Roy D. Fulayter, Crawford F. Smith, III
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Publication number: 20160265547Abstract: A fan for a gas turbine engine is disclosed. The fan includes a fan disk and a plurality of fan blades coupled to the fan disk. The fan disk is adapted for rotation about a central axis. The fan blades are coupled to the fan disk for rotation therewith about the central axis.Type: ApplicationFiled: March 9, 2016Publication date: September 15, 2016Inventor: Roy D. Fulayter
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Publication number: 20160238034Abstract: A fan assembly for use in a gas turbine engine includes a fan wheel and a plurality of blades extending radially from the fan wheel away from a central axis of the fan assembly. Each of the blades includes a root coupled with the fan wheel and an airfoil extending radially outwardly from the root. The blades are adapted to rotate about the central axis to push air.Type: ApplicationFiled: February 12, 2016Publication date: August 18, 2016Inventors: Roy D. Fulayter, Jonathan M. Rivers
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Publication number: 20160194961Abstract: A blisk assembly for vibration dampening includes a disk portion extending circumferentially about a central axis of the blisk, a plurality of blades integrally coupled to the disk, and a piezoelectric damping ring that includes a damping ring and a plurality of piezoelectric elements coupled to the damping ring. The disk portion includes a groove configured to receive the piezoelectric damping ring. As a result of centrifugal forces applied to the piezoelectric damping ring during rotation of the blisk assembly, mechanical energy may be generated at one or more of the plurality of piezoelectric elements, which is converted to electrical energy and transmitted to another one or more of the plurality of piezoelectric elements. Accordingly, the one or more of the piezoelectric elements having received the electricity can convert the electricity to mechanical energy to provide vibration damping.Type: ApplicationFiled: September 4, 2015Publication date: July 7, 2016Inventors: Roy D. Fulayter, Daniel Hoyniak
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Publication number: 20160097290Abstract: A nacelle for a gas turbine jet engine for an aircraft includes flow disruptors to provide boundary layer turbulence when the engine is exposed to air flow that is obtuse to direction of travel of the engine.Type: ApplicationFiled: August 28, 2015Publication date: April 7, 2016Inventors: Roy D. Fulayter, Crawford F. Smith