Patents by Inventor Todd S. Taylor
Todd S. Taylor 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: 11408368Abstract: A propulsion unit includes a gas turbine engine arranged along an axis and an exhaust system coupled to the gas turbine engine. The gas turbine engine includes an engine core configured to discharge a core flow and a fan configured to be driven by the engine core to discharge a bypass flow. The exhaust system receives the mixed bypass and core flows from the gas turbine engine.Type: GrantFiled: March 31, 2020Date of Patent: August 9, 2022Assignees: Rolls-Royce North American Technologies Inc., Rolls-Royce CorporationInventors: David L. Sutterfield, Todd S. Taylor, Jack D. Petty, Andrew Sanderson, Bryan H. Lerg
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Patent number: 11339744Abstract: A dual flow path exhaust assembly for use with a combined turbofan and ramjet engine includes a turbofan engine exhaust duct, a ramjet engine exhaust duct, a combined outlet, and door configured to move between an open position and a closed position to selectively isolate the turbofan engine exhaust duct from the combined outlet.Type: GrantFiled: February 7, 2020Date of Patent: May 24, 2022Assignee: Rolls-Royce North American Technologies Inc.Inventors: Kenneth M. Pesyna, Todd S. Taylor, Nicholas Metzger, Timothy Roesler
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Patent number: 11339745Abstract: A dual flow path exhaust assembly for use with a combined turbofan and ramjet engine includes a turbofan engine exhaust duct, a ramjet engine exhaust duct, a combined outlet, and door configured to move between an open position and a closed position to selectively isolate the turbofan engine exhaust duct from the combined outlet.Type: GrantFiled: February 7, 2020Date of Patent: May 24, 2022Assignee: Rolls-Royce North American Technologies Inc.Inventors: Nicholas Metzger, Todd S. Taylor, Kenneth M. Pesyna, Timothy Roesler
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Patent number: 11286878Abstract: A propulsion unit includes a gas turbine engine arranged along an axis and an exhaust system coupled to the gas turbine engine. The gas turbine engine includes an engine core configured to discharge a core flow and a fan configured to be driven by the engine core to discharge a bypass flow. The exhaust system receives the mixed bypass and core flows from the gas turbine engine.Type: GrantFiled: March 31, 2020Date of Patent: March 29, 2022Assignees: Rolls-Royce North American Technologies Inc., Rolls-Royce CornorationInventors: Todd S. Taylor, David L. Sutterfield, Jack D. Petty, Andrew Sanderson, Bryan H. Lerg
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Publication number: 20210301761Abstract: A propulsion unit includes a gas turbine engine arranged along an axis and an exhaust system coupled to the gas turbine engine. The gas turbine engine includes an engine core configured to discharge a core flow and a fan configured to be driven by the engine core to discharge a bypass flow. The exhaust system receives the mixed bypass and core flows from the gas turbine engine.Type: ApplicationFiled: March 31, 2020Publication date: September 30, 2021Inventors: Todd S. Taylor, David L. Sutterfield, Jack D. Petty, Andrew Sanderson, Bryan H. Lerg
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Publication number: 20210301760Abstract: A propulsion unit includes a gas turbine engine arranged along an axis and an exhaust system coupled to the gas turbine engine. The gas turbine engine includes an engine core configured to discharge a core flow and a fan configured to be driven by the engine core to discharge a bypass flow. The exhaust system receives the mixed bypass and core flows from the gas turbine engine.Type: ApplicationFiled: March 31, 2020Publication date: September 30, 2021Inventors: David L. Sutterfield, Todd S. Taylor, Jack D. Petty, Andrew Sanderson, Bryan H. Lerg
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Patent number: 10227896Abstract: Systems and methods for suppressing infrared radiation generated by a turbine engine. A system comprises a primary assembly having a center body, a plurality of vanes extending from the center body, an outer radial duct with the plurality of vanes extending therethrough, a structural baffle, and a mixer. The primary assembly is disposed in the exhaust flow path of a turbine engine and encased in ducting and/or an airfoil. An air flow path defined between the center body and outer radial duct is axially spit by an interface rim and flow segregator. The flow segregator segregates engine core flow from ambient air flow.Type: GrantFiled: March 17, 2016Date of Patent: March 12, 2019Assignees: ROLLS-ROYCE CORPORATION, ROLLS-ROYCE NORTH AMERICAN TECHNOLOGIES INC.Inventors: James C. Muskat, Todd S. Taylor, Mike Nesteroff, Eric Donovan, James Carl Loebig
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Patent number: 10024537Abstract: A combustor for use in a gas turbine engine includes a chute and a combustion liner defining a combustion chamber and a chute-receiving aperture that extends through the combustion liner. The chute extends through the chute-receiving aperture of the combustion liner and defines a passageway sized to convey air from an environment outside the combustion chamber through the combustion liner into the combustion chamber.Type: GrantFiled: June 9, 2015Date of Patent: July 17, 2018Assignees: Rolls-Royce North American Technologies Inc., Rolls-Royce CorporationInventors: Todd S. Taylor, Jack D. Petty, Kenneth W. Froemming
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Publication number: 20170342863Abstract: Systems and methods for suppressing infrared radiation generated by a turbine engine. A system comprises a primary assembly having a center body, a plurality of vanes extending from the center body, an outer radial duct with the plurality of vanes extending therethrough, a structural baffle, and a mixer. The primary assembly is disposed in the exhaust flow path of a turbine engine and encased in ducting and/or an airfoil. An air flow path defined between the center body and outer radial duct is axially spit by an interface rim and flow segregator. The flow segregator segregates engine core flow from ambient air flow.Type: ApplicationFiled: March 17, 2016Publication date: November 30, 2017Inventors: James C. Muskat, Todd S. Taylor, Mike Nesteroff, Eric Donovan, James Carl Loebig
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Publication number: 20150362190Abstract: A combustor for use in a gas turbine engine includes a chute and a combustion liner defining a combustion chamber and a chute-receiving aperture that extends through the combustion liner. The chute extends through the chute-receiving aperture of the combustion liner and defines a passageway sized to convey air from an environment outside the combustion chamber through the combustion liner into the combustion chamber.Type: ApplicationFiled: June 9, 2015Publication date: December 17, 2015Inventors: Todd S. Taylor, Jack D. Petty, Kenneth W. Froemming
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Patent number: 8869538Abstract: A gas turbine engine is disclosed having a compressor, combustor, and turbine and a flow path therethrough. A flow path member is disposed between an inner surface of the flow path and a rotating shaft that couples the compressor and turbine. The flow path member directs a cooling fluid along a path to cool a portion of the gas turbine engine between the inner surface and the rotating shaft. The flow path member is retained to permit radially free motion and can also be retained to permit axially free motion. The flow path member can have feed holes that permit the cooling fluid to pass.Type: GrantFiled: December 22, 2011Date of Patent: October 28, 2014Assignee: Rolls-Royce North American Technologies, Inc.Inventors: Sujit Nanda, Todd S. Taylor, Brad Farris
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Publication number: 20130139514Abstract: A method is disclosed herein for reducing binding between a combustor liner of a gas turbine engine and a free-standing ring disposed about the combustor liner. The method comprises the step of disposing a rolling assembly to roll between the combustor liner and the free-standing ring during relative radial displacement.Type: ApplicationFiled: March 7, 2011Publication date: June 6, 2013Inventors: Bruce Edward Varney, Vickie Rae Smiley, Todd S. Taylor, Jack Dwane Petty, SR.
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Publication number: 20120159958Abstract: A gas turbine engine is disclosed having a compressor, combustor, and turbine and a flow path therethrough. A flow path member is disposed between an inner surface of the flow path and a rotating shaft that couples the compressor and turbine. The flow path member directs a cooling fluid along a path to cool a portion of the gas turbine engine between the inner surface and the rotating shaft. The flow path member is retained to permit radially free motion and can also be retained to permit axially free motion. The flow path member can have feed holes that permit the cooling fluid to pass.Type: ApplicationFiled: December 22, 2011Publication date: June 28, 2012Inventors: Sujit Nanda, Todd S. Taylor, Brad Farris
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Patent number: 7900461Abstract: The invention is a combination that includes a gas turbine engine extending along an axis. The gas turbine engine includes an annular combustor with a combustor liner. The combination of the invention also includes a plurality of projections extending from the combustor liner and spaced from one another circumferentially about the axis. The combination of the invention also includes a free-standing ring disposed about the combustor liner and positioned adjacent to the plurality of projections along the axis. The plurality of projections engage a corresponding circumferentially-facing portion of the free-standing ring and circumferentially support the combustor liner while allowing relative radial displacement between the combustor liner and the free-standing ring. The combination of the invention also includes a rolling assembly operably disposed between the free-standing ring and the plurality of projections to reduce binding during the relative radial displacement.Type: GrantFiled: May 31, 2007Date of Patent: March 8, 2011Assignee: Rolls-Royce CorporationInventors: Bruce Edward Varney, Vickie Rae Smiley, Todd S. Taylor, Jack Dwane Petty, Sr.
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Publication number: 20100011780Abstract: The invention is a combination that includes a gas turbine engine extending along an axis. The gas turbine engine includes an annular combustor with a combustor liner. The combination of the invention also includes a plurality of projections extending from the combustor liner and spaced from one another circumferentially about the axis. The combination of the invention also includes a free-standing ring disposed about the combustor liner and positioned adjacent to the plurality of projections along the axis. The plurality of projections engage a corresponding circumferentially-facing portion of the free-standing ring and circumferentially support the combustor liner while allowing relative radial displacement between the combustor liner and the free-standing ring. The combination of the invention also includes a rolling assembly operably disposed between the free-standing ring and the plurality of projections to reduce binding during the relative radial displacement.Type: ApplicationFiled: May 31, 2007Publication date: January 21, 2010Inventors: BRUCE EDWARD VARNEY, Vickie Rae Smiley, Todd S. Taylor, Jack Dwane Petty, SR.