Patents by Inventor Jack D. Petty

Jack D. Petty 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).

  • Combustor for a gas turbine engine with ceramic matrix composite sealing element
    Patent number: 11466858
    Abstract: A combustor for a gas turbine engine includes a combustor shell, a burner seal, and a burner seal retainer. The combustor shell includes metallic materials and is formed to define an interior combustion space. The burner seal includes ceramic matrix composite materials and is configured to extend through apertures formed in the combustor shell and the heat shield. The burner seal retainer is configured to retain the burner seal to the combustor shell.
    Type: Grant
    Filed: October 11, 2019
    Date of Patent: October 11, 2022
    Assignees: Rolls-Royce Corporation, Rolls-Royce North American Technologies Inc.
    Inventors: Ted J. Freeman, Aaron D. Sippel, Jack D. Petty, Gregory W. Zeaton
  • Reconfigurable exhaust nozzle for a gas turbine engine
    Patent number: 11408368
    Abstract: 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: Grant
    Filed: March 31, 2020
    Date of Patent: August 9, 2022
    Assignees: Rolls-Royce North American Technologies Inc., Rolls-Royce Corporation
    Inventors: David L. Sutterfield, Todd S. Taylor, Jack D. Petty, Andrew Sanderson, Bryan H. Lerg
  • Exhaust nozzle having a compliant shell for a gas turbine engine
    Patent number: 11326551
    Abstract: An exhaust nozzle for use with a gas turbine engine includes an outer shroud, an inner plug spaced radially apart from the outer shroud, and at least one support vane that is coupled to the outer shroud. The outer shroud and the inner plug cooperate to provide an exhaust nozzle flow path therebetween. The at least one support vane interconnects the outer shroud and the inner plug to support the inner plug in the exhaust nozzle flow path.
    Type: Grant
    Filed: February 27, 2020
    Date of Patent: May 10, 2022
    Assignees: Rolls-Royce North American Technologies Inc., Rolls-Royce Corporation
    Inventors: David L. Sutterfield, Jack D. Petty, Bryan H. Lerg, Andrew Sanderson
  • Exhaust nozzle with centerbody support structure for a gas turbine engine
    Patent number: 11313320
    Abstract: An exhaust nozzle for use with a gas turbine engine includes an outer shroud, an inner plug spaced radially apart from the outer shroud, and at least one support vane that is coupled to the outer shroud. The outer shroud and the inner plug cooperate to provide an exhaust nozzle flow path therebetween. The at least one support vane interconnects the outer shroud and the inner plug to support the inner plug in the exhaust nozzle flow path.
    Type: Grant
    Filed: February 27, 2020
    Date of Patent: April 26, 2022
    Assignees: Rolls-Royce North American Technologies Inc., Rolls-Royce Corporation
    Inventors: David L. Sutterfield, Jack D. Petty, Bryan H. Lerg, Andrew Sanderson
  • Variable area nozzle exhaust system with integrated thrust reverser
    Patent number: 11286878
    Abstract: 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: Grant
    Filed: March 31, 2020
    Date of Patent: March 29, 2022
    Assignees: Rolls-Royce North American Technologies Inc., Rolls-Royce Cornoration
    Inventors: Todd S. Taylor, David L. Sutterfield, Jack D. Petty, Andrew Sanderson, Bryan H. Lerg
  • Exhaust nozzle with vane support structure for a gas turbine engine
    Patent number: 11274630
    Abstract: An exhaust nozzle for use with a gas turbine engine includes an outer shroud and a nozzle-plug assembly coupled to the outer shroud. The nozzle-plug assembly includes an inner plug and at least one support vane that is coupled to the outer shroud to support the inner plug in an exhaust nozzle flow path.
    Type: Grant
    Filed: February 27, 2020
    Date of Patent: March 15, 2022
    Assignees: Rolls-Royce North American Technologies Inc., Rolls-Royce Corporation
    Inventors: David L. Sutterfield, Jack D. Petty, Bryan H. Lerg, Andrew Sanderson
  • Combustor liner for a gas turbine engine with ceramic matrix composite components
    Patent number: 11226099
    Abstract: A combustor adapted for use in a gas turbine engine includes a metallic combustor shell forming an interior space, a heat shield, and a liner arranged in the interior space of the metallic case. The liner defines a combustion chamber in which fuel is burned during operation of a gas turbine engine.
    Type: Grant
    Filed: October 11, 2019
    Date of Patent: January 18, 2022
    Assignees: Rolls-Royce Corporation, Rolls-Royce North American Technologies Inc.
    Inventors: Ted J. Freeman, Aaron D. Sippel, Jack D. Petty, Gregory W. Zeaton
  • RECONFIGURABLE EXHAUST NOZZLE FOR A GAS TURBINE ENGINE
    Publication number: 20210301760
    Abstract: 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: Application
    Filed: March 31, 2020
    Publication date: September 30, 2021
    Inventors: David L. Sutterfield, Todd S. Taylor, Jack D. Petty, Andrew Sanderson, Bryan H. Lerg
  • VARIABLE AREA NOZZLE EXHAUST SYSTEM WITH INTEGRATED THRUST REVERSER
    Publication number: 20210301761
    Abstract: 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: Application
    Filed: March 31, 2020
    Publication date: September 30, 2021
    Inventors: Todd S. Taylor, David L. Sutterfield, Jack D. Petty, Andrew Sanderson, Bryan H. Lerg
  • EXHAUST NOZZLE WITH CENTERBODY SUPPORT STRUCTURE FOR A GAS TURBINE ENGINE
    Publication number: 20210270208
    Abstract: An exhaust nozzle for use with a gas turbine engine includes an outer shroud, an inner plug spaced radially apart from the outer shroud, and at least one support vane that is coupled to the outer shroud. The outer shroud and the inner plug cooperate to provide an exhaust nozzle flow path therebetween. The at least one support vane interconnects the outer shroud and the inner plug to support the inner plug in the exhaust nozzle flow path.
    Type: Application
    Filed: February 27, 2020
    Publication date: September 2, 2021
    Inventors: David L. Sutterfield, Jack D. Petty, Bryan H. Lerg, Andrew Sanderson
  • EXHAUST NOZZLE WITH VANE SUPPORT STRUCTURE FOR A GAS TURBINE ENGINE
    Publication number: 20210270207
    Abstract: An exhaust nozzle for use with a gas turbine engine includes an outer shroud and a nozzle-plug assembly coupled to the outer shroud. The nozzle-plug assembly includes an inner plug and at least one support vane that is coupled to the outer shroud to support the inner plug in an exhaust nozzle flow path.
    Type: Application
    Filed: February 27, 2020
    Publication date: September 2, 2021
    Inventors: David L. Sutterfield, Jack D. Petty, Bryan H. Lerg, Andrew Sanderson
  • COMBUSTOR LINER FOR A GAS TURBINE ENGINE WITH CERAMIC MATRIX COMPOSITE COMPONENTS
    Publication number: 20210108798
    Abstract: A combustor adapted for use in a gas turbine engine includes a metallic combustor shell forming an interior space, a heat shield, and a liner arranged in the interior space of the metallic case. The liner defines a combustion chamber in which fuel is burned during operation of a gas turbine engine.
    Type: Application
    Filed: October 11, 2019
    Publication date: April 15, 2021
    Inventors: Ted J. Freeman, Aaron D. Sippel, Jack D. Petty, Gregory W. Zeaton
  • COMBUSTOR FOR A GAS TURBINE ENGINE WITH CERAMIC MATRIX COMPOSITE SEALING ELEMENT
    Publication number: 20210108799
    Abstract: A combustor for a gas turbine engine includes a combustor shell, a burner seal, and a burner seal retainer. The combustor shell includes metallic materials and is formed to define an interior combustion space. The burner seal includes ceramic matrix composite materials and is configured to extend through apertures formed in the combustor shell and the heat shield. The burner seal retainer is configured to retain the burner seal to the combustor shell.
    Type: Application
    Filed: October 11, 2019
    Publication date: April 15, 2021
    Inventors: Ted J. Freeman, Aaron D. Sippel, Jack D. Petty, Gregory W. Zeaton
  • Deflection seal system
    Patent number: 10927957
    Abstract: A seal assembly can accommodate deflection between two components through a cartridge that is slidingly engaged with a slide plate.
    Type: Grant
    Filed: August 22, 2018
    Date of Patent: February 23, 2021
    Assignee: Rolls-Royce North American Technologies Inc.
    Inventors: Michel S. Smallwood, Mark A. Herbertz, Kenneth W. Froemming, Jack D. Petty
  • DEFLECTION SEAL SYSTEM
    Publication number: 20200063869
    Abstract: A seal assembly can accommodate deflection between two components through a cartridge that is slidingly engaged with a slide plate.
    Type: Application
    Filed: August 22, 2018
    Publication date: February 27, 2020
    Inventors: Michel S. Smallwood, Mark A. Herbertz, Kenneth W. Froemming, Jack D. Petty
  • Gas turbine engine with health monitoring system
    Patent number: 10480342
    Abstract: A gas turbine engine includes a turbine having a plurality of vanes, a plurality of blades, a turbine shroud arranged around the vanes and blades, and a turbine case arranged around the turbine shroud. The turbine shroud is sized to block combustion products from passing over the blades without pushing the blades to rotate. The turbine shroud includes a runner arranged around the blades and a carrier arranged around the runner.
    Type: Grant
    Filed: January 19, 2016
    Date of Patent: November 19, 2019
    Assignee: Rolls-Royce Corporation
    Inventors: Bruce E. Varney, Jack D. Petty, Daniel K. Vetters, Eugene Clemens
  • Gas turbine engine with compliant layer for turbine shroud mounts
    Patent number: 10294809
    Abstract: A turbine shroud for use in a gas turbine engine includes a carrier, a blade track segment, and a load-distribution system. The carrier is arranged around a central axis of the turbine shroud. The blade track segment is configured to be supported by the carrier. The load-distribution system is positioned between the carrier and the blade track segment to distribute loads transmitted between the carrier and the blade track segment.
    Type: Grant
    Filed: March 9, 2016
    Date of Patent: May 21, 2019
    Assignees: Rolls-Royce North American Technologies Inc., Rolls-Royce Corporation
    Inventors: Daniel K. Vetters, Jack D. Petty
  • Gas turbine engine with compliant layer for turbine vane assemblies
    Patent number: 10273818
    Abstract: A turbine vane assembly for use in a gas turbine engine includes an endwall, a flow path component, and a load-distribution system. The endwall is arranged around a central axis of the turbine vane assembly. The flow path component is configured to direct fluid flow through the turbine vane assembly. The load-distribution system is positioned between the endwall and the flow path component to distribute loads transmitted between the endwall and the flow path component.
    Type: Grant
    Filed: April 15, 2016
    Date of Patent: April 30, 2019
    Assignees: Rolls-Royce North American Technologies Inc., Rolls-Royce Corporation
    Inventors: Daniel K. Vetters, Jack D. Petty
  • Turbine shroud with mounted full hoop blade track
    Patent number: 10247040
    Abstract: A gas turbine engine includes a turbine having a plurality of vanes, a plurality of blades, a turbine shroud arranged around the vanes and blades, and a turbine case arranged around the turbine shroud. The turbine shroud is sized to block combustion products from passing over the blades without pushing the blades to rotate. The turbine shroud includes a runner arranged around the blades and a carrier arranged around the runner.
    Type: Grant
    Filed: January 19, 2016
    Date of Patent: April 2, 2019
    Assignees: Rolls-Royce North American Technologies Inc., Rolls-Royce Corporation
    Inventors: Bruce E. Varney, Jack D. Petty, Daniel K. Vetters, Eugene Clemens
  • Full hoop blade track with interstage cooling air
    Patent number: 10240476
    Abstract: A gas turbine engine includes a turbine having a plurality of vanes, a plurality of blades, a turbine shroud arranged around the vanes and blades, and a turbine case arranged around the turbine shroud. The turbine shroud is sized to block combustion products from passing over the blades without pushing the blades to rotate. The turbine shroud includes a runner arranged around the blades and a carrier arranged around the runner.
    Type: Grant
    Filed: January 19, 2016
    Date of Patent: March 26, 2019
    Assignees: Rolls-Royce North American Technologies Inc., Rolls-Royce Corporation
    Inventors: Bruce E. Varney, Jack D. Petty, Daniel K. Vetters, Eugene Clemens