Patents by Inventor David L. Sutterfield

David L. Sutterfield 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).

  • Single movement convergent and convergent-divergent nozzle
    Patent number: 11680495
    Abstract: A variable exhaust nozzle for use with a gas turbine engine includes an outer shroud and an inner plug that can move relative to the outer shroud. The relative movement of the inner plug and the outer shroud changes the shape of the variable exhaust nozzle from one that converges in area to one that converges and then diverges in area.
    Type: Grant
    Filed: April 12, 2022
    Date of Patent: June 20, 2023
    Assignee: Rolls-Royce North American Technologies Inc.
    Inventors: Andrew Sanderson, David L. Sutterfield, Bryan H. Lerg
  • 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
  • SINGLE MOVEMENT CONVERGENT AND CONVERGENT-DIVERGENT NOZZLE
    Publication number: 20220235668
    Abstract: A variable exhaust nozzle for use with a gas turbine engine includes an outer shroud and an inner plug that can move relative to the outer shroud. The relative movement of the inner plug and the outer shroud changes the shape of the variable exhaust nozzle from one that converges in area to one that converges and then diverges in area.
    Type: Application
    Filed: April 12, 2022
    Publication date: July 28, 2022
    Inventors: Andrew Sanderson, David L. Sutterfield, 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
  • Single movement convergent and convergent-divergent nozzle
    Patent number: 11319832
    Abstract: A variable exhaust nozzle for use with a gas turbine engine includes an outer shroud and an inner plug that can move relative to the outer shroud. The relative movement of the inner plug and the outer shroud changes the shape of the variable exhaust nozzle from one that converges in area to one that converges and then diverges in area.
    Type: Grant
    Filed: February 27, 2020
    Date of Patent: May 3, 2022
    Assignee: Rolls-Royce North American Technologies Inc.
    Inventors: Andrew Sanderson, David L. Sutterfield, Bryan H. Lerg
  • 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
  • Methodology for minimizing aerodynamic buzz in an exhaust nozzle
    Patent number: 11274631
    Abstract: A variable exhaust nozzle for a gas turbine engine includes an outer shroud and an inner plug. The outer shroud is arranged circumferentially about an axis. The inner plug extends along the axis and is at least partially located within the outer shroud. At least one of the outer shroud and the inner plug are movable selectively to cause a variable area region of the variable exhaust nozzle to change.
    Type: Grant
    Filed: February 27, 2020
    Date of Patent: March 15, 2022
    Assignee: Rolls-Royce North American Technologies Inc.
    Inventors: Andrew Sanderson, David L. Sutterfield, Bryan H. Lerg
  • 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
  • SINGLE MOVEMENT CONVERGENT AND CONVERGENT-DIVERGENT NOZZLE
    Publication number: 20210270145
    Abstract: A variable exhaust nozzle for use with a gas turbine engine includes an outer shroud and an inner plug that can move relative to the outer shroud. The relative movement of the inner plug and the outer shroud changes the shape of the variable exhaust nozzle from one that converges in area to one that converges and then diverges in area.
    Type: Application
    Filed: February 27, 2020
    Publication date: September 2, 2021
    Inventors: Andrew Sanderson, David L. Sutterfield, Bryan H. Lerg
  • 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
  • METHODOLOGY FOR MINIMIZING AERODYNAMIC BUZZ IN AN EXHAUST NOZZLE
    Publication number: 20210270206
    Abstract: A variable exhaust nozzle for a gas turbine engine includes an outer shroud and an inner plug. The outer shroud is arranged circumferentially about an axis. The inner plug extends along the axis and is at least partially located within the outer shroud. At least one of the outer shroud and the inner plug are movable selectively to cause a variable area region of the variable exhaust nozzle to change.
    Type: Application
    Filed: February 27, 2020
    Publication date: September 2, 2021
    Inventors: Andrew Sanderson, David L. Sutterfield, 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
  • Coanda device for a round exhaust nozzle
    Patent number: 10563613
    Abstract: A gas turbine engine system is disclosed herein. The gas turbine engine system includes an engine core configured to discharge air through an exhaust nozzle along a central axis and a thrust director arranged near the exhaust nozzle and configured to redirect the discharge air by applying flow to the discharge air near the exhaust nozzle.
    Type: Grant
    Filed: July 26, 2016
    Date of Patent: February 18, 2020
    Assignee: Rolls-Royce North American Technologies Inc.
    Inventors: David L. Sutterfield, Bryan H. Lerg
  • Seals for a gas turbine engine
    Patent number: 10480336
    Abstract: A sealing assembly may include a support, an engine component, and a seal. The engine component may be mounted relative to the support to define a gap between the engine component and the support. The seal may be arranged between the support and the engine component to block gasses from passing through the gap. The seal may be adapted to compress and expand to fill the gap during expansion and contraction of the adjacent components that occurs during operation of a gas turbine engine including the sealing assembly.
    Type: Grant
    Filed: December 12, 2017
    Date of Patent: November 19, 2019
    Assignee: Rolls-Royce North American Technologies Inc.
    Inventors: David L. Sutterfield, Gregory W. Zeaton
  • Nozzle support system
    Patent number: 10451003
    Abstract: A nozzle support system for a nozzle of a gas turbine includes an outer ring, an inner ring disposed within the outer ring, and a plurality of links pivotally attaching the outer ring to the inner ring. Each one of the links may have an outer end that is pivotally attached to the outer ring, and each one of the links may have an inner end that is pivotally attached to the inner ring, such that the inner ring moves along a longitudinal axis of the outer ring.
    Type: Grant
    Filed: October 27, 2015
    Date of Patent: October 22, 2019
    Assignee: Rolls-Royce North American Technologies, Inc.
    Inventors: David L. Sutterfield, Randall E. Yount
  • Pivoting stowable spray bar
    Patent number: 10385781
    Abstract: An exemplary fuel spray bar system can include a conduit, which is pivotally attached to an engine frame and configured to deliver fuel from a fuel line to an engine flow path. The system further includes a drive mechanism, which is configured to move the conduit between a stowed position and a deployed position.
    Type: Grant
    Filed: December 14, 2015
    Date of Patent: August 20, 2019
    Assignee: Rolls-Royce North American Technologies, Inc.
    Inventors: David L. Sutterfield, William J. Dionne
  • SEALS FOR A GAS TURBINE ENGINE
    Publication number: 20180100405
    Abstract: A sealing assembly may include a support, an engine component, and a seal. The engine component may be mounted relative to the support to define a gap between the engine component and the support. The seal may be arranged between the support and the engine component to block gasses from passing through the gap. The seal may be adapted to compress and expand to fill the gap during expansion and contraction of the adjacent components that occurs during operation of a gas turbine engine including the sealing assembly.
    Type: Application
    Filed: December 12, 2017
    Publication date: April 12, 2018
    Inventors: David L. Sutterfield, Gregory W. Zeaton