Patents Assigned to Rolls-Royce North American Technologies, Inc.
  • 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
  • Secure engine communication
    Patent number: 11290301
    Abstract: A method of communication, within a processing system of a gas turbine engine, between a first electronic component and a second electronic component, comprising: generating by the first electronic component, a request, comprising a digital certificate, intern comprising a first host public key and a first client public key, signed with a first host private key, to initiate a trusted communication session with a second electronic component; encrypting at the first electronic component, at least a portion of the request with a first client private key; transmitting the request to the second electronic component; the first host private key and the first host public key defining a first asymmetric keypair and the first client private key and the first client public key defining a second asymmetric keypair.
    Type: Grant
    Filed: November 19, 2019
    Date of Patent: March 29, 2022
    Assignees: ROLLS-ROYCE NORTH AMERICAN TECHNOLOGIES INC., ROLLS-ROYCE CORPORATION
    Inventors: Richard J. Skertic, John J. Costello, Robert T. Duge
  • Gas turbine engine with variable pitch fan and variable pitch compressor geometry
    Patent number: 11286865
    Abstract: A gas turbine engine includes a fan and an engine core that includes a compressor, a combustor, and a turbine. The fan and the compressor include variable pitch geometry. The gas turbine engine further includes a control system configured to adjust the variable pitch geometry of the fan and the compressor to optimize a performance characteristic of the gas turbine engine.
    Type: Grant
    Filed: September 14, 2018
    Date of Patent: March 29, 2022
    Assignee: Rolls-Royce North American Technologies Inc.
    Inventors: Kyle Klein, Michael Karam, Jonathan Sands
  • Method of Controlling Thermal Energy Storage in a Thermal Energy Management System
    Publication number: 20220090868
    Abstract: Methods are provided for controlling thermal energy storage in a thermal energy management system that may operate in response to a variable or high transient heat load. Thermal energy management systems are also provided for controlling thermal energy storage that may operate in response to a variable or high transient heat load.
    Type: Application
    Filed: September 24, 2020
    Publication date: March 24, 2022
    Applicants: Rolls-Royce North American Technologies Inc., Rolls-Royce Corporation
    Inventors: Eric Sean Donovan, Timothy Unton, Peter Gegg
  • Turbine shroud segment with flange-facing perimeter seal
    Patent number: 11280206
    Abstract: A turbine shroud adapted for use in a gas turbine engine includes a plurality of metallic carrier segments and a plurality of blade track segments mounted to corresponding metallic carrier segments. Cooling air is directed onto the blade track segments to cool the blade track segments when exposed to high temperatures in a gas turbine engine.
    Type: Grant
    Filed: September 20, 2019
    Date of Patent: March 22, 2022
    Assignee: Rolls-Royce North American Technologies Inc.
    Inventors: Daniel K. Vetters, Mark O'Leary
  • INTEGRATED CIRCUIT THERMAL MANAGEMENT SYSTEM
    Publication number: 20220087068
    Abstract: An integrated circuit thermal management system includes an enclosure, a heat exchanger, an integrated circuit, a slide having a moveable slide body, an electromagnetic coil, a magneto caloric material and controller circuitry. The heat exchanger is positioned on a first side of the enclosure, and the integrated circuit is positioned on a second side of the enclosure with a temperature sensor configured to generate a temperature signal indicative of a temperature of the integrated circuit. The slide is disposed in the enclosure extending between the heat exchanger and the integrated circuit. The electromagnetic coil and the magnetocaloric material are included on the slide body. The controller is configured to control energization of the magnetic coil and movement of the magnetocaloric material on the slide body between the heat exchanger and the integrated circuit based on the temperature signal.
    Type: Application
    Filed: September 17, 2020
    Publication date: March 17, 2022
    Applicants: Rolls-Royce North American Technologies Inc., Rolls-Royce Corporation
    Inventors: Richard Joseph Skertic, Eric E. Wilson, John Joseph Costello
  • 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
  • Keystoned blade track
    Patent number: 11274567
    Abstract: A blade track for a gas turbine engine includes a plurality of blade track segments. The blade track segments are arranged circumferentially around a central axis to form the blade track.
    Type: Grant
    Filed: April 16, 2019
    Date of Patent: March 15, 2022
    Assignees: Rolls-Royce North American Technologies Inc., Rolls-Royce Corporation
    Inventors: Daniel K. Vetters, Aaron D. Sippel, David J. Thomas, Andrew J. Eifert, Paul A. Davis, Simon L. Jones, Peter Broadhead, Bruce E. Varney, Jeffrey A. Walston, Steven Hillier
  • 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
  • Thermal management system and method for cooling a hybrid electric aircraft propulsion system
    Patent number: 11273925
    Abstract: A method for cooling a hybrid electric aircraft propulsion system comprises transporting a coolant through a two-phase pumped loop (TPPL) in thermal contact with an electrical machine and a plurality of power modules to be cooled, where the TPPL includes: a parallel arrangement of cold plates; an evaporator; a condenser; a first control valve; a liquid receiver; and a pump. A sensor positioned upstream of the cold plates, and in some cases upstream of the liquid receiver, measures pressure and/or temperature of a return stream of the coolant and transmits measurement data to a first controller electrically connected to the first control valve. The first controller regulates flow of a first liquid stream through the first control valve based on the pressure and/or temperature measured by the sensor, thereby keeping the return stream at a temperature within a predetermined temperature range.
    Type: Grant
    Filed: October 14, 2020
    Date of Patent: March 15, 2022
    Assignee: ROLLS-ROYCE NORTH AMERICAN TECHNOLOGIES INC.
    Inventors: Paul O'Meallie, Daniel G. Edwards, Douglas J. Snyder
  • Variable pitch for coordinated control
    Patent number: 11273921
    Abstract: A system is described that includes a turbine engine including an engine fan including one or more variable-pitch blades driven by a shaft, which rotates at a rotational speed which depends on a pitch of the one or more variable-pitch blades of the engine fan. The system further includes a generator configured to produce alternating-current (AC) electricity at a particular frequency relative to the rotational speed of the shaft. The system also includes a propulsor, which includes a propulsor motor and a propulsor fan. The propulsor motor is configured to drive, based on the AC electricity produced by the generator, the propulsor fan. The system includes a controller configured to control the particular frequency of the AC electricity by at least controlling the pitch of the one or more variable-pitch blades of the engine fan and thereby the rotational speed of the generator.
    Type: Grant
    Filed: March 4, 2020
    Date of Patent: March 15, 2022
    Assignee: Rolls-Royce North American Technologies, Inc.
    Inventor: Michael James Armstrong
  • Gas turbine generator speed DC to DC converter control system
    Patent number: 11271501
    Abstract: A system includes a gas turbine operational at a constant rated rotational speed, a speed sensor to measure an actual speed of the gas turbine, a turbine controller to control the gas turbine to the constant rated rotational speed, and a generator coupled with the gas turbine and rotatable to output electric power. The system also includes a DC to DC converter to output a load current on a load bus to supply a load. The DC to DC converter is supplied input electric power from the generator. The system also includes an energy storage device cooperative operable with the DC to DC converter to supply power on the load bus, and a controller to receive the actual speed and adjust an output electrical current set point of the DC to DC converter to compensate for deviation of the actual speed from the constant rated speed of the gas turbine.
    Type: Grant
    Filed: November 21, 2019
    Date of Patent: March 8, 2022
    Assignee: ROLLS-ROYCE NORTH AMERICAN TECHNOLOGIES INC.
    Inventor: Keith D. Noderer
  • Flexible seal for gas turbine engine
    Patent number: 11268477
    Abstract: A coupling adapted for use with a gas turbine engine includes a first flange, a second flange, and a seal assembly. The first flange is coupled with an exhaust end of the gas turbine engine. The second flange is coupled with ducting downstream of the gas turbine engine. The seal assembly extends between the first flange and the second flange and is configured to block the gases from passing radially between the first flange and the second flange.
    Type: Grant
    Filed: October 14, 2019
    Date of Patent: March 8, 2022
    Assignee: Rolls-Royce North American Technologies Inc.
    Inventor: Mark O'Leary
  • Blisk bonded CMC airfoil having attachment
    Patent number: 11268389
    Abstract: A turbine blade is secured with a turbine disk by a retention assembly. The turbine blade includes a blade stem and the disk includes at least one mount post for mounting of the turbine blade. The retention assembly is secured with the disk by forming a diffusion joint with the disk.
    Type: Grant
    Filed: May 14, 2018
    Date of Patent: March 8, 2022
    Assignees: Rolls-Royce North American Technologies Inc., Rolls-Royce Corporation
    Inventors: Ted J. Freeman, Aaron D. Sippel, Bruce E. Varney
  • CMC blade track with integral abradable
    Patent number: 11261750
    Abstract: A system and method for forming a ceramic matrix composite blade track is provided. The method may include stacking a plurality of first plies to form a first porous preform layer, the first plies including a plurality of first ceramic fibers. The method may further include stacking a plurality of second plies to form a second porous preform layer, the second plies including a plurality of second ceramic fibers. The method may further include combining the first porous preform layer and the second porous preform layer to form a unified porous preform. The method may further include forming a structural layer by infiltrating the first porous preform with a first ceramic matrix material, and forming an abradable layer by infiltrating the second porous preform with a second ceramic matrix material.
    Type: Grant
    Filed: March 26, 2018
    Date of Patent: March 1, 2022
    Assignees: ROLLS-ROYCE NORTH AMERICAN TECHNOLOGIES INC., ROLLS-ROYCE CORPORATION
    Inventors: Sean Landwehr, Ted Freeman, Aaron Sippel
  • Turbomachine stage and method of making same
    Patent number: 11261875
    Abstract: A turbomachine comprises a hub and a plurality of blade elements. Each blade element comprises a blade, a platform, and a tang. The plurality of blade elements are arranged circumferentially around the hub, each interlocking or affixed with an adjacent blade element and retained in position by the hub. Each blade elements formed from a single stamped blank to provide an inexpensive method of manufacture, for low cost turbomachinery.
    Type: Grant
    Filed: December 13, 2019
    Date of Patent: March 1, 2022
    Assignee: Rolls-Royce North American Technologies, Inc.
    Inventor: Edward C. Rice
  • Dual mode starter generator
    Patent number: 11261795
    Abstract: A system for starting a turbine engine. The system may comprise a gearbox, a first starter, and a second starter. The gearbox may have a gearbox input shaft. The gearbox may be coupled to the turbine engine. The gearbox input shaft may be rotatively coupled to a spool of the turbine engine. The first starter may be coupled to the gearbox input shaft. The second starter may have a second-starter output shaft. The second-starter output shaft may be coaxial with the gearbox input shaft. The second starter may be coupled to the gearbox input shaft through the first starter.
    Type: Grant
    Filed: November 27, 2018
    Date of Patent: March 1, 2022
    Assignee: Rolls-Royce North American Technologies, Inc.
    Inventors: John Kusnierek, Matthew J. Starr
  • Ceramic seal component for gas turbine engine and process of making the same
    Patent number: 11255206
    Abstract: A ceramic brush seal for a gas turbine engine, and a process for manufacturing the seal are provided. In one example, the process includes deinfiltrating an edge of a plurality of plies having a preimpregnated configuration. The edge is defined by a plurality of ceramic fibers extending away from a portion edge of a matrix infiltrated portion of each of the plies. In another example, the process includes masking an edge of a plurality of plies, the edge being defined by a plurality of ceramic fibers extending away from a portion edge of a body portion of each of the plies, and infiltrating the body portion of the plurality of plies with a ceramic matrix slurry. The plies are stacked, formed into a green body and then fired to form the component. The plies may include oxide/oxide woven ceramic fiber plies.
    Type: Grant
    Filed: March 23, 2020
    Date of Patent: February 22, 2022
    Assignee: ROLLS-ROYCE NORTH AMERICAN TECHNOLOGIES INC.
    Inventor: Ronald Walter Overholser
  • Gas turbine engine with microchannel cooled electric device
    Patent number: 11255215
    Abstract: A gas turbine engine includes an electrical device and a microchannel cooling system in communication with the electrical device to remove heat.
    Type: Grant
    Filed: July 5, 2018
    Date of Patent: February 22, 2022
    Assignee: Rolls-Royce North American Technologies Inc.
    Inventor: Douglas J. Snyder
  • COMPRESSOR TURBINE WHEEL
    Publication number: 20220034227
    Abstract: A turbine wheel for a gas turbine engine including a compressor impeller and a radial inflow turbine integral to or attached to the compressor impeller is provided. A compressor turbine wheel including features to increase surface area of a surface of the compressor impeller and/or the radial inflow turbine and/or a passage to flow air between the compressor impeller and the radial inflow turbine is further provided. Methods for cooling radial inflow turbines integral to compressor impellers are further provided.
    Type: Application
    Filed: August 3, 2020
    Publication date: February 3, 2022
    Applicant: Rolls-Royce North American Technologies Inc.
    Inventors: Douglas David Dierksmeier, Michael A. Karam