Patents Assigned to Rolls-Royce North American
  • Gas turbine engine with fan track liner having triply periodic minimal surface reinforcement
    Patent number: 12084977
    Abstract: A fan case assembly adapted for use with a gas turbine engine includes a fan case and a fan track liner. The fan case that extends circumferentially about an axis. The fan track liner extends circumferentially at least partway about the axis and is coupled with the fan case. The fan track liner includes an abradable section and a core section located radially outward of the abradable section. The core section defines a triply periodic minimal surface geometry.
    Type: Grant
    Filed: October 10, 2023
    Date of Patent: September 10, 2024
    Assignee: Rolls-Royce North American Technologies Inc.
    Inventor: Timothy Unton
  • Adjustable air flow plenum with sliding doors for a fan of a gas turbine engine
    Patent number: 12078070
    Abstract: A fan case assembly adapted for use with a gas turbine engine includes a case at extends circumferentially at least partway about an axis of the gas turbine engine and a plurality of vanes. The case is formed to define a plenum that that extends circumferentially at least partway about the axis. The plurality of vanes are arranged in the plenum and spaced apart circumferentially about the axis.
    Type: Grant
    Filed: August 16, 2023
    Date of Patent: September 3, 2024
    Assignees: Rolls-Royce North American Technologies Inc., Rolls-Royce Corporation
    Inventors: Robert W. Heeter, Daniel E. Molnar, Jr., Jonathan M. Rivers
  • Anti-ice mixing unit utilizing bleed air for a gas turbine engine
    Patent number: 12078103
    Abstract: A thermal management system for a gas turbine engine includes an inlet, a compressor, a mixing unit, and a fuel source. The compressor includes a low pressure stage and a high pressure stage. The mixing unit includes a first valve port fluidically connected to a low pressure bleed line of the compressor and a high pressure bleed line of the compressor and having an adjustable inlet gate on each of these lines and an outlet fluidically connected to the inlet of the engine to prevent ice accretion in the inlet or de-ice the inlet. The fuel source is configured to provide fuel to the mixing unit to actuate the adjustable inlet gates to regulate the amounts of low pressure bleed air and high pressure bleed air directed to the outlet.
    Type: Grant
    Filed: August 4, 2023
    Date of Patent: September 3, 2024
    Assignee: Rolls-Royce North American Technologies Inc.
    Inventor: Rex M. Little
  • Inlets for gas turbine engine bypass duct heat exchangers
    Patent number: 12071913
    Abstract: A bypass duct assembly for a gas turbine engine includes a bypass duct, a heat exchanger assembly, and an inlet cowl. The bypass duct is configured to direct bypass air around an engine core of the gas turbine engine. The heat exchanger assembly includes a heat exchanger located in the bypass duct and configured to transfer heat to the bypass air. The inlet cowl is coupled with the bypass duct and the heat exchanger assembly. The inlet cowl includes a cowl duct configured to collect a first portion of the bypass air and conduct the first portion of the bypass air into the heat exchanger and a flow diverter that guides a second portion of the bypass air around the heat exchanger.
    Type: Grant
    Filed: July 31, 2023
    Date of Patent: August 27, 2024
    Assignee: Rolls-Royce North American Technologies Inc.
    Inventors: Patrick C. Sweeney, Douglas J. Snyder, Kerry J. Lighty, Scott Schwenker
  • Multiple intake distortion adaptive fan for gas turbine engine
    Patent number: 12065258
    Abstract: An aircraft includes a duct system configured to receive a flow of air therethrough and a gas turbine engine. The duct system includes a main duct and inlet ducts arranged fluidly upstream of the main duct so as to conduct the flow of air from the inlet ducts into the main duct. The gas turbine engine in downstream fluid communication with the main duct.
    Type: Grant
    Filed: January 25, 2023
    Date of Patent: August 20, 2024
    Assignees: Rolls-Royce North American Technologies Inc., Rolls-Royce Corporation
    Inventors: Robert W. Heeter, Daniel E. Molnar, Jr., Kathryn A. Sontag, Michael G. Meyer
  • Adaptive vertical lift engine (AVLE) fan
    Patent number: 12065967
    Abstract: A turbofan engine has a fan portion in fluid communication with a core stream and a bypass stream of air separated by splitters disposed both upstream and downstream of the fan portion. A blade splitter (shroud) on the fan partially spans the fan blade thus separating the core and bypass streams downstream while leaving a gap upstream for communication between the flows. The communication gap expands the operational range of the fan over fans without the communication gap.
    Type: Grant
    Filed: December 29, 2022
    Date of Patent: August 20, 2024
    Assignee: Rolls-Royce North American Technologies Inc.
    Inventor: William Barry Bryan
  • Distributed electric and hybrid fans for distortion tolerance of turbofan engines
    Patent number: 12065979
    Abstract: A gas turbine engine comprises a primary fan and an engine core. The primary fan is mounted for rotation about an axis of the gas turbine engine to provide thrust. The engine core is coupled to the primary fan and configured to drive the primary fan about the axis to cause the fan to push air to provide thrust for the gas turbine engine.
    Type: Grant
    Filed: December 27, 2022
    Date of Patent: August 20, 2024
    Assignees: Rolls-Royce North American Technologies Inc., Rolls-Royce Corporation
    Inventors: Robert W. Heeter, Daniel E. Molnar, Jr., Kathryn A. Sontag, Michael G. Meyer
  • Rotating detonation augmentors with adjustable throats for gas turbine engines
    Patent number: 12065965
    Abstract: A gas turbine engine includes a bypass duct and a rotating detonation augmentor. The bypass duct is configured to conduct air through a flow path arranged around an engine core of the gas turbine engine to provide thrust for propelling the gas turbine engine. The rotating detonation augmentor is located in the bypass duct and configured to be selectively operated to detonate fuel and a portion of the air to increase the thrust for propelling the gas turbine engine.
    Type: Grant
    Filed: August 15, 2023
    Date of Patent: August 20, 2024
    Assignees: Rolls-Royce North American Technologies Inc., Rolls-Royce Corporation
    Inventors: Victor L. Oechsle, Kenneth M. Pesyna, Bryan H. Lerg, Michael C. Monzella, Zachary A. Rauch, Michael Moser
  • Adjustable depth tip treatment with axial member with pockets for a fan of a gas turbine engine
    Patent number: 12066035
    Abstract: A fan case assembly adapted for use with a gas turbine engine includes a case at extends circumferentially at least partway about an axis of the gas turbine engine and a plurality of vanes. The case is formed to define a channel that that extends circumferentially at least partway about the axis. The plurality of vanes are arranged in the channel and spaced apart circumferentially about the axis.
    Type: Grant
    Filed: August 16, 2023
    Date of Patent: August 20, 2024
    Assignees: Rolls-Royce North American Technologies Inc., Rolls-Royce Corporation
    Inventors: Robert W. Heeter, Daniel E. Molnar, Jr., Michael S. Krautheim
  • Gas turbine engine system with motor-generator
    Patent number: 12060833
    Abstract: In some examples, a gas turbine engine including a high-pressure (HP) spool assembly including a HP shaft, a HP compressor and HP turbine; a lower pressure (LP) spool assembly including a LP shaft and LP turbine; a motor-generator coupled to the LP shaft; and a controller. The controller is configured to control the motor-generator to operate in a motor mode to apply torque the LP shaft during a starting of the HP spool assembly, and control the motor-generator to operate in a generator mode for a least a period of time following the starting of the HP spool assembly.
    Type: Grant
    Filed: August 10, 2021
    Date of Patent: August 13, 2024
    Assignee: Rolls-Royce North American Technologies, Inc.
    Inventors: Sean Andrew Morgan, Timothy Unton, Alan W. Smith, Adam Lagrange, James Christopher Muskat
  • CMAS resistant thermal barrier coating system
    Patent number: 12043550
    Abstract: An article may include a substrate and a coating system on the substrate. The coating system may include a thermal barrier coating (TBC) layer and a CMAS resistant layer on the TBC layer. The CMAS layer includes a rare-earth (RE) monosilicate composition including a plurality of RE metal cations, wherein RE monosilicate composition is configured to react with CMAS to form a reaction product including a RE apatite phase with a RE2O3·SiO2 composition, wherein the RE of the RE2O3·SiO2 composition includes at least one of the plurality of RE metal cations of the RE monosilicate.
    Type: Grant
    Filed: June 17, 2021
    Date of Patent: July 23, 2024
    Assignees: Rolls-Royce Corporation, Rolls-Royce North American Technologies, Inc.
    Inventors: Robert Alexander Sean Golden, Adam Lee Chamberlain, Matthew R. Gold
  • Aircraft with thermal energy storage system with bypass control
    Patent number: 12025057
    Abstract: A thermal energy system for use with an aircraft includes a cooling loop and a cooler. The cooling loop includes a fluid conduit and a pump configured to move fluid through the fluid conduit to transfer heat from a heat source to the fluid in the fluid conduit to cool the heat source. The cooler includes an air-stream heat exchanger located in a duct and is in thermal communication with the fluid conduit to transfer heat between the fluid in the cooling loop and the air passing through the duct.
    Type: Grant
    Filed: April 7, 2022
    Date of Patent: July 2, 2024
    Assignee: Rolls-Royce North American Technologies Inc.
    Inventor: Douglas J. Snyder
  • Plug nozzle for high mach gas turbine engines
    Patent number: 12025074
    Abstract: A propulsion unit includes a gas turbine engine and an exhaust nozzle coupled to an aft end of the gas turbine engine. The exhaust nozzle is configured to interact with exhaust gases exiting the gas turbine engine in an aft direction. The exhaust nozzle includes an outer nozzle case and an inner plug that cooperate to define an exhaust flow path therebetween. The exhaust nozzle is configured to manipulate the exhaust gases to provide different thrust capabilities for the gas turbine engine.
    Type: Grant
    Filed: August 14, 2023
    Date of Patent: July 2, 2024
    Assignee: Rolls-Royce North American Technologies Inc.
    Inventors: Kenneth M. Pesyna, Andrew M. Simonich
  • Distributed electric tip fans for distortion tolerance of turbofan engines
    Patent number: 12025059
    Abstract: A gas turbine engine comprises a primary fan and an engine core. The primary fan is mounted for rotation about an axis of the gas turbine engine to provide thrust. The engine core is coupled to the primary fan and configured to drive the primary fan about the axis to cause the fan to push air to provide thrust for the gas turbine engine.
    Type: Grant
    Filed: December 27, 2022
    Date of Patent: July 2, 2024
    Assignees: Rolls-Royce North American Technologies Inc., Rolls-Royce Corporation
    Inventors: Robert W. Heeter, Daniel E. Molnar, Jr., Kathryn A. Sontag, Michael G. Meyer
  • METHODS AND SYSTEMS FOR MEASURING STATE OF CHARGE OF A PHASE CHANGE MATERIAL THERMAL BATTERY
    Publication number: 20240210121
    Abstract: A thermal battery system may be provided comprising: a vessel comprising a phase change material and a gas; a heat exchanger configured to transfer heat to and/or from the phase change material; a temperature sensor configured to detect an indication of a temperature of the gas; a pressure sensor configured to detect an indication of a pressure of the gas; and a processor configured to determine a state of charge of the thermal battery system from the indication of the pressure and the indication of the temperature of the gas.
    Type: Application
    Filed: January 26, 2024
    Publication date: June 27, 2024
    Applicant: Rolls-Royce North American Technologies Inc.
    Inventors: Nader Maharmeh, Craig English, Eric Donovan, Eugene Jansen, Ryan Young
  • Clocking balance weight rotor assembly for gas turbine engines
    Patent number: 12018579
    Abstract: A rotor assembly includes a first rotor arranged circumferentially about a central axis. A second rotor is arranged circumferentially about the central axis and couples to the first rotor for rotation therewith. A balance weight located in a space radially between the first rotor and the second rotor.
    Type: Grant
    Filed: August 8, 2023
    Date of Patent: June 25, 2024
    Assignee: Rolls-Royce North American Technologies Inc.
    Inventor: Ryan C. Humes
  • Rotor assembly for gas turbine engines with replaceable balance weight pins
    Patent number: 12018580
    Abstract: A rotor assembly includes a first rotor arranged circumferentially about a central axis. A second rotor is arranged circumferentially about the central axis and couples to the first rotor for rotation therewith. A balance weight assembly is configured to balance a weight distribution of the rotor assembly.
    Type: Grant
    Filed: August 8, 2023
    Date of Patent: June 25, 2024
    Assignee: Rolls-Royce North American Technologies Inc.
    Inventor: Ryan C. Humes
  • Adjustable depth tip treatment with rotatable ring with pockets for a fan of a gas turbine engine
    Patent number: 12018621
    Abstract: A fan case assembly adapted for use with a gas turbine engine includes a case at extends circumferentially at least partway about an axis of the gas turbine engine and a plurality of vanes. The case is formed to define a channel that extends circumferentially at least partway about the axis. The plurality of vanes are arranged in the channel and spaced apart circumferentially about the axis.
    Type: Grant
    Filed: August 16, 2023
    Date of Patent: June 25, 2024
    Assignees: Rolls-Royce North American Technologies Inc., Rolls-Royce Corporation
    Inventors: Robert W. Heeter, Daniel E. Molnar, Jr., Michael S. Krautheim
  • Windmill synchronization in an electric propulsion system
    Patent number: 12017788
    Abstract: A propulsion system is described that includes an electrical bus, a generator configured to provide electrical power to the electrical bus, a plurality of propulsors configured to provide thrust by simultaneously being driven by the electrical power at the electrical bus, and a controller. The controller is configured to synchronize a rotational speed of an individual propulsor from the plurality of propulsors with a rotational speed of the generator after the individual propulsor has become unsynchronized with the rotational speed of the generator by controlling at least one of the rotational speed of the generator, nozzle area of the individual propulsor, or a pitch angle of the individual propulsor.
    Type: Grant
    Filed: August 30, 2021
    Date of Patent: June 25, 2024
    Assignee: Rolls-Royce North American Technologies, Inc.
    Inventors: Michael James Armstrong, Mark Jon Blackwelder
  • Thermal management system with impact resistant packaging
    Patent number: 12022636
    Abstract: A weapons system includes a high-energy beam unit and a power and thermal management system. The high-energy beam unit is configured to discharge high-energy beams. The power and thermal management system is configured to supply power to the high-energy beam unit and to manage the temperature of the high-energy beam unit.
    Type: Grant
    Filed: February 8, 2021
    Date of Patent: June 25, 2024
    Assignee: Rolls-Royce North American Technologies Inc.
    Inventor: Tim Unton