Patents Assigned to Rolls-Royce North American Technologies, Inc.
  • THERMAL ENERGY STORAGE AND HEAT REJECTION SYSTEM
    Publication number: 20220205691
    Abstract: A cooling system is provided including a two-phase pump loop and a vapor compression system. The two-phase pump loop cools a thermal load with a first coolant. The vapor compression system is configured to circulate a second coolant. The vapor compression system includes a liquid vapor separator which separates the second coolant into a liquid portion and a gaseous portion. The liquid vapor separator is a thermal energy storage for the two-phase pump loop. A condenser of the two-phase pump loop transfers heat from the first coolant to the liquid portion of the second coolant in the liquid-vapor separator.
    Type: Application
    Filed: March 18, 2022
    Publication date: June 30, 2022
    Applicants: Rolls-Royce Corporation, Rolls-Royce North American Technologies Inc.
    Inventors: Brian Thomas Spangler, Douglas J. Snyder
  • Hybrid propulsion systems
    Patent number: 11370554
    Abstract: An example hybrid aircraft propulsion system includes one or more power units configured to output electrical energy onto one or more electrical busses; a plurality of propulsors; and a plurality of electrical machines, each respective electrical machine configured to drive a respective propulsor of the plurality of propulsors using electrical energy received from at least one of the one or more electrical busses.
    Type: Grant
    Filed: November 8, 2018
    Date of Patent: June 28, 2022
    Assignee: Rolls-Royce North American Technologies, Inc.
    Inventor: Stephen Andrew Long
  • Topology of a solid state power controller with two mid-capacitors
    Patent number: 11374400
    Abstract: A bi-directional direct current (DC) solid state power controller (SSPC) architecture and control method. The SSPC protects a DC distribution system by isolating both the positive and negative buses independently in case of short circuit or ground fault. The SSPC architecture includes two self-heal interleaved capacitors and includes a fast, soft-charging control technique that provides line-isolated charging of the DC bulk capacitor to avoid inrush current when powering up the DC distribution system. The soft-charging function alternately charges one of the two interleaved capacitors, while the other capacitor discharges to the DC bulk capacitor. Repetitive switching results in a charging and discharging process that increases the voltage of the DC bulk capacitor prior to powering up the DC distribution system, while keeping the DC power source isolated from the load.
    Type: Grant
    Filed: December 1, 2020
    Date of Patent: June 28, 2022
    Assignees: ROLLS-ROYCE SINGAPORE PTE. LTD., ROLLS-ROYCE NORTH AMERICAN TECHNOLOGIES, INC.
    Inventors: Chandana Jayampathi Gajanayake, David Loder, Yu Yang, Amit Kumar Gupta
  • Gas turbine engine cooled sump buffer air system
    Patent number: 11365682
    Abstract: A shaft assembly for a gas turbine engine includes a shaft, a bearing, and an annular sump cover. The shaft is arranged along an axis and configured to rotate about the axis. The bearing is coupled to the shaft to facilitate rotation of the shaft about the axis. The annular sump cover is fixed relative to the axis and is configured to allow a lubrication fluid and a buffer air into an air chamber formed between the shaft, the bearing, and the annular sump cover.
    Type: Grant
    Filed: March 4, 2021
    Date of Patent: June 21, 2022
    Assignee: Rolls-Royce North American Technologies Inc.
    Inventors: Kerry J. Lighty, Paul O'Meallie
  • Vapor leak separation and detection system
    Patent number: 11365909
    Abstract: A cooling system includes a first cooling loop, a second cooling loop and a heat exchanger configured to transfer heat from the first cooling loop to the second cooling loop. The first cooling loop includes a vapor/liquid separation feature configured to separate vapor present in the first cooling loop due to a leak between the first cooling loop and the second cooling loop. The first cooling loop also includes a pressure sensor configured to detect an increase in pressure in the first cooling loop that may result from a leak of second coolant into the first cooling loop.
    Type: Grant
    Filed: June 11, 2020
    Date of Patent: June 21, 2022
    Assignee: Rolls-Royce North American Technologies Inc.
    Inventors: Alan W. Smith, Kerry J. Lighty, Paul O'Meallie, Sean Morgan
  • Fan rotor with tapered drive joint
    Patent number: 11365630
    Abstract: A rotor assembly adapted for a gas turbine engine includes a shaft, a wheel, and a retaining nut. The shaft extends along an axis and includes a first tapered surface. The wheel is arranged circumferentially around the shaft and includes a second tapered surface. The retaining nut is fastened to the shaft and applies an axial force to the wheel to couple the wheel with the shaft.
    Type: Grant
    Filed: December 28, 2020
    Date of Patent: June 21, 2022
    Assignee: Rolls-Royce North American Technologies Inc.
    Inventors: Kerry J. Lighty, Paul O'Meallie, Brian R. Bennett, Matthew Jordan
  • Coverage cooling holes
    Patent number: 11359495
    Abstract: A member may have a primary major surface and a secondary major surface. The member may form an array of apertures extending from the primary major surface to the secondary major surface. The array of apertures includes at least one aperture comprising two or more conduits. The axis of each conduit intersects the axis of each other conduit in the aperture. The cross-section of at least one of the conduits perpendicular to its axis may be circular. In some embodiments, an aperture may comprise two or three conduits.
    Type: Grant
    Filed: January 7, 2019
    Date of Patent: June 14, 2022
    Assignees: Rolls- Royce Corporation, Rolls-Royce North American Technologies Inc.
    Inventors: James Loebig, James Christopher Muskat, Christopher Dwayne DeBruhl
  • Gas turbine engine with pyrotechnic air starter
    Patent number: 11346284
    Abstract: A gas turbine engine includes a bypass duct, a compressor, and a pyrotechnic gas conduit. The bypass duct conducts bypass air between an outer bypass wall and an inner bypass wall. The compressor includes an impeller to compress engine air. The pyrotechnic gas conduit is configured to conduct a gas onto the impeller to start the gas turbine engine.
    Type: Grant
    Filed: March 4, 2021
    Date of Patent: May 31, 2022
    Assignee: Rolls-Royce North American Technologies Inc.
    Inventors: Matthew Jordan, Kerry J. Lighty, Paul O'Meallie
  • Turbine blade with abradable tip
    Patent number: 11346232
    Abstract: The present disclosure relates to turbine blades adapted for use in gas turbine engines. In particular, this disclosure is directed to turbine blades that include components made from ceramic matrix composite materials and that incorporate abradable materials.
    Type: Grant
    Filed: April 23, 2018
    Date of Patent: May 31, 2022
    Assignees: Rolls-Royce Corporation, Rolls-Royce North American Technologies Inc.
    Inventors: Aaron D. Sippel, Ted J. Freeman
  • Combustor for a gas turbine engine with ceramic matrix composite heat shield
    Patent number: 11346555
    Abstract: A combustor adapted for use in a gas turbine engine a combustor shell, a heat shield, and a heat shield retainer. The combustor shell is made from metallic materials and is formed to define an internal cavity. The heat shield is formed from ceramic matrix composite materials and is coupled to the dome panel. The heat shield retainer is configured to retain the heat shield to the combustor shell.
    Type: Grant
    Filed: October 8, 2019
    Date of Patent: May 31, 2022
    Assignees: Rolls-Royce Corporation, Rolls-Royce North American Technologies Inc.
    Inventors: Ted J. Freeman, Aaron D. Sippel, Paulo Bazan
  • METHODS AND SYSTEMS FOR MEASURING STATE OF CHARGE OF A PHASE CHANGE MATERIAL THERMAL BATTERY
    Publication number: 20220163270
    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: November 25, 2020
    Publication date: May 26, 2022
    Applicant: Rolls-Royce North American Technologies Inc.
    Inventors: Nader Maharmeh, Craig English, Eric Donovan, Eugene Jansen, Ryan Young
  • Blade retainer for gas turbine engine
    Patent number: 11339674
    Abstract: A blade retainer adapted for use in a gas turbine engine is configured to block axial movement of a blade. The blade retainer includes a first brace, a second brace, and a web that extends between the first brace and the second brace. The blade retainer is configured to block axial movement of a root of the blade out of a blade receiver slot.
    Type: Grant
    Filed: August 14, 2018
    Date of Patent: May 24, 2022
    Assignee: Rolls-Royce North American Technologies Inc.
    Inventor: Patrick Bailey
  • Dual flowpath exhaust for fuel cooling in a hypersonic propulsion system
    Patent number: 11339745
    Abstract: 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: Grant
    Filed: February 7, 2020
    Date of Patent: May 24, 2022
    Assignee: Rolls-Royce North American Technologies Inc.
    Inventors: Nicholas Metzger, Todd S. Taylor, Kenneth M. Pesyna, Timothy Roesler
  • Pressure equalization in a dual flow path exhaust of a hypersonic propulsion system
    Patent number: 11339744
    Abstract: 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: Grant
    Filed: February 7, 2020
    Date of Patent: May 24, 2022
    Assignee: Rolls-Royce North American Technologies Inc.
    Inventors: Kenneth M. Pesyna, Todd S. Taylor, Nicholas Metzger, Timothy Roesler
  • Aircraft with electric propulsor
    Patent number: 11338926
    Abstract: A propulsor includes an electric motor, a fan unit, and a thrust system positioned downstream of and coupled to the fan unit. The electric motor converts electrical power to mechanical rotation to rotationally drive the fan unit and create an air stream directed towards the thrust control system.
    Type: Grant
    Filed: August 10, 2018
    Date of Patent: May 24, 2022
    Assignee: Rolls-Royce North American Technologies Inc.
    Inventor: Douglas D. Dierksmeier
  • ELECTROMAGNETIC CARBON SEAL SYSTEM
    Publication number: 20220154649
    Abstract: A seal system may include a static housing, a carbon seal positioned in the static housing, a runner having a sealing surface aligned with the carbon seal, a number of electromagnets positioned in the static housing, and a controller circuitry. The controller circuitry may control a variable flow of electric current to control an electromagnetic field respectively generated by each of the electromagnets. The controller circuitry may variably apply the electromagnetic field to move at least one of the carbon seal or the runner and correspondingly adjust an applied force loading of an interface of the carbon seal and the sealing surface of the runner.
    Type: Application
    Filed: November 18, 2020
    Publication date: May 19, 2022
    Applicant: Rolls-Royce North American Technologies Inc.
    Inventor: Timothy Unton
  • REFRIGERATION OR TWO PHASE PUMP LOOP COOLING SYSTEM
    Publication number: 20220154980
    Abstract: A cooling system comprising a cooling circuit connecting a heat exchanger and a heat load. The cooling system comprising a first velocity fuse upstream of the heat exchanger or heat load and a second velocity fuse or valve downstream of the heat exchanger or heat load. The heat exchanger or heat load is dynamically isolated from the rest of the cooling system by the first velocity fuse or the second velocity fuse in response to a velocity of a flow of cooling fluid exceeding a respective velocity setting of the first velocity fuse or the second velocity fuse.
    Type: Application
    Filed: November 19, 2020
    Publication date: May 19, 2022
    Applicant: Rolls-Royce North American Technologies Inc.
    Inventor: Timothy Unton
  • System and method of transferring power in a gas turbine engine
    Patent number: 11333080
    Abstract: A method of extracting work from a convertible gas turbine engine having a core flowpath and a bypass flowpath. The method comprises operating the convertible gas turbine engine at a first volumetric flow rate through the core flowpath and a second volumetric flow rate through the bypass flowpath to produce a first work output of the convertible gas turbine engine; extracting the first work output via an unshrouded fan and a shaft at a first fan to shaft extraction ratio; altering the second volumetric flowrate through the bypass flowpath while maintaining the first work output; and extracting the first work output via an unshrouded fan and a shaft at a second fan to shaft extraction ratio.
    Type: Grant
    Filed: December 10, 2019
    Date of Patent: May 17, 2022
    Assignee: Rolls-Royce North American Technologies Inc.
    Inventors: Charles L. McNeil, John Kusnierek
  • THERMAL MANAGEMENT SYSTEM WITH DUAL-USE SERIAL THERMAL ENERGY STORAGE FOR SYSTEM SIZE REDUCTION
    Publication number: 20220151102
    Abstract: Thermal management systems for cooling high-power, low-duty-cycle thermal loads by rejecting heat from the thermal loads to the ambient environment are provided. The thermal management systems include a two-phase pump loop in fluid communication with a vapor compression system loop, evaporators disposed in parallel between the two-phase pump loop and the vapor compression system loop, and a thermal energy storage loop including a cold-temperature tank and a warm-temperature tank thermally coupled to the two-phase pump loop and the vapor-compression system loop. Methods of transferring heat from one or more thermal loads to an ambient environment are also provided.
    Type: Application
    Filed: November 6, 2020
    Publication date: May 12, 2022
    Applicant: Rolls-Royce North American Technologies Inc.
    Inventor: Douglas J. Snyder
  • Gas turbine engine vane end devices
    Patent number: 11326464
    Abstract: A turbomachinery component of a gas turbine engine is disclosed having a number of techniques of reducing the effects of a gap flow between an airfoil member of the gas turbine engine and a wall of the gas turbine engine. The airfoil member can be variable and in one form is a variable turbine vane. In one embodiment a brush seal is included between the vane and the wall. In another form a wear surface is disposed between the vane and the wall. In yet another form a moveable member capable of being actuated to change position can be disposed between the vane and the wall to alter the size of a gap between the two.
    Type: Grant
    Filed: June 26, 2019
    Date of Patent: May 10, 2022
    Assignees: Rolls-Royce North American Technologies Inc., Rolls-Royce Corporation
    Inventors: Linnea Taketa, John Munson, Ted J. Freeman