Patents Assigned to Rolls-Royce North American Technologies, Inc.
  • BLOW DOWN IMPINGEMENT START SYSTEM
    Publication number: 20210215100
    Abstract: A start system for an expendable gas turbine engine is provided. The start system may include: a tank configured to store a pressurized gas comprising oxygen; a non-pyrotechnic igniter in communication with a combustion chamber of the expendable gas turbine engine; a starter tube configured to feed the pressurized gas from the tank into the combustion chamber; and a valve configured to regulate a flow of the pressurized gas from the tank into the starter tube; wherein, the start system is configured to startup the expendable gas turbine engine by the flow of the pressurized gas from the tank, through the valve and the starter tube, into the combustion chamber and, from the combustion chamber, into a plurality of turbine blades of the expendable gas turbine engine, and by ignition, by the non-pyrotechnic igniter, of fuel injected into the combustion chamber.
    Type: Application
    Filed: January 14, 2020
    Publication date: July 15, 2021
    Applicant: Rolls-Royce North American Technologies Inc.
    Inventors: Michael John Head, Michael Karam, Timothy C. Roesler
  • HIGH HEAT FLUX POWER ELECTRONICS COOLING DESIGN
    Publication number: 20210210361
    Abstract: A base plate for cooling a power electronics device is provided, the base plate comprising cooling fins, the base plate configured to receive the power electronics device directly above the cooling fins, the cooling fins integral to the base plate, the base plate configured to conduct a liquid coolant past the cooling fins
    Type: Application
    Filed: January 3, 2020
    Publication date: July 8, 2021
    Applicant: Rolls-Royce North American Technologies Inc.
    Inventor: Douglas J. Snyder
  • ADAPTIVE CONTROL OF COATING THICKNESS
    Publication number: 20210207947
    Abstract: An example method that includes receiving, by a computing device, a geometry of the component that includes a plurality of locations on a surface of the component; determining, by the computing device, a respective target thickness of the coating for each respective location of the plurality of locations based on a target coated component geometry and the geometry of the component; and determining, by the computing device, a number of passes or velocity of a coating device for each respective position of a plurality of positions to achieve the respective target thickness for each respective location.
    Type: Application
    Filed: March 19, 2021
    Publication date: July 8, 2021
    Applicant: Rolls-Royce North American Technologies, Inc.
    Inventors: Keith Bourne, Matthew R. Gold, Marshall Louis Sweet, Frol Periverzov, Benjamin Zimmerman
  • Method and process for securing an executable image
    Patent number: 11057240
    Abstract: Control systems and methods for securely loading software in a power control system. In some examples, the control system includes a computing device and a plurality of security modules. The computing device may obtain and divide an executable image into a plurality of images. The computing device may generate a control hash as a function of the plurality of images, and record the control hash. The computing device may store each of the plurality of images in a plurality of security modules. At boot up, the computing device may load, from each security module, the stored image, and store each image to a memory device. The computing device may generate a hash based on the stored images, and compare the generated hash to the recorded control hash. Based on the comparison, the computing device may allow execution of the executable image.
    Type: Grant
    Filed: February 22, 2019
    Date of Patent: July 6, 2021
    Assignees: ROLLS-ROYCE NORTH AMERICAN TECHNOLOGIES INC., ROLLS-ROYCE CORPORATION
    Inventors: Richard Joseph Skertic, John Joseph Costello
  • Brazed blade track for a gas turbine engine
    Patent number: 11053806
    Abstract: A blade track for a gas turbine engine includes segments and joints that couple the segments together. Each segment extends part-way around a central axis of the engine and the joints couple together adjacent segments to form a full hoop.
    Type: Grant
    Filed: October 23, 2019
    Date of Patent: July 6, 2021
    Assignees: Rolls-Royce Corporation, Rolls-Royce North American Technologies Inc.
    Inventors: Aaron D. Sippel, Daniel K. Vetters, Jun Shi, David J. Thomas, Andrew J. Eifert, Peter Broadhead
  • Gas turbine engine composite vane assembly and method for making the same
    Patent number: 11053801
    Abstract: A gas turbine engine composite vane assembly and method for making same are disclosed. The method includes providing at least two gas turbine engine airfoil composite preform components. The airfoil composite preform components are interlocked with a first locking component so that mating faces of the airfoil composite preform components face each other. A filler material is inserted between the mating surfaces of the airfoil composite preform components.
    Type: Grant
    Filed: November 27, 2018
    Date of Patent: July 6, 2021
    Assignees: Rolls-Royce Corporation, Rolls-Royce North American Technologies Inc.
    Inventors: Richard C. Uskert, David J. Thomas, Wayne S. Steffier, Robert J. Shinavski, Adam L. Chamberlain
  • Turbine shroud assembly with ceramic matrix composite blade track segments and full hoop carrier
    Patent number: 11053817
    Abstract: A turbine shroud adapted for use in a gas turbine engine includes a blade track segment and a carrier. The blade track segment includes an arcuate shroud wall that extends circumferentially partway around an axis and a mount post that extends radially outward away from the shroud wall. The carrier is coupled with the mount post of the blade track segment to support the blade track segment.
    Type: Grant
    Filed: November 19, 2019
    Date of Patent: July 6, 2021
    Assignees: Rolls-Royce Corporation, Rolls-Royce North American Technologies Inc.
    Inventors: Ted J. Freeman, Aaron D. Sippel, Paulo Bazan
  • Gas turbine engine fuel additive control system
    Patent number: 11041446
    Abstract: A gas turbine engine fuel additive control system includes a sensor positioned to sense an operational parameter of a gas turbine engine that includes a compressor section, a combustion section, and a turbine section. The system also includes a control valve positioned to supply a fuel additive to a fuel line. The fuel line contains fuel for supply to the combustion section of the gas turbine engine to which the fuel additive is selectively added by injection into the fuel line. The system also includes a controller configured to monitor the operational parameter in real time during operation of the gas turbine engine and adjust the control valve to dynamically modulate an amount of the fuel additive being supplied in the fuel in accordance with operation of the gas turbine engine.
    Type: Grant
    Filed: June 21, 2018
    Date of Patent: June 22, 2021
    Assignees: ROLLS-ROYCE CORPORATION, ROLLS-ROYCE NORTH AMERICAN TECHNOLOGIES INC.
    Inventors: Kenneth L. Graham, John Joseph Costello, Richard Joseph Skertic
  • Recuperated superheat return trans-critical vapor compression system
    Patent number: 11035595
    Abstract: Methods and systems for recuperated superheat return are provided. A coolant is supplied in a vapor state to a compressor. The coolant compressed by the compressor is cooled with a gas cooler. The coolant cooled by the gas cooler is supplied to an inlet of a high pressure side of a recuperator. The coolant from an outlet of the high pressure side of the recuperator is supplied to a portion of a coolant circuit. The coolant is supplied back from the portion of the coolant circuit to an inlet of a low pressure side of the recuperator. The coolant in the low pressure side of the recuperator is heated with thermal energy transferred by the recuperator from the coolant in the high pressure side of the recuperator. The coolant in the vapor state from an outlet of the low pressure side of the recuperator is supplied to the compressor.
    Type: Grant
    Filed: May 8, 2018
    Date of Patent: June 15, 2021
    Assignee: ROLLS-ROYCE NORTH AMERICAN TECHNOLOGIES INC.
    Inventors: Eugene C. Jansen, Eric S. Donovan
  • Method to pilot using flexible profile
    Patent number: 11035241
    Abstract: A fan assembly for use in a gas turbine engine of an aircraft includes a fan disk having a number of fan blades and a windage shield coupled to the fan disk to move therewith. The fan assembly supplies air for use in the engine. The windage shield rotates with the fan disk during operation of the gas turbine engine and directs air supplied by the fan blade.
    Type: Grant
    Filed: August 5, 2019
    Date of Patent: June 15, 2021
    Assignee: Rolls-Royce North American Technologies Inc.
    Inventors: Samuel J. Lacombe, Patrick E. Bailey
  • Optical interface and distributed fiber optic communication network for controlling a gas turbine engine and method
    Patent number: 11038591
    Abstract: A distributed fiber optic communication network for controlling a gas turbine engine includes a computation module and an input/output (I/O) module. The computation module and the I/O module are connected via the communication network. The communication network comprises multi-mode fiber optic cables, wherein data is transferred thereon on multiple frequency bands. The frequency bands range from about 300 nm to about 1550 nm. A method of frequency hopping is provided in which communication band instructions are stored locally on nodes of the communication network and may include communication band instructions transmitted to nodes of the communication network on a dedicated band.
    Type: Grant
    Filed: June 28, 2019
    Date of Patent: June 15, 2021
    Assignees: Rolls-Royce Corporation, Rolls-Royce North American Technologies, Inc.
    Inventors: John Joseph Costello, Richard Joseph Skertic
  • Compressed gas integrated power and thermal management system
    Patent number: 11028773
    Abstract: Systems and methods are provided that use compressed gas to power a turbine, which in turn powers a generator, where an expansion of the compressed gas provides cooling for an electrical load that is powered by the generator.
    Type: Grant
    Filed: September 24, 2018
    Date of Patent: June 8, 2021
    Assignee: Rolls-Royce North American Technologies Inc.
    Inventors: Michael Karam, Robert Duge
  • Reduced leakage air seal
    Patent number: 11028715
    Abstract: An air seal for a jet turbine engine with an upper stator, lower stator and finned turbine disk. The thermal expansion of the stators may be regulated by a control ring, which has a lower rate of thermal expansion that the stators, to prevent rubbing between the stator and fins.
    Type: Grant
    Filed: October 2, 2018
    Date of Patent: June 8, 2021
    Assignee: Rolls-Royce North American Technologies, Inc.
    Inventor: Douglas David Dierksmeier
  • Ceramic matrix composite blade track assembly with tip clearance control
    Patent number: 11028722
    Abstract: The present disclosure is directed to a blade track assembly used in a gas turbine engine. The blade track assembly includes blade track segments made from ceramic matrix composite materials and a tip clearance control system for adjusting the inner diameter of the blade track assembly during use in an engine.
    Type: Grant
    Filed: May 30, 2018
    Date of Patent: June 8, 2021
    Assignees: Rolls-Royce North American Technologies Inc., Rolls-Royce Corporation
    Inventors: Ted J. Freeman, Aaron D. Sippel
  • High temperature panel damper for sheet metal structures
    Patent number: 11028732
    Abstract: An exhaust assembly for use with a gas turbine engine includes an exhaust duct and a damper system coupled to the exhaust duct. The exhaust duct is configured for fluid communication with the gas turbine engine to receive hot exhaust gases produced by the gas turbine engine. The exhaust duct includes a plurality of panels that define an exhaust passageway. The damper system is coupled to one of the plurality of panels and is configured to dampen vibration of the exhaust duct during use of the gas turbine engine.
    Type: Grant
    Filed: September 5, 2019
    Date of Patent: June 8, 2021
    Assignee: Rolls-Royce North American Technologies Inc.
    Inventors: William McGivern, Michel S. Smallwood
  • Turbine wheel assembly with retainer rings for ceramic matrix composite material blades
    Patent number: 11021974
    Abstract: A wheel assembly for a gas turbine engine includes a disk, an annular coverplate, and an anti-rotation feature. The disk is adapted to receive blades and rotate about an axis during use of the gas turbine engine. The annular coverplate is coupled with the disk and adapted to block axial movement of the blades. The anti-rotation feature is coupled with the disk and the annular coverplate to resist rotation of the annular coverplate relative to the disk.
    Type: Grant
    Filed: October 10, 2018
    Date of Patent: June 1, 2021
    Assignees: Rolls-Royce North American Technologies Inc., Rolls-Royce Corporation
    Inventors: Ted J. Freeman, Aaron D. Sippel, James Sellhorn
  • Method for reducing condenser size and power on a heat rejection system
    Patent number: 11022360
    Abstract: A heat transfer system for high transient heat loads includes a fluid, a heat exchanger; a compressor downstream of the heat exchanger outlet; a condenser downstream of the compressor outlet, and a thermal energy storage (TES) section downstream of the condenser outlet and upstream of the heat exchanger. The TES section may include a first pressure regulating valve downstream of a TES unit; and a second pressure regulating valve upstream of the first pressure regulating valve.
    Type: Grant
    Filed: April 10, 2019
    Date of Patent: June 1, 2021
    Assignee: ROLLS-ROYCE NORTH AMERICAN TECHNOLOGIES INC.
    Inventors: Eric Donovan, Michael Head, Tim Unton, Eugene Jansen
  • Aircraft having a gas turbine generator with power assist
    Patent number: 11022042
    Abstract: A system platform includes a gas turbine engine coupled to a generator. The generator, driven by the gas turbine engine, supplies power to subsystems of the platform.
    Type: Grant
    Filed: August 29, 2016
    Date of Patent: June 1, 2021
    Assignee: Rolls-Royce North American Technologies Inc.
    Inventor: Erik A. Munevar
  • Variable pitch blade holder for gas turbine engine
    Patent number: 11021972
    Abstract: A variable pitch blade holder for use with a gas turbine engine. The variable pitch blade holder is configured to retain a blade and to rotate about a center axis with the blade during operation of the gas turbine engine. The blade holder is adapted to rotate about a pitch change axis to vary a pitch of the blade.
    Type: Grant
    Filed: August 14, 2018
    Date of Patent: June 1, 2021
    Assignee: Rolls-Royce North American Technologies Inc.
    Inventor: Patrick Bailey
  • Control of low pressure generator for gas turbine engine
    Patent number: 11014513
    Abstract: A turbofan gas turbine engine includes low pressure (LP) motor-generator operable in either a generation mode or a drive mode, an high pressure (HP) motor-generator operable in a either a generation mode or a drive mode, and a power control module for selectively operating the LP and HP motor-generators according to operational conditions of the engine.
    Type: Grant
    Filed: May 9, 2017
    Date of Patent: May 25, 2021
    Assignee: Rolls-Royce North American Technologies Inc.
    Inventors: Donald Klemen, Michael J. Armstrong