Patents Assigned to Rolls-Royce North American Technologies, Inc.
  • INLET GUIDE VANE DRAW HEAT EXCHANGER SYSTEM
    Publication number: 20210277827
    Abstract: A system includes a housing for a gas turbine engine, and a fan disposed in the housing to rotate coaxially with a gas turbine included in the housing. The system also includes an inlet guide vane disposed in the housing in axial alignment with the fan and configured to have an open position where a first flow of air is received by the fan through the inlet guide vane, and a closed position where airflow through the inlet guide vane is obstructed. The system further includes a heat exchanger disposed in a supply passage in fluid communication with a second flow of air received by the fan. The second flow of air is received by the fan via the supply passage with the inlet guide vane in the open position or in the closed position.
    Type: Application
    Filed: March 9, 2020
    Publication date: September 9, 2021
    Applicant: Rolls-Royce North American Technologies Inc.
    Inventors: Douglas David Dierksmeier, Douglas Boyd, Douglas J. Snyder, Graham Burkholder, William Barry Bryan
  • Turbine shroud assembly with dovetail retention system
    Patent number: 11111796
    Abstract: A turbine shroud assembly for use with a gas turbine engine includes a turbine outer case, a blade track segment, and a carrier assembly. The turbine outer case is arranged around an axis. The blade track segment is configured to define a portion of a gas path of the gas turbine engine. The carrier assembly is coupled to the turbine outer case and supports the blade track segment.
    Type: Grant
    Filed: May 18, 2020
    Date of Patent: September 7, 2021
    Assignees: Rolls-Royce North American Technologies Inc., Rolls-Royce Corporation
    Inventors: Ted J. Freeman, Aaron D. Sippel, Alexandra Baucco, Anthony Razzell, Michael J. Whittle, Jeffrey Crutchfield
  • Inlet particle separator
    Patent number: 11111855
    Abstract: A gas turbine engine includes an engine core, a propulsion unit, and a particle separator. The engine core is configured to combust fuel and air to drive rotation of the propulsion unit. The propulsion unit is driven to rotate by the engine core to provide thrust for the gas turbine engine. The particle separator is configured to separate unwanted particles from air being directed toward the engine core.
    Type: Grant
    Filed: May 23, 2019
    Date of Patent: September 7, 2021
    Assignee: Rolls-Royce North American Technologies Inc.
    Inventor: Douglas D. Dierksmeier
  • Impeller shroud with slidable coupling for clearance control in a centrifugal compressor
    Patent number: 11105338
    Abstract: A system for controlling the clearance distance between an impeller blade tip of a centrifugal compressor and a radially inner surface of an impeller shroud in a turbine engine. The system comprises a high pressure air source, an air piston mounted between an engine casing and the shroud and adapted to receive high pressure air from the high pressure air source, a mounting arm coupling the shroud and air piston, and a slidable coupling adapted to allow axial movement of the shroud and joining the shroud to an axial member.
    Type: Grant
    Filed: September 23, 2019
    Date of Patent: August 31, 2021
    Assignees: Rolls-Royce Corporation, Rolls-Royce North American Technologies Inc.
    Inventors: Michael Nesteroff, Jonathan Acker, Jeffrey Crutchfield, Nate Cooper, Mark Whitlock, Nathan Ottow
  • Windmill synchronization in an electric propulsion system
    Patent number: 11104447
    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 propulsory 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 propulsory 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: February 21, 2017
    Date of Patent: August 31, 2021
    Assignee: Rolls-Royce North American Technologies, Inc.
    Inventors: Michael James Armstrong, Mark Jon Blackwelder
  • Turbine shroud assembly with sheet-metal sealing features
    Patent number: 11092027
    Abstract: A turbine shroud assembly for use with a gas turbine engine includes a carrier assembly coupled to a blade track segment, and a sheet-metal seal that seals on axial and radial facing surfaces therebetween. The blade track segment includes a shroud wall that extends circumferentially partway around an axis and an attachment feature that extends radially outward from the shroud wall. The carrier is coupled with the attachment feature to support the blade track segment.
    Type: Grant
    Filed: November 19, 2019
    Date of Patent: August 17, 2021
    Assignees: Rolls-Royce North American Technologies Inc., Rolls-Royce Corporation
    Inventors: Ted J. Freeman, David J. Thomas, Jeffrey A. Walston, Aaron D. Sippel
  • Gas turbine engine with mount for interchangeable inlets
    Patent number: 11085373
    Abstract: A gas turbine engine includes an engine unit and an inlet. The engine unit includes an engine core that includes a compressor, a combustor, and a turbine and a nacelle arranged circumferentially around at least a portion of the engine core. The inlet is removably coupled with the nacelle and configured to conduct fluid into the engine unit. The inlet includes a nose and an intake lip arranged circumferentially around the nose to define an intake passage that extends through the inlet.
    Type: Grant
    Filed: January 31, 2019
    Date of Patent: August 10, 2021
    Assignee: Rolls-Royce North American Technologies Inc.
    Inventor: Douglas D. Dierksmeier
  • Gas turbine combustor liner with integral chute made by additive manufacturing process
    Patent number: 11085639
    Abstract: Systems and methods are provided for a combustion liner assembly comprising at least a portion of a combustion liner of a combustor, the combustion liner defining a combustion chamber. A chute integral with at least the portion of the combustion liner is provided, the chute having an inlet, an outlet, and a body extending between the inlet and the outlet. The body of the chute extends towards a midline of the combustion chamber. The inlet is located in an outer surface of the combustion liner, and the outlet opens into the combustion chamber. A cooling channel is provided that extends from the outer surface of the combustion liner along the body of the chute.
    Type: Grant
    Filed: December 27, 2018
    Date of Patent: August 10, 2021
    Assignees: Rolls-Royce North American Technologies Inc., Rolls-Royce Corporation
    Inventors: Kevin Sauer, Christopher D. DeBruhl
  • Blade tip for ceramic matrix composite blade
    Patent number: 11085302
    Abstract: Turbine blades for use in gas turbine engines are disclosed herein. Each blade includes an airfoil and a protective crown. The airfoil includes ceramic matrix composite materials. The protective crown includes ceramic-containing materials and is mounted to a radially-outer end portion of the airfoil.
    Type: Grant
    Filed: March 20, 2018
    Date of Patent: August 10, 2021
    Assignees: Rolls-Royce North American Technologies Inc., Rolls-Royce High Temperature Composites Inc.
    Inventors: Ted J. Freeman, Jeremy P. Roehm, Robert J. Shinavski
  • Particle separator
    Patent number: 11073083
    Abstract: An air-inlet duct includes an outer wall, an inner wall, and a splitter. The splitter cooperates with the outer wall to establish a particle separator which separates particles entrained in an inlet flow moving through the air-inlet duct to provide a clean flow of air to a compressor section of a gas turbine engine.
    Type: Grant
    Filed: February 6, 2019
    Date of Patent: July 27, 2021
    Assignees: Rolls-Royce North American Technologies Inc., University of Virginia Patent Foundation
    Inventors: Philip H. Snyder, Eric Loth, Dominic L. Barone
  • Turbine shroud assembly with case captured seal segment carrier
    Patent number: 11073045
    Abstract: A turbine module includes a turbine rotor assembly, a turbine case, and a turbine shroud assembly. The turbine rotor assembly is mounted to rotate about a central reference axis. The turbine case is spaced radially outward from the turbine rotor assembly circumferentially around the central reference axis. The turbine shroud assembly includes a plurality of turbine shroud segments mounted to the turbine case. Each turbine shroud segment includes a blade track segment that faces the turbine rotor assembly and a carrier mounted to the turbine case.
    Type: Grant
    Filed: December 18, 2019
    Date of Patent: July 27, 2021
    Assignees: Rolls-Royce Corporation, Rolls-Royce North American Technologies Inc.
    Inventors: Aaron D. Sippel, Ted J. Freeman
  • Turbine shroud assembly with sealed pin mounting arrangement
    Patent number: 11066947
    Abstract: A shroud assembly adapted for use with a gas turbine engine includes a seal segment, a carrier, and a mount system. The seal segment extends circumferentially at least partway around an axis to define a gas path boundary of the shroud assembly. The carrier is configured to support the seal segment in position radially relative to the axis. The mount system couples the seal segment with the carrier.
    Type: Grant
    Filed: December 18, 2019
    Date of Patent: July 20, 2021
    Assignees: Rolls-Royce Corporation, Rolls-Royce North American Technologies Inc.
    Inventors: Aaron D. Sippel, Ted J. Freeman, Alexandra Baucco, Jeffrey A. Walston
  • 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