Patents Assigned to Rolls-Royce
  • Patent number: 12368359
    Abstract: An example electrical machine is described that includes active segments for variable voltage generation. The electrical machine includes a drive shaft, a fixed rotor segment, an active rotor segment, and an actuator mechanism. The fixed rotor segment is coupled to the drive shaft, where the fixed rotor segment has affixed thereon first permanent magnets of alternating polarity. The active rotor segment axially is adjacent to the fixed rotor segment along the drive shaft. The active rotor segment also has affixed thereon second permanent magnets of alternating polarity. The actuator mechanism is configured to articulate the active rotor segment relative to the fixed rotor segment and thereby alter a phase of the second permanent magnets relative to the first permanent magnets in order to change a first voltage generated by the electrical machine to a second voltage generated by the electrical machine.
    Type: Grant
    Filed: May 9, 2023
    Date of Patent: July 22, 2025
    Assignee: Rolls-Royce Corporation
    Inventors: David Russell Trawick, Mathew Gregory Hill
  • Patent number: 12359851
    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: Grant
    Filed: March 18, 2022
    Date of Patent: July 15, 2025
    Assignees: Rolls-Royce Corporation, Rolls-Royce North American Technologies Inc.
    Inventors: Brian Thomas Spangler, Douglas J. Snyder
  • Patent number: 12359909
    Abstract: Techniques are described by which to enable uniform machined parts inspection processes. A device comprising a memory and a processor may be configured to perform the techniques. The memory may store a unified scan of a workholding piece with a machined part, where the unified scan defines a coordinate system for the workholding piece. The memory may also store a reference model of the machined part. The processor may align, based on the coordinate system for the workholding piece, the unified scan of the workholding piece with the machined part to the reference model, and perform, after aligning the unified scan to the reference model, a comparison of the unified scan to the reference model. The processor may output, based on the comparison, an indication of compliance or non-compliance with the tolerances for the machined part.
    Type: Grant
    Filed: April 29, 2022
    Date of Patent: July 15, 2025
    Assignee: Rolls-Royce Corporation
    Inventors: Monica Sy Munoz, Matthew Roman McHugh
  • Patent number: 12358075
    Abstract: An additive manufacturing system may include an energy delivery device configured to deliver energy to a component to form a melt pool at least partially surrounded by a cooling region; and an optical system comprising: an imaging device; and an occulting device, wherein the occulting device is configured to occult at least part of thermal emissions produced by the energy and the melt pool and transmit at least some thermal emissions produced by the cooling region.
    Type: Grant
    Filed: November 23, 2021
    Date of Patent: July 15, 2025
    Assignee: Rolls-Royce Corporation
    Inventors: Baily Thomas, Scott Nelson, Abdalla R. Nassar, John Grubbs
  • Publication number: 20250223924
    Abstract: A cryogenic fueled aircraft propulsion system comprises a gas turbine engine mounted to a wing by an engine pylon, and configured to receive cryogenic fuel, the gas turbine engine comprising a core compressor. The propulsion system further comprises a pre-heater configured to heat the fuel prior to delivery to the gas turbine engine. The pre-heater is located within the engine pylon, aft of the engine core compressor.
    Type: Application
    Filed: April 10, 2024
    Publication date: July 10, 2025
    Applicant: Rolls-Royce plc
    Inventors: Chloe J. PALMER, Matthew J. Willshee
  • Publication number: 20250226123
    Abstract: An assembly for nuclear applications includes a tubular cladding for containing nuclear fuel. The tubular cladding comprises a ceramic matrix composite. An assembly tube surrounds the tubular cladding, and a collar is positioned between the tubular cladding and the assembly tube. The collar extends circumferentially around the cladding and comprises the ceramic matrix composite. The tubular cladding may be centered within the assembly tube by the collar.
    Type: Application
    Filed: June 23, 2023
    Publication date: July 10, 2025
    Applicant: Rolls-Royce High Temperature Composites Inc.
    Inventor: Sujit Nanda
  • Publication number: 20250226691
    Abstract: A method for operating a power delivery network, including: detecting a load demand on the power delivery network; detecting a first power delivery information by a first power delivery device and a second power delivery information by a power delivery group; determining—based on a load demand, the first power delivery information, and the second power delivery information—a first load distribution by way of a nonlinear optimization, the first load distribution including a first partial load for the first power delivery device and a second partial load for the power delivery group; determining, by way of a mixed-integer linear optimization, a second load distribution through which the second partial load is distributed between second power delivery devices of the power delivery group; operating the power delivery network with the first load distribution; and operating the power delivery group with the second load distribution.
    Type: Application
    Filed: March 27, 2025
    Publication date: July 10, 2025
    Applicant: Rolls-Royce Solutions GmbH
    Inventors: Alexander Bernhard, Carsten Schäfer, Dennis Beermann
  • Publication number: 20250224114
    Abstract: A fuel injector for a hydrogen combusting aircraft gas turbine engine has at least one air through-passage extending axially from a front face to a rear face. The injector further comprises a fuel manifold in communication with a hydrogen fuel feed line. A plurality of fuel outlets is provided surrounding the or each air passage and an annular fuel gallery is provided around each air through passage configured to supply the fuel outlets, the annular fuel gallery communicating with the fuel manifold.
    Type: Application
    Filed: March 27, 2024
    Publication date: July 10, 2025
    Applicant: Rolls-Royce plc
    Inventor: Edward A. WALTERS
  • Publication number: 20250223906
    Abstract: The present disclosure relates to a rotor stage 100 for a gas turbine engine 10 comprising: a platform 120 having a first material composition, a plurality of blades 160 extending from the platform 120, and a damper element 200. The platform 120 comprises a platform engagement surface 110. The damper element comprises a body portion 201 and an engagement portion 205. The engagement portion 205 has a second material composition comprising a composite friction material. The engagement portion 205 comprises a damper engagement surface 210 that engages with the platform engagement surface 110.
    Type: Application
    Filed: December 10, 2024
    Publication date: July 10, 2025
    Applicant: Rolls-Royce plc
    Inventor: Nigel J. CHIVERS
  • Patent number: 12355320
    Abstract: A winding head for a stator tooth of an electric motor is provided. A stator core has a first stator flange and a second stator flange that are joined by a stator joint part. The stator core has an I-shaped cross section perpendicular to a longitudinal elongation with a first end and a second end. The winding head is configured to extend the longitudinal elongation at the first end. The winding head has a first winding head flange and a second winding head flange that are joined by a winding head joint part, and the winding head extends at least partially an elongation of a shape of the stator core. The winding head also has a winding hole at the first winding head flange and a winding opening at the winding head joint part. The winding hole and opening are connected by a groove in the winding head joint part.
    Type: Grant
    Filed: November 16, 2020
    Date of Patent: July 8, 2025
    Assignee: Rolls-Royce Deutschland Ltd & Co KG
    Inventors: Dániel Kutrovich, Zoltán Nádudvari, János Dorogi, Gergely György Balazs
  • Patent number: 12351522
    Abstract: An article may include a substrate and a coating system on the substrate. The coating system may include a thermal and/or environmental barrier coating (T/EBC) layer, wherein the T/EBC layer includes a silicate phase including more than one metal cation.
    Type: Grant
    Filed: December 20, 2019
    Date of Patent: July 8, 2025
    Assignees: Rolls-Royce Corporation, University of Virginia Patent Foundation
    Inventors: Adam Lee Chamberlain, Elizabeth J. Opila, Mackenzie J. Ridley
  • Publication number: 20250215884
    Abstract: A method for operating a power generation device, including the steps of: providing that the power generation device includes a charge air compressor; detecting a charge air pressure downstream of the charge air compressor, and checking the charge air pressure downstream of the charge air compressor for a pressure drop; detecting an additional operating parameter of the power generation device which is correlated with the charge air pressure; evaluating the additional operating parameter in regard to a plausibility of a surge event having caused the pressure drop in the charge air pressure; and identifying the surge event of the charge air compressor if a drop in the charge air pressure—which is detected—is identified, and, based on the step of evaluating the additional operating parameter, the surge event is evaluated to be plausible for having caused the pressure drop in the charge air pressure.
    Type: Application
    Filed: February 7, 2025
    Publication date: July 3, 2025
    Applicant: Rolls-Royce Solutions GmbH
    Inventors: Tobias Schmid, Moritz Röthlingshöfer, Erika Schäfer
  • Patent number: 12345208
    Abstract: An apparatus for an aircraft includes an electric machine and a gas turbine. The gas turbine includes a compressor, a turbine unit having a high-pressure turbine and a low-pressure turbine, and a combustion chamber. The compressor is connected via a high-pressure shaft to the high-pressure turbine, and the low-pressure turbine is connected via a low-pressure shaft directly to an output shaft of the electric machine. The high-pressure shaft and the low-pressure shaft are rotatable in different directions. The electric machine is operable as a generator and may be operated as a motor to start the gas turbine. The output shaft is connected via a gear box unit and a free-wheel to the high-pressure shaft. The free-wheel separates the connection between the output shaft of the electric machine and the high-pressure shaft in the presence of a torque flow from the high-pressure shaft in a direction of the output shaft.
    Type: Grant
    Filed: September 28, 2023
    Date of Patent: July 1, 2025
    Assignee: Rolls-Royce Deutschland Ltd & Co KG
    Inventors: Stephen Mountain, Christian Seydel, Gideon Daniel Venter, Sebastian Kopp
  • Patent number: 12345211
    Abstract: A method of mitigating uncommanded or uncontrollable high thrust in a gas turbine engine is provided. The method may comprise pumping fuel to a combustor from a fuel tank, controlling a flow rate of the fuel to the combustor with a metering valve, spilling a portion of the fuel pumped by the pump with a primary spill valve, controlling a pressure of the fuel flowing to the combustor via a pressure valve, detecting a pressure differential across the pressure valve with a pressure transducer, determining the flow rate of the fuel based on the detected pressure differential and the positional feedback of the pressure valve opening, comparing the determined flow rate with a demand flow rate, and opening a secondary spill valve when the determined flow rate exceeds the demand flow rate.
    Type: Grant
    Filed: August 21, 2023
    Date of Patent: July 1, 2025
    Assignees: Rolls-Royce North American Technologies, Inc., Rolls-Royce Corporation
    Inventors: Govindaraj Kalyanasamy, Mihir Desai, Andrew Lee, Mark Collett
  • Patent number: 12337336
    Abstract: A centrifugal air-oil separator system for a gas turbine engine system is described. The air-oil separator system has a rotatable shaft and the shaft includes an axially extending bore formed at least partially through the shaft. A gear is integral to or mounted on an outer surface of the shaft. The air-oil separator system also includes a bolt-on breather mounted on the shaft and independent from and in contiguous contact with the gear to assist in separating the oil from the air. Various types of materials may be utilized in the construction of the air-oil separator system.
    Type: Grant
    Filed: May 24, 2023
    Date of Patent: June 24, 2025
    Assignee: Rolls-Royce North American Technologies Inc.
    Inventors: Michael Kabbes, Jacob Harral, Michael Dornfeld, Kenneth Miller
  • Patent number: 12334859
    Abstract: An example system includes a power electronics system; a starter electrically connected to the power electronics system and configured to start a gas-turbine engine of an aircraft; and an energy storage system electrically connected to the power electronics system and configured to provide direct current (DC) electrical energy to the power electronics system, wherein the power electronics system is configured to deliver alternating current (AC) electrical energy to the starter to start the gas-turbine engine using the DC electrical energy from the energy storage system and AC electrical energy sourced from an AC electrical bus of the aircraft.
    Type: Grant
    Filed: August 12, 2022
    Date of Patent: June 17, 2025
    Assignees: Rolls-Royce North American Technologies, Inc., Rolls-Royce Corporation
    Inventors: Peter Schenk, Erik A. Munevar, Rigoberto J. Rodriguez
  • Publication number: 20250180435
    Abstract: A method for detecting a burner failure in a gas turbine engine that has a combustor and a turbine disposed downstream of the combustor. The combustor has a plurality of burners arranged annularly. The method includes providing a plurality of temperature sensors arranged annularly at an outlet of the turbine; obtaining a plurality of temperature signals from the plurality of temperature sensors; determining a plurality of validated temperature signals from the plurality of temperature signals; determining a temperature focus at least based on the plurality of validated temperature signals; improving the temperature focus such that the temperature focus is within a tolerance range; and performing at least one hazard protection action at least when the temperature focus crosses a predetermined threshold.
    Type: Application
    Filed: March 1, 2024
    Publication date: June 5, 2025
    Applicant: Rolls-Royce plc
    Inventor: Mark J E BELLIS
  • Patent number: 12320295
    Abstract: In some examples, a system including a gas turbine engine, the engine including a high-pressure (HP) shaft; HP compressor; HP turbine, second shaft; second compressor; second turbine, the second turbine being coupled to the second compressor via the second shaft (e.g., LP shaft); and a generator coupled to the LP shaft. The generator is configured to generate electrical power from rotation of the LP shaft, and increase electrical power generated by the generator to increase a torque applied to the LP shaft by the generator, e.g., in combination with reduction in engine thrust, or in response to the detection of a stall and/or surge of the engine. The increase in torque applied to the second shaft is configured to increase a rate at which a rotational speed of the second shaft decreases, e.g., in combination with the reduction in engine thrust or during the stall/surge of the engine.
    Type: Grant
    Filed: December 27, 2021
    Date of Patent: June 3, 2025
    Assignee: Rolls-Royce North American Technologies, Inc.
    Inventors: Sean Andrew Morgan, Timothy Unton, Alan W. Smith, Adam Lagrange, James Christopher Muskat
  • Patent number: 12312979
    Abstract: A vane assembly includes an outer case, a plurality of vanes, and an inner body assembly. The outer case defines an outer boundary of a flow path of the vane assembly. The plurality of vanes extend radially inward from the outer case relative to a central axis. The inner body assembly is configured to secure the plurality of vanes radially relative to the central axis. The inner body assembly includes an inner case arranged circumferentially about the central axis, a band coupled with the inner case, and a retainer ring that extends into the band and into each of the plurality of vanes.
    Type: Grant
    Filed: February 21, 2024
    Date of Patent: May 27, 2025
    Assignee: Rolls-Royce North American Technologies Inc.
    Inventors: David L. Sutterfield, Aric Acius
  • Publication number: 20250164061
    Abstract: Apparatus for supporting at least a part of an engine, the engine comprising: an engine stand configured to support at least a part of an engine; an accelerometer coupled to the engine stand and configured to: measure acceleration of the engine stand, and generate accelerometer data; and a first processor configured to receive the accelerometer data from the accelerometer.
    Type: Application
    Filed: October 23, 2024
    Publication date: May 22, 2025
    Applicant: Rolls-Royce plc
    Inventor: Michael J. WINGFIELD