Patents Assigned to Rolls-Royce plc
  • BLADE MOUNTING
    Publication number: 20200149400
    Abstract: An aerofoil blade having a root portion provided with a low friction coating layer. The low friction coating layer is affixed to the root portion by an adhesive layer. The adhesive layer has a service temperature of 125° C. or more, for example 140° C. or more.
    Type: Application
    Filed: October 10, 2019
    Publication date: May 14, 2020
    Applicant: ROLLS-ROYCE plc
    Inventor: Christopher M. WHITHEAD
  • Vane cooling system
    Patent number: 10648344
    Abstract: A vane cooling system for a gas turbine engine comprises a vane (20a) arranged on a stator and having a chamber (27,28) extending continuously from a radially inner end to a radially outer end of the vane. The vane (20a) has a first inlet (41) and a second inlet (42). A first cooling fluid feed (54) in communication with the first inlet (41) and a second cooling fluid feed (43) in communication with the second inlet (42). The first cooling fluid feed (54) has a higher pressure than the second cooling fluid feed (43). A flow adjustment device (45) is arranged for adjusting a flow of the second cooling fluid feed (43) into the second inlet (42). The chamber is divided by a restrictor plate (25, 26) to provide an inner chamber (27) and a wall-side chamber (28) bordering the inner chamber (27). The first inlet (41) enters the wall-side chamber (28) and the second inlet (42) enters the central chamber (27).
    Type: Grant
    Filed: April 5, 2018
    Date of Patent: May 12, 2020
    Assignee: Rolls-Royce PLC
    Inventor: Simon Pitt
  • Method of manufacturing a coated turbine blade and a coated turbine vane
    Patent number: 10648349
    Abstract: A method of manufacturing a coated turbine vane (34) comprises manufacturing a turbine vane (34) having a platform (44) and an aerofoil (42) extending from the platform (44), a curved transition (60) connects the platform (44) to the aerofoil (42) and a recess (64) is provided in the curved transition (60) from the platform (44) to the aerofoil (42). A bond coating (70) is deposited on the platform (44), the aerofoil (42), the curved transition (60) and the recess (64). A ceramic thermal barrier coating (72) is deposited on the platform (44), the recess (64) and the curved transition (60) by plasma spraying. The recess (64) reduces the size of the step due to the ceramic thermal barrier coating (72) and hence improves the aerodynamics of the turbine vane (34).
    Type: Grant
    Filed: March 8, 2018
    Date of Patent: May 12, 2020
    Assignee: ROLLS-ROYCE PLC
    Inventors: Andrew Hewitt, Ian W R Harrogate
  • Turbine engine
    Patent number: 10648475
    Abstract: A gas turbine engine for an aircraft includes an engine core including a turbine, compressor, and core shaft connecting turbine to compressor; a fan located upstream of the engine core and including a plurality of fan blades each having a leading and trailing edge. The turbine includes a lowest pressure turbine stage having a row of rotor blades, each rotor blades extending radially and having a leading and trailing edge. The engine has a fan tip axis that joins a radially outer tip of the leading edge of a fan blade and the radially outer tip of the trailing edge of a rotor blade of the lowest pressure stage. The fan tip axis lies in a longitudinal plane which contains a centreline of engine. A fan axis angle is defined as the angle between fan tip axis and centreline, and is in a range between 10 and 20 degrees.
    Type: Grant
    Filed: November 1, 2019
    Date of Patent: May 12, 2020
    Assignee: ROLLS-ROYCE plc
    Inventors: Richard G Stretton, Michael C Willmot
  • CONTROL SYSTEM FOR A GAS TURBINE ENGINE
    Publication number: 20200141330
    Abstract: A control system for a gas turbine engine includes an engine core, the engine core including combustion equipment, a turbine, a compressor, and a core shaft connecting the turbine to the compressor. The control system includes at least one variable stator vane for controlling the angle at which gas enters the engine core, and there is a bypass passage within the engine core for directing gas flow to bypass the combustion equipment.
    Type: Application
    Filed: October 29, 2019
    Publication date: May 7, 2020
    Applicant: ROLLS-ROYCE PLC
    Inventors: Luis F. LLANO, Arthur L. ROWE
  • METHOD OF UPGRADING A MODULAR GAS TURBINE ENGINE
    Publication number: 20200141239
    Abstract: A method of upgrading a modular gas turbine engine, which includes: a first fan module with a fan having plurality of fan blades; a first engine core module including an engine core and a gearbox providing drive to the fan; and a first fan case module with a fan case arranged to enclose the fan blades, the method including: disassembling the gas turbine engine, replacing one of the first fan module, first engine core module or first fan case module with a replacement fan module, a replacement engine core module or a replacement fan case module; and reassembling the gas turbine engine using the replacement module, which is compatible with the others of the first fan module, first engine core module or first fan case module; and the replacement module designed to different parameters to one of the first fan module, first engine core module or first fan case module.
    Type: Application
    Filed: October 17, 2019
    Publication date: May 7, 2020
    Applicant: ROLLS-ROYCE PLC
    Inventors: Joseph B. COOPER, Katie PHILLIPS
  • GAS TURBINE ENGINE POWER SETTING
    Publication number: 20200141267
    Abstract: A method of calibrating a gas turbine engine having a propulsive fan, and an engine core, the method including: measuring a total thrust generated by the engine; measuring the thrust generated by the engine core; measuring first and second engine performance parameters; based on the total thrust and engine core thrust, determining a thrust generated by the propulsive fan; providing a first power setting parameter associating the fan thrust with the first engine performance parameter; and providing a second power setting parameter associating the engine core thrust with the second engine performance parameter.
    Type: Application
    Filed: May 28, 2019
    Publication date: May 7, 2020
    Applicant: ROLLS-ROYCE plc
    Inventors: Matthew J. WILSON, William RENOLD-SMITH
  • CALIBRATING AN ENGINE CORE
    Publication number: 20200141266
    Abstract: A method of calibrating an engine core of a gas turbine engine, wherein the engine core includes a turbine, combustion equipment, a compressor, and a core shaft connecting the turbine to the compressor, the core shaft arranged to drive a propulsive fan of the gas turbine engine, the method including: providing a resistance load on the core shaft, the resistance load arranged to replicate the load of a propulsive fan; driving the engine core; measuring a performance parameter or the engine core; measuring a thrust generated by the engine core; and determining power rating data of the engine core, providing a correlation between the performance parameter and the thrust.
    Type: Application
    Filed: May 14, 2019
    Publication date: May 7, 2020
    Applicant: ROLLS-ROYCE plc
    Inventor: Joseph B COOPER
  • FUEL METERING SYSTEM
    Publication number: 20200141332
    Abstract: The present disclosure provides a fuel metering system for a gas turbine engine, the fuel metering system comprising: a fuel supply line; a fuel metering valve configured to pass an amount of fuel received from the fuel supply line to the gas turbine engine; an engine control unit configured to control the position of the fuel metering valve according to a demanded fuel flow to the gas turbine engine; a flow sensor configured to provide a measurement of a flow of fuel in the fuel metering system; wherein the engine control unit is further configured to determine a fuel flow to the gas turbine engine based upon the measurement from the flow sensor; and wherein the engine control unit is further configured to identify a loss of fuel flow control by comparing the demanded fuel flow to the determined fuel flow to the gas turbine engine.
    Type: Application
    Filed: September 30, 2019
    Publication date: May 7, 2020
    Applicant: ROLLS-ROYCE plc
    Inventor: Michael GRIFFITHS
  • ACTUATOR
    Publication number: 20200141263
    Abstract: A modular fluid-drive rotary actuator comprising a housing defining a chamber, a rotary driver disposed within the chamber. The rotary driver may comprise a modular driver assembly of at least two drive wheels, and/or the housing may comprise at least a first end part, a second end part and an interchangeable intermediate part disposed between them. There is also disclosed a method of reconfiguring a fluid-driven rotary actuator by replacement, addition or removal of one or more drive wheels or housing parts.
    Type: Application
    Filed: October 8, 2019
    Publication date: May 7, 2020
    Applicant: ROLLS-ROYCE plc
    Inventors: Timothy TRAMONTIN, Zahid M HUSSAIN
  • COOLING OF GAS TURBINE ENGINE ACCESSORIES
    Publication number: 20200141274
    Abstract: A gas turbine engine for an aircraft is provided. The engine includes an engine core comprising a turbine, a compressor, and a core shaft connecting the turbine to the compressor. The engine further includes core casings surrounding the engine core. The engine further includes an aerodynamic cowl which surrounds the core casings. The engine further includes a propulsive fan located upstream of the engine core, the fan generating a core airflow which enters the core engine and a bypass airflow which enters a bypass duct surrounding the aerodynamic cowl. The engine further includes one or more engine accessories mounted in a space between the core casings and the aerodynamic cowl.
    Type: Application
    Filed: October 10, 2019
    Publication date: May 7, 2020
    Applicant: ROLLS-ROYCE plc
    Inventors: Emile RAYA, Lucian INGLEY, Zahid M. HUSSAIN
  • CASING ASSEMBLY FOR A GAS TURBINE ENGINE
    Publication number: 20200141265
    Abstract: There is described a casing assembly for a gas turbine engine, the casing assembly comprising: an annular casing having a longitudinal axis; a unison ring assembly configured for rotation about the longitudinal axis; a plurality of vanes rotatably coupled to the annular casing; and a plurality of linkages, wherein each of the plurality of vanes is coupled to the unison ring assembly by a respective one of the plurality of linkages. Each linkage comprises: a first link coupled to the respective vane; and a second link rotatably coupled to the first link and rotatably coupled to the unison ring assembly, such that rotation of the unison ring assembly about the longitudinal axis effects rotation of the respective vane.
    Type: Application
    Filed: September 3, 2019
    Publication date: May 7, 2020
    Applicant: ROLLS-ROYCE plc
    Inventor: Neelambaran KARAPURATH
  • METHOD OF CONTROLLING A GAS TURBINE ENGINE
    Publication number: 20200141333
    Abstract: A method of controlling a gas turbine engine having a propulsive fan and an engine core, the method includes: measuring a first engine performance parameter indicative of the output of the fan; measuring a second engine performance parameter indicative of the output of the engine core; determining a thrust contribution generated by the fan based on a first power setting parameter and the first engine performance parameter; determining a thrust contribution generated by the engine core based on a second power setting parameter and the second engine performance parameter; determining the total thrust based on the fan thrust and core thrust; and controlling the engine based on the determined total thrust, wherein the total thrust includes the fan thrust and the engine core thrust.
    Type: Application
    Filed: November 1, 2019
    Publication date: May 7, 2020
    Applicant: ROLLS-ROYCE plc
    Inventor: William RENOLD-SMITH
  • METHOD OF REPLACING A MODULE
    Publication number: 20200141313
    Abstract: A method of replacing a module in a modular gas turbine engine having a first fan module; a first propulsor module including an engine core and a gearbox; and a first fan case module having a fan case; includes the steps of: disassembling the gas turbine engine, replacing one of the fan module, propulsor module or fan case module with a replacement fan module, a replacement propulsor module or a replacement fan case module, the replacement module, having the same configuration as the first module; and reassembling the gas turbine engine using the replacement module.
    Type: Application
    Filed: October 2, 2019
    Publication date: May 7, 2020
    Applicant: ROLLS-ROYCE plc
    Inventors: Joseph B. COOPER, Lawrence M.T. BIGG
  • GAS TURBINE ENGINE
    Publication number: 20200141314
    Abstract: A method of operating a gas turbine engine. The method includes determining a first compressor non-dimensional rotational speed set point, determining a current first compressor rotational speed and first compressor inlet temperature, and transferring power between the first and second shafts such that the first shaft non-dimensional rotational speed matches the set point.
    Type: Application
    Filed: January 7, 2020
    Publication date: May 7, 2020
    Applicant: ROLLS-ROYCE plc
    Inventors: Ahmad RAZAK, Paul FLETCHER
  • SOUND ABSORBER
    Publication number: 20200141357
    Abstract: A sound absorber for an engine of an aircraft, the sound absorber comprising: a base body having a bottom plate, a wall enclosing the bottom plate and an opening enabling entry of air into the base body; and a porous tongue having a fixed end connected to the wall and a free end; wherein the tongue is porous.
    Type: Application
    Filed: September 17, 2019
    Publication date: May 7, 2020
    Applicant: ROLLS-ROYCE plc
    Inventor: Paul B. MURRAY
  • GAS TURBINE ENGINE
    Publication number: 20200141358
    Abstract: A gas turbine engine for an aircraft includes: an engine core having a turbine, a compressor, and a core shaft connecting the turbine to the compressor, wherein the engine core extends along a rotational axis, and has an engine core diameter perpendicular to the rotational axis; and a fan having a plurality of fan blades extending radially from the rotational axis, wherein the fan has a fan diameter perpendicular to the rotational axis, wherein a ratio of the engine core diameter to the fan diameter is between 1:1.7 and 1:2.2.
    Type: Application
    Filed: May 28, 2019
    Publication date: May 7, 2020
    Applicant: ROLLS-ROYCE plc
    Inventors: Joseph B. COOPER, Geraint REES
  • FAN CASE
    Publication number: 20200141277
    Abstract: A fan case for a gas turbine aircraft engine, the fan case formed of a wall extending in a loop around an axis (9?) and along the axis (9?), and having a case length along the axis (9?), and a case perimeter around the axis, wherein the fan case comprises two or more longitudinal segments configured to be assembled to form the wall, wherein each longitudinal segment includes a portion of the wall extending at least part of the length of the fan case and forming an incomplete portion of the perimeter of the fan case.
    Type: Application
    Filed: October 10, 2019
    Publication date: May 7, 2020
    Applicant: ROLLS-ROYCE plc
    Inventors: Joseph B. COOPER, Geraint REES
  • FLUID ATOMIZER
    Publication number: 20200139390
    Abstract: A fluid atomizer and methods of atomizing fluids are disclosed. The fluid atomizer may comprise an inner member and one or more outer members. The inner member defines an interior conduit for providing a first-fluid flowpath from a supply end of the atomizer to a discharge end of the atomizer along a central axis. The one or more outer members are positioned radially outward of the inner member from the central axis. The inner and outer members define a second-fluid flowpath extending from a second-fluid supply conduit to a second-fluid discharge plenum. The second-fluid flowpath comprises a tangential conduit spiraling along the axis from the second-fluid supply conduit to a terminal end; an annulus downstream from and in fluid communication with the tangential conduit; and a second-fluid discharge plenum downstream from and in fluid communication with the annulus.
    Type: Application
    Filed: November 1, 2018
    Publication date: May 7, 2020
    Applicants: Rolls-Royce Corporation, Rolls-Royce plc
    Inventors: Neal Thomson, Christopher Walters
  • Bladed disk
    Patent number: 10641112
    Abstract: A bladed disk may be arranged to rotate about an axis of rotation and including a rotor disk having an axial length extending from a first end to a second end, along the axis of rotation and a radial thickness extending between a first radius from the axis of rotation and a second radius from the axis of rotation, less than the first radius. The bladed disk may include a plurality of blades formed integrally with the rotor disk and arranged circumferentially around the rotor disk, and a first set of divides and a second set of divides, each divide comprising a partial break in the rotor disk extending axially from the first end of the rotor disk to the second end of the rotor disk and radially from the first radius to a third radius, less than the first radius and greater than the second radius.
    Type: Grant
    Filed: August 27, 2018
    Date of Patent: May 5, 2020
    Assignee: Rolls-Royce plc
    Inventors: Jae-Hoon Chung, Malcolm L. Hillel