Patents Assigned to Rolls-Royce plc
  • OIL PIPE ASSEMBLY
    Publication number: 20190226404
    Abstract: The present disclosure concerns an oil pipe assembly for transfer of oil within an engine. Examples disclosed include an oil pipe assembly (200) for an engine, comprising: an outer manifold (203) having a cooling fluid inlet (206) and a cooling fluid outlet (210); an inner manifold (204); an oil pipe (201) extending between the outer and inner manifolds (203, 204); a first outer pipe (207) surrounding the oil pipe (201) and defining a first cooling fluid passage (205); a second outer pipe (209) surrounding the oil pipe (201) and defining a second cooling fluid passage (208), wherein a cooling fluid path through the oil pipe assembly (200) is defined by a series arrangement of the cooling fluid inlet (206), the first cooling fluid passage (205), the second cooling fluid passage (208) and the cooling fluid outlet (210).
    Type: Application
    Filed: January 15, 2019
    Publication date: July 25, 2019
    Applicant: ROLLS-ROYCE plc
    Inventor: Mark JE BELLIS
  • AIRCRAFT NOZZLE
    Publication number: 20190226424
    Abstract: A flap for a variable area exhaust nozzle of a gas turbine engine. The flap includes a support structure and a gas shield retained thereto. The support structure and the gas shield include a pair of grooves extending in a longitudinal direction of the flap and a pair of corresponding tongues that engage the pair of grooves so as to retain the gas shield to the support structure and to allow movement of the gas shield by thermal expansion along the support structure in the longitudinal direction.
    Type: Application
    Filed: January 15, 2019
    Publication date: July 25, 2019
    Applicant: ROLLS-ROYCE plc
    Inventors: Jack F COLEBROOKE, David STEELE
  • AIRCRAFT NOZZLE
    Publication number: 20190226423
    Abstract: There is disclosed a flap for a variable area exhaust nozzle of a gas turbine engine. The flap comprises a support structure and a gas shield connected to the support structure, wherein the support structure is corrugated to accommodate thermal expansion of the gas shield in a direction of corrugation.
    Type: Application
    Filed: January 2, 2019
    Publication date: July 25, 2019
    Applicant: ROLLS-ROYCE plc
    Inventor: Jack F. COLEBROOKE
  • Turbine tip clearance control method and system
    Patent number: 10358933
    Abstract: A method of controlling a rotor tip clearance in a gas turbine engine (10). The method comprises determining an engine or component remaining useful life Tr, and controlling a tip clearance control arrangement (38) to maintain a rotor tip clearance (36) at a target tip clearance Dtarget. The target tip clearance Dtarget is determined in accordance with a function of remaining engine life Tr.
    Type: Grant
    Filed: August 31, 2017
    Date of Patent: July 23, 2019
    Assignee: ROLLS-ROYCE plc
    Inventor: Matthew Moxon
  • Aerofoil
    Patent number: 10358931
    Abstract: An aerofoil component defines an in use leading edge and a trailing edge. The leading edge has at least one serration defining an apex and a nadir. The leading edge has a generally chordwise extending slot located at the nadir of each serration.
    Type: Grant
    Filed: January 25, 2017
    Date of Patent: July 23, 2019
    Assignee: ROLLS-ROYCE plc
    Inventors: Chaitanya Paruchuri, Philip Joseph, Jae-Wook Kim
  • Gas turbine engine
    Patent number: 10358941
    Abstract: A gas turbine engine comprises a gearbox comprising a sun gear, an annulus gear, a plurality of planet gears and a planet gear carrier. The sun gear meshes with the planet gears and the planet gears mesh with the annulus gear. Each planet gear is rotatably mounted in the planet gear carrier. The planet gear carrier comprises a plurality of axles arranged parallel to the axis of the gearbox. The axially spaced ends of each axle are secured to the planet gear carrier. Each planet gear is rotatably mounted on a corresponding one of the axles by a bearing arrangement. Each bearing arrangement comprises a journal bearing and a rolling element bearing and each planet gear is rotatably mounted on a journal bearing and each journal bearing is rotatably mounted on an axle by at least one rolling element bearing.
    Type: Grant
    Filed: June 16, 2017
    Date of Patent: July 23, 2019
    Assignee: ROLLS-ROYCE plc
    Inventor: Jason J Madge
  • Investment casting
    Patent number: 10357823
    Abstract: A method for designing a baffle including using patterns to produce an array of shell moulds, generating a 3-D image of the outer surface of each shell mould in the array of shell moulds, stacking the individual 3-D images for a plurality of the shell moulds to produce a conglomerate shell mould profile, determining a maximum cross sectional area of the conglomerate shell mould profile in a plane orthogonal to a direction along which the shell moulds are to be drawn through the baffle, defining a baffle profile segment which is consistent with a substantial portion of the conglomerate shell mould profile at the maximum cross sectional area, scaling the baffle profile segment to provide an offset clearance between the baffle profile segment and the maximum cross sectional area of the conglomerate shell mould profile, and reproducing the baffle profile segment to provide an array of baffle profile segments.
    Type: Grant
    Filed: August 14, 2017
    Date of Patent: July 23, 2019
    Assignee: ROLLS-ROYCE plc
    Inventors: John S. Torpey, George Durrant, Felicity Freeman
  • Aircraft
    Patent number: 10358229
    Abstract: An aircraft including trailing edge flaps, a wing mounted propulsor positioned such that the flaps are located in a slipstream of the first propulsor in use when deployed. The aircraft further including a thrust vectorable propulsor configured to selectively vary the exhaust efflux vector of the propulsor in at least one plane. The thrust vectorable propulsor includes a ducted fan configurable between a first mode, in which the fan provides net forward thrust to the aircraft, and a second mode in which the fan provides net drag to the aircraft. The fan is positioned to ingest a boundary layer airflow in use when operating in the first mode.
    Type: Grant
    Filed: April 21, 2016
    Date of Patent: July 23, 2019
    Assignee: ROLLS-ROYCE plc
    Inventor: Matthew Moxon
  • COMBUSTION CHAMBER ARRANGEMENT
    Publication number: 20190218924
    Abstract: A combustion chamber arrangement comprises an outer casing surrounding an annular combustion chamber, the combustion chamber surrounding an inner casing and a stage of combustion chamber outlet guide vanes arranged at the downstream end of the combustion chamber. The stage of outlet guide vanes interconnects the outer casing and the inner casing. The combustion chamber comprises a radially inner annular wall structure. A sealing ring is mounted on the inner casing which is configured to allow relative radial movement but to restrict relative axial and circumferential movement between the sealing ring and the inner casing. A first seal allows relative axial movement between the sealing ring and the downstream end of the radially inner wall of the combustion chamber. A second seal allows relative axial movement between the sealing ring and the stage of outlet guide vanes.
    Type: Application
    Filed: December 18, 2018
    Publication date: July 18, 2019
    Applicant: ROLLS-ROYCE plc
    Inventor: Thomas G. MULCAIRE
  • ANNULUS FILLER
    Publication number: 20190218912
    Abstract: An annulus filler (32, 132) for mounting on a rotor disc (24, 124) of fan (13, 113) of a gas turbine engine (10), the annulus filler (32, 132) including a top wall (42, 142) arranged to bridge a circumferential gap (34) between two adjacent fan blades (26, 126) extending from the rotor disc (24, 124), along an axial length of the fan blades (26, 126), wherein the top wall (42, 142) is arranged to define an airflow surface (36, 136) for air being drawn between the two adjacent fan blades (26, 126) in an axial direction, from a first end (30a, 130a) of the fan (13, 113), to a second end (30b, 130b) of the fan (13, 113); wherein the annulus filler (32, 132) defines a volume (68, 168) beneath the top wall (42, 142); and wherein the annulus filler (32, 132) further includes an end wall (70, 170) arranged to close the volume (68, 168) at the second end (30b, 130b) of the fan (13, 113), to form a windage shield.
    Type: Application
    Filed: December 27, 2018
    Publication date: July 18, 2019
    Applicant: ROLLS-ROYCE plc
    Inventors: Matthew D. CURREN, Matthew A C. HOYLAND
  • BLADE FOR A GAS TURBINE ENGINE
    Publication number: 20190218920
    Abstract: There is disclosed a blade for a gas turbine engine comprising an asymmetrical blade root.
    Type: Application
    Filed: December 27, 2018
    Publication date: July 18, 2019
    Applicant: ROLLS-ROYCE plc
    Inventor: Michael P. KEENAN
  • MOUNT FOR A GAS TURBINE ENGINE UNIT
    Publication number: 20190218939
    Abstract: A mount for a gas turbine engine unit. The mount comprises a unit interface for securing a unit to the mount. The unit interface comprises an internal cavity in communication with a cooling aperture to be overlaid by unit secured to the unit interface. The mount further comprises a structural framework for securing the mount to a gas turbine engine. The structural framework comprises an internal cooling conduit for delivering cooling airflow from an air source to the internal cavity of the unit interface.
    Type: Application
    Filed: December 27, 2018
    Publication date: July 18, 2019
    Applicant: ROLLS-ROYCE plc
    Inventors: Simon M. RUSTON, Rong YANG
  • FAN DISC ASSEMBLY
    Publication number: 20190218922
    Abstract: The present disclosure concerns a fan disc assembly, and in particular a fan disc assembly for a gas turbine engine. Example embodiments disclosed include a fan disc assembly for a gas turbine engine, comprising: a fan disc with a central bore comprising a bore forward section, a bore aft section and a bore spline between the bore forward and aft sections; a shaft mounted within the central bore of the fan disc, the shaft comprising a shaft forward section connected to the bore forward section, a shaft aft section connected to the bore aft section and a shaft spline between the forward and aft sections and mating with the bore spline; wherein the bore aft section comprises a tapered surface mating against a corresponding tapered surface on the shaft aft section.
    Type: Application
    Filed: December 17, 2018
    Publication date: July 18, 2019
    Applicant: ROLLS-ROYCE plc
    Inventor: Clive BREEN
  • FAN DISC ASSEMBLY
    Publication number: 20190218923
    Abstract: The present disclosure concerns a fan disc assembly, and in particular a fan disc assembly for a gas turbine engine. Example embodiments disclosed include a fan disc assembly for a gas turbine engine, comprising: a fan disc with a central bore comprising a bore forward section, a bore aft section and a bore spline between the bore forward and aft sections; a shaft mounted within the central bore of the fan disc, the shaft comprising a shaft forward section connected to the bore forward section, a shaft aft section connected to the bore aft section and a shaft spline between the forward and aft sections and mating with the bore spline, wherein an outer radial surface of the bore forward section is secured to an inner radial surface of the shaft forward section with a second interference fit.
    Type: Application
    Filed: December 17, 2018
    Publication date: July 18, 2019
    Applicant: ROLLS-ROYCE plc
    Inventor: Clive BREEN
  • FAN DISC ASSEMBLY
    Publication number: 20190218921
    Abstract: The present disclosure concerns a fan disc assembly, and in particular a fan disc assembly for a gas turbine engine. Embodiments disclosed include a fan disc assembly for a gas turbine engine, comprising: a fan disc with a central bore comprising a bore forward section, a bore aft section and a bore spline between the bore forward and aft sections; a shaft mounted within the central bore of the fan disc, the shaft comprising a shaft forward section connected to the bore forward section, a shaft aft section connected to the bore aft section and a shaft spline between the forward and aft sections and mating with the bore spline; and an aft collar surrounding the shaft aft section and connecting the shaft aft section to the bore aft section to secure the fan disc from radial translation relative to the shaft.
    Type: Application
    Filed: December 17, 2018
    Publication date: July 18, 2019
    Applicant: ROLLS-ROYCE plc
    Inventor: Clive BREEN
  • ACCESSORY GEARBOX ASSEMBLY AND A GAS TURBINE ENGINE COMPRISING AN ACCESSORY GEARBOX ASSEMBLY
    Publication number: 20190218978
    Abstract: A gas turbine engine accessory gearbox assembly comprising an accessory gearbox and a plurality of accessories arranged to be driven by the accessory gearbox. The accessory gearbox comprises a gear train and an accessory gearbox casing enclosing the gears of the gear train. Each accessory is driven by a shaft and the shaft of each accessory has a spur gear. The gear train comprises the spur gears of the accessories. The shaft of at least one of the accessories has a bevel gear and the bevel gear is arranged to mesh with a further bevel gear and the further bevel gear is arranged to drive the accessory gearbox assembly. The accessories may be arranged in V-shape on the core engine casing within an aerodynamic core nacelle.
    Type: Application
    Filed: December 27, 2018
    Publication date: July 18, 2019
    Applicant: ROLLS-ROYCE plc
    Inventors: David A. EDWARDS, Stewart T. THORNTON
  • GAS TURBINE ENGINE OIL CIRCULATION
    Publication number: 20190218936
    Abstract: The disclosure relates to an oil circulation system for a gas turbine engine, and in particular to a gas turbine engine comprising a bearing chamber with a plurality of oil injectors. Example embodiments include a gas turbine engine, comprising: a bearing chamber (301) surrounding a turbine shaft (308) of the engine; an oil feed injection line (305) arranged to supply oil from an oil collecting compartment to a plurality of oil injectors (306, 401, 402) within the bearing chamber (301); an oil exit pipe (309, 313) arranged to allow oil to exit the bearing chamber (301); and an oil supply pump arranged to recirculate oil from the oil collecting compartment to the oil feed injection line (305), wherein the plurality of oil injectors comprise an injector (401, 402) arranged to direct oil towards an inlet of the oil exit pipe (309, 313).
    Type: Application
    Filed: January 3, 2019
    Publication date: July 18, 2019
    Applicant: ROLLS-ROYCE plc
    Inventors: Neil R. FOMISON, Alessio LENZI
  • Method of manufacturing a component from a nickel-based superalloy
    Patent number: 10351940
    Abstract: A method of manufacturing a component from a nickel-based superalloy comprises the steps of: providing a vacuum induction casting furnace; positioning a component mould onto a chill plate within the furnace; casting a component blank; peening the surface of the component blank; applying a surface modification technique to the surface of the component blank; solution heat treating the component blank at or above the ??-solvus temperature for the superalloy; and precipitation heat treating the component blank.
    Type: Grant
    Filed: August 24, 2017
    Date of Patent: July 16, 2019
    Assignee: ROLLS-ROYCE plc
    Inventor: John H Boswell
  • Variable stator vane rigging
    Patent number: 10352187
    Abstract: A variable vane mechanism for adjusting the angle of stator vanes in a gas turbine engine is provided. The mechanism includes a circumferentially extending unison ring that is driven circumferentially around a casing by an actuator. The unison ring is connected to the stator vanes via levers such that the angle of the vanes changes with circumferential movement of the unison ring. The unison ring and the casing are each provided with at least one rigging hole in order to set the initial angle of the vanes. At least one of the unison ring and the casing are each provided with at least two rigging holes, so that the initial angle of the vanes can be adjusted by selecting different combinations of rigging holes. This may allow accumulations in tolerances to be compensated for and/or may allow the engine to be tested at different initial vane angles.
    Type: Grant
    Filed: August 4, 2017
    Date of Patent: July 16, 2019
    Assignee: ROLLS-ROYCE plc
    Inventor: Michael P. Keenan
  • Methods of analysing apparatus
    Patent number: 10352823
    Abstract: Engine health monitoring is used to assess the health of an engine, such as a gas turbine engine. Blades mounted on a shaft produce a modal response when excited. The shaft has an order related component that varies with the rotational velocity of the shaft. Modal responses are increased when the natural frequency range of the selected blade mode intersects with one of the order related components. By applying a short time chirp-Fourier transform with a frequency speed that is a function of a rate of change in the rotational velocity of the shaft a selected signal can be isolated. Cracks in the blades can be detected from the isolated signal.
    Type: Grant
    Filed: July 5, 2013
    Date of Patent: July 16, 2019
    Assignee: ROLLS-ROYCE plc
    Inventors: Paul Anuzis, Leonid Moiseevich Gelman