Patents Assigned to Rolls-Royce plc
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Patent number: 10851715Abstract: A gas turbine engine for an aircraft including: an engine core including a turbine, a compressor, and a core shaft connecting the turbine to the compressor; a fan located upstream of the engine core, the fan including a plurality of fan blades; a gearbox that receives an input from the core shaft and outputs drive to a fan shaft via an output of the gearbox so as to drive the fan at a lower rotational speed than the core shaft; and a fan shaft mounting structure arranged to mount the fan shaft within the engine, the fan shaft mounting structure including at least two supporting bearings connected to the fan shaft. A fan-gearbox axial distance is defined as the axial distance between the output of the gearbox and the fan axial centreline, the fan-gearbox axial distance being greater than or equal to 0.35 m.Type: GrantFiled: March 17, 2020Date of Patent: December 1, 2020Assignee: ROLLS-ROYCE plcInventor: Mark Spruce
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Patent number: 10851655Abstract: A fan for a gas turbine engine, the fan comprising a first set of fan blades and a second set of fan blades arranged circumferentially around a hub. Each of the fan blades of the first and second set comprises an organic matrix composite body and a leading edge member connected to the body. The leading edge member of the first set of fan blades has a mass less than the leading edge member of the second set of fan blades.Type: GrantFiled: February 19, 2018Date of Patent: December 1, 2020Assignee: ROLLS-ROYCE plcInventor: Gabriel Gonzalez-Gutierrez
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Patent number: 10850857Abstract: The present disclosure concerns the detection of ice within a system. More specifically, but not exclusively, the disclosure concerns the detection of ice accretion within a gas turbine engine. The apparatus and method relies on heating a first region (38) of a component (44) and comparing the measured temperature of the first region (38) with a second temperature value, possibly measured at a distinct second region (40) of the component (44).Type: GrantFiled: July 18, 2018Date of Patent: December 1, 2020Assignee: ROLLS-ROYCE plcInventor: David P. Scothern
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Patent number: 10851656Abstract: An article includes a substrate, a bond coat on the substrate, and a multilayer environmental barrier coating (EBC) on the bond coat. The multilayer EBC includes a first EBC layer defining a first thickness and a second EBC layer defining a second thickness. The first EBC layer includes a first rare earth disilicate and a first concentration of a sintering aid that includes alumina. The second EBC layer includes a second rare earth disilicate and a second concentration of the sintering aid that includes alumina, less than the first concentration of the sintering aid.Type: GrantFiled: September 25, 2018Date of Patent: December 1, 2020Assignees: Rolls-Royce Corporation, Rolls-Royce PLCInventors: Stephanie Gong, Taylor K. Blair, Ngunjoh Lawrence Ndamka, Li Li, Sunny Chang, Ann Bolcavage
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Publication number: 20200370511Abstract: A gas turbine engine for an aircraft includes: an engine core with a turbine, a compressor, and a core shaft connecting the turbine and compressor, the engine core having an inlet upstream of the compressor and an outlet downstream of the turbine; a fan upstream of the engine core, the fan including a plurality of fan blades; a gearbox receiving an input from the core shaft and outputs drive to the fan to drive the fan at a lower rotational speed than the core shaft; and a nacelle surrounding the engine core defining a bypass duct and a bypass exhaust nozzle, wherein the gas turbine engine is configured such that an axial Mach number at the engine core inlet (which is less than around 0.7) multiplied by an axial Mach number of an exhaust airflow from the bypass exhaust nozzle is between around 0.30 to 0.56 at maximum take-off conditions.Type: ApplicationFiled: August 13, 2019Publication date: November 26, 2020Applicant: ROLLS-ROYCE PLCInventor: Craig W BEMMENT
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Publication number: 20200370435Abstract: A gas turbine engine for an aircraft including: an engine core including a turbine, a compressor, and a core shaft connecting the turbine to the compressor; and a fan located upstream of the engine core, the fan including a plurality of fan blades, wherein the gas turbine engine is configured such that a flow velocity ratio between a first flow velocity at an exit of the engine core and a second flow velocity at an inlet of the engine core is within a range from around 0.82 to around 1.1 at cruise conditions.Type: ApplicationFiled: July 16, 2019Publication date: November 26, 2020Applicant: ROLLS-ROYCE plcInventor: Craig W. BEMMENT
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Publication number: 20200370481Abstract: A gas turbine engine for an aircraft and a method of operating a gas turbine engine on an aircraft. Embodiments disclosed include a gas turbine engine for an aircraft including: an engine core has a turbine, a compressor, and a core shaft; a fan located upstream of the engine core, the fan has a plurality of fan blades; a nacelle surrounding the engine core and defining a bypass duct and bypass exhaust nozzle; and a gearbox that receives an input from the core shaft and outputs drive to the fan wherein the gas turbine engine is configured such that a jet velocity ratio of a first jet velocity exiting from the bypass exhaust nozzle to a second jet velocity exiting from an exhaust nozzle of the engine core at idle conditions is greater by a factor of 2 or more than the jet velocity ratio at maximum take-off conditions.Type: ApplicationFiled: July 30, 2019Publication date: November 26, 2020Applicant: ROLLS-ROYCE plcInventor: Craig W. BEMMENT
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Publication number: 20200370997Abstract: A techniques for improved guiding of hyper-redundant manipulator probes into a constrained space which make use of the known characteristics of the space into which the probe is being inserted to increase the efficiency of the computation of the path of the probe. Embodiments of the invention achieve this through an optimisation function which determined a new orientation which minimises the deviation between each of: a) the point on the probe where the probe starts to follow a defined curve within the constrained space and a predetermined initial point, and b) the distal end of the probe and said defined curve.Type: ApplicationFiled: March 13, 2020Publication date: November 26, 2020Applicant: ROLLS-ROYCE plcInventor: David I. PALMER
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Publication number: 20200370512Abstract: A gas turbine engine for an aircraft, the gas turbine engine comprising: an engine core including a turbine, a compressor, and a core shaft connecting the turbine to the compressor; a fan located upstream of the engine core, the fan including a plurality of fan blades; and a nacelle surrounding the engine core and defining a bypass duct and bypass exhaust nozzle, wherein the gas turbine engine is configured such that a first velocity ratio between an axial exhaust flow velocity from the turbine and a fully expanded axial exhaust flow velocity from the bypass exhaust nozzle is greater than around 0.655 under maximum take-off conditions.Type: ApplicationFiled: July 30, 2019Publication date: November 26, 2020Applicant: ROLLS-ROYCE plcInventor: Craig W. BEMMENT
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Publication number: 20200373849Abstract: A power converter. The power converter comprising: two or more multi-phase AC sources; an AC-DC converter circuit for each of the multi-phase AC sources, each AC-DC converter circuit being connected to a respective multi-phase AC source via a multi-phase input and configured to rectify a received multi-phase current into a DC current; a transformer, which is connected between the multi-phase AC inputs; a DC-link, shared between each of the AC-DC converter circuits; a load, connected to the DC-link and able to receive DC current therefrom; and a common mode filter, located within the DC-link, and configured to reduce a circulatory current which, when the power converter is in use, flows from the transformer through one of the AC-DC converter circuits, through the DC-link and through a further of the AC-DC converter circuits back to the transformer.Type: ApplicationFiled: May 20, 2020Publication date: November 26, 2020Applicant: ROLLS-ROYCE plcInventors: Jih-Sheng LAI, Pabbathi VENKATESH, Xiong LIU
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Publication number: 20200369175Abstract: A computer-based method is provided of forecasting total electric vehicle state of charge and total electric vehicle energy storage capacity in a parking area having parking bays with respective electrical vehicle charging and discharging facilities. Electric vehicles occupying the bays can provide temporary energy storage capacity to an energy grid. The forecasting method includes: forecasting future occupation of the bays by electric vehicles based on expected arrival times and expected stay durations; obtaining expected charge and discharge capabilities of the vehicles; forecasting a total state of charge and total energy storage capacity in the parking area; recording actual arrivals and departures; and adjusting the forecast of future occupation and the forecast of total state of charge and total energy storage capacity in the parking area.Type: ApplicationFiled: May 6, 2020Publication date: November 26, 2020Applicant: ROLLS-ROYCE plcInventors: Talib E. RAJABALLY, Maszatul MANSOR
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Patent number: 10844721Abstract: A gas turbine engine for an aircraft includes an engine core with a turbine, a compressor, and a core shaft connecting them. The engine includes a fan, with a plurality of fan blades, located upstream of the core and a gearbox receiving an input from the core shaft and outputting drive so the fan is at a lower rotational speed than the core shaft. The turbine includes a plurality of stages of axially spaced rotor blades mounted on a rotor, which are surrounded by a turbine casing. The turbine has an inlet defined at an upstream end of a first stage of blades and an outlet defined at a downstream end of a last stage of blades and a ratio of the area of the outlet to the inlet is at between 2.5 and 3.5. This increases the pressure ratio of and power extracted from the turbine and the engine.Type: GrantFiled: June 18, 2019Date of Patent: November 24, 2020Assignees: ROLLS-ROYCE plc, ITP NEXT GENERATION TURBINES SLUInventors: Roderick M Townes, Diego Torre Ruiz
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Patent number: 10844492Abstract: An arrangement comprising a component (203) adjacent to a ceramic matrix composite in a gas turbine engine is shown. The component comprises a nickel-base superalloy substrate (301) and a cobalt-modified beta-nickel-aluminide coating (302) on the substrate to prevent interdiffusion between the substrate and the ceramic matrix composite. The substrate is coated by depositing a cobalt layer on the substrate, depositing an aluminium layer on the cobalt layer and then forming a cobalt-modified beta nickel aluminide coating.Type: GrantFiled: May 17, 2018Date of Patent: November 24, 2020Assignee: ROLLS-ROYCE PLCInventors: Ngunjoh L. Ndamka, Paul Morrell
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Patent number: 10844738Abstract: This document discloses a wall arrangement for a gas turbine engine, comprising: an annular wall comprising a plurality of circumferential wall segments, adjacent wall segments having opposing first and second end wall portions which define a separating gap therebetween, the gap including a saddle portion which faces radially outwards and comprises a first sealing face on the first end wall portion and a second sealing face on the second end wall portion; and, a longitudinal seal member having a curved sealing surface located within the saddle portion, wherein the curved sealing surface contacts either or both first and second sealing faces along the length of the saddle portion in use, wherein the seal member includes one or more axial restraint features which engage with a corresponding feature of the wall segment or a supporting structure thereof.Type: GrantFiled: February 24, 2017Date of Patent: November 24, 2020Assignee: ROLLS-ROYCE plcInventor: Steven Hillier
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Patent number: 10844232Abstract: A thermochromic paint including: 1 wt % to 90 wt % binder; 2 wt % to 40 wt % filler comprising an inorganic oxide; and 0.1 wt % to 28 wt % organic compound including a chromophore. The paint provides an irreversible indication of maximum temperature.Type: GrantFiled: July 17, 2017Date of Patent: November 24, 2020Assignee: ROLLS-ROYCE PLCInventors: Harry Mackilligin, Neil Champness, Peter Licence
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Patent number: 10844732Abstract: A method of manufacturing the aerofoil, and an aerofoil. The method includes: casting a first body portion having a passage passing there-through; casting a second body portion; and joining the first body portion and the second body portion to form the aerofoil. The passage extends from an opening at a first end at or near a leading edge to an opening at a second end at or near a trailing edge. The passage is formed during the casting process by a core; and the core is supported at the first and second ends through the respective openings of the passage.Type: GrantFiled: November 15, 2018Date of Patent: November 24, 2020Assignee: Rolls-Royce plcInventor: Adrian L. Harding
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Publication number: 20200362728Abstract: An aircraft gas turbine engine comprises at least a first main engine shaft an electric machine coupled to the main engine shaft, and a lubrication pump configured to provide oil to at least a part of the electric machine. The lubrication pump is controlled by a controller. The controller is configured to operate the lubrication pump in a main gas turbine engine running mode, in which the lubrication pump is driven to provide lubrication to the electric machine at a first flow rate relative to the rotational rate of the main engine shaft, and a fault mode, in which the lubrication pump is driven to provide lubrication to the electric machine at a second, higher flow rate relative to the rotational rate of the main engine shaft.Type: ApplicationFiled: April 9, 2020Publication date: November 19, 2020Applicant: ROLLS-ROYCE plcInventor: Paul R. DAVIES
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Patent number: 10835189Abstract: Provided herein are x-ray imaging systems, methods of x-radiography, and methods of manufacture of collimators suitable for use in x-ray imaging systems and methods of x-radiography. The systems, methods and devices proposed here may assist in providing for improved magnification of x-rays in an x-ray imaging system with improved image quality compared to known systems. It may find applications in a variety of x-ray applications, for example x-ray CT (Computed Tomography) and 2D projectional radiography for e.g. non-destructing testing purposes.Type: GrantFiled: March 4, 2019Date of Patent: November 17, 2020Assignee: ROLLS-ROYCE PLCInventors: Daniel Clark, Timothy J. Barden
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Patent number: 10837311Abstract: A valve monitoring apparatus has a system to determine a state of a valve. The system determines a fluid flow first pressure at a first location within a gas turbine engine, and a second pressure of a compressed fluid at a second location within the engine when the valve is in the first position; and compares the first and second pressures to determine the valve state. The system is arranged to command the valve to move from the first position towards a second position; determine the second pressure of the compressed fluid at the second location; compare the pressure at the second location when the valve is in the first position to the pressure at the second location when the valve has been commanded to move towards the second position; and, determine whether the valve has moved from the first position towards the second position when commanded to do so.Type: GrantFiled: May 3, 2017Date of Patent: November 17, 2020Assignee: ROLLS-ROYCE plcInventor: David P Scothern
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Patent number: 10837370Abstract: A gas turbine engine including: an engine core including a turbine, a compressor, and a core shaft connecting the turbine to the compressor; a fan located upstream of the engine core; a fan shaft mounting structure that includes supporting bearings connected to the fan shaft; and an epicyclic gearbox that can receive input from the core shaft, and output drive to the fan shaft so as to drive the fan at a lower rotational speed than the core shaft. The gearbox includes a sun gear, planet gears, a ring gear, and a planet carrier for mounting the planet gears. A torsional stiffness of the planet carrier is greater than or equal to 1.6×108 Nm/rad. The fan shaft mounting structure has: a radial bending stiffness greater than or equal to 7.00×108 N/m, and/or a tilt stiffness greater than or equal to 1.50×107 Nm/rad.Type: GrantFiled: March 17, 2020Date of Patent: November 17, 2020Assignee: ROLLS-ROYCE plcInventor: Mark Spruce
