Patents Assigned to Rolls-Royce plc
  • AIRCRAFT ENGINE OPERABILITY
    Publication number: 20200011238
    Abstract: A gas turbine engine has a cycle operability parameter ? in a defined range to achieve improved overall performance, taking into account fan operability and/or bird strike requirements as well as engine efficiency. The defined range of cycle operability parameter ? may be particularly beneficial for gas turbine engines in which the fan is driven by a turbine through a gearbox.
    Type: Application
    Filed: May 14, 2019
    Publication date: January 9, 2020
    Applicant: ROLLS-ROYCE plc
    Inventors: Michael O. HALES, Craig W. BEMMENT, Stephane M. M. BARALON, Benjamin J. SELLERS, Christopher BENSON, Benedict R. PHELPS, Mark J. WILSON
  • GAS TURBINE ENGINE OPERATING POINT
    Publication number: 20200011333
    Abstract: A gas turbine engine has an engine core and a bypass duct. A fan drives the flow through the bypass duct. A bypass efficiency is defined as the efficiency of the fan compression of the bypass flow. The bypass efficiency is a function of the bypass flow rate at a given set of conditions. The bypass flow rate at the optimum bypass efficiency is appreciably lower than the maximum bypass flow rate at the given conditions. This results in increased design flexibility and improved overall engine performance.
    Type: Application
    Filed: April 30, 2019
    Publication date: January 9, 2020
    Applicant: ROLLS-ROYCE plc
    Inventors: Stephane M M BARALON, Mark J WILSON, Benedict R PHELPS
  • AIRCRAFT ENGINE FAN
    Publication number: 20200011273
    Abstract: A gas turbine engine system has an engine core and a bypass duct. A fan drives the flow through the bypass duct. A bypass efficiency is defined as the efficiency of the fan compression of the bypass flow. The bypass efficiency is a function of the bypass flow rate at a given set of conditions. The fan bypass inlet mass flow rate at the reference operating point is appreciably higher than the mass flow rate through the bypass duct at the peak bypass efficiency at a given fan reference rotational speed and cruise conditions. This results in increased design flexibility and improved overall engine performance.
    Type: Application
    Filed: May 14, 2019
    Publication date: January 9, 2020
    Applicant: ROLLS-ROYCE plc
    Inventors: Stephane M. M. BARALON, Mark J. WILSON, Benedict R. PHELPS
  • COOLING
    Publication number: 20200010208
    Abstract: An electric propulsion unit (102) for an aircraft is shown. A fan (202) produces a pressured airflow (P) by raising the pressure of an incident airflow (I). An electric machine (201) is arranged to drive the fan and is located within a casing (204). A primary cooling circuit (205) is located within the casing, and includes the electric machine and a first pass of a fluid-fluid heat exchanger (208), thereby placing the electric machine and the fluid-fluid heat exchanger in thermal communication. A secondary cooling circuit includes a second pass of the fluid-fluid heat exchanger and an air-fluid heat exchanger (210) located within the pressurised airflow produced by the fan, thereby placing the fluid-fluid heat exchanger and the air-fluid heat exchanger in thermal communication.
    Type: Application
    Filed: June 11, 2019
    Publication date: January 9, 2020
    Applicant: ROLLS-ROYCE plc
    Inventors: Richard PEACE, Adam NEWMAN
  • HIGH EFFICIENCY GAS TURBINE ENGINE
    Publication number: 20200011274
    Abstract: A gas turbine engine has a quasi-non-dimensional mass flow rate in a defined range and a specific thrust in a defined range to achieve improved over all performance, taking into account fan operability and/or bird strike requirements as well as engine efficiency. The defined ranges of quasi-non-dimensional mass flow rate and specific thrust may be particularly beneficial for gas turbine engines in which the fan is driven by a turbine through a gearbox.
    Type: Application
    Filed: May 28, 2019
    Publication date: January 9, 2020
    Applicant: ROLLS-ROYCE plc
    Inventors: Benjamin J. SELLERS, Craig W. BEMMENT, Michael O. HALES, Stephane M. M. BARALON, Benedict R. PHELPS, Christopher BENSON, Mark J. WILSON
  • BLADE FOR A GAS TURBINE ENGINE
    Publication number: 20200011188
    Abstract: A blade for a gas turbine engine that includes a blade root having an asymmetric lobe.
    Type: Application
    Filed: June 11, 2019
    Publication date: January 9, 2020
    Applicant: ROLLS-ROYCE plc
    Inventor: Andrew MEKERESZ
  • APPARATUS FOR GAS TURBINE ENGINES
    Publication number: 20200011250
    Abstract: Apparatus for a gas turbine engine, the apparatus comprising: a core engine casing having a longitudinal axis and including: an inner wall defining at least part of a core airflow path through the gas turbine engine; an outer wall defining an external surface of the core engine casing, a first cavity being defined between the inner wall and the outer wall of the core engine casing; a plurality of guide vanes extending radially from the outer wall of the core engine casing; a torque box defined within the first cavity of the core engine casing and at least partially overlapping axially with the plurality of guide vanes, the torque box defining a second cavity; and an accessory gear box positioned within the second cavity of the torque box.
    Type: Application
    Filed: June 11, 2019
    Publication date: January 9, 2020
    Applicant: ROLLS-ROYCE plc
    Inventors: Alan R. MAGUIRE, Richard G. STRETTON
  • Methods, apparatus, computer programs, and non-transitory computer readable storage mediums for controlling at least one of a first robot and a second robot to collaborate within a system
    Patent number: 10525595
    Abstract: A method of controlling at least one of a first robot and a second robot to collaborate within a system, the first robot and the second robot being physically separate to one another, the method including: receiving sensed data associated with the second robot; determining position and/or orientation of the second robot using the received sensed data; determining an action for the second robot using the determined position and/or orientation of the second robot; and providing a control signal to the second robot to cause the second robot to perform the determined action to collaborate with the first robot.
    Type: Grant
    Filed: June 8, 2017
    Date of Patent: January 7, 2020
    Assignee: ROLLS-ROYCE plc
    Inventors: Andrew D Norton, James Kell, Dragos A Axinte
  • GAS TURBINE
    Publication number: 20200003128
    Abstract: A gas turbine engine, in particular an aircraft engine, includes: a turbine connected via an input shaft device to a gearbox device having a sun gear, a planet carrier having a plurality of planet gears attached thereto, and a ring gear, the sun gear is connected to the input shaft device, the planet carrier or the ring gear is connected to a propulsive fan via an output shaft device of the gearbox device, with a rear carrier bearing device radially between the planet carrier and a static structure on the input side of the gearbox device or a front carrier bearing device radially between the planet carrier and a static structure on the output side of the gearbox device.
    Type: Application
    Filed: June 25, 2019
    Publication date: January 2, 2020
    Applicant: ROLLS-ROYCE plc
    Inventors: Alan R. MAGUIRE, Geoffrey HUGHES
  • GAS TURBINE
    Publication number: 20200003069
    Abstract: A gas turbine engine, in particular an aircraft engine, includes: a turbine connected via an input shaft device to a gearbox device having a sun gear, a planet carrier having a plurality of planet gears attached thereto, and a ring gear, the sun gear is connected to the input shaft device, the planet carrier or the ring gear is connected to a propulsive fan via an output shaft device of the gearbox device, with a rear carrier bearing device radially between the planet carrier and a static structure on the input side of the gearbox device, an inter-shaft bearing system being positioned radially between the input shaft device and the planet carrier of the gearbox device. The input shaft device having a high rigidity or the input shaft device having a means for decreasing the rigidity, in particular a diaphragm section.
    Type: Application
    Filed: June 25, 2019
    Publication date: January 2, 2020
    Applicant: ROLLS-ROYCE plc
    Inventor: Alan R. MAGUIRE
  • VARIABLE STATOR VANE ARRANGEMENT
    Publication number: 20200003073
    Abstract: A variable stator vane arrangement is provided in which the variable stator vanes extend from a first end at a radially inner flow boundary to a second end at a radially outer flow boundary. At least one of the radially inner flow boundary and the radially outer flow boundary is faceted, such that the surface of the faceted flow boundary comprises flat portions at the interfaces with the respective first or second end of each stator vane. The flat portions mean that the tips of the variable stator vanes can be made substantially flush with the flat casing portions. This may improve aerodynamic efficiency and/or increase the design flexibility on where to position the pivot axis of the variable stator vanes.
    Type: Application
    Filed: May 22, 2019
    Publication date: January 2, 2020
    Applicant: ROLLS-ROYCE plc
    Inventors: Neelambaran KARAPURATH, Robert J. KYLE
  • AERODROME SYSTEM AND METHOD
    Publication number: 20200005657
    Abstract: An aerodrome system for an aerodrome is provided. The aerodrome system comprises a plurality of light emitting elements configured to emit light from a surface of the aerodrome upon which aircraft may take-off, land and manoeuvre; and a controller operatively coupled to each of the light emitting elements so as to selectively control the light emitting elements, wherein the light emitting elements form pixels of a display and the controller is configured to control an image displayed by the display so as to display and demarcate at least one runway for aircraft to take-off or land, wherein the light emitting elements are spaced such that the controller may display the runway with a variable orientation and the controller is further configured to change the image displayed by the display so as to change the orientation of the runway.
    Type: Application
    Filed: June 3, 2019
    Publication date: January 2, 2020
    Applicant: ROLLS-ROYCE plc
    Inventor: Matthew MOXON
  • GAS TURBINE ENGINE
    Publication number: 20200003122
    Abstract: A gas turbine engine for an aircraft includes: a fan adjacent the engine air intake, including a plurality of fan blades; downstream of the fan, an engine core including a turbine, a compressor, and a core shaft connecting the turbine and compressor; an engine core housing at least partly encasing the core; a fan case surrounding the fan and defining at least part of a bypass duct radially outside the core; a plurality of outlet guide vanes extending between the engine core housing and an outlet guide vane support region of the case, adjacent an upstream end of the bypass duct; one or more supports extending from the case to the engine core housing, wherein: a first end of the supports fixes to the case at the outlet guide vane support region; a second end of the supports fixes to the engine core housing adjacent an engine core exhaust.
    Type: Application
    Filed: June 6, 2019
    Publication date: January 2, 2020
    Applicant: ROLLS-ROYCE plc
    Inventor: Johnathan H. WILSHAW
  • GAS TURBINE
    Publication number: 20200003127
    Abstract: A gas turbine engine, in particular an aircraft engine, includes: a turbine connected via an input shaft device to a gearbox device having a sun gear, a planet carrier having a plurality of planet gears attached thereto, and a ring gear, the sun gear is connected to the input shaft device, the planet carrier or the ring gear is connected to a propulsive fan via an output shaft device of the gearbox device, with a rear carrier bearing device radially between the planet carrier and a part on the input shaft on the input side of the gearbox device.
    Type: Application
    Filed: June 25, 2019
    Publication date: January 2, 2020
    Applicant: ROLLS-ROYCE plc
    Inventor: Mark N. BINNINGTON
  • Oil chamber wall
    Patent number: 10519804
    Abstract: An oil chamber wall arrangement is described as comprising: a chamber wall surrounding a rotor; a plurality of apertures defining through-holes for a flow of oil through the chamber wall, the apertures being defined by a pair of axially separated opposing walls and a pair of circumferentially opposing walls wherein the circumferentially opposing walls are separated by a midline which is radial to the rotational axis of the rotor and at least one of the pair of circumferentially opposing walls is not parallel to the radial midline.
    Type: Grant
    Filed: April 20, 2017
    Date of Patent: December 31, 2019
    Assignee: ROLLS-ROYCE plc
    Inventor: Merijn Alexander Brand Van Den Berg
  • Gas turbine engine with variable guide vanes and a unison ring
    Patent number: 10519798
    Abstract: A gas turbine engine comprises a plurality of variable guide vanes, a unison ring, and a lever arrangement connecting the unison ring to the variable guide vanes. The lever arrangement comprises a lever pin received by the unison ring, and a bush provided between the lever pin and the unison ring. The bush comprises a sprung region biased outwardly away from the lever pin towards the unison ring.
    Type: Grant
    Filed: September 8, 2017
    Date of Patent: December 31, 2019
    Assignee: ROLLS-ROYCE PLC
    Inventor: Michael G. Kennedy
  • Aircraft electrical network
    Patent number: 10518863
    Abstract: An aircraft has an internal combustion engine and a wing including a hollow structural member. The aircraft has an electrical network including: at least one alternating current electrical generator configured to be driven by the internal combustion engine; an electrical motor configured to drive an aircraft propulsor; at least one conductor configured to electrically couple the electrical motor and the electrical generator; wherein the electrical conductor is formed of the hollow structural member of the aircraft wing.
    Type: Grant
    Filed: April 10, 2017
    Date of Patent: December 31, 2019
    Assignee: ROLLS-ROYCE plc
    Inventor: Matthew Moxon
  • Control systems for machines
    Patent number: 10520911
    Abstract: A control system for a machine comprising a plurality of independently replaceable machine modules comprises a controller operable to control operation of the machine. Memory stores machine data for use by the controller. Communication means are operable to provide communication for data transfer between the controller and the memory. The memory includes a plurality of memory modules associated with respective machine modules. Each of the memory modules is replaceable with the respective associated machine module and independently of other memory modules. The communication means is operable to provide communication for data transfer between the controller and a replacement memory module associated with a replacement machine module.
    Type: Grant
    Filed: August 22, 2016
    Date of Patent: December 31, 2019
    Assignee: ROLLS-ROYCE plc
    Inventor: Peter Beecroft
  • GAS TURBINE ENGINE SPOOL
    Publication number: 20190390605
    Abstract: A spool of a gas turbine engine includes: a compressor having one or more compressor stages; a turbine having one or more turbine stages; and a core shaft joining the compressor to the turbine. The core shaft includes a bolted joint which connects a compressor end portion of the core shaft to a turbine end portion of the core shaft by a circumferential row of fastening bolts. The spool further includes a tie bar which extends through the core shaft to tie the compressor to the turbine.
    Type: Application
    Filed: June 13, 2019
    Publication date: December 26, 2019
    Applicant: ROLLS-ROYCE plc
    Inventor: Crispin D BOLGAR
  • INVESTMENT CASTING PATTERN
    Publication number: 20190388961
    Abstract: An investment casting pattern including: a consumable body formed of: a first body portion; and a second body portion; and a fastener arranged to form an interface between the first body portion and the second body portion, and to locate the first body portion relative to the second body portion, wherein the fastener is formed of a different material than the first body portion and the second body portion.
    Type: Application
    Filed: June 11, 2019
    Publication date: December 26, 2019
    Applicants: ROLLS-ROYCE plc, Rolls-Royce Deutschland Ltd & Co KG
    Inventors: David Stefan ISLES, Mareike WIEBALCK, Peter JESSON, Mark MULLAN, Christopher A HALL