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    Transmittance parameters
    1.
    发明授权
    Transmittance parameters 有权

    公开(公告)号：US12152542B2

    公开(公告)日：2024-11-26

    申请号：US18328991

    申请日：2023-06-05

    Applicant: ROLLS-ROYCE plc

    Inventor： Peter Swann ,  David M. Beaven ,  Craig W. Bemment ,  Alastair G. Hobday ,  Benjamin J. Keeler ,  Christopher P. Madden ,  Martin K. Yates

    IPC: F02C9/40 ,  F02C9/28

    Abstract: The present application provides a method of determining one or more fuel characteristics of an aviation fuel suitable for powering a gas turbine engine of an aircraft. The method includes: passing UV-visual spectrum light through the fuel; measuring a transmittance parameter indicating the transmittance of light through the fuel; determining one or more fuel characteristics of the fuel based on the transmittance parameter; and communicating the one or more fuel characteristic to a control module of the gas turbine engine or the aircraft. Also disclosed is a fuel characteristic determination system, a method of operating an aircraft, and an aircraft.

    Aircraft refuelling
    2.
    发明授权
    Aircraft refuelling 有权

    公开(公告)号：US12241423B2

    公开(公告)日：2025-03-04

    申请号：US18125431

    申请日：2023-03-23

    Applicant: ROLLS-ROYCE PLC

    Inventor： Craig W Bemment ,  Benjamin J Keeler ,  Paul W Ferra ,  Alastair G Hobday ,  Kevin R McNally ,  Andrea Minelli ,  Martin K. Yates

    IPC: F02C9/40 ,  F02C9/28

    Abstract: A method of refuelling an aircraft comprising a gas turbine engine and a fuel tank arranged to provide fuel to the gas turbine engine comprises obtaining an amount of energy required for an intended flight profile; obtaining a calorific value of fuel available to the aircraft for refuelling; calculating the amount of the available fuel needed to provide the required energy; and refuelling the aircraft with the calculated amount of the available fuel. The calculating the amount of the available fuel needed to provide the required energy may comprise obtaining an energy content of fuel already in the fuel tank and subtracting that from the determined amount of energy required for the intended flight profile.

    HEAT TRANSFER
    4.
    发明公开
    HEAT TRANSFER 审中-公开

    公开(公告)号：US20240287937A1

    公开(公告)日：2024-08-29

    申请号：US18657237

    申请日：2024-05-07

    Applicant: ROLLS-ROYCE plc

    Inventor： Craig W. BEMMENT ,  Alastair G. Hobday ,  Benjamin J. Keeler ,  Andrea Minelli ,  Andrew T. Smith ,  Martin K. Yates

    IPC: F02C7/224 ,  F02C7/14 ,  F02C7/32

    CPC classification number: F02C7/224 ,  F02C7/14 ,  F02C7/32 ,  F05D2260/20

    Abstract: A method of operating a gas turbine engine having an engine core having a turbine, a compressor, a combustor arranged to combust a fuel, and a core shaft connecting the turbine to the compressor; a fan located upstream of the engine core; a fan shaft; a gearbox that receives an input from the core shaft and outputs drive to the fan via the fan shaft; a heat exchange system having at least one fuel-oil heat exchanger arranged to transfer heat to the fuel; and a fuel pump arranged to deliver the fuel to the combustor, wherein the fuel pump is located downstream of the at least one fuel-oil heat exchanger. The method comprises controlling the heat exchange system so as to raise the fuel temperature to at least 135° C. on entry to the combustor at cruise conditions.

    Assembly of a servo pump and a hydraulic motor
    6.
    发明授权
    Assembly of a servo pump and a hydraulic motor 有权

    公开(公告)号：US11162426B2

    公开(公告)日：2021-11-02

    申请号：US16932940

    申请日：2020-07-20

    Applicant: ROLLS-ROYCE plc

    Inventor： Martin K. Yates ,  Stephanie E. Watkins ,  Geir Leivseth

    IPC: F02C7/228 ,  F15B13/02 ,  F23R3/34

    Abstract: An assembly of a servo pump and a hydraulic motor. The assembly has a housing which contains the pump and the motor. The motor has a rotating body which rotates under the motive power of a pressurised motor liquid flow. The motor has a high pressure region which receives the pressurised motor liquid flow, and a low pressure region through which the motor liquid flow leaves the motor. The pump also has a rotating body. The pump has a low pressure region which receives servo liquid flow to be pumped by its rotating body, and a high pressure region through which pressurised servo liquid flow leaves the pump. Each rotating body is mounted on a respective journal.

    Gear pump
    7.
    发明授权
    Gear pump 有权

    公开(公告)号：US10174760B2

    公开(公告)日：2019-01-08

    申请号：US15255945

    申请日：2016-09-02

    Applicant: ROLLS-ROYCE plc

    Inventor： David Brookes ,  Martin K. Yates

    IPC: F04C14/28 ,  F04C2/14 ,  F04C14/08 ,  F02C7/236 ,  F04C29/00 ,  F04C2/08 ,  F04C2/10 ,  F04C11/00 ,  F04C15/00

    Abstract: A gear pump has first and second meshing gears for pumping a fluid. The gear pump further has a first electrical motor having a first rotor, a first stator and first coil windings. The gear pump further has a second electrical motor having a second rotor, a second stator and second coil windings. The first rotor is operatively connected to the first gear and the second rotor is operatively connected to the second gear such that each gear is rotated by its respective rotor. The first and second coil windings are energized by respective and separate first and second electrical power circuits such that the first and second meshing gears can be driven independently of each other.

    Combustion staging system
    9.
    发明授权
    Combustion staging system 有权

    公开(公告)号：US11204168B2

    公开(公告)日：2021-12-21

    申请号：US16011865

    申请日：2018-06-19

    Applicant: ROLLS-ROYCE PLC

    Inventor： Martin K. Yates ,  Daniel J. Bickley

    IPC: F23R3/34 ,  F23R3/28 ,  F23K5/14 ,  F23K5/06 ,  F02C9/34 ,  F02C7/228 ,  F02C7/232 ,  F02C9/26 ,  F02C7/14 ,  F02C7/22 ,  F02C7/236

    Abstract: A combustion staging system has: a splitter; pilot and mains fuel manifolds; mains flow control valves; and fuel servo line. Each mains flow control valve has a chamber containing a piston, the chamber to a piston mains side fed by the mains fuel manifold, and the chamber to a piston servo side fed by the servo line. The piston has an open pilot-and-mains position allowing flow from the chamber mains side to the respective injector mains discharge orifice. The piston prevents flow from the chamber mains side. The piston is movable under a pressure change in the servo line relative to the mains fuel manifold. The system has a servo pump and a hydraulic motor driving it. The servo pump changes fuel pressure. Motive power for the hydraulic motor is fuel diverted from a fuel pump high pressure output, the motor returning the diverted fuel to a low pressure input.

    Aero-engine low pressure pump
    10.
    发明授权
    Aero-engine low pressure pump 有权

    公开(公告)号：US10197062B2

    公开(公告)日：2019-02-05

    申请号：US15256108

    申请日：2016-09-02

    Applicant: Rolls-Royce PLC

    Inventor： David Brookes ,  Martin K. Yates

    IPC: F04D15/00 ,  F02C7/236 ,  F02C9/30 ,  F02C7/22 ,  F02K3/06 ,  F04D1/00 ,  F04D13/06 ,  F04D29/22

    Abstract: An aero-engine low pressure pump is provided for supplying fuel at a raised pressure to a high pressure pump. The low pressure pump has a pumping mechanism which raises the pressure of fuel flowing though the mechanism. The low pressure pump further has electrical motor which drives the pumping mechanism. The low pressure pump further has a variable frequency motor drive which supplies electrical power to the electrical motor. The variable frequency motor drive measures the electrical power supplied to the electrical motor. The low pressure pump further has a control unit which compares the measured electrical power to a reference power, and, when the measured electrical power is less than the reference power by a predetermined amount, controls the motor drive to increase the power supplied to the electrical motor thereby increasing the pressure rise produced by the pumping mechanism.

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