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    Fuel delivery
    2.
    发明授权
    Fuel delivery 有权

    公开(公告)号：US12163479B2

    公开(公告)日：2024-12-10

    申请号：US18125477

    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: F02C9/28 ,  B64D27/12 ,  B64D37/00 ,  B64D41/00

    Abstract: The present application discloses a method of determining one or more fuel characteristics of an aviation fuel suitable for powering a gas turbine engine of an aircraft, the gas turbine engine having a combustor supplied with fuel from a fuel system, the method comprising: determining a mass of the fuel being supplied to the combustor; determining a corresponding volume of the fuel being supplied to the combustor; and determining one or more fuel characteristics based on the determined mass and volume. Also disclosed is a fuel characteristic determination system, a method of operating an aircraft, and an aircraft.

    Fuelling schedule
    3.
    发明授权
    Fuelling schedule 有权

    公开(公告)号：US11815031B2

    公开(公告)日：2023-11-14

    申请号：US17853074

    申请日：2022-06-29

    Applicant: ROLLS-ROYCE PLC

    Inventor： Peter Swann ,  Craig W Bemment ,  Alastair G Hobday ,  Benjamin J Keeler ,  Christopher P Madden

    IPC: F02C9/28 ,  B64D37/04 ,  B64D27/10 ,  G08G5/00

    CPC classification number: F02C9/28 ,  B64D27/10 ,  B64D37/04 ,  G08G5/0034

    Abstract: A method of operating an aircraft including a gas turbine engine and a plurality of fuel tanks arranged to provide fuel to the gas turbine engine, where at least two of the fuel tanks contain fuels with different fuel characteristics. The method includes obtaining a flight profile for a flight of the aircraft; and determining a fuelling schedule for the flight based on the flight profile and the fuel characteristics. The fuelling schedule governs the variation with time of how much fuel is drawn from each tank. Fuel input to the gas turbine engine may then be controlled in operation in accordance with the fuelling schedule.

    Contrail parameters
    4.
    发明授权
    Contrail parameters 有权

    公开(公告)号：US12152497B2

    公开(公告)日：2024-11-26

    申请号：US18328225

    申请日：2023-06-02

    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: F01D21/00 ,  F02C9/28

    Abstract: A method of determining one or more fuel characteristic of an aviation fuel suitable for powering a gas turbine engine of an aircraft is disclosed. The method includes: determining, during use of the gas turbine engine, one or more contrail parameters related to contrail formation by the gas turbine engine. The determining of the one or more contrail parameters includes performing a sensor measurement on a region behind the gas turbine engine in which a contrail is or can be formed. The method also includes determining one or more fuel characteristics of the fuel based on the one or more contrail parameters. A fuel characteristic determination system, a method of operating an aircraft and an aircraft are also disclosed.

    Heat transfer
    5.
    发明授权
    Heat transfer 有权

    公开(公告)号：US12098677B2

    公开(公告)日：2024-09-24

    申请号：US18337497

    申请日：2023-06-20

    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 includes operating the gas turbine engine using a fuel having a lubricity of between 0.71 mm and 0.90 mm wear scar diameter (WSD) at 25° C.

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