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    Aircraft operation
    1.
    发明授权
    Aircraft operation 有权

    公开(公告)号：US12241422B2

    公开(公告)日：2025-03-04

    申请号：US18212290

    申请日：2023-06-21

    Applicant: ROLLS-ROYCE PLC

    Inventor： Benjamin J Keeler ,  David M Beaven ,  Craig W Bemment ,  Paul W Ferra ,  Kevin R McNally ,  Andrea Minelli ,  Martin K Yates

    IPC: F02C9/28

    Abstract: A method of determining at least one fuel characteristic of a fuel provided to a gas turbine engine of an aircraft includes making an operational change, the operational change being effected by a controllable component of a propulsion system of which the gas turbine engine forms a part, and being arranged to affect operation of the gas turbine engine, sensing a response to the operational change; and determining the at least one fuel characteristic based on the response to the operational change.

    Method of operating a gas turbine engine
    2.
    发明授权
    Method of operating a gas turbine engine 有权

    公开(公告)号：US12241421B1

    公开(公告)日：2025-03-04

    申请号：US18753264

    申请日：2024-06-25

    Applicant: ROLLS-ROYCE PLC

    Inventor： Andrea Minelli ,  Craig W Bemment ,  Benjamin J Keeler ,  David M Beaven ,  Kevin R McNally

    IPC: F02C7/14 ,  F02C7/06 ,  F02C7/36

    Abstract: A method of operating a gas turbine engine comprising an engine core comprising 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 gearbox that receives an input from the core shaft and outputs drive to the fan; an oil loop system arranged to supply oil to the gearbox; and a heat exchange system comprising an air-oil heat exchanger through which the oil flows, a fuel-oil heat exchanger through which the oil and the fuel flow; and a valve arranged to allow a proportion of the oil sent via at least one of the heat exchangers to be varied, is disclosed, the method comprising controlling the valve such that, under cruise conditions, an oil flow ratio of: rate ⁢ of ⁢ oil ⁢ flow ⁢ into ⁢ air - oil ⁢ heat ⁢ exchanger rate ⁢ of ⁢ oil ⁢ flow ⁢ into ⁢ fuel - oil ⁢ heat ⁢ exchanger is in the range from 0 to 0.59.

    Gas turbine temperature sensor
    3.
    发明授权
    Gas turbine temperature sensor 有权

    公开(公告)号：US12281614B1

    公开(公告)日：2025-04-22

    申请号：US18753237

    申请日：2024-06-25

    Applicant: ROLLS-ROYCE plc

    Inventor： Andrea Minelli ,  Benjamin J Keeler ,  Craig W Bemment ,  David M Beaven ,  Kevin R Mcnally

    IPC: F02C7/14 ,  F02C7/36

    Abstract: A method of operating a gas turbine engine including: an engine core with a turbine, compressor, a fuel combustor, and a core shaft connecting the turbine to the compressor; a fan; a gearbox that receives an input from the core shaft and outputs drive to the fan; an oil loop system arranged to supply oil to the gearbox; and a heat exchange system including: an air-oil heat exchanger through which the oil flows; a fuel-oil heat exchanger through which the oil and the fuel flow; a temperature sensor downstream of the fuel-oil heat exchanger; and a valve arranged to allow oil or air flow rate through at least one heat exchanger to be varied, the method including: determining if the fuel temperature has increased above a set threshold at cruise conditions; and in response, controlling the valve so as to change the flow rate through the heat exchanger.

    Aircraft operation
    7.
    发明授权
    Aircraft operation 有权

    公开(公告)号：US11859565B2

    公开(公告)日：2024-01-02

    申请号：US17853333

    申请日：2022-06-29

    Applicant: ROLLS-ROYCE PLC

    Inventor： Benjamin J Keeler ,  David M Beaven ,  Craig W Bemment ,  Paul W Ferra ,  Kevin R Mcnally ,  Andrea Minelli ,  Martin K Yates

    IPC: F02C9/28

    CPC classification number: F02C9/28 ,  F05D2220/323 ,  F05D2240/35 ,  F05D2270/303 ,  F05D2270/309 ,  F05D2270/3013

    Abstract: A gas turbine engine includes: a combustor that combust the fuel and having an exit, a combustor exit temperature (T40) is the average temperature of flow and a combustor exit pressure (P40) is the total pressure there; a turbine including a rotor having a leading edge and a trailing edge, and wherein a turbine rotor entry temperature (T41) is an average temperature of flow at the leading edge and a turbine rotor entry pressure (P41) is the total pressure there; and a compressor having an exit, wherein a compressor exit temperature (T30) is the average temperature of flow at the exit from the compressor and a compressor exit pressure (P30) is the total pressure there (all at cruise conditions). A method of determining at least one fuel characteristic includes changing a fuel supplied to the engine; and determining a change in a relationship between T30 or P30, T40 and T41, or of P40 and P41, respectively.

    Exhaust content
    8.
    发明授权
    Exhaust content 有权

    公开(公告)号：US12152496B2

    公开(公告)日：2024-11-26

    申请号：US18138333

    申请日：2023-04-24

    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: 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 method comprises: determining, during use of the gas turbine engine, one or more exhaust content parameters by performing a sensor measurement on an exhaust of the gas turbine engine; and determining one or more fuel characteristics of the fuel based on the one or more exhaust parameters including the nvPM content of the exhaust. Also disclosed is a fuel characteristic determination system, a method of operating an aircraft, and an aircraft.

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