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    Aircraft propulsion
    21.
    发明授权
    Aircraft propulsion 有权

    公开(公告)号：US12240614B2

    公开(公告)日：2025-03-04

    申请号：US18209136

    申请日：2023-06-13

    Applicant: ROLLS-ROYCE plc

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

    IPC: B64D37/04 ,  B64D27/10 ,  B64D41/00 ,  F02C7/22 ,  F02C9/26

    Abstract: A power system for an aircraft includes one or more gas turbine engines arranged to burn a fuel so as to provide power to the aircraft; a plurality of fuel tanks each arranged to contain a fuel to be used to provide power to the aircraft; and a fuel manager. At least two of the fuel tanks contain different fuels, which have different proportions of a sustainable aviation fuel. The fuel manager is arranged to store information on the fuel contained in each fuel tank; and to control fuel supply so as to select a specific fuel accordingly to power at least the majority of operations on the ground. The fuel manager may additionally identify which tank contains the fuel with the highest proportion of a sustainable aviation fuel; and that fuel may be used to power at least the majority of operations on the ground.

    Engine parameters
    26.
    发明授权
    Engine parameters 有权

    公开(公告)号：US11643980B1

    公开(公告)日：2023-05-09

    申请号：US17853233

    申请日：2022-06-29

    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

    CPC classification number: F02C9/28 ,  F05D2220/323 ,  F05D2270/30

    Abstract: A method of determining a calorific value of fuel supplied to a gas turbine engine of an aircraft comprises sensing at least one engine parameter during a first time period of aircraft operation during which the gas turbine engine uses the fuel; and, based on the at least one sensed engine parameter, determining a calorific value of the fuel. The sensing may be repeated such that the at least one engine parameter is monitored over time. The gas turbine engine may be a propulsive gas turbine engine of the aircraft or a gas turbine engine of an auxiliary power unit of the aircraft.

    Gas turbine engine heat exchange
    28.
    发明授权
    Gas turbine engine heat exchange 有权

    公开(公告)号：US12241415B1

    公开(公告)日：2025-03-04

    申请号：US18753128

    申请日：2024-06-25

    Applicant: ROLLS-ROYCE plc

    Inventor： Benjamin J Keeler ,  Craig W Bemment ,  Andrea Minelli ,  Alastair G Hobday ,  Andrew T Smith

    IPC: F02C7/14 ,  F28D21/00

    Abstract: A method of operating a gas turbine engine includes an engine core with a turbine, compressor, fuel combustor, and core shaft; a fan 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 supplying oil to the gearbox; and a heat exchange system including: air-oil and fuel-oil heat exchangers, and wherein the oil loop system branches such that part of the oil flows along each branch and the air-oil and fuel-oil heat exchangers are parallel on different branches; and a modulation valve allows the oil sent via each branch to be varied, the method including controlling the heat exchange system wherein, under cruise conditions, a heat transfer ratio of: rate ⁢ of ⁢ heat ⁢ transfer ⁢ from ⁢ oil ⁢ to ⁢ air rate ⁢ of ⁢ heat ⁢ transfer ⁢ from ⁢ oil ⁢ to ⁢ fuel is in the range from 0 to 0.67.

    Gas turbine engine heat exchange
    29.
    发明授权
    Gas turbine engine heat exchange 有权

    公开(公告)号：US12158115B2

    公开(公告)日：2024-12-03

    申请号：US18337568

    申请日：2023-06-20

    Applicant: ROLLS-ROYCE plc

    Inventor： Craig W Bemment ,  Alastair G Hobday ,  Benjamin J Keeler ,  Christopher P Madden ,  Andrea Minelli ,  Andrew T Smith ,  Peter Swann ,  Martin K Yates

    IPC: F02C9/38 ,  F02C7/14 ,  F02C7/16 ,  F02C7/224

    Abstract: A method of operating a gas turbine engine including: a combustor arranged to combust a fuel; and a fuel management system arranged to provide the fuel to the combustor, wherein the fuel management system includes two fuel-oil heat exchangers through which oil and fuel flow, which are arranged to transfer heat between the oil and fuel and include primary and secondary fuel-oil heat exchangers; a fuel pump arranged to deliver the fuel to the combustor, wherein the fuel pump is located between the heat exchangers; and a recirculation valve located downstream of the primary heat exchanger, the recirculation valve arranged to allow a controlled amount of fuel which has passed through the primary heat exchanger to be returned to the inlet. The method includes selecting one or more fuels such that the calorific value of the fuel provided to the gas turbine engine is at least 43.5 MJ/kg.

    Exhaust content
    30.
    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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