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26 条记录 (耗时 0.016 秒)

    AIRCRAFT HEAT MANAGEMENT
    2.
    发明公开
    AIRCRAFT HEAT MANAGEMENT 审中-公开

    公开(公告)号：EP4390094A1

    公开(公告)日：2024-06-26

    申请号：EP23216513.4

    申请日：2023-12-14

    申请人： Rolls-Royce plc

    发明人： Bemment, Craig ,  Keeler, Benjamin ,  Madden, Christopher ,  Minelli, Andrea ,  Swann, Peter ,  Yates, Martin

    IPC分类号： F02C7/14 ,  F02C7/36 ,  F01D25/18 ,  F02C7/06 ,  F02C7/224

    CPC分类号： F02C7/14 ,  F05D2260/21320130101 ,  F05D2260/9820130101 ,  F02C7/36 ,  F05D2260/4031120130101 ,  F02C7/06 ,  F01D25/18 ,  F02C7/224

    摘要： A method (18000) of operating a gas turbine engine (10) is disclosed, the gas turbine engine (10) comprising an engine core (11) comprising a turbine (19), a compressor (14), a combustor (16) arranged to combust a fuel, and a core shaft (26) connecting the turbine to the compressor; a fan (23) located upstream of the engine core (11); a fan shaft (42); a main gearbox (30) that receives an input from the core shaft (26) and outputs drive to the fan (23) via the fan shaft (42), the main gearbox (30) comprising gears (28, 32, 38) and journal bearings (44); a recirculating lubrication system (2000a') arranged to supply oil to lubricate the gears and journal bearings, the lubrication system comprising a first oil tank (2002') arranged to supply oil to the gears and journal bearings and a second oil tank (2008b') arranged to supply oil to the journal bearings only; and a heat exchange system (1007, 2020) arranged to transfer heat between the oil and the fuel. The method (18000) comprises, at cruise conditions: transferring 200 - 600 kJ/m3 of heat to the fuel from the oil through the heat exchange system (1007, 2020) so as to control the oil temperature; and providing cooler oil to the journal bearings (44) than to the gears (28, 32, 38).

    GAS TURBINE ENGINE
    4.
    发明公开
    GAS TURBINE ENGINE 审中-公开

    公开(公告)号：EP3741982A1

    公开(公告)日：2020-11-25

    申请号：EP20171457.3

    申请日：2020-04-27

    申请人： Rolls-Royce plc

    发明人： Bemment, Craig

    IPC分类号： F02K3/06 ,  F02C3/107 ,  F02C7/36

    摘要： The present disclosure relates to a gas turbine engine for an aircraft. Example embodiments include a gas turbine engine (10) for an aircraft comprising: an engine core (11) comprising a turbine (19), a compressor (14), and a core shaft (26) connecting the turbine to the compressor; and a fan (23) located upstream of the engine core, the fan comprising a plurality of fan blades, wherein the gas turbine engine (10) is configured such that a flow velocity ratio between a first flow velocity at an exit of the engine core (11) and a second flow velocity at an inlet of the engine core (11) is within a range from around 0.82 to around 1.1 at cruise conditions.

    AIRCRAFT FUELLING
    7.
    发明公开
    AIRCRAFT FUELLING 审中-公开

    公开(公告)号：EP4390098A1

    公开(公告)日：2024-06-26

    申请号：EP23216527.4

    申请日：2023-12-14

    申请人： Rolls-Royce plc

    发明人： Madden, Christopher ,  Bemment, Craig ,  Smith, Andrew ,  Swann, Peter

    IPC分类号： F02C7/224 ,  F02C7/228

    CPC分类号： F02C7/224 ,  F02C7/228 ,  F05D2260/21320130101

    摘要： There is provided a method (300) of operating a gas turbine engine (10). The gas turbine engine (10) comprises a combustor (16). The combustor (16) comprises a combustion chamber (120) and a plurality of fuel spray nozzles (124) configured to inject fuel into the combustion chamber (120). The plurality of fuel spray nozzles (124) comprises a first subset (124A) of fuel spray nozzles (124) and a second subset (124B) of fuel spray nozzles (124). The combustor (16) is operable in a condition in which the first subset (124A) of fuel spray nozzles (124) are supplied with more fuel than the second subset (124B) of fuel spray nozzles (124). A ratio of the number of fuel spray nozzles (124) in the first subset (124A) of fuel spray nozzles (124) to the number of fuel spray nozzles (124) in the second subset (124B) of fuel spray nozzles (124) is in the range of 1:2 to 1:5. The method (200) comprises: providing (301) a fuel to the one or more fuel-oil heat exchangers (114); transferring (302) heat from oil to the fuel in the one or more fuel-oil heat exchangers (114); and providing (303) the fuel from the one or more fuel-oil heat exchangers (114) to the plurality of fuel spray nozzles (124). Heat is transferred from the oil to the fuel in the one or more fuel-oil heat exchangers (114) to raise a temperature of the fuel to an average of at least 135°C on injection of the fuel into the combustion chamber (120) at cruise conditions. Also provided is a gas turbine engine (10) for an aircraft.

    FLEET FUEL ALLOCATION
    8.
    发明公开
    FLEET FUEL ALLOCATION 审中-公开

    公开(公告)号：EP4261398A1

    公开(公告)日：2023-10-18

    申请号：EP23165300.7

    申请日：2023-03-30

    申请人： Rolls-Royce plc

    发明人： Swann, Peter ,  Bemment, Craig ,  Madden, Christopher

    IPC分类号： F02C7/22 ,  F02C9/40 ,  G06Q10/0631

    摘要： The present application discloses a computer implemented method (4090) of determining a fleetwide fuel allocation for a plurality of missions carried out by a plurality of aircraft, the plurality of missions being supplied with fuel from a fuel source comprising an amount of a default fuel and an amount of a non-default fuel, the fuel allocation indicating the amount of the non-default fuel and the default fuel to be allocated to each of the plurality of missions, the default fuel and the non-default fuel having one or more fuel characteristics different from each other. The method comprises the following steps: obtaining (4092) an initial proposed fuel allocation for each of the plurality of missions; performing (4094) a fleet-wide optimisation in which the proposed fuel allocation of each of the plurality of missions is modified within the constraints of the total available default and/or non-default fuel from the fuel source to minimise a sum of per-mission nvPM impact parameters over all of the plurality of missions, each of the plurality of missions being associated with a respective per-mission nvPM impact parameter determined according to a fuel usage for that mission, the fuel usage defining how the fuel allocation for the respective mission is to be used during that mission; and determining (4096) the fleetwide fuel allocation for the plurality of missions based on the fleet-wide optimisation. Also disclosed is a method (4100) of loading fuel onto a plurality of aircraft, a non-transitory computer readable medium and a fleetwide fuel allocation determination system (5100).

    GAS TURBINE ENGINE
    9.
    发明公开
    GAS TURBINE ENGINE 审中-公开

    公开(公告)号：EP3855005A2

    公开(公告)日：2021-07-28

    申请号：EP21150296.8

    申请日：2021-01-05

    申请人： Rolls-Royce plc

    发明人： Bemment, Craig ,  Dunning, Pascal

    IPC分类号： F02C9/00 ,  F02K3/06 ,  B64D31/00

    摘要： A gas turbine engine (10) comprises a fan (23), a compressor (14, 15), a low pressure turbine (19) and a high pressure turbine (17). The fan diameter is greater than 250 cm and less than 381 cm, and the gas turbine engine has a first thrust at sea level static conditions and a second thrust at end of runway conditions, and a thrust take-off ratio greater than 1.32, wherein the thrust take-off ratio is the ratio of the first thrust to the second thrust.

    GAS TURBINE ENGINE
    10.
    发明公开
    GAS TURBINE ENGINE 审中-公开

    公开(公告)号：EP3792471A1

    公开(公告)日：2021-03-17

    申请号：EP20190605.4

    申请日：2020-08-12

    申请人： Rolls-Royce plc

    发明人： Bemment, Craig

    IPC分类号： F02C7/06 ,  F02C7/36

    摘要： There is provided a gas turbine engine comprising a low pressure shaft and a high pressure shaft; wherein the low pressure shaft connects a fan to a fan drive turbine, and the high pressure shaft connects a high pressure turbine to a compressor section. The low pressure shaft and the high pressure shaft are arranged such that when operating at idle the idle shaft speed ratio is greater than 6.05. The idle shaft speed ratio is the ratio of the speed of the high pressure shaft to the speed of the low pressure shaft at idle conditions.