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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
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).
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2.发明公开
公开(公告)号：EP4033082A1
公开(公告)日：2022-07-27
申请号：EP22150415.2
申请日：2022-01-06
申请人： Rolls-Royce plc
发明人： Swann, Peter , Madden, Christopher
摘要： In an aircraft comprising a set of lean-burn gas turbine engines each operating in pilot-plus-mains mode with a given initial fuel flow Wo, a method of controlling the optical depth of contrails produced by a first group of the engines comprises the steps of (i) reducing fuel flow to each engine in the first group to change the operation of each engine in the first group from pilot-plus-mains mode to pilot-only mode, and (ii) adjusting fuel flow to one or more engines in a second group of the engines such that the total fuel flow to engines of the second group is increased, all engines of the second group remaining in pilot-plus-mains mode, and wherein the set of lean-burn engines consists of the first and second groups. Depending on atmospheric conditions, the average optical depth of contrails produced by the engines may be enhanced or reduced compared to the case where all engines operate in pilot-plus-mains mode with a fuel flow W 0 .
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公开(公告)号：EP4390096A1
公开(公告)日：2024-06-26
申请号：EP23216526.6
申请日：2023-12-14
申请人： Rolls-Royce plc
发明人： Madden, Christopher , Bemment, Craig , Ferra, Paul , Keeler, Benjamin , Minelli, Andrea , Swann, Peter , Yates, Martin
CPC分类号： F02C7/224 , F02C7/14 , F02C9/20 , F05D2260/21320130101 , F05D2270/30320130101
摘要： There is provided a method (300) of operating a gas turbine engine (10) having a lean burn staged combustion system having a combustor (16) in which fuel is combusted. The gas turbine engine (10) comprises a fuel-oil heat exchanger (114) arranged to transfer heat between oil and fuel that is provided to the combustor (16). The method (300) comprises transferring heat (301) from the oil to the fuel before the fuel enters the combustor (16) so as to raise the fuel temperature to an average of at least 135°C on entry to the combustor (16) at cruise conditions. Also provided is a gas turbine for an aircraft.
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公开(公告)号：EP3875741A1
公开(公告)日：2021-09-08
申请号：EP21155908.3
申请日：2021-02-09
申请人： Rolls-Royce plc
发明人： Madden, Christopher , Swann, Peter
摘要： A gas turbine engine for an aircraft. The gas turbine comprises a combustor (206), a fuel injection system (305,307,308,312) connected with a source of fuel (306) and configured to inject fuel into the combustor, a water injection system (301,303,304,311) connected with a source of water (302) and which is configured to inject water into the combustor, and a control system (212). The control system is configured to identify an atmospheric condition; determine a water-fuel ratio for injection into the combustor of the gas turbine engine in response to the atmospheric condition; and control injection of fuel and water by the fuel injection system and the water injection system according to said water-fuel ratio to control an soot emissions caused by combustion of fuel therein.
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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
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.
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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
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).
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公开(公告)号：EP4144973A1
公开(公告)日：2023-03-08
申请号：EP22191701.6
申请日：2022-08-23
申请人： Rolls-Royce plc
发明人： Swann, Peter , Madden, Christopher
摘要： A gas turbine engine (105) comprising a variable geometry combustor (206, 206', 206") having fuel injectors (302), a rich-burn zone (1101), a quick-quench zone (1102), and a lean-burn zone (1104), and further comprising quench ports (1103) for admitting quench air to the quick-quench zone; a variable geometry airflow arrangement (303) for the variable geometry combustor, which is configured to vary an airflow through the fuel injectors and/or the quench ports; and a control system configured to control the variable geometry airflow arrangement in dependence upon an airflow delivered to the combustor, a fuel flow to the fuel injectors, and a target index of soot emissions to control the quantity of soot produced by combustion.
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公开(公告)号：EP4144972A1
公开(公告)日：2023-03-08
申请号：EP22191700.8
申请日：2022-08-23
申请人： Rolls-Royce plc
发明人： Swann, Peter , Madden, Christopher
摘要： A gas turbine engine (105) comprising a variable geometry combustor (206, 206', 206") having pilot fuel injectors (302) and main fuel injectors (304); a fuel metering system configured to control fuel flow to the pilot fuel injectors and the main fuel injectors; a variable geometry airflow arrangement (305) for the variable geometry combustor, which is configured to vary the airflow through the pilot fuel injectors and/or the main fuel injectors; a control system configured to control the variable geometry airflow arrangement in dependence upon airflow delivered to the combustor, the fuel flow to the pilot fuel injectors and the main fuel injectors, and a target index of soot emissions, thereby controlling airflow through the pilot fuel injectors and/or the main fuel injectors and hence the quantity of soot produced by combustion.
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公开(公告)号：EP4394169A1
公开(公告)日：2024-07-03
申请号：EP23216502.7
申请日：2023-12-14
申请人： Rolls-Royce plc
发明人： Madden, Christopher , Beaven, David , Bemment, Craig , Ferra, Paul , Keeler, Benjamin , Swann, Peter , Yates, Martin
CPC分类号： F02C7/222 , F02C7/224 , F02C7/236 , F02C7/228 , F02C9/40 , F05D2260/9820130101 , F05D2260/21320130101 , F05D2260/20520130101 , F05D2270/30320130101 , F02C7/14 , F02C3/24
摘要： There is provided a method (1000) of operating a gas turbine engine (10). The gas turbine engine (10) comprises a combustor (16) having a plurality of fuel spray nozzles (403, 404) and a fuel system arranged to provide fuel to the combustor (16). The fuel system comprises: a fuel pump (904); a fuel distributing valve (909) downstream of the fuel pump (904) arranged to distribute fuel to the plurality of fuel spray nozzles (403, 404) and bias fuel flow to the nozzles (403, 404) such that a first subset (403) of the plurality of fuel spray nozzles (403, 404) receives more fuel than a second subset (404) of the plurality of fuel spray nozzles (403, 404); and a fuel-oil heat exchanger (903). The method (1000) comprises providing a fuel to the combustor (16) and transferring heat from oil to the fuel in the fuel-oil heat exchanger (903) before the fuel enters the combustor (16) so as to lower a viscosity of the fuel to 0.58 mm2/s or lower on entry to the combustor (16) at cruise conditions. Also provided is a gas turbine engine (10) for an aircraft.
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公开(公告)号：EP4390229A1
公开(公告)日：2024-06-26
申请号：EP23216518.3
申请日：2023-12-14
申请人： Rolls-Royce plc
发明人： Madden, Christopher , Beaven, David , Bemment, Craig , Ferra, Paul , Gunasekaran, Barani , Keeler, Benjamin , Swann, Peter , Yates, Martin
摘要： There is provided a method (1000) of operating a gas turbine engine (10). The gas turbine engine (10) comprises a staged combustor (16) comprising an arrangement of fuel spray nozzles (403, 404) in which fuel flow is biased to a subset of the nozzles (403, 404) adjacent one or more ignitors (405) during a re-light procedure. The method (1000) comprises providing fuel (1001) to the combustor (16) having a calorific value of at least 43.5 MJ/kg. Also disclosed is a gas turbine engine (10).
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