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公开(公告)号：EP4390090A1
公开(公告)日：2024-06-26
申请号：EP23216503.5
申请日：2023-12-14
申请人： Rolls-Royce plc
发明人： Bemment, Craig W , Hobday, Alastair G , Keeler, Benjamin J , Madden, Christopher P , Minelli, Andrea , Smith, Andrew T , Swann, Peter , Yates, Martin K
CPC分类号： F02C7/224 , F02C7/06 , F02C7/36 , F02K3/06 , F05D2220/7620130101 , F05D2260/21320130101 , F05D2270/11220130101 , F05D2270/30320130101
摘要： A method (12000) of operating a gas turbine engine (10) is disclosed, the gas turbine engine (10) comprising an engine core comprising a turbine, a compressor, a combustor (16) 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 (42); a gearbox (30) that receives an input from the core shaft and outputs drive to the fan via the fan shaft (42); a primary oil loop system (2000) arranged to supply oil to the gearbox (30); and a heat exchange system. The heat exchange system comprises an air-oil heat exchanger (2020) through which oil in the primary oil loop system (2000) flows; and a fuel-oil heat exchanger (1006) through which the oil in the primary oil loop system (2000) and the fuel flow such that heat is transferred between the oil and the fuel, and wherein the primary oil loop system (2000) branches such that a proportion of the oil can flow along each branch and the air-oil and fuel-oil heat exchangers are arranged in a parallel configuration on different branches of the primary oil loop system (2000); and a modulation valve (2016) arranged to allow the proportion of oil sent via each branch to be varied. The method comprises controlling (12200) the heat exchange system so as to raise the fuel temperature to at least 135°C on entry to the combustor (16) at cruise conditions.
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公开(公告)号：EP4227508A1
公开(公告)日：2023-08-16
申请号：EP23153267.2
申请日：2023-01-25
申请人： Rolls-Royce plc
发明人： Swann, Peter
摘要： An engine system comprises a first fuel store, a second fuel store, an engine arranged to produce mechanical power by combustion or oxidation of a fuel in an engine, a fuel distribution system arranged to deliver fuel from the first and second fuel stores to the engine, the first fuel delivered at a first mass flow rate, the second fuel delivered at a second mass flow rate, the first and second mass flow rates contributing to a total mass flow rate of fuel to the engine, and a control system arranged to increase the relative fraction of the total mass flow rate of fuel represented by the second mass flow rate during a period of acceleration of the engine, in order to control a surge margin of the engine, wherein the second fuel is selected to have a higher specific energy than the first fuel and to release a greater mass of water per unit mass of fuel than the first fuel.
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公开(公告)号：EP4202197A1
公开(公告)日：2023-06-28
申请号：EP22210134.7
申请日：2022-11-29
申请人： Rolls-Royce plc
发明人： Swann, Peter , Bemment, Craig W , Hobday, Alastair G , Keeler, Benjamin J , Madden, Christopher P
摘要： A method 3020 of operating an aircraft comprising a gas turbine engine and a plurality of fuel tanks arranged to provide fuel to the gas turbine engine, wherein at least two of the fuel tanks contain fuels with different fuel characteristics, the method 3020 comprising obtaining 3022 a flight profile for a flight of the aircraft 1; and determining 3024 a fuelling schedule for the flight based on the flight profile and the fuel characteristics, the fuelling schedule governing the variation with time of how much fuel is drawn from each tank. Fuel input to the gas turbine engine may then be controlled 3026 in operation in accordance with the fuelling schedule.
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公开(公告)号：EP4155211A1
公开(公告)日：2023-03-29
申请号：EP22192721.3
申请日：2022-08-30
申请人： Rolls-Royce plc
发明人： Swann, Peter , Britchford, Kevin
摘要： An aircraft propulsion system (5) comprises first and second thrust producing gas turbine engines (10a, 10b). The system comprises a controller (36) configured to determine a required overall propulsion system thrust level, and determine an engine core power level contribution from each aircraft gas turbine engine such that the overall propulsion system produces a minimum overall noise level and meets the required overall propulsion system thrust level. In meeting the minimum overall noise level, at least the first and second gas turbine engines are operated at different engine core power settings.
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公开(公告)号：EP2677138A3
公开(公告)日：2018-01-24
申请号：EP13168161.1
申请日：2013-05-17
申请人： Rolls-Royce plc
发明人： Swann, Peter
摘要： A fuel system (10) comprising a fluid blender (14) in fluid communication with a source of a first fuel composition and a source of a second fuel composition via at least one inlet (32, 34). The blender (14) is operable to receive at least the first fuel composition and/or second fuel composition via the at least one inlet (32, 34), and output a resultant fuel composition comprising the received fuel compositions via at least one outlet (36). The at least one outlet (36) is in fluid communication with an engine fuel injection device (38).
摘要翻译： 一种燃料系统（10），包括经由至少一个入口（32,34）与第一燃料成分的来源和第二燃料成分的来源流体连通的流体混合器（14）。 混合器（14）可操作以经由至少一个入口（32,34）接收至少第一燃料组合物和/或第二燃料组合物，并且经由至少一个出口（32,34）输出包含接收到的燃料组合物的所得燃料组合物 36）。 该至少一个出口（36）与发动机燃料喷射装置（38）流体连通。
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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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公开(公告)号：EP4390097A1
公开(公告)日：2024-06-26
申请号：EP23216529.0
申请日：2023-12-14
申请人： Rolls-Royce plc
CPC分类号： F02C7/224 , F02C7/228 , F02C7/14 , F05D2260/21320130101
摘要： There is provided a method (400) 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 (401) a fuel to the one or more fuel-oil heat exchangers (114); transferring (402) heat from oil to the fuel in the one or more fuel-oil heat exchangers (114); and providing (403) the fuel from the one or more fuel-oil heat exchangers (114) to the plurality of fuel spray nozzles (124). Transferring (402) heat from the oil to the fuel comprises transferring 200-600 kW/m3 of heat from oil to the fuel in the one or more fuel-oil heat exchangers (114) at cruise conditions before providing the fuel to the plurality of fuel spray nozzles (124). Also provided is a gas turbine engine (10) for an aircraft.
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公开(公告)号：EP4390087A1
公开(公告)日：2024-06-26
申请号：EP23216520.9
申请日：2023-12-14
申请人： Rolls-Royce plc
发明人： Bemment, Craig W , Hobday, Alastair G , Keeler, Benjamin J , Madden, Christopher P , Minelli, Andrea , Smith, Andrew T , Swann, Peter , Yates, Martin K
摘要： A method (10000) of operating a gas turbine engine (10) is disclosed, the gas turbine engine (10) comprising a combustor (16) arranged to combust a fuel; and a fuel management system arranged to provide the fuel to the combustor (16), wherein the fuel management system comprises two fuel-oil heat exchangers through which oil and the fuel flow, the heat exchangers arranged to transfer heat between the oil and the fuel and comprising a primary fuel-oil heat exchanger (1004) and a secondary fuel-oil heat exchanger (1006); a fuel pump (1003) arranged to deliver the fuel to the combustor (16), wherein the fuel pump (1003) is located between the two fuel-oil heat exchangers; and a recirculation valve (6010) located downstream of the primary fuel-oil heat exchanger (1004), the recirculation valve (6010) arranged to allow a controlled amount of fuel which has passed through the primary fuel-oil heat exchanger (1004) to be returned to the inlet of the primary fuel-oil heat exchanger (1004). The method comprises selecting (10100) one or more fuels such that the calorific value of the fuel provided to the gas turbine engine (10) is at least 43.5 MJ/kg.
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公开(公告)号：EP4261395A1
公开(公告)日：2023-10-18
申请号：EP23165284.3
申请日：2023-03-30
申请人： Rolls-Royce plc
IPC分类号： F02C3/20 , F02C7/22 , F02C9/40 , G06Q10/0631
摘要： The present application discloses a computer implemented method (4070) of determining a fuel allocation for an aircraft (1). The aircraft (1) comprises a first fuel source (302) adapted to contain a first fuel having a first fuel characteristic and a second fuel source (304) adapted to contain a second fuel having a second fuel characteristic, the second fuel characteristic being different from the first. The aircraft (1) further comprises one or more gas turbine engines (10) powered by fuel from the first and second fuel sources (302, 304). The gas turbine engines (10) each comprise a staged combustion system (64) having pilot fuel injectors (313) and main fuel injectors (314), the staged combustion system (64) being operable in a pilot-only range of operation and a pilot-and-main range of operation. The gas turbine engines (10) each comprise a fuel delivery regulator (306) arranged control delivery of fuel to the pilot and main fuel injectors (313, 314) from the first fuel source (302) and the second fuel source (304). The method (4070) comprises the following steps: obtaining (4072) a proposed mission description comprising a list of operating conditions for the gas turbine engines during the mission; obtaining (4074) nvPM impact parameters for the gas turbine engines (10), the impact parameters being associated with each operating condition of the proposed mission using compositions of fuel which include fuel from the first fuel source (302), fuel from the second fuel source (304), or a blend thereof; calculating (4076) an optimised set of one or more fuel characteristics for each flight condition of the proposed flight defined in the flight description based on the nvPM impact parameters; and determining (4078) a fuel allocation based on the optimised set of one or more fuel characteristics. Also disclosed is method (4080) of loading fuel onto an aircraft (1), a non-transitory computer readable medium, a fuel allocation determination system (5000), and an aircraft (1).
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