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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：EP4261138A1
公开(公告)日：2023-10-18
申请号：EP23165313.0
申请日：2023-03-30
申请人： Rolls-Royce plc
发明人： Bemment, Craig W , Keeler, Benjamin J , Ferra, Paul W , Hobday, Alastair G , McNally, Kevin R , Minelli, Andrea , Yates, Martin K
摘要： A method 2020 of refuelling an aircraft comprising a gas turbine engine and a fuel tank arranged to provide fuel to the gas turbine engine comprises obtaining 2022 an amount of energy required for an intended flight profile; obtaining 2024 a calorific value of fuel available to the aircraft for refuelling; calculating 2026 the amount of the available fuel needed to provide the required energy; and refuelling 2029 the aircraft with the calculated amount of the available fuel. The calculating 2026 the amount of the available fuel needed to provide the required energy may comprise obtaining an energy content of fuel already in the fuel tank and subtracting that from the determined amount of energy required for the intended flight profile.
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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：EP4390095A1
公开(公告)日：2024-06-26
申请号：EP23216524.1
申请日：2023-12-14
申请人： Rolls-Royce plc
CPC分类号： F02C7/224 , F02C7/14 , F05D2260/21320130101 , F02C9/20
摘要： A method (11000) of operating a gas turbine engine (10) is disclosed, the gas turbine engine (10) comprising a fuel delivery system (1000, 6000) arranged to provide fuel; a combustor (16) arranged to combust at least a proportion of the fuel; a primary fuel-oil heat exchanger (1004) arranged to have up to 100% of the fuel provided by the fuel delivery system (1000, 6000) flow therethrough; and a secondary fuel-oil heat exchanger (1006) arranged to have a proportion of the fuel from the primary fuel-oil heat exchanger (1004) flow therethrough. Fuel is arranged to flow from the primary fuel-oil heat exchanger (1004) to the secondary fuel-oil heat exchanger (1006) and oil is arranged to flow from the secondary fuel-oil heat exchanger to the primary fuel-oil heat exchanger. The method (11000) comprises transferring (11200) 200 - 600 kJ/m3 of heat to the fuel from the oil in the primary fuel-oil heat exchanger (1004) at cruise conditions.
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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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公开(公告)号：EP4390093A1
公开(公告)日：2024-06-26
申请号：EP23216510.0
申请日：2023-12-14
申请人： Rolls-Royce plc
发明人： Bemment, Craig , Hobday, Alastair , Keeler, Benjamin , Minelli, Andrea , Smith, Andrew , Yates, Martin
IPC分类号： F02C7/14 , F02C7/22 , F02C7/224 , F02C7/228 , F02C7/236 , F02C9/40 , F02C3/24 , F02C7/18 , F02C7/32
CPC分类号： F02C7/14 , F02C7/18 , F02C7/32 , F02C7/236 , F02C7/224 , F02C9/40 , F02C3/24 , F05D2260/21320130101 , F05D2260/9820130101 , F05D2220/7620130101 , F05D2260/20520130101 , F05D2270/30320130101
摘要： A method (13000) of operating a gas turbine engine (10) is disclosed, the gas turbine engine (10) comprising an engine core (11) 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 (11); 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 heat exchange system comprising one or more heat exchangers arranged to transfer heat to the fuel; and a fuel pump arranged to deliver the fuel to the combustor (16), wherein the fuel pump is located downstream of the one or more heat exchangers. The method (13000) comprises controlling (13200) 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：EP4345272A1
公开(公告)日：2024-04-03
申请号：EP23198861.9
申请日：2023-09-21
申请人： Rolls-Royce plc
发明人： Minelli, Andrea
摘要： A gas turbine engine for an aircraft comprises: an engine core comprising a compressor, a combustor, a turbine, and a core shaft connecting the turbine to the compressor; a fan; turbomachinery bearings; a power gearbox adapted to drive the fan at a lower rotation speed than the turbine; and a heat management system configured to provide lubrication and cooling to the gearbox and turbomachinery bearings, and comprising a pipe assembly adapted to provide a lubricant flow to the gearbox and turbomachinery bearings to remove the heat generated by the gearbox and turbomachinery bearings, at least one air-lubricant heat exchanger to dissipate a first amount of heat to a first heat sink, and at least one fuel-lubricant heat exchanger to dissipate a second amount of heat to a second heat sink; wherein the first heat sink is air and the second heat sink is fuel.
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公开(公告)号：EP4345270A1
公开(公告)日：2024-04-03
申请号：EP23198864.3
申请日：2023-09-21
申请人： Rolls-Royce plc
发明人： Minelli, Andrea
摘要： A gas turbine engine for an aircraft comprises: an engine core comprising a compressor, a combustor, a turbine, and a core shaft connecting the turbine to the compressor; a fan comprising a plurality of fan blades and arranged upstream of the engine core; turbomachinery bearings; a power gearbox adapted to drive the fan at a lower rotation speed than the turbine; and a heat management system configured to provide lubrication and cooling to the power gearbox and turbomachinery bearings, and comprising a pipe assembly adapted to provide a lubricant flow to the power gearbox and turbomachinery bearings to remove the heat generated by the power gearbox and turbomachinery bearings, at least one air-lubricant heat exchanger to dissipate a first amount of heat to a first heat sink, and at least one fuel-lubricant heat exchanger to dissipate a second amount of heat to a second heat sink, wherein the first heat sink is air and the second heat sink is fuel.
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公开(公告)号：EP4223998A1
公开(公告)日：2023-08-09
申请号：EP23150896.1
申请日：2023-01-10
申请人： Rolls-Royce plc
发明人： Minelli, Andrea
IPC分类号： F02C7/224
摘要： The present invention provides a combination of a gas turbine engine and a power electronics for powering aircraft and/or engine systems. The engine includes an engine core comprising a turbine, a combustor, a compressor, and a core shaft connecting the turbine to the compressor, and a fuel circuit for supplying a fuel flow to the combustor. The power electronics is configured to transfer heat produced by the power electronics to a cooling flow formed by a portion of the fuel flow. The fuel circuit is configured to circulate the cooling flow in a loop during selected engine conditions such that the cooling flow transfers heat from the power electronics to a phase change material located on the loop. The phase change material has a phase change temperature at a predetermined limiting temperature whereby the phase change material stores heat from the cooling flow to prevent the power electronics exceeding the limiting temperature.
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公开(公告)号：EP4202195A1
公开(公告)日：2023-06-28
申请号：EP22209108.4
申请日：2022-11-23
申请人： Rolls-Royce plc
发明人： Keeler, Benjamin J , Beaven, David M , Bemment, Craig W , Ferra, Paul W , McNally, Kevin R , Minelli, Andrea , Yates, Martin K
摘要： A gas turbine engine of an aircraft forms part of a propulsion system, and comprises: a combustor arranged to combust the fuel and having an exit, and wherein a combustor exit temperature - T40 - is defined as an average temperature of flow at the combustor exit and a combustor exit pressure - P40 - is defined as the total pressure there; a turbine comprising a rotor having a leading edge and a trailing edge, and wherein a turbine rotor entry temperature - T41 - is defined as an average temperature of flow at the leading edge of the rotor of the turbine and a turbine rotor entry pressure - P41 - is defined as the total pressure there; and a compressor having an exit, wherein a compressor exit temperature - T30 - is defined as an average temperature of flow at the exit from the compressor at cruise conditions and a compressor exit pressure - P30 - is defined as the total pressure there (all at cruise conditions). A method of determining at least one fuel characteristic of a fuel provided to the gas turbine engine comprises changing a fuel supplied to the gas turbine engine; and determining the at least one fuel characteristic of the fuel based on a change in a relationship between T30 or P30 and one of T40 and T41, or of P40 and P41, respectively.
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