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1. 发明公开

EP4390087A1 GAS TURBINE ENGINE HEAT EXCHANGE 审中-公开
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
IPC分类号： F02C3/24 , F02C7/14 , F02C7/224 , F02C9/36 , F02C9/40
CPC分类号： F02C3/24 , F02C7/224 , F02C7/14 , F02C9/40 , F02C9/36 , F05D2260/21320130101
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.

2. 发明公开

EP4202436A1 AVIATION FUEL 审中-实审
公开(公告)号：EP4202436A1
公开(公告)日：2023-06-28
申请号：EP22209100.1
申请日：2022-11-23
申请人： Rolls-Royce plc
发明人： Swann, Peter , Beaven, David M , Bemment, Craig W , Hobday, Alastair G , Keeler, Benjamin J , Madden, Christopher P , Yates, Martin K
IPC分类号： G01N33/28
摘要： The present application discloses a method (1030) of determining one or more fuel characteristics of an aviation fuel (F) for powering a gas turbine engine (10) of an aircraft (1). The method comprises: measuring (1031) one or more trace substance parameters of the fuel (F), the one or more trace substance parameters each associated with a respective trace substance in the fuel (F); and
determining (1032) one or more fuel characteristics of the fuel (F) based on the one or more trace substance parameters. Also disclosed is a fuel characteristic determination system (126), a method (1065) of operating an aircraft (1), and an aircraft.

3. 发明公开

EP4390090A1 A GAS TURBINE ENGINE 审中-公开
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
IPC分类号： F02C7/06 , F02C7/224 , F02C7/36 , F02K3/06
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.

4. 发明公开

EP4202197A1 FUELLING SCHEDULE 审中-实审
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
IPC分类号： F02C7/22 , F02C9/28 , F02C9/40
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.

5. 发明公开

EP4261396A1 FUEL DELIVERY 审中-实审
公开(公告)号：EP4261396A1
公开(公告)日：2023-10-18
申请号：EP23165309.8
申请日：2023-03-30
申请人： Rolls-Royce plc
发明人： Swann, Peter , Bemment, Craig W , Madden, Christopher P
IPC分类号： F02C3/20 , F02C9/28 , F02C9/40
摘要： The present application discloses a gas turbine engine (10) for an aircraft (1), comprising:
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; and a fuel delivery regulator (306) arranged to control delivery of fuel to the pilot and main fuel injectors (313, 314). The fuel delivery regulator (306) is arranged to receive fuel from a first fuel source (302) containing a first fuel having a first fuel characteristic and a second fuel source (304) containing a second fuel having a second fuel characteristic, the second fuel characteristic being different from the first. The fuel delivery regulator (306) is arranged to deliver fuel to the pilot fuel injectors (313) during at least part of the pilot-only range of operation having a different fuel characteristic from fuel delivered to one or both of the pilot and main fuel injectors (313, 314) during at least part of the pilot-and-main range of operation. A method (4000) of operating a gas turbine engine (10) is also disclosed.

6. 发明公开

EP4202198A1 FUEL CHARACTERISTICS 审中-实审
公开(公告)号：EP4202198A1
公开(公告)日：2023-06-28
申请号：EP22209097.9
申请日：2022-11-23
申请人： Rolls-Royce plc
发明人： Swann, Peter , Bemment, Craig W , Hobday, Alastair G , Keeler, Benjamin J , Madden, Christopher P
IPC分类号： F02C9/40 , F01D21/00 , F02C9/28
摘要： A method 2000 of identifying a fuel contained in a fuel tank of an aircraft and arranged to power a gas turbine engine of the aircraft is performed by processing circuitry of the aircraft and comprises: obtaining 2002 at least one fuel characteristic of any fuel already present in the fuel tank prior to refuelling; determining 2004 at least one fuel characteristic of a fuel added to the fuel tank on refuelling; and calculating 2006 at least one fuel characteristic of the resultant fuel in the fuel tank after refuelling. The method 2000 may further controlling 2008 the propulsion system of the aircraft based on the calculated at least one fuel characteristic of the resultant fuel in the fuel tank after refuelling.

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