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1. 发明公开

EP4390093A1 GAS TURBINE ENGINE FOR AN AIRCRAFT AND METHOD OF OPERATION 审中-公开
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.

2. 发明公开

EP4390098A1 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.

3. 发明公开

EP3719276A1 OIL PIPE ASSEMBLY 有权
公开(公告)号：EP3719276A1
公开(公告)日：2020-10-07
申请号：EP20162607.4
申请日：2020-03-12
申请人： Rolls-Royce plc
发明人： Booth, Michael , Smith, Andrew , Patel, Ajay
IPC分类号： F02C7/06 , F01D25/18 , F16L9/18 , G01M3/28
摘要： An oil pipe assembly (100) for a gas turbine engine (10). The oil pipe assembly includes a first pipe (105) that defines a first fluid passage (110) between an oil supply and a bearing chamber (55), and a second pipe (115) that houses the first pipe and defines a second fluid passage (120) between the first pipe and the second pipe that is supplied with cooling air. The oil pipe assembly also includes a restrictor (140) that extends from the second pipe (115) and restricts the passage of fluid from the second fluid passage (120) before it flows into a breather. Pressure and temperature sensors (150, 155) are located adjacent the restrictor (140) to detect and measure changes in air pressure and air temperature adjacent the restrictor from which a controller (160) identifies whether a leak has occurred in the first pipe or the second pipe. A method for detecting a leak in the oil pipe assembly (100), and a gas turbine (10) are also described.

4. 发明公开

EP4390097A1 COMBUSTION MANAGEMENT 审中-公开
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
发明人： Madden, Christopher , Bemment, Craig , Smith, Andrew , Swann, Peter
IPC分类号： F02C7/14 , F02C7/224 , F02C7/228
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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