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1. 发明公开

EP3597894A1 SUPERSONIC AIRCRAFT TURBOFAN 无效转让
公开(公告)号：EP3597894A1
公开(公告)日：2020-01-22
申请号：EP19182551.2
申请日：2019-06-26
申请人： Rolls-Royce plc
发明人： Whurr, John , Hickey, Conor
IPC分类号： F02K1/08 , F02K1/09 , F02K1/34 , F02K1/38 , F02K1/48 , F02K1/12 , F02K3/06
摘要： The present disclosure relates to a turbofan engine having: an engine core having a centre axis and comprising in flow series a compressor, a combustor and a turbine; and a bypass duct surrounding the engine core, the bypass duct having a bypass duct exit area (A COLD ) at its downstream end. The engine further comprises an exhaust nozzle assembly comprising: coaxially arranged inner mixer and outer exhaust nozzles, the exhaust nozzle being axially downstream of said mixer nozzle; a core flow duct defined by the mixer nozzle, the core flow duct having a core exit area (A HOT ); and an exhaust duct defined at least in part by the exhaust nozzle downstream of the mixer nozzle, the exhaust duct having an exhaust throat area (A 8 ). The bypass duct exit area (A COLD ) and core exit area (A HOT ) are axially aligned at a mixing plane to form a mixing plane area (A MIX ). The turbofan engine has a transonic thrust condition, a supersonic cruise condition and a take-off condition. In the supersonic cruise condition, the exhaust throat area (A 8 ) is increased relative to the exhaust throat area (A 8 ). In the take-off condition, the core exit area (A HOT ) is increased relative to the core exit area (A HOT ) in the transonic condition, and the bypass duct exit area (A COLD ) is decreased relative to the bypass duct exit area (A COLD ) in the transonic condition.

2. 发明公开

EP4215738A3 HYBRID POWER SYSTEM 有权
公开(公告)号：EP4215738A3
公开(公告)日：2023-10-04
申请号：EP23150231.1
申请日：2023-01-04
申请人： Rolls-Royce plc
发明人： Hickey, Conor , MacKay, Andrew
IPC分类号： F02C9/00 , B64C11/44 , B64D27/24 , F02K5/00
摘要： A hybrid power system for an aircraft comprises a gas turbine connected to a generator for generating electrical power; an electrical storage device configured to output electrical power; a propulsor; a motor operable to drive the propulsor using electrical power from either or both of the generator and the electrical storage device; and a controller. The controller, to meet a propulsor power demand, is configured to control (i) an amount of electrical power generated by the generator, and (ii) an amount of electrical power outputted by the electrical storage device. In a first control mode coinciding with an increase in the propulsor power demand sufficient to cause a transient excursion of the operating point of a compressor of the gas turbine from a steady state working line, the controller is further configured to temporarily increase the amount of electrical power outputted by the electrical storage device such that the transient excursion is reduced.

3. 发明授权

EP3599368B1 EXHAUST NOZZLE ASSEMBLY 有权转让
公开(公告)号：EP3599368B1
公开(公告)日：2020-08-26
申请号：EP19181190.0
申请日：2019-06-19
申请人： Rolls-Royce plc
发明人： Watson, Jonathan , Hickey, Conor
IPC分类号： F02K1/09 , F02K1/38

4. 发明公开

EP3597893A1 SUPERSONIC AIRCRAFT TURBOFAN 无效转让
公开(公告)号：EP3597893A1
公开(公告)日：2020-01-22
申请号：EP19181409.4
申请日：2019-06-20
申请人： Rolls-Royce plc
发明人： Stieger, Rory , Hickey, Conor
IPC分类号： F02K1/06 , F02K3/06 , F02K1/17 , F02K3/075
摘要： A turbofan engine for providing propulsive thrust to a supersonic aircraft is provided. The engine has an engine core comprising in flow series a compressor, a combustor and a turbine. The engine further has a fan located upstream of the engine core. The engine further has a supersonic intake for slowing down incoming air to subsonic velocities at an inlet to the fan formed by the intake. The engine further has a bypass duct surrounding the engine core, wherein the fan generates a core airflow to the engine core and a bypass airflow through the bypass duct. The engine further has a mixer for mixing an exhaust gas flow exiting the engine core and the bypass airflow exiting the bypass duct. The engine further has a thrust nozzle rearwards of the mixer for discharging the mixed flows, the thrust nozzle having a variable area throat. The engine further has a controller configured to control the thrust produced by the engine over a range of flight operations including on-the-ground subsonic take-off and subsequent off-the-ground subsonic climb. To achieve a high level of engine thrust during the take-off operation, the controller performs the take-off operation with a reduced area of the variable area throat, and to achieve a reduced jet noise after take-off, during the climb operation the controller increases the area of the variable area throat.

5. 发明公开

EP4215738A2 HYBRID POWER SYSTEM 有权
公开(公告)号：EP4215738A2
公开(公告)日：2023-07-26
申请号：EP23150231.1
申请日：2023-01-04
申请人： Rolls-Royce plc
发明人： Hickey, Conor , MacKay, Andrew
IPC分类号： F02C9/00 , B64C11/44 , B64D27/24 , F02K5/00
摘要： A hybrid power system for an aircraft comprises a gas turbine connected to a generator for generating electrical power; an electrical storage device configured to output electrical power; a propulsor; a motor operable to drive the propulsor using electrical power from either or both of the generator and the electrical storage device; and a controller. The controller, to meet a propulsor power demand, is configured to control (i) an amount of electrical power generated by the generator, and (ii) an amount of electrical power outputted by the electrical storage device. In a first control mode coinciding with an increase in the propulsor power demand sufficient to cause a transient excursion of the operating point of a compressor of the gas turbine from a steady state working line, the controller is further configured to temporarily increase the amount of electrical power outputted by the electrical storage device such that the transient excursion is reduced.

6. 发明公开

EP3599368A1 EXHAUST NOZZLE ASSEMBLY 有权转让
公开(公告)号：EP3599368A1
公开(公告)日：2020-01-29
申请号：EP19181190.0
申请日：2019-06-19
申请人： Rolls-Royce plc
发明人： Watson, Jonathan , Hickey, Conor
IPC分类号： F02K1/09 , F02K1/38
摘要： The present disclosure relates to an exhaust nozzle assembly for a gas turbine engine having a centre axis. The assembly comprises concentrically arranged inner mixer and outer exhaust nozzles, the exhaust nozzle extending axially downstream of said mixer nozzle. A centre-body is axially mounted within and extends axially downstream from the mixer nozzle. A core flow duct is defined by the mixer nozzle and the centre-body, the core flow duct having a core exit area. An exhaust duct is defined at least in part by the exhaust nozzle downstream of the mixer nozzle, the exhaust duct having an exhaust exit area. The mixer nozzle comprises a mixer cowl which is axially-translatable along the centre axis and the exhaust nozzle comprises an exhaust cowl which is either axially-translatable along or angularly-adjustable relative to the centre axis. The assembly further comprises an actuation mechanism and the mixer cowl and exhaust cowl are movable by the actuation mechanism between a first position in which the core exit area and exhaust exit area are maximum and a second position in which the core exit area and exhaust exit area are minimum.

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