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    SUPERSONIC AIRCRAFT TURBOFAN
    7.
    发明公开
    SUPERSONIC AIRCRAFT TURBOFAN 审中-公开

    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.