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    MULTI-ENGINE SYSTEM AND POWER TRANSFER BETWEEN ENGINES THEREOF
    1.
    发明公开
    MULTI-ENGINE SYSTEM AND POWER TRANSFER BETWEEN ENGINES THEREOF 审中-公开

    公开(公告)号：EP4124574A1

    公开(公告)日：2023-02-01

    申请号：EP22186942.3

    申请日：2022-07-26

    申请人： PRATT & WHITNEY CANADA CORP.

    发明人： COUTU, Daniel

    IPC分类号： B64D27/14 ,  B64D33/00 ,  B64D35/08 ,  B64C27/14

    摘要： A multi-engine system (42) for an aircraft, has: a first engine (10A) having a first output shaft (32), a first core shaft (34), and a first electric machine (51A) operable as a generator drivingly engaged by the first output shaft (32) or the first core shaft (34); a second engine (10B) having a second output shaft (32), a second core shaft (34), and a second electric machine (51B) operable as an electric motor drivingly engaged to the second core shaft (34); a reduction gearbox (46) drivingly engaged by the first output shaft (32) and by the second output shaft (32) for driving a common load (44); and a transmission path between the first engine (10A) and the second engine (10B), the transmission path being independent from the reduction gearbox (46) and being one or more of: a torque-transfer connection between the second core shaft (34) and the first core shaft (34) or the first output shaft (32) via a coupling gearbox (52), and an electrical connection between the generator (51A) and the electric motor to transmit electrical power to the electric motor.

    HYBRID AIRCRAFT PROPULSION SYSTEM
    6.
    发明公开
    HYBRID AIRCRAFT PROPULSION SYSTEM 审中-公开

    公开(公告)号：EP3569498A1

    公开(公告)日：2019-11-20

    申请号：EP19171413.8

    申请日：2019-04-26

    申请人： Rolls-Royce plc

    发明人： Scothern, David

    IPC分类号： B64C21/06 ,  B64D27/12 ,  B64D27/14 ,  B64D27/24

    摘要： A hybrid aircraft propulsion system. The sytem comprises a gas turbine engine (5) comprising a compressor (11), a combustor (12), one or more turbines (13), a shaft (14) coupled to one of the turbines (13), and a bypass fan (10) mechanically driven by the shaft (14). The system further comprises an electrical generator (15) mechanically coupled to the shaft (14), and an auxiliary propulsor (6) mechanically coupled to an electric motor (16) and electrically coupled to the electric generator (15). At maximum power, the gas turbine engine (5) is configured to produce a turbine entry temperature at maximum power between 1800 Kelvin and 2000 Kelvin, the engine comprises a fan bypass ratio of between 4:1 and 13:1, and the generator is configured to absorb between 10% and 60% of the mechanical power generated by the turbine.

    AIRCRAFT HAVING AN AFT ENGINE
    7.
    发明公开
    AIRCRAFT HAVING AN AFT ENGINE 审中-公开

    公开(公告)号：EP3546348A1

    公开(公告)日：2019-10-02

    申请号：EP19155374.2

    申请日：2019-02-04

    申请人： General Electric Company

    发明人： YAO, Jixian ,  PASTOUCHENKO, Nikolai N. ,  LONNEMAN, Patrick John ,  MARRINAN, Patrick Michael ,  CEDAR, Richard David

    IPC分类号： B64C23/00 ,  B64D27/20 ,  B64D27/24 ,  B64D27/14

    摘要： An aircraft 10 includes a boundary layer ingestion fan 100 defining a centerline 116 and including a plurality of fan blades 120 rotatable about the centerline 116. The aircraft 10 also includes a fuselage 20 extending between a forward end 14 and an aft end 16 along a longitudinal direction (L), the boundary layer ingestion fan 100 positioned within the fuselage 20 at the aft end 16 of the fuselage 20, the fuselage 20 defining an inlet 102 upstream of the boundary layer ingestion fan 100 extending at least about 180 degrees around the centerline 116 of the boundary layer ingestion fan 100, the fuselage 20 further defining an exhaust 104 downstream of the boundary layer ingestion fan 100.

    PASSIVE INTERNAL ICE PROTECTION SYSTEMS FOR ENGINE INLETS
    9.
    发明公开
    PASSIVE INTERNAL ICE PROTECTION SYSTEMS FOR ENGINE INLETS 有权
    用于发动机进气道的被动内冰保护系统

    公开(公告)号：EP3170751A1

    公开(公告)日：2017-05-24

    申请号：EP16170623.9

    申请日：2016-05-20

    申请人： Bell Helicopter Textron Inc.

    发明人： AUBERT, Roger J.

    IPC分类号： B64D27/14 ,  B64D33/02

    CPC分类号： F02C7/055 ,  B64C27/06 ,  B64D27/14 ,  B64D33/02 ,  B64D2033/022 ,  B64D2033/0233 ,  B64D2033/0246 ,  F02C7/047 ,  F05D2220/329 ,  F05D2230/60 ,  F05D2300/171 ,  F05D2300/614

    摘要： A system (230) includes an engine cover (124; 200) covering a side-facing rotorcraft engine (120) and having an opening (204) and an ice protection member (126; 210) mounted on the engine cover (124; 200) between the opening (204) and the engine (120), an area of the ice protection member (126; 210) smaller than an area of the opening (204). The ice protection member (126; 210) is configured to partially cover the opening (204) to prevent ice having a particular size from entering into the engine (120) and to allow air flow downstream into the engine (120).

    摘要翻译： 一种系统（230）包括覆盖侧向旋翼飞行器发动机（120）并且具有安装在发动机盖（124; 200）上的开口（204）和防冰构件（126; 210）的发动机盖（124; 200） ）在所述开口（204）和所述发动机（120）之间，所述防冰构件（126; 210）的面积小于所述开口（204）的面积。 防冰构件（126; 210）构造成部分地覆盖开口（204）以防止具有特定尺寸的冰块进入发动机（120）并且允许空气流向下游进入发动机（120）。