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156 条记录 (耗时 0.019 秒)

    NACELLE FOR AN AIRCRAFT AFT FAN
    1.
    发明公开
    NACELLE FOR AN AIRCRAFT AFT FAN 审中-实审

    公开(公告)号：EP4292939A3

    公开(公告)日：2024-03-20

    申请号：EP23207884.0

    申请日：2018-01-10

    申请人： General Electric Company

    发明人： RAMAKRISHNAN, Kishore ,  WOOD, Trevor Howard

    IPC分类号： B64D27/20 ,  B64C7/02 ,  B64D33/02 ,  B64D27/14 ,  B64D27/32 ,  B64D27/33

    摘要： An aircraft (10) is provided including a fuselage (12) extending between a forward end (16) and an aft end (18). An aft engine is mounted to the fuselage (12) at the aft end of the fuselage (18). The aft engine includes a nacelle (306) having a forward section. An airflow duct (344) is also provided extending at least partially through the nacelle (306) and including an opening on the forward section of the nacelle (330). The opening is configured for providing an airflow to, or receiving an airflow from, the forward section of the nacelle (306) to increase an amount of, e.g., boundary layer airflow received within the aft engine during operation of the aircraft (10), to guide the flow of boundary layer airflow into the engine more smoothly, or to reduce a distortion on the engine.

    AIRCRAFT HAVING AN AFT ENGINE
    6.
    发明公开
    AIRCRAFT HAVING AN AFT ENGINE 审中-公开

    公开(公告)号：EP3984879A1

    公开(公告)日：2022-04-20

    申请号：EP21213544.6

    申请日：2017-08-25

    申请人： General Electric Company

    发明人： RAMAKRISHNAN, Kishore ,  YAO, Jixian ,  PASTOUCHENKO, Nikolai ,  MALCEVIC, Ivan

    IPC分类号： B64C1/16 ,  B64D27/20 ,  B64C21/08 ,  B64C1/00 ,  B64D27/14

    摘要： An aircraft is provided including a fuselage that extends along a longitudinal direction between a forward end and an aft end. A boundary layer ingestion fan is mounted to the fuselage at the aft end and is configured for ingesting boundary layer airflow off the surface of the fuselage. The fuselage defines a profile proximate the boundary layer ingestion fan that is optimized for ingesting a maximum amount of boundary layer air and improving propulsive efficiency of the aircraft. More specifically, the fuselage defines a cross sectional profile upstream of the boundary layer ingestion fan that has more cross sectional area in a top half relative to a bottom half as defined relative to a centerline of the boundary layer ingestion fan.

    SYSTEMS AND METHODS FOR HYBRID ELECTRIC GAS TURBINE ENGINES
    8.
    发明公开
    SYSTEMS AND METHODS FOR HYBRID ELECTRIC GAS TURBINE ENGINES 审中-公开

    公开(公告)号：EP3943733A1

    公开(公告)日：2022-01-26

    申请号：EP21168570.6

    申请日：2021-04-15

    申请人： Raytheon Technologies Corporation

    发明人： KUPRATIS, Daniel ,  ROBERGE, Gary

    IPC分类号： F02C6/00 ,  F02C6/20 ,  F02K1/00 ,  F02K5/00 ,  F02C7/04 ,  F02K3/04 ,  B64D27/20

    摘要： A hybrid electric gas turbine propulsion system (100) may comprise: a first propulsion system (401), a second propulsion system (402), and a third propulsion system (403). The first propulsion system (401) may comprise a first fan (212), a first turbine (252), a first compressor (232), and a first electric motor (190), the first fan (212) operably coupled to the first turbine (252) and the first compressor (232) by a first shaft (126), the first shaft (126) coupled to the first electric motor (190), the first shaft (126) configured to be disposed radially inward of a fuselage (12) of an aircraft (10). The second propulsion system (402) and the third propulsion system (403) may be in accordance with the first propulsion system (401). The hybrid electric gas turbine propulsion system (100) may be symmetric about a vertical plane extending through a neutral aerodynamic axis (104).

    MOTOR-INTEGRATED FLUID MACHINE AND VERTICAL TAKEOFF AND LANDING AIRCRAFT
    9.
    发明公开
    MOTOR-INTEGRATED FLUID MACHINE AND VERTICAL TAKEOFF AND LANDING AIRCRAFT 审中-公开

    公开(公告)号：EP3904216A1

    公开(公告)日：2021-11-03

    申请号：EP20755522.8

    申请日：2020-01-14

    申请人： MITSUBISHI HEAVY INDUSTRIES, LTD.

    发明人： FUJIWARA, Naoaki

    IPC分类号： B64D27/20 ,  B64D27/24 ,  H02K7/14

    摘要： A motor-integrated fan having an intake port and a blow-out port comprises a rotary part 12 that is rotatably supported by a shaft, and a motor 14 that rotates the rotary part 12. The motor 14 is an outer periphery drive motor that rotates the rotary part 12 by supplying motive power from a duct provided on the outer peripheral side of the shaft. The motor 14 includes: a permanent magnet 45 provided on a rotary support ring 33 connected to the outer peripheral side of blades 32 of the rotary part 12; and a coil 46 provided opposite the permanent magnet 45 in the axial direction of the axis of rotation. Among the plurality of blades 32, a first blade 32a and a second blade 32b are located at different positions in the axial direction.