利索-全球专利检索

  1. 登录
  2. 注册

搜索结果

156 条记录 (耗时 0.015 秒)

    AIRCRAFT HAVING AN AFT ENGINE
    92.
    发明公开
    AIRCRAFT HAVING AN AFT ENGINE 审中-公开

    公开(公告)号：EP4223632A1

    公开(公告)日：2023-08-09

    申请号：EP23166092.9

    申请日：2017-08-25

    申请人： General Electric Company

    发明人： PASTOUCHENKO, Nikolai ,  MALCEVIC, Ivan

    IPC分类号： B64C21/04 ,  B64C21/06 ,  B64D27/20

    摘要： An air injection assembly for an aircraft is provided. The aircraft includes a fuselage extending between a forward end and an aft end along a longitudinal direction and a boundary layer ingestion fan mounted to the fuselage at the aft end of the fuselage. The air injection assembly includes at least one injection port defined on a surface of the fuselage at a location upstream of the boundary layer ingestion fan. A supplemental airflow is provided through a fluid passageway to the injection port where it is ejected to displace at least a portion of relatively higher velocity boundary layer airflow. In this manner, the airflow entering boundary layer ingestion fan is more uniform, has less swirl distortion, and has a lower average velocity.

    FUSELAGE FOR AN AIRCRAFT WITH FUSELAGE-INTEGRATED TAILPLANE
    94.
    发明公开
    FUSELAGE FOR AN AIRCRAFT WITH FUSELAGE-INTEGRATED TAILPLANE 审中-公开

    公开(公告)号：EP4180332A1

    公开(公告)日：2023-05-17

    申请号：EP21207682.2

    申请日：2021-11-11

    申请人： Airbus Defence and Space GmbH

    发明人： Stangl, Wolfgang ,  Osterhuber, Robert ,  Ernstberger, Philipp

    IPC分类号： B64D27/20 ,  B64D33/04 ,  B64D29/06 ,  B64C15/02 ,  B64C1/16 ,  F02K1/00 ,  B64C15/12

    摘要： A fuselage (3) for an aircraft (1) is described. The fuselage has a control element (20) with an integrated engine outlet (23). The control element (20) is integrated at a rear end (2) of the fuselage (3), so that the control element (20) terminates flush with an outer skin (4) of the fuselage in a circumferential direction of the fuselage (3). An outer wall (40) of the control element (20) surrounds the engine outlet (23) so that the engine outlet (23) is directed towards an open rear side (6) of the control element (20). The control element (20) is connected to the fuselage (3) such that the control element (20) jointly the engine outlet (23) is pivotable about a rotation axis (26) with respect to the fuselage (3). The rotation axis (26) runs transversely to a longitudinal direction (8) of the fuselage (3) and the control element (20) functions as a tailplane when pivoting about the rotation axis (26).

    AFT ENGINE NACELLE SHAPE FOR AN AIRCRAFT
    96.
    发明公开
    AFT ENGINE NACELLE SHAPE FOR AN AIRCRAFT 审中-公开

    公开(公告)号：EP4098557A1

    公开(公告)日：2022-12-07

    申请号：EP22187100.7

    申请日：2016-09-20

    申请人： General Electric Company

    发明人： MARRINAN, Patrick Michael ,  BECKER, Thomas Lee ,  MURROW, Kurt David ,  YAO, Jixian

    IPC分类号： B64C1/16 ,  B64C21/06 ,  B64D27/20 ,  B64D29/04 ,  B64D33/02

    摘要： An aircraft (10) including a fuselage (20) and an aft engine (200) is provided. The fuselage (20) extends from a forward end (14) of the aircraft (10) towards an aft end (16) of the aircraft (10). The aft engine (200) is mounted to the fuselage (20) proximate the aft end (16) of the aircraft (10) and includes a fan (222) and a nacelle (224). The fan (222) is rotatable about a central axis (220) of the aft engine (200) and includes a plurality of fan blades (228). The nacelle (224) of the aft engine (200) surrounds the plurality of fan blades (228) and defines a bottom portion (248) having a forward end (14). Additionally, the nacelle (224) defines a curved surface at the forward end (14) of the bottom portion (248), the curved surface including a reference point where the curved surface defines the smallest radius of curvature (266). The nacelle (224) further defines a normal reference line (268) extending normal from the reference point. The normal reference line (268) defines an angle with the central axis (220) of the aft engine (200) greater than zero to, e.g., allow for a maximum amount of airflow into the aft engine (200).