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    REAR ASSEMBLY OF AN AIRCRAFT TURBOJET ENGINE NACELLE COMPRISING A THRUST REVERSER WITH SLIDING CASCADES
    1.
    发明申请
    REAR ASSEMBLY OF AN AIRCRAFT TURBOJET ENGINE NACELLE COMPRISING A THRUST REVERSER WITH SLIDING CASCADES 审中-公开

    公开(公告)号：US20200347801A1

    公开(公告)日：2020-11-05

    申请号：US16933179

    申请日：2020-07-20

    申请人： Safran Nacelles

    发明人： Pierre CARUEL ,  Loïc GRALL ,  Alexis HEAU ,  Olivier KERBLER ,  Mélody SERISET

    IPC分类号： F02K1/72 ,  F02K1/76

    摘要： A nacelle rear assembly of a nacelle of a turbojet engine of an aircraft extends along a longitudinal central axis (A) and includes a sliding cascade thrust reverser. The cascade thrust reverser includes at least one sliding cowl, a deflection cascade including a plurality of rows of vanes that each extend around the longitudinal central axis (A) and that are longitudinally arranged from a first front row of vanes up to a last rear row of vanes, each row of vanes including at least one deflection vane for deflecting the airflow toward the outside of the rear assembly of the nacelle, the deflection cascade being movably integral with the sliding cowl, wherein the deflection cascade includes at least one additional neutral row of vanes that is interposed between the last row of vanes and the sliding cowl and that includes at least one neutral vane.

    AIRCRAFT ENGINE NACELLE
    2.
    发明申请
    AIRCRAFT ENGINE NACELLE 审中-公开

    公开(公告)号：US20200317355A1

    公开(公告)日：2020-10-08

    申请号：US16907346

    申请日：2020-06-22

    申请人： Safran Nacelles

    发明人： Loïc GRALL ,  Mélody SERISET ,  Alexis HEAU ,  Benjamin BREBION ,  Olivier KERBLER

    IPC分类号： B64D29/00 ,  F02K1/70 ,  F02K1/09

    摘要： A nacelle of an aircraft turbofan engine including an air inlet upstream from the engine, a median section configured to surround a fan of the engine and delimited on the outside by a fan cowl supported by a fan housing to which it is attached at the upstream portion, a downstream section delimiting an annular flow path in which the air is configured to flow and housing thrust reversal devices, the thrust reversal approach including a movable cowl associated with at least one actuator for moving the movable cowl between a direct jet position, in which it provides the aerodynamic continuity of the nacelle and an indirect jet position in which it opens up a passage in the nacelle by uncovering cascade vanes arranged around this flow path that receive the cold air flow to return it towards the outside and forwards, the cascade vanes being attached to the movable cowl.

    GRID-TYPE THRUST REVERSER FOR TURBOJET ENGINE
    3.
    发明申请
    GRID-TYPE THRUST REVERSER FOR TURBOJET ENGINE 有权

    公开(公告)号：US20210079871A1

    公开(公告)日：2021-03-18

    申请号：US16914782

    申请日：2020-06-29

    申请人： Safran Nacelles

    发明人： Loïc GRALL ,  Alexis HEAU ,  Benjamin BREBION ,  Sébastien Michel Thierry GUILLEMANT ,  Mélody SERISET ,  Patrick BOILEAU

    IPC分类号： F02K1/70

    摘要： A grid-type thrust reverser for a turbojet engine includes a moving O-shaped thrust reverser body that is generally cylindrical in shape around a longitudinal central axis (A) and includes an inner wall configured to delimit a cold air stream, with an inner structure that surrounds the turbojet engine, the movable thrust reverser body being mounted so as to be able to slide along the longitudinal central axis (A) between a direct jet position in which the outer cowl covers the thrust reverser grids, and a thrust-reversal position in which the outer cowl uncovers the thrust reverser grids. The movable thrust reverser body includes a first half-portion and a second half-portion that are mounted so as to each pivot about a longitudinal pivot axis (B), between a closed position and an open gullwing position for removing the turbojet engine, via the cradle.