公开(公告)号：US20210079871A1

公开(公告)日：2021-03-18

申请号：US16914782

申请日：2020-06-29

Applicant: Safran Nacelles

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

IPC: F02K1/70

Abstract: 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.

公开(公告)号：US20200031485A1

公开(公告)日：2020-01-30

申请号：US16467718

申请日：2017-12-01

Applicant: Safran Nacelles

Inventor： Olivier KERBLER ,  Laurent Georges VALLEROY ,  Corentin HUE ,  Alexis HEAU

IPC: B64D29/06 ,  B64D45/00

Abstract: A nacelle for an aircraft turbojet engine includes a thrust-reversing device with a fixed structure and a movable structure translatably movable along an axis substantially parallel with a longitudinal axis of the nacelle between a retracted position in which it provides aerodynamic continuity with the fixed structure of the nacelle during operation of the nacelle with forward thrust and a deployed position in which it opens a passage intended for the circulation of a diverted secondary air flow during operation of the nacelle with reverse thrust. The nacelle includes at least one position sensor configured and arranged in the nacelle for detecting a deformation of the movable structure exceeding a permitted predetermined deformation threshold.

公开(公告)号：US20190316545A1

公开(公告)日：2019-10-17

申请号：US16421519

申请日：2019-05-24

Applicant: Safran Nacelles

Inventor： Alexis HEAU ,  Laurent Georges VALLEROY ,  Goulwen LANSONNEUR

IPC: F02K1/72 ,  B64D29/06

Abstract: An aircraft turbojet engine nacelle includes a rear section without a lower bifurcation, the rear section including a thrust reverser system, and the thrust reverser system including a movable cowl. The nacelle includes a guide system including a movable portion and a fixed portion, the movable portion being secured in translation to the movable cowl and cooperating with the fixed portion and the fixed portion being fixed relative to the nacelle. The guide system is disposed proximate to a position called the “6 O'clock” position. In one form, the length of the fixed portion of the guide system is larger than or equal to 50% of the length of the movable portion.

公开(公告)号：US20200347801A1

公开(公告)日：2020-11-05

申请号：US16933179

申请日：2020-07-20

Applicant: Safran Nacelles

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

IPC: F02K1/72 ,  F02K1/76

Abstract: 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.

公开(公告)号：US20200317355A1

公开(公告)日：2020-10-08

申请号：US16907346

申请日：2020-06-22

Applicant: Safran Nacelles

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

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

Abstract: 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.