公开(公告)号：US11428190B2

公开(公告)日：2022-08-30

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 ,  F02K1/80 ,  B64D29/06 ,  B64D29/08

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：US11338930B2

公开(公告)日：2022-05-24

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 ,  F02K1/09 ,  F02K1/70

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.

公开(公告)号：US11767808B2

公开(公告)日：2023-09-26

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 ,  B64D29/06 ,  F02K3/06

CPC classification number: F02K1/72 ,  F02K1/763 ,  B64D29/06 ,  F02K3/06 ,  F05D2220/323 ,  F05D2240/129

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：US11186379B2

公开(公告)日：2021-11-30

申请号：US15653971

申请日：2017-07-19

Applicant: SAFRAN NACELLES

Inventor： Patrick Boileau ,  Olivier Kerbler ,  Julien Lezerac ,  Aurélien Gonzalez ,  Loïc Grall ,  Ludovic Toupet

IPC: B64D27/18 ,  F02K1/72 ,  B64D27/26 ,  B64D29/06 ,  F02C7/20 ,  B64D29/02

Abstract: The present disclosure concerns a system for installing and removing a propulsion unit on a pylon of an aircraft, a propulsion unit of the type including a nacelle and a turbojet engine, the turbojet engine being linked on the pylon by at least one front suspension and one rear suspension. The system includes a supporting structure which is adapted to support a thrust reverser device, a front suspension of the turbojet engine, which carries a front part of the supporting structure, and which is removably fastened on a front part of the pylon, and a rear suspension of the turbojet engine which carries a rear part of the supporting structure, and which is removably fastened on a rear part of the pylon, and the disengagement of said suspensions of the pylon allowing removing the propulsion unit mounted on the pylon.

公开(公告)号：US10590886B2

公开(公告)日：2020-03-17

申请号：US15655276

申请日：2017-07-20

Applicant: SAFRAN NACELLES

Inventor： Olivier Kerbler ,  Fabrice Henri Emile Metezeau ,  Patrick Gonidec ,  Loïc Grall

IPC: F02K1/72 ,  B64D33/04 ,  B64D29/06 ,  B64D27/16

Abstract: The present disclosure relates to an aircraft turbojet engine nacelle, the nacelle including a rear section without a lower bifurcation, the rear section including a thrust reversal system, the thrust reversal system including a mobile cowl. The nacelle includes a guide system that translates as one with the mobile cowl, the guide system collaborating with at least one slide that is fixed in relation to the nacelle, the guide system and the slide being arranged near the position referred to as the 6 o'clock position.