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：US11624339B2

公开(公告)日：2023-04-11

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：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：US11549462B2

公开(公告)日：2023-01-10

申请号：US16884948

申请日：2020-05-27

Applicant: Safran Nacelles ,  Safran Aircraft Engines

Inventor： Sébastien Michel Thierry Guillemant ,  Pierre Caruel ,  Olivier Kerbler ,  Alexis Heau ,  Mathieu Lerouvreur ,  Antoine Elie Hellegouarch

IPC: F02K1/72 ,  F01D9/06

Abstract: A turbojet engine nacelle having a cascade-type thrust reverser includes a movable frame surrounding a cold air flow path, guided axially by longitudinal rails fixed to an intermediate casing surrounding the cold air flow path and supporting cascades of thrust-reversal guide vanes and mobile rear cowls. The nacelle has a passage of ancillaries opening radially towards the outside of the movable frame, in a zone with no bearing structure passing radially across the cold air flow path. The movable frame is cut in an axial plane at the passage for the passage of ancillaries, and each edge of the cut of the movable frame is connected to the intermediate casing by a slide rail fitted on a longitudinal rail arranged each on one side of this passage.