公开(公告)号：US12209554B2

公开(公告)日：2025-01-28

申请号：US18002445

申请日：2021-06-02

Applicant: SAFRAN NACELLES

Inventor： Romain Gardel ,  Thomas Marlay ,  Matthieu Menielle ,  Ophélie Schmitter

IPC: F02K1/76 ,  B64D29/00 ,  F02K1/60

Abstract: A thrust reverser for an aircraft propulsion unit. The thrust reverser includes three gates that can be deployed downstream of an outlet section of the propulsion unit. The device increases the possibilities for installation of the reverser, in particular when a tail assembly extends in line with the propulsion unit.

公开(公告)号：US12158122B2

公开(公告)日：2024-12-03

申请号：US18069282

申请日：2022-12-21

Applicant: SAFRAN NACELLES

Inventor： Romain Gardel ,  Pierre-Alain Reboul ,  Jérôme Corfa ,  Jean-Philippe Joret ,  Thomas Marlay ,  Matthieu Menielle

IPC: F02K1/76 ,  F02K1/60 ,  F02K1/70

Abstract: A nacelle for an aircraft propulsion assembly includes an actuator, a secondary door subject to the actuator and contributing to defining an external aerodynamic surface of the nacelle in a first position, a main door contributing to defining the external aerodynamic surface and including a recess that the actuator passes through in a deployed position but not in a retracted position, and a flap connected to the main door. The flap is movable between a closed position wherein the flap closes off at least a first region of the recess through which the actuator passes in the deployed position whereby the flap contributes to defining the external aerodynamic surface, and an open position wherein the flap is moved away from the recess so as to clear the passage for the actuator through the first region of the recess.

公开(公告)号：US12246846B2

公开(公告)日：2025-03-11

申请号：US18251095

申请日：2021-11-02

Applicant: SAFRAN NACELLES

Inventor： Hazem Kioua ,  Damien Lemoine ,  Pierre-Alain Reboul ,  Matthieu Menielle

IPC: B64D29/06 ,  B64D27/40 ,  B64C30/00

Abstract: A propulsion unit for an aircraft, includes a support structure, a nacelle and a turbomachine. The support structure is configured to independently support, on the one hand, the turbomachine and, on the other hand, preferably by a cradle, an air inlet and/or a rear section of the nacelle.

公开(公告)号：US11293378B2

公开(公告)日：2022-04-05

申请号：US16889154

申请日：2020-06-01

Applicant: Safran Nacelles

Inventor： Alexis Tabouret ,  Quentin Girardie ,  Jérôme Corfa ,  Matthieu Menielle ,  Fabrice Provost

IPC: F02K1/72 ,  F02K1/80 ,  F02K1/76

Abstract: A thrust reverser for a nacelle of an aircraft engine includes a movable cowl movable between a closed position in which thrust is not reversed and an open position for uncovering cascades reversing that reverse the direction of the cold air flow diverted from the annular secondary air flow path. The movable cowl includes a radially outer portion disposed proximate a leading edge of an aircraft wing and at least one avoidance panel on the radially outer portion designed to inhibit interference with a movable slat of the leading edge of the aircraft wing. The avoidance panel is pivotally mounted with respect to a fixed structure of the thrust reverser. At least one energy storing device constrains the avoidance panel to bear against the movable cowl, at least when the thrust reverser is in the closed position.