公开(公告)号：US12214893B2

公开(公告)日：2025-02-04

申请号：US18258319

申请日：2021-12-21

Applicant: SAFRAN NACELLES

Inventor： Hazem Kioua ,  Thomas Marlay ,  Damien Lemoine ,  Ophélie Schmitter

IPC: F01D17/00 ,  B64D33/02

Abstract: An air inlet for an aircraft propulsion unit having a movable upstream portion, a stationary downstream portion and at least one member for longitudinally translating the movable upstream portion between a retracted position in which the movable upstream portion is adjacent to the stationary downstream portion, and an extended position in which the movable upstream portion is separated from the stationary downstream portion, the moving member having at least one guiding bar connected to the movable upstream portion and a drive bar having a plurality of teeth, the stationary downstream portion having, for each moving member, a gear wheel configured to co-operate with the teeth in order to form a rack-and-pinion connection and at least one guiding member of the guiding bar.

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：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：US12110120B2

公开(公告)日：2024-10-08

申请号：US18255025

申请日：2021-12-01

Applicant: SAFRAN NACELLES

Inventor： Hazem Kioua ,  Thomas Marlay ,  Charles-Antoine Lampaert ,  Pierre-Alain Reboul

IPC: B64D27/40 ,  B64D29/06 ,  B64D29/08 ,  F01D25/24 ,  F01D25/28 ,  F02C7/00 ,  F02C7/04 ,  F02C7/20

CPC classification number: B64D27/40 ,  B64D29/06 ,  B64D29/08 ,  F01D25/243 ,  F01D25/28 ,  F02C7/00 ,  F02C7/04 ,  F02C7/20 ,  F05D2220/323

Abstract: A propulsion unit for an aircraft includes a gas generator; an air inlet; and a sealing system inserted axially between the air inlet and the gas generator. The sealing system has at least: a compression ring with a first axial end configured for mechanical connection to one of the gas generator and the air inlet. The compression ring also has a second opposite axial end configured to be axially separated from the other of the gas generator and the air inlet by an annular space. An annular seal is mounted in the space and configured to be axially compressed by reduction of the axial dimension of said space.

公开(公告)号：US20240294265A1

公开(公告)日：2024-09-05

申请号：US18258319

申请日：2021-12-21

Applicant: SAFRAN NACELLES

Inventor： Hazem Kioua ,  Thomas Marlay ,  Damien Lemoine ,  Ophélie Schmitter

IPC: B64D33/02 ,  F01D17/00

CPC classification number: B64D33/02 ,  F01D17/00 ,  F05D2260/53

Abstract: An air inlet for an aircraft propulsion unit having a movable upstream portion, a stationary downstream portion and at least one member for longitudinally translating the movable upstream portion between a retracted position in which the movable upstream portion is adjacent to the stationary downstream portion, and an extended position in which the movable upstream portion is separated from the stationary downstream portion, the moving member having at least one guiding bar connected to the movable upstream portion and a drive bar having a plurality of teeth, the stationary downstream portion having, for each moving member, a gear wheel configured to co-operate with the teeth in order to form a rack-and-pinion connection and at least one guiding member of the guiding bar.

公开(公告)号：US12006893B2

公开(公告)日：2024-06-11

申请号：US17632755

申请日：2020-07-31

Applicant: SAFRAN NACELLES

Inventor： Fabien Charliac ,  Benjamin Brebion ,  Thomas Marlay ,  Antoine Cordiez

IPC: F02K1/76 ,  F02K1/72

CPC classification number: F02K1/76 ,  F02K1/72

Abstract: A thrust reverser for an aircraft propulsion unit, of the type having a mobile cowl able to move between a closed position that allows the propulsion unit to generate thrust and an open position that allows the propulsion unit to generate a reverse-thrust for slowing the aircraft. The reverser includes braking elements such as a slot and a peg respectively integral with a fixed part of the reverser and with the mobile cowl. These braking elements are configured to cooperate with one another by sliding, with friction, when the mobile cowl effects an overtravel, beyond the open position, so as to generate a braking force that opposes this movement. In one preferred embodiment, the slot for this purpose includes a restriction in section along the direction of travel of the mobile cowl.