公开(公告)号：US20250101931A1

公开(公告)日：2025-03-27

申请号：US18726915

申请日：2023-01-06

Applicant: SAFRAN NACELLES

Inventor： Patrick GONIDEC ,  Loïc CHAPELAIN (Deceased) ,  Patrick André BOILEAU

IPC: F02K1/72

Abstract: A thrust reverser for an aircraft propulsion assembly, including a fixed structure equipped with at least one cascade as well as a radially inner delimiting wall of a secondary vein, and a movable structure including at least one reverser cowling, the cascade being arranged, in the forward direct thrust position, in a housing of the reverser cowling, and, in the retracted thrust reversal position, the wall reveals a passage opening of the secondary vein towards the cascade, the thrust reverser also including at least one sealing membrane designed to deflect at least one portion of the secondary flow. A hook is provided for securing the membrane to a rear cascade support frame, and to the radially inner delimiting wall of the secondary vein.

公开(公告)号：US20240093661A1

公开(公告)日：2024-03-21

申请号：US18264328

申请日：2022-02-02

Applicant: SAFRAN NACELLES

Inventor： Patrick André BOILEAU ,  Fabien JOURDAN

IPC: F02K1/72 ,  F02K1/76

CPC classification number: F02K1/72 ,  F02K1/766

Abstract: A thrust reverser with movable grids, includes structure for connecting, by recessing, a front frame of an outer cowl and a rear frame of the grids. The reverser includes loading structure configured to exert a stress pressing against the connecting structure, under the action of a circumferential pull of the front frame of the outer cowl or of a tightening band supported by the front frame.

公开(公告)号：US20220316427A1

公开(公告)日：2022-10-06

申请号：US17843219

申请日：2022-06-17

Applicant: Safran Nacelles

Inventor： Xavier CAZUC ,  Vincent DUTOT ,  Sébastien Laurent Marie PASCAL ,  Stephane RIQUIER ,  Patrick André BOILEAU ,  Fabien JOURDAN

IPC: F02K1/76

Abstract: A thrust reverser for a turbojet aircraft nacelle includes a fixed structure, a movable structure and an actuator. The actuator extends along a main axis and is connected by a first connection to the fixed structure and by a second connection to the movable structure for the deployment of the movable structure between a direct jet position and a reverse jet position. The actuator is also connected to the fixed structure by a third connection arranged longitudinally between the first connection and the second connection. An axis of the third connection is radially eccentric from the main axis and the third connection allows a predetermined displacement of the actuator with respect to the fixed structure.