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：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：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.