公开(公告)号：US20240351699A1

公开(公告)日：2024-10-24

申请号：US18637871

申请日：2024-04-17

Applicant: SAFRAN NACELLES

Inventor： Bertrand Léon Marie DESJOYEAUX ,  Mathieu François Eric PREAU ,  Marc VERSAEVEL ,  Pierre Charles CARUEL ,  Geneviève CLUZEAU

IPC: B64D33/02

CPC classification number: B64D33/02 ,  B64D2033/0206

Abstract: An acoustic panel for an aircraft turbomachine has a sandwich structure. The sandwich structure includes a cell structure with a plurality of acoustic cells, a perforated acoustic structure, and a porous acoustic structure attached to the perforated acoustic structure. The perforated acoustic structure is arranged between the cell structure and the porous acoustic structure. The porous acoustic structure is multi-layered and has a first woven textile layer and a second woven textile layer connected to the first layer. The second layer is arranged between the first layer and the perforated acoustic structure.

公开(公告)号：US20250010971A1

公开(公告)日：2025-01-09

申请号：US18710348

申请日：2022-11-16

Applicant: SAFRAN NACELLES

Inventor： Bertrand Léon Marie DESJOYEAUX ,  Fabrizio PAGANO ,  Mathieu François Eric PREAU ,  Mathieu VIVIENT

IPC: B64C1/00

Abstract: An open composite panel for an aircraft includes a composite skin having an inner face and an outer face, and a plurality of stiffening ribs, each rib extending over the inner face of the skin in a respective direction of extension and projecting from the inner face to a top that is opposite said inner face. The plurality of ribs includes at least one reinforced rib, each reinforced rib having at least one elongate stiffening portion extending along the top of the reinforced rib, said stiffening portion including fibers extending substantially in the direction of extension of the reinforced rib.

公开(公告)号：US20230003176A1

公开(公告)日：2023-01-05

申请号：US17903359

申请日：2022-09-06

Applicant: Safran Nacelles

Inventor： Bertrand Léon Marie DESJOYEAUX ,  Marc VERSAEVEL ,  Mathieu François Eric PREAU ,  Laurent MOREAU

IPC: F02K1/82 ,  B64D33/02

Abstract: A method for manufacturing an alveolar core structure includes at least one cell including a secondary duct having a first end defining a sound wave inlet, and an opposite second end, the secondary duct comprising a sound wave outlet. The method also includes a fastening step in which adhesive tapes transverse to the longitudinal direction of said first plate are applied on a first longitudinal plate. The secondary duct in the form of a flattened element is fastened, on the first plate, by gluing at its sound wave inlet. A second plate is applied. A step of deploying the first and second plates so as to form the peripheral wall of the cells and so that the flattened element is deployed.

公开(公告)号：US20220403754A1

公开(公告)日：2022-12-22

申请号：US17774340

申请日：2020-11-04

Applicant: SAFRAN NACELLES

Inventor： Bertrand Léon Marie DESJOYEAUX ,  Mathieu François Eric PREAU

IPC: F01D25/00 ,  F01D25/24

Abstract: An assembly includes a first part and a second part separate from the first part, the first and second parts being intended to be in frictional contact, the first part being made of an organic matrix composite material that has, on its surface, an abrasion-resistant area including a resin that contains polytetrafluoroethylene particles, the polytetrafluoroethylene particles being only present at the surface of the first part, and the second part being made of an organic matrix composite material and being in contact with the abrasion-resistant area of the first part.