公开(公告)号：US11506144B2

公开(公告)日：2022-11-22

申请号：US16785117

申请日：2020-02-07

Applicant: SAFRAN ,  Safran Nacelles

Inventor： Géraldine Oliveux ,  Bertrand Desjoyeaux ,  Cedric Thomas

IPC: F02K1/72 ,  F02K1/54

Abstract: A thrust reverser cascade for an aircraft nacelle includes a plurality of blades having a first and a second surface, the blades being connected to members connected to attachment flanges for attaching the thrust reverser cascade to the nacelle. At least one of the surfaces of the blades is covered with at least one layer of fibers, each layer including a plurality of fiber pieces which are pre-impregnated with resin. The fiber pieces are superimposed on one another, positioned parallel to the aerodynamic surface of the blade and oriented in different directions.

公开(公告)号：US10906841B2

公开(公告)日：2021-02-02

申请号：US15878443

申请日：2018-01-24

Applicant: Safran Nacelles

Inventor： Arnaud Delehouze ,  Sylvain Sentis ,  Bertrand Desjoyeaux

IPC: B32B3/10 ,  C04B35/80 ,  C04B35/117 ,  C04B38/00 ,  F02C7/045 ,  C04B35/18 ,  F02C7/24 ,  C04B30/02 ,  G10K11/162 ,  C04B111/52 ,  B32B19/04

Abstract: The present disclosure concerns a porous body made of a ceramic-matrix composite material for an acoustic attenuation panel and a method of manufacturing the porous body. The porous body includes a plurality of interwoven ceramic fibers, a metal oxide matrix, and a plurality of channels interwoven with the ceramic fibers and interconnected together. The channels define at least one cavity. In one form, at least one channel is wrapped around a ceramic fiber. In another form, at least one ceramic fiber and at least one channel are twisted together. In yet another form, at least one channel is wrapped around a ceramic fiber and twisted with the ceramic fiber. The present disclosure also concerns an acoustic attenuation panel including the porous body and an aircraft propulsion unit having such a panel.

公开(公告)号：US12170077B2

公开(公告)日：2024-12-17

申请号：US17716089

申请日：2022-04-08

Applicant: Safran Nacelles

Inventor： Marc Versaevel ,  Bertrand Desjoyeaux ,  Mathieu Preau

IPC: G10K11/172 ,  B64D33/02

Abstract: An acoustic attenuation panel includes a perforated acoustic wall, a first honeycomb structure coupled to the perforated acoustic wall and including a plurality of acoustic cells defined by peripheral partitions, a second honeycomb structure including a plurality of acoustic cells defined by peripheral partitions, and a septum which includes a plurality of macro-perforations and is positioned between the first honeycomb structure and the second honeycomb structure. Each acoustic cell of the first honeycomb structure and each acoustic cell of the at least second honeycomb structure are arranged opposite a single perforation of the septum.

公开(公告)号：US12122106B2

公开(公告)日：2024-10-22

申请号：US17843224

申请日：2022-06-17

Applicant: Safran Nacelles

Inventor： Bertrand Desjoyeaux ,  Mickaël Sorel ,  Franck Maze ,  Géraldine Oliveux

IPC: B29C70/46 ,  B29C33/00 ,  B29C33/48 ,  B29C70/54 ,  B29L31/30

CPC classification number: B29C70/46 ,  B29C33/0033 ,  B29C33/485 ,  B29C70/54 ,  B29L2031/3076

Abstract: Tooling for manufacture of an apertured element made of a composite material includes first and second sole plates and tooling elements. Each sole plate is configured to be placed on either side of the apertured element to be manufactured. The tooling elements are placed between the first and second sole plates. The tooling elements include at least one core and peripheral bars. The core is configured to delimit a cell of the apertured element to be manufactured. The core is movable in translation along the first and second sole plates. The peripheral bars are placed on a periphery of the core and configured to delimit the apertured element to be manufactured. At least one peripheral bar is movable in translation along the first and second sole plates.

公开(公告)号：US11141960B2

公开(公告)日：2021-10-12

申请号：US16555575

申请日：2019-08-29

Applicant: Safran Nacelles ,  Safran Ceramics

Inventor： Bertrand Desjoyeaux ,  Davi Silva De Vasconcellos ,  Aline Planckeel

IPC: C04B35/64 ,  B32B18/00 ,  C04B35/628 ,  B64D29/00 ,  B64C1/00 ,  B64F5/10 ,  B28B1/00 ,  C04B35/117 ,  C04B35/18 ,  C04B35/565 ,  C04B35/80

Abstract: A part for an aircraft turbojet engine nacelle is made of a composite material and includes at least one outer face (S1), a fibrous preform including fiber locks and having a surface(s) delimiting depressions between fiber locks, a covering material which at least partially covers the surface(s) of the fibrous preform and in particular the depressions, and a matrix which binds entirely the covering material and the fibrous preform. The covering material is a fibrous mat and the outer face (S1) is smooth. A method for manufacturing such a part includes manufacturing the fibrous preform, providing a fibrous mat, depositing the fibrous preform and fibrous mat in a mold, dispersing the matrix between the fibers of the preform and mat and consolidating the fibrous preform and mat.

公开(公告)号：US11655044B2

公开(公告)日：2023-05-23

申请号：US16549359

申请日：2019-08-23

Applicant: Safran Nacelles

Inventor： Bertrand Desjoyeaux ,  Sylvain Sentis ,  Arnaud Delehouze ,  François Taillard

IPC: B64D29/02 ,  C04B35/80 ,  D03D25/00 ,  D03D15/00 ,  C04B35/117 ,  C04B35/18 ,  C04B35/565 ,  D03D15/275

CPC classification number: B64D29/02 ,  C04B35/117 ,  C04B35/18 ,  C04B35/565 ,  C04B35/80 ,  D03D15/00 ,  D03D15/275 ,  D03D25/005 ,  C04B2235/5224 ,  C04B2235/5228 ,  C04B2235/5244 ,  C04B2235/5248 ,  C04B2235/5256 ,  D10B2101/08 ,  D10B2101/12 ,  D10B2505/02

Abstract: An rear fairing for a pylon supporting an aircraft turbojet engine forms an aerodynamic surface covering the base of the pylon. The rear fairing is elongated in a longitudinal direction and includes a floor arranged opposite the hot gases exiting the turbojet engine and side walls constituting aerodynamic surfaces. The floor and the side walls include ceramic matrix composite materials made from preforms formed by layers of superimposed warp and weft yarns, the preforms have interlayer weaving yarns connecting the layers to one another.

公开(公告)号：US11472133B2

公开(公告)日：2022-10-18

申请号：US16785979

申请日：2020-02-10

Applicant: Safran Nacelles

Inventor： Bertrand Desjoyeaux ,  Davi Silva De Vasconcellos ,  Benjamin Provost

IPC: B29C33/68 ,  B29C70/32 ,  B29C70/22 ,  C04B35/628 ,  C04B35/64 ,  C04B35/80 ,  C08J5/24 ,  B29L23/00 ,  F02K1/44

Abstract: A method for manufacturing a fibrous tubular structure including lobes, in which fibers are draped/deposited on a mandrel having a shape corresponding to that of the fibrous structure, includes draping/deposition carried out such that at least one group of fibers has a same orientation with respect to the axis (A) of said fibrous structure, then, the fibers having been draped over an angular sector less than the total periphery of the mandrel, one of the ends of the fibrous structure is separated from the mandrel in order to allow the continuation of the draping on the same mandrel.

公开(公告)号：US11427299B2

公开(公告)日：2022-08-30

申请号：US16800211

申请日：2020-02-25

Applicant: Safran Nacelles ,  Safran Ceramics

Inventor： Bertrand Desjoyeaux ,  Davi Silva De Vasconcellos ,  Florent Bouillon ,  Arnaud Delehouze

IPC: B64C7/02 ,  B64C1/40 ,  B64C21/02 ,  B64D33/02

Abstract: The present disclosure relates to a cell structure for an acoustic attenuation device for a nacelle of an aircraft propulsion assembly. This cell structure includes lateral partitions forming channels that each extend between a first end and a second end and skin elements arranged so that each channel is at least partly closed at the first end thereof by at least one skin element. Each skin element is connected to a respective lateral partition and can move relative to the other lateral partitions. A continuous skin can be assembled on this cell structure so as to at least partly close the channels at the second end thereof and to thus form an acoustic attenuation device.

公开(公告)号：US12264625B2

公开(公告)日：2025-04-01

申请号：US17729541

申请日：2022-04-26

Applicant: Safran Nacelles

Inventor： Pierre Caruel ,  Bertrand Desjoyeaux ,  Bertrand Leroyer ,  Marc Versaevel ,  Laurent Georges Valleroy

IPC: F02C7/045 ,  B32B3/12 ,  B32B3/26

Abstract: An acoustic attenuation panel includes a cellular structure including a plurality of acoustic cells separated from one another by peripheral partitions, a perforated acoustic structure, the perforated acoustic structure and the cellular structure being formed in one piece in a first material, and a porous acoustic layer formed of a second material and fastened to a surface of the perforated acoustic structure by entangling the first material and the second material.

公开(公告)号：US11932399B2

公开(公告)日：2024-03-19

申请号：US17412676

申请日：2021-08-26

Applicant: Safran Nacelles ,  SAFRAN CERAMICS

Inventor： Bertrand Desjoyeaux ,  Davi Silva De Vasconcellos ,  François Taillard ,  Florent Bouillon

IPC: B64C7/02 ,  B32B3/28 ,  B64D29/06 ,  B64D33/02 ,  B64D33/04 ,  F02C7/045 ,  F02K1/82

CPC classification number: B64C7/02 ,  B64D29/06 ,  B64D33/02 ,  F02C7/045 ,  F02K1/827 ,  B64D2033/0206 ,  F05D2260/96 ,  F05D2300/6033

Abstract: A sandwich panel for an aircraft turbojet nacelle includes an outer skin in contact with an air flow, an inner skin opposed to the outer skin, and an intermediate system comprising partitions connecting the inner and outer skins so as to form cells, the inner skin of at least one cell having at least one corrugation configured to allow the materials making up the sandwich panel to deform in the event of thermal variation.