公开(公告)号：US20200071234A1

公开(公告)日：2020-03-05

申请号：US16555575

申请日：2019-08-29

Applicant: Safran Nacelles ,  Safran Ceramics

Inventor： Bertrand DESJOYEAUX ,  Davi SILVA DE VASCONCELLOS ,  Aline PLANKEEL

IPC: C04B35/80 ,  B28B1/00 ,  C04B35/628 ,  C04B35/64 ,  B64D29/00 ,  B64C1/00 ,  B64F5/10

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：US20180230063A1

公开(公告)日：2018-08-16

申请号：US15878432

申请日：2018-01-24

Applicant: Safran Nacelles

Inventor： Arnaud Delehouze ,  Sylvain SENTIS ,  Bertrand DESJOYEAUX ,  Marc VERSAEVEL ,  Frédéric Fosse

IPC: C04B35/80 ,  C04B35/628 ,  C04B35/64 ,  G10K11/162 ,  F02K1/82

Abstract: A method for producing an acoustic attenuation panel from a composite material with a ceramic oxide matrix is provided that includes draping a plurality of plies having fibrous reinforcements including fibers of ceramic material in a mold to define a first skin, depositing blocks made of fugitive material on the first skin such that a space between two blocks is defined, and draping a second plurality of plies on a surface formed by the blocks such that a second skin is defined. Rounded corners of the blocks define radii for connecting the first and second skins with walls of a honeycomb core of the acoustic panel. The method further includes using a liquid medium to infiltrate the skins and spaces with a precursor of a ceramic phase, removing the liquid medium by evaporation or polymerization, and sintering to consolidate the ceramic oxide material and removal the fugitive material.

公开(公告)号：US20180148187A1

公开(公告)日：2018-05-31

申请号：US15884507

申请日：2018-01-31

Applicant: Safran Nacelles

Inventor： Laurent Georges VALLEROY ,  Marc VERSAEVEL ,  Bertrand DESJOYEAUX ,  Patrick GONIDEC

IPC: F02K1/34 ,  G10K11/168 ,  B64D27/16 ,  B64D29/00

CPC classification number: B64D33/06 ,  B64D27/16 ,  B64D29/00 ,  B64D29/06 ,  F02K1/72 ,  F02K1/827 ,  F05D2260/96 ,  G10K11/168 ,  Y02T50/671

Abstract: The present disclosure particularly relates to an acoustic attenuation structure for a propulsion assembly of an aircraft. The acoustic attenuation structure includes an acoustically reflective wall and a sandwich panel. The sandwich panel includes a honeycomb structure surrounded by two acoustically porous skins, a rear skin and a skin. The acoustically reflective wall and the sandwich panel are arranged in such a way as to be separated by a layer of air.

公开(公告)号：US20170370247A1

公开(公告)日：2017-12-28

申请号：US15672638

申请日：2017-08-09

Applicant: Safran Nacelles

Inventor： Benjamin PROVOST ,  Bertrand DESJOYEAUX ,  Sébastien LOUCHARD ,  Arnaud MARICAL

IPC: F01D25/00 ,  F01D25/24 ,  D03D49/00 ,  D03D3/06 ,  F02K1/64

CPC classification number: F01D25/005 ,  D03D3/06 ,  D03D25/005 ,  D03D49/00 ,  D10B2505/02 ,  F01D25/24 ,  F02K1/64 ,  F05D2220/323 ,  F05D2230/50 ,  F05D2240/10 ,  F05D2300/603

Abstract: The present disclosure provides a method for manufacturing a preform made of reinforcement fibers woven in a longitudinal direction. The preform is impregnated with resin in order to form an elongated element having a variable transverse cross-section. In one form, the method includes the step of simultaneously including a reduction (or increase) in width and an increase (or reduction) in height. The variable cross-section includes, along the length thereof, a consistent number (c) of continuous warp threads arranged in layers. The method for reducing width includes carrying out a change in weave, adding additional weft threads, and simultaneously drawing the teeth of the longitudinal beater reed closer together so as to increase the number of layers.

公开(公告)号：US20170184023A1

公开(公告)日：2017-06-29

申请号：US15459014

申请日：2017-03-15

Applicant: SAFRAN NACELLES

Inventor： Bertrand DESJOYEAUX ,  Simon VERGER ,  Sylvain SENTIS

IPC: F02C7/045 ,  B64D27/16 ,  F02K3/06 ,  B64D33/02

CPC classification number: F02C7/045 ,  B64D27/16 ,  B64D29/06 ,  B64D33/02 ,  B64D2033/0206 ,  B64D2033/0286 ,  F01D25/243 ,  F02K1/827 ,  F02K3/06 ,  F05D2220/323 ,  F05D2230/53 ,  F05D2250/75 ,  F05D2260/30 ,  F05D2260/31 ,  F05D2260/96 ,  F05D2300/121 ,  F05D2300/133 ,  F05D2300/603 ,  Y02T50/672

Abstract: A device for fastening a downstream end of an air inlet on a fan casing of an aircraft turbojet engine nacelle is provided. The device includes an acoustic shroud, a first flange coupled to the fan casing, a second L-shaped flange having a base coupled to the acoustic shroud, and a collar linked to the first flange. The acoustic shroud extends from an upstream segment to a downstream segment which defines an inner skin and an outer skin that encloses an acoustic panel. The collar further includes a protrusion that extends from the outer skin to the downstream segment.