公开(公告)号：US20240391206A1

公开(公告)日：2024-11-28

申请号：US18795709

申请日：2024-08-06

Applicant: Safran Nacelles ,  Safran Ceramics

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

IPC: B32B5/02 ,  B32B3/12 ,  F02K1/82

Abstract: A method for manufacturing a panel for a nacelle of an aircraft propulsion assembly includes: preparing mold elements each including lateral faces, an upper face, and a lower face; draping a material on a portion of the upper face and/or the lower face and at least one of the lateral faces of each of the mold elements to form at least one fold; and extracting the mold elements such that the at least one fold forms a cellular structure of the panel. The portion of the material on the upper face and/or the lower face forms a peripheral portion of the fold. The portion on the at least one of the lateral faces of each of the mold elements forms a central portion of the fold. The central portion is a portion of transverse partition walls of the panel, which define a plurality of cells.

公开(公告)号：US20200300196A1

公开(公告)日：2020-09-24

申请号：US16800286

申请日：2020-02-25

Applicant: Safran Nacelles ,  Safran Ceramics

Inventor： Bertrand DESJOYEAUX ,  Davi SILVA DE VASCONCELLOS ,  Florent BOUILLON ,  Arnaud DELEHOUZE

IPC: F02K1/44 ,  F02K1/82 ,  F02C7/045

Abstract: A panel for a nacelle of an aircraft propulsion assembly includes two skins and a cell structure provided with transverse partitions defining cells. The cell structure includes folds with at least one central part forming at least one part of at least one transverse partition and at least one peripheral part extending along at least one of the skins. A nacelle with such a panel is provided, as well as a method for manufacturing such a panel.

公开(公告)号：US20200338840A1

公开(公告)日：2020-10-29

申请号：US16758277

申请日：2018-10-23

Applicant: SAFRAN CERAMICS

Inventor： Mathieu SCHWARTZ ,  Arnaud DELEHOUZE ,  Nicolas LAVAL ,  Bertrand DESJOYEAUX

IPC: B29C70/52 ,  C04B35/80 ,  B29C70/38 ,  B28B23/02 ,  C04B35/622

Abstract: An installation for depositing a shaped filled roving intended to be used to manufacture a composite-material component, includes a device for feeding a fibrous roving impregnated with a composition including a binder and ceramic or carbon fillers, a die for shaping and draining the binder defined by at least one porous surface, the die having an evolving section between an inlet section and an outlet section, the inlet section being larger than the outlet section, a support in communication with the die outlet on which the shaped roving is to be deposited, and a first conveying device configured to convey the roving from the feed device through the die and to the support.

公开(公告)号：US20210380220A1

公开(公告)日：2021-12-09

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 ,  B64D33/02 ,  B64D29/06 ,  F02C7/045 ,  F02K1/82

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.

公开(公告)号：US20210046671A1

公开(公告)日：2021-02-18

申请号：US17046958

申请日：2019-04-04

Applicant: SAFRAN CERAMICS

Inventor： Eric PHILIPPE ,  Paul CARMINATI ,  Medhy Damien BOUNIA ,  Bertrand DESJOYEAUX

IPC: B28B1/26 ,  B28B17/00 ,  C04B35/80 ,  C04B35/628

Abstract: A process for manufacturing a composite part includes arranging a fibrous preform in a mold including an impregnation chamber which includes in its lower part a filter by making a first face of the preform rest on the filter, the impregnation chamber being closed by a flexible membrane placed opposite a second face of the preform, the membrane separating the impregnation chamber from a compaction chamber. The process further includes injecting a compression fluid into the compaction chamber so as to apply a first pressure on the membrane and injecting a slurry including ceramic particles into the impregnation chamber with a second pressure while maintaining the injection of the compression fluid, the second injection pressure of the slurry being lower than the first pressure on the membrane.

公开(公告)号：US20200339243A1

公开(公告)日：2020-10-29

申请号：US16921163

申请日：2020-07-06

Applicant: Safran Nacelles ,  Safran Ceramics

Inventor： Florent BOUILLON ,  Franck DUPE ,  Benoît CARRERE ,  Bertrand DESJOYEAUX

IPC: B64C7/02 ,  F02K1/34 ,  F02C7/045 ,  F02K1/82

Abstract: A structure for the nacelle of an aircraft propulsion unit includes a first skin and stiffeners arranged to hold acoustic treatment modules against the first skin. Each acoustic treatment module includes a honeycomb core and a second skin, such that the honeycomb core is sandwiched between the first skin and the second skin. Such a structure allows the structural reinforcement function provided by the stiffeners to be separated from the acoustic treatment function performed by the acoustic treatment modules which are simply bearing on the first skin.

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：US20200001504A1

公开(公告)日：2020-01-02

申请号：US16481199

申请日：2018-02-01

Applicant: SAFRAN CERAMICS

Inventor： Mathieu SCHWARTZ ,  Arnaud DELEHOUZE ,  Nicolas LAVAL ,  Bertrand DESJOYEAUX

IPC: B29B11/16 ,  B29C70/38

Abstract: A method of fabricating a composite part, includes forming a fiber preform for the part that is to be obtained by depositing a plurality of fiber structures impregnated with a thermoplastic polymer onto a surface, with deposition being performed by automated fiber placement; eliminating the thermoplastic polymer present in the preform by dissolution with a solvent; and injecting a liquid impregnation composition into the pores of the fiber preform after eliminating the thermoplastic polymer in order to form a matrix in the pores of the fiber preform.