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：US20200180238A1

公开(公告)日：2020-06-11

申请号：US16785979

申请日：2020-02-10

Applicant: Safran Nacelles

Inventor： Bertrand DESJOYEAUX ,  Davi SILVA DE VASCONCELLOS ,  Benjamin PROVOST

IPC: B29C70/22 ,  B29C70/32 ,  B29C33/68 ,  C08J5/24 ,  C04B35/80 ,  C04B35/628 ,  C04B35/64

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：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：US20200095954A1

公开(公告)日：2020-03-26

申请号：US16693551

申请日：2019-11-25

Applicant: Safran Nacelles

Inventor： Bertrand DESJOYEAUX ,  Benjamin PROVOST ,  Fabien DEPEUX ,  Davi SILVA DE VASCONCELLOS

IPC: F02K1/48 ,  B29C70/22 ,  D03D3/02 ,  D03D3/08

Abstract: A tubular structure having lobes is produced as a single piece over at least two lobes. Circumferential fibres of the structure have a constant orientation with respect to the longitudinal axis (A) of the structure in any plane (P) transverse to the longitudinal axis. The structure is obtained by weaving or by filament winding.

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.