Safran Nacelles

Safran Ceramics

Davi Silva De Vasconcellos

Bertrand Desjoyeaux

Florent Bouillon

Benjamin Provost

Arnaud Delehouze

Bertrand Léon Marie Desjoyeaux

Aline Planckeel

François Taillard

Fabien Depeux

A method for producing a part made of composite material, includes obtaining a mold includes (i) a fibrous texture, (ii) a granular filtration layer located between a drainage surface of the texture and a permeable discharge surface and including a powder of filtration particles, and (iii) an element for retaining the granular layer, which element is distinct from the layer and located between the permeable discharge surface and the drainage surface, introducing a suspension including matrix particles in a liquid medium through an introduction surface of the fibrous texture that is distinct from the drainage surface, the liquid medium passing through the drainage surface, the granular filtration layer and the retention element to be discharged through the permeable discharge surface, and the matrix particles being retained in the pores of the fibrous texture by the granular filtration layer, and forming the part made of composite material by forming a matrix.

Method for producing a part made of composite material

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.

Structural and/or acoustic panel of a nacelle of an aircraft propulsion assembly and related manufacturing method

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.

Expandable cellular system for a sandwich panel

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.

Lobed tubular piece made of a composite with unidirectional fibers

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.

Cell structure and acoustic attenuation device for a nacelle of an aircraft propulsion assembly

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.

Tubular fibrous structure with lobes

A part for an aircraft turbojet engine nacelle is made of a composite material and includes at least one outer face (S), 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 (S) 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.

Growing community of inventors

Moissy Cramayel, France

Davi Silva De Vasconcellos