Safran Aircraft Engines

Yanneck Wielhorski

Julien Schneider

Julien Paul Schneider-Die-Gross

Santiago Velasco-forero

Samy Blusseau

An installation for compacting strands or a preform including strands, the strands or the preform including at least a first portion in which the strands are twisted at a first angle and a second portion in which the strands are twisted at a second angle different from the first angle, the installation including a mould which includes the strands or the preform, and wherein the mould has at least a first part in which the first portion of the strands or of the preform is disposed, having a first thickness and a second part in which the second portion of the strands or of the preform is disposed, having a second thickness different from the first thickness.

Adjustment of twist to optimize moulds and the shaping of textile architectures

A method for automatically reconstituting the architecture, along a reinforcing axis, of the reinforcement of a composite material, includes acquiring images of the reinforcement of the composite material, each image being acquired along a section plane perpendicular to the reinforcing axis; for each image acquired, detecting, using a neural network, barycentre and/or the circumference of each section of the reinforcing thread; for at least one acquired reference image, assigning a tag corresponding to a reinforcing thread, to each detected barycentre or circumference; for each other acquired image, assigning, to each detected barycentre and/or each detected circumference, the tag of the corresponding barycentre in the acquired reference image; reconstituting the architecture of each reinforcing thread from each detected barycentre and/or circumference having the tag of the reinforcing thread and the position on the reinforcing axis associated with the acquired image on which the barycentre and/or the circumference has been detected.

Method for automatically reconstituting the reinforcing architecture of a composite material

A fibrous preform of a turbomachine component has a three-dimensional weave formed by a plurality of woven strands, wherein, in a shear plane of the component, all or part of the strands present in this plane have fibers forming an angle between 10° and 50° with their centerline.

Growing community of inventors

MOISSY-CRAMAYEL, France

Yanneck Wielhorski