Safran Ceramics

Safran Aircraft Engines

Safran

Safran Nacelles

Aline Planckeel

Dominique Marie Christian Coupe

Gael Evain

Claire Groleau

Marie Lefebvre

Eric Philippe

Bertrand Desjoyeaux

Clement Roussille

Clément Roussille

Thierry Guy Xavier Tesson

Thierry Tesson

Davi Silva De Vasconcellos

Gaël Evain

Jérémy Paul André Blachier

In a method for three-dimensional weaving of a fibrous structure between layers of warp yarns and layers of weft yarns, the weft yarns are woven in a plurality of columns spaced apart from one another in a longitudinal direction. The method includes weaving deployment portions in the fibrous structure that is interwoven with an adjacent portion, the weft yarns of the weft yarn columns of the adjacent portion being juxtaposed in a first stacking direction perpendicular to the longitudinal direction. During the process of weaving the deployment portions, the weft yarns of each weft yarn column are positioned against the fell of the fibrous structure in stacking directions that are different from the first stacking direction.

Method for three-dimensional weaving of a fibrous structure with orientation of weft columns in a deployment portion and resulting fibrous structure

A Jacquard type loom intended to produce a fibrous structure by three-dimensional weaving between a plurality of warp yarns and a plurality of weft yarns extending in a horizontal direction, the loom including a reed movable between a rest position upstream of the rapier and a beat-up position of a fell of the fibrous structure in a beat-up direction parallel to the horizontal direction. The reed includes at least two stationary portions forming an angle therebetween. The reed is mounted on the loom by a positioning mechanism able to orient the reed about an axis of rotation so as to adjust an angular position of the stationary portions of the reed relative to a horizontal reference plane. The loom include vertical translation elements able to move the reed or the fell of the fibrous structure in the vertical direction.

Weaving loom with tiltable reed and weaving method

The invention relates to a three-dimensionally woven multilayer fibrous structure () having the same number of warp yarns woven at any level along the warp direction, the fibrous structure () comprising, in the warp direction, a first part () and a second part (), the first part () having a thickness measured in a direction perpendicular to the warp and weft directions, greater than the second part (), characterised in that the spacing between two weft planes along the warp direction is greater in the second part than in the first part (), and in that the number of weft yarns is lower in the second part () than in the first part ().

Method for manufacturing a ring sector

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.

Composite part with smooth outer face and manufacturing method thereof

A turbine ring assembly includes both a plurality of ring sectors made of ceramic matrix composite material forming a turbine ring and also a ring support structure having first and second annular flanges, each ring sector having first and second tabs, the tabs of each ring sector being held between the two annular flanges of the ring support structure. Each of the first and second tabs of the ring sectors has an annular groove. Each of the first and second annular flanges of the ring support structure has an annular projection received respectively in the annular groove of the first tab or in the annular groove of the second tab of each ring sector. A resilient element is interposed between the annular projection of the first flange and the annular grooves of the first tabs, and also between the annular projection of the second flange and the annular grooves of the second tabs.

Turbine ring assembly supported by flanges

A turbine ring assembly includes a ring support structure and a plurality of ring sectors made of CMC material and forming a turbine ring, each ring sector including an annular base with respective end portions having edges that are held facing an edge of the end portion of the annular base of a sector that is adjacent in the turbine ring. The assembly includes resilient holder devices for holding the ring sectors in position on the ring support structure, and each resilient holder device includes a spring element present beside the outside face of the ring support structure.

Turbine ring assembly with sealing

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Le Haillan, France

Aline Planckeel