Safran

Safran Aircraft Engines

Adrien Touze

Nicolas Pierre Lanfant

Olivier Foussard

Didier Payen

Dominique Marie Christian Coupe

Raoul Jaussaud

Thierry Patrick Chauvin

Nicolas Cambyse Ashtari

Marc-Emmanuel Jean François Techer

Romain Picon

Benoît Bazin

Romain Venat

Enrico Giovanni Obert

Benoit Bazin

Nate Gravelle

Sébastien Dunaud

Loïc Sorgnard

Magali Mélanie Coulaud

Matthieu Stackler

Christophe Ravey

A process for manufacturing a blade made of composite material for a turbomachine is provided. The blade includes an airfoil having a pressure side and a suction side which extend from a leading edge to a trailing edge of the airfoil. The blade further includes a metal sheath that extends along the leading edge of the airfoil. The process includes the steps of: a) placing a preform, made by three-dimensionally weaving fibers, in a mold, a polymerizable adhesive being inserted between the sheath and the edge of the preform; and b) injecting polymerizable resin into the mold to impregnate the preform so as to form the airfoil after solidifying, wherein the resin is injected within a time interval during which the adhesive reaches a freezing point.

Method for manufacturing a composite blade for an aircraft engine

A process for manufacturing a blade made of composite material for a turbomachine. The blade includes an airfoil having a pressure side and a suction side which extend from a leading edge to a trailing edge of the airfoil. The blade further includes a metal sheath that extends along the leading edge of the airfoil. The process includes the steps of: placing a preform, produced by three-dimensionally weaving fibers, in a mold, the sheath being positioned on an edge of the preform intended to form the leading edge of the airfoil; and injecting polymerizable resin into the mold to impregnate the preform so as to form the airfoil after solidifying. At least one double-sided adhesive film may be inserted between the sheath and the edge of the preform prior to injection of the resin.

Composite blade for an aircraft engine and methods for manufacturing and repairing same

A process for shaping, by compaction, a fibrous structure obtained by three-dimensional or multilayer weaving between a plurality of layers of warp yarns and a plurality of layers of weft yarns. The yarns of each plurality of layers of warp yarns and layers of weft yarns are coated with a sizing composition. The shaping includes a pre-compaction stage followed by a stage of final compaction of the fibrous structure. During pre-compaction and final compaction, the fibrous structure is at a temperature greater than or equal to the softening temperature of the sizing composition. The process further includes the cooling of the fibrous preform obtained after final compaction of the fibrous structure.

Method for shaping a fibrous preform by compacting in order to produce a composite material part

The invention relates to a resin injection regulator for a resin injection circuit in a mould for producing a composite part, in particular a turbine engine composite part, characterised in that it comprises at least one vessel which is connected to said circuit and inside of which a movable wall means can be moved in a sealed manner, said movable wall means defining in said vessel a first cavity which forms a container for accumulation of resin and is designed to be connected to at least one part of said circuit, and a second cavity which is designed to be connected to a source of pressurised fluid, said movable wall means being designed to be urged by the pressurised fluid with which the second cavity is supplied in order to exert a pressure on the resin contained in the first cavity by isolating said resin from said fluid.

Resin injection regulator, resin injection circuit and associated methods

Methods for manufacturing a turbomachine composite part, such as a fan blade, are provided. The composite part has a fibrous structure with a three-dimensional fibrous preform coated with a surface fibrous web, and which is embedded in a polymer matrix The methods include: forming the surface web in a cavity of a mold in order to shape it, wetting and forming the preform on the surface web in order to shape it, and closing the mold, drying the fibrous structure, and injecting thermosetting resin into the mold in order to form said polymer matrix. The surface web is wetted before and/or during the forming thereof.

Method for manufacturing a turbomachine composite part

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Saint Maurice Montcouronne, France

Adrien Touze