Societe Nationale D'etude Et De Construction De Moteurs D'aviation

Societe Cotton Textiles Pour Materiaux Innovants 'Ctmi'

Laurent Jean David

Christophe Jean Champenois

Robert Lucien Martinou

Daniel G Girault

Gerard Michel Gueldry

Christophe Gerard Grosbois

Joel M Benoit

Gerard Francedillaois Inizan

Patrick Fouche

Catherine L Guet

Francedillaois Billaut

Jean Pierre Dessinges

A high-strength hybrid component including a relatively soft first part made of a composite material including an organic matrix reinforced with fibers, a relatively hard second part made of metal, metal alloy, or ceramic, and a transition layer made of a composite material including a matrix of a material that is weldable to the hard part and fibers that are extensions of the fibers of the soft part. The transition layer matrix and the hard part may be formed by deposition of molten material on to the fiber preform of the soft part using flame, electric arc, or plasma. The resin matrix of the soft part is impregnated into the preform and polymerized afterwards. Alternatively, the hard part may be machined to shape and welded to the transition layer before completing the soft part.

Hybrid component with high strength/mass ratio and method of

A linked multilayer woven fabric for use in the production of structural composite materials has a base weave comprising twenty-eight weft yarns which are distributed in eight columns containing alternately four superimposed yarns and three superimposed yarns such that they are in a staggered arrangement on seven levels, and twelve warp yarns which are arranged in four parallel planes each containing three superimposed parallel warp yarns. In each plane, one of the warp yarns connects the upper outermost weft yarn of one of the weft columns containing four weft yarns to the corresponding weft yarn of the following base weave group via the upper intermediate weft yarn of the weft column midway between the other two columns, a second of the warp yarns connects the upper intermediate weft yarn of said one column to the corresponding weft yarn of the following base weave group via the lower intermediate weft yarn of said midway column, and the third warp yarn connects the lower intermediate weft yarn of said one column to the corresponding weft yarn of the following base weave group via the lower outermost weft yarn of said midway column.

Linked multilayer fabric for structural composite materials

The invention provides a high-strength hybrid component comprising a relatively soft first part -made of a composite material consisting of an organic matrix reinforced with fibres, a relatively hard second part made of metal, metal alloy or ceramic, and a transition layer made of a composite material consisting of a matrix of a material which is weldable to the hard part and fibres which are extensions of the fibres of the soft part. The transition layer matrix and the hard part may be formed by deposition of molten material on to the fibre preform of the soft part, using flame, electric arc or plasma, and the resin matrix of the soft part is impregnated into the preform and polymerized afterwards. Alternatively, the hard part may be machined to shape and welded to the transition layer before completing the soft part.

A process for moulding high strength elongated parts made of a fibre-resin composite material, especially turbomachine blades such as fan blades, is disclosed wherein a plurality of heating and cooling elements are arranged within the body of the mould at intervals along the length of the mould cavity, and the liquid resin which is injected at one end into the mould cavity containing the fibre preform is polymerized progressively from the opposite end of the mould cavity, while maintaining the supply of liquid resin under pressure to the cavity, by successively de-activating the cooling elements, which maintain the resin in the liquid state, at predetermined time intervals starting from said opposite end of the mould cavity and progressing in turn towards said one end, and in synchronism therewith successively activating the heating elements to raise the temperature of the resin to the polymerizing temperature progressing in turn from said opposite end to said one end of the mould cavity. The process enables shrink cavities in the finished part to be avoided.

Process for moulding high strength elongated parts made of a fibre-resin

A turbomachine blade, particularly a fan blade for an aircraft jet engine, is made of a composite material comprising reinforcing fibres embedded in a thermosetting resin matrix, wherein the reinforcing fibres form a multilayer woven fabric in which the warp fibres of each layer are interwoven not only with the weft fibres of the layer but also with the weft fibres of at least the layers immediately above and below it so that the layers are all interconnected. Also, each layer only partly covers the layer below it so that the ends of the warp and weft fibres of a layer extend to near the surface of the blade, and the thickness of the blade at any point is determined by the number of layers present at that point.

Turbomachine blade made of composite material

A gas turbine blade includes a central core covered by a plurality of layers of composite material, and optionally also an outer sleeve of woven composite material. A network of transverse seams pass through the layers of composite material, and preferably also the core and the outer sleeve. This construction is particularly applicable to large diameter turbine blades.

Growing community of inventors

St Germain les Corbeil, France

Laurent Jean David