Safran

Safran Aircraft Engines

Safran Ceramics

Bruno Jacques Gérard Dambrine

Dominique Coupe

Jonathan Goering

Dominique Marie Christian Coupe

Thierry Godon

Yann Didier Simon Marchal

Michael Podgorski

Ludovic Edmond Camille Molliex

Bastien Tranquart

Catherine Billotte Cabre

Antoine Phelippeau

Jérémy Hellot

Alain Robert Yves Perroux

Edu Ruiz

Sylvain Turenne

Marc-Antoine Colot

Michaël Podgorski

Charles Leleu

Jean-Noël Mahieu

Wen Zhang

Emilie Chantal Gisèle Mendez

Yvan Rappart

Hubert Jean-Marie Fabre

A fibrous preform for forming the fibrous reinforcement of a composite material part, the fibrous preform being made as a single piece and obtained by three-dimensional weaving, the preform including first and second skins and a longitudinal stiffening portion connecting the first to the second skin, the longitudinal stiffening portion forming a stiffening element of the part in the longitudinal direction. The preform has an intermediate portion extending in the longitudinal direction between two end portions. The longitudinal stiffening portion includes, in the intermediate portion, longitudinal non-woven threads or strands held together by first transverse threads or strands coming from the first skin and second transverse threads or strands coming from the second skin. In the end portions, the longitudinal threads or strands of the longitudinal stiffening portion are woven with the transverse threads or strands.

Woven fibrous preform for producing a part from composite material, in particular a turbomachine blade

A part of a turbomachine made of composite material includes a fiber reinforcement having a three-dimensional weaving including a first set of yarns made of a first material, wherein the fiber reinforcement includes a vibration-damping element formed by a second set of yarns including a second material which is viscoelastic and which is different to the first material, the second set of yarns being woven with the first set of yarns.

Fiber-reinforced composite part with increased vibration resistance

A fibrous texture intended to form the fibrous reinforcement of a turbomachine part, includes first yarns bonded with second yarns, and at least one vibration damping element of viscoelastic material present in a recess defined by a second de-bonding zone, the de-bonding zone separating, on a portion of the texture, a first surface part of the texture from a second part of the texture formed by a three-dimensional fabric in which the first yarns are bonded with the second yarns, the first surface part of the texture being formed by a unidimensional layer of first yarns or being formed by a two-dimensional fabric in which the first yarns are bonded with the second yarns.

Woven fibrous texture

A process for manufacturing a part made of a ceramic matrix composite material, includes coating an outer surface of a porous preform with a layer of a fugitive material to form a model of the part to be obtained, the fugitive material being wax or resin, the fugitive material layer in the model not exceeding the highest peak of surface undulations of the preform, and ceramic and/or carbon particles being present in the porosity of the preform, coating the model formed with a ceramic powder composition, heat treating the coated model to remove the fugitive material and form a ceramic shell mold by sintering of the ceramic powder composition, introducing a molten composition including silicon into the shell mold to obtain the part in the shell mold, the molten composition infiltrating the porosity of the preform to form the ceramic matrix, and separating the shell mold from the part obtained.

Method for manufacturing a CMC part

A process for manufacturing a composite material component including a fiber reinforcement based on carbon fibers densified by a matrix, includes successively producing a fiber structure by multilayer three-dimensional weaving, placing the fiber structure in a closed mold, and injecting a resin into the mold, and wherein, during the weaving of the fiber structure, the process further includes spraying carbon nanoparticles onto the carbon fibers.

Method for manufacturing a component made of a composite material with a reinforced matrix, and device for the implementation thereof

A method of fabricating a composite material casing of varying thickness for a gas turbine includes using three-dimensional or multilayer weaving to make a fiber texture in the form of a strip; winding the fiber texture as a plurality of superposed layers onto a mandrel of profile corresponding to the profile of the casing to be fabricated, so as to obtain a fiber preform of shape corresponding to the shape of the casing to be fabricated; and densifying the fiber preform with a matrix. During winding of the fiber texture on the mandrel, a textile strip is interposed between the adjacent turns of the fiber texture, the textile strip presenting a width that is less than the width of the fiber texture and defining a retention zone of the casing.

Lighter-weight casing made of composite material and method of manufacturing same

A composite material part includes a fiber preform forming fiber reinforcement including a stack of at least two fiber plies, each of the fiber plies being made of an interlock weave three-dimensional fabric and each of the fiber plies having a number of warp yarn layers or a number of weft yarn layers that is greater than or equal to three; and a matrix present in the pores of the fiber preform.

Composite material part

A method of fabricating a part out of composite material, includes forming a fiber texture from refractory fibers; impregnating the fiber texture for a first time with a first slip containing first refractory particles; eliminating the liquid phase from the first slip so as to leave within the texture only the first refractory particles; impregnating the fiber texture for a second time with a second slip containing second refractory particles; eliminating the liquid phase from the second slip so as to leave within the texture only the second refractory particles and obtain a fiber preform filled with the first and second refractory particles; and sintering the first and second refractory particles present in the fiber preform in order to form a refractory matrix in the preform.

Method for manufacturing part made of composite material

A method of fabricating a part out of composite material, includes forming a fiber texture from refractory fibers; placing the texture in a mold having an impregnation chamber including in its bottom portion a part made of porous material, the impregnation chamber being closed in its top portion by a deformable impermeable diaphragm separating the impregnation chamber from a compacting chamber; injecting a slip containing a powder of refractory particles into the impregnation chamber; injecting a compression fluid into the compacting chamber, to force the slip to pass through the texture; draining the liquid of the slip via the porous material part, while retaining the powder of refractory particles inside the texture so as to obtain a fiber preform filled with refractory particles; drying the fiber preform; unmolding the preform; and sintering the refractory particles present in the preform in order to form a refractory matrix in the preform.

Growing community of inventors

Moissy-Cramayel, France

Bruno Jacques Gérard Dambrine