Snecma

Safran Aircraft Engines

Safran

Thierry Godon

Bruno Jacques Gerard Dambrine

Bruno Jacques Gérard Dambrine

Alain Robert Yves Perroux

Franck Bernard Leon Varin

Julien Schneider

Dominique Magnaudeix

Bruno Dambrine

Philippe Henrio

Michaël Podgorski

François Trochu

Johann Feunteun

Eduardo Antonio Julian Ruiz

A method of impregnating a fiber texture of hollow shape, the method including introducing a first suspension containing a first powder of solid particles of ceramic or carbon material into an inside volume defined by an inside face of a fiber texture of hollow shape placed in a mold, an outer face of the fiber texture being presented facing a wall of the mold; and using the action of centrifugal force to impregnate the fiber texture with the first suspension by causing the mold to rotate and varying the speed of rotation of the mold during the impregnation of the texture with the first suspension.

Method of impregnating a fiber texture of hollow shape

An assembly of two parts, one of the parts being made of composite material with fiber reinforcement obtained from a fiber preform made by three-dimensional weaving and densified with a matrix, the assembly including a mechanical anchor element secured to one of the parts and inserted inside the other part.

Assembly of two parts, one of which is made of composite material, the parts being assembled together by a mechanical anchor element

A method of fastening structural metal reinforcement on a portion of a gas turbine blade made of composite material and an injection mold for performing the method, the method including positioning the structural metal reinforcement in an injection mold, positioning the portion of the blade onto which the structural metal reinforcement is to be fastened in the injection mold, the portion of the blade and the structural metal reinforcement being positioned relative to each other in their final relative position while leaving between them a gap, injecting adhesive into the gap between the structural metal reinforcement and the portion of the blade onto which the structural metal reinforcement is to be fastened, and polymerizing the adhesive.

Method of fastening structural metal reinforcement on a portion of a gas turbine blade made of composite material, and an injection mold for performing such a method

A method of impregnating a fiber preform with an impregnation composition, includes applying a liquid on a structure, the structure including a chamber in which a fiber preform for impregnating is present, the chamber being defined between a rigid support on which the fiber preform is placed and a wall, the wall having a face situated facing the fiber preform; and an impregnation composition for impregnating the fiber preform, the impregnation composition being present in the chamber; the liquid being applied against the wall on its side opposite from the chamber, the wall being configured so that its face situated facing the fiber preform conserves its shape during the application of the liquid, the applied liquid enabling sufficient pressure to be created to move the wall towards the rigid support and impregnate the fiber preform with the impregnation composition.

Method for impregnation of a fibrous preform and device for implementation of the said method

A method is provided of bonding together at least two parts. The method includes assembling together at least two parts and at least one adhesive layer, the adhesive being configured so that its adhesive power increases on heating as a result of it polymerizing, at least one of the parts being made of composite material or of metal, the adhesive layer being present, after assembly, between the parts, the assembled together parts and the adhesive being present in a chamber defined by a wall, the wall having an inside face situated facing a first part present between the adhesive layer and the wall, the first part being intended to be bonded to a second part and only a fraction of the second part being present inside the chamber; and applying a liquid against the wall on its side opposite from the chamber.

Method for adhering parts and device for implementing said method

A method of injection molding a part made of composite material is provided. The method includes placing a preform in a mold; injecting a resin into the mold so as to impregnate the preform; unmolding the part after curing the resin; and subjecting the resin and the preform to pressure inside the mold while the resin is curing.

Process for injection moulding a composite part

A method for the production of a fibrous metal structure by weaving with metal weft yarns and metal warp yarns. The method includes weaving the fibrous structure by successive weaving of metal clasps that are used as weft yarns. For the purpose of weaving, each of the arms of each of the metal clasps is introduced into at least one shed, each shed being formed by two warp yarns.

Method for producing a fibrous metal structure by means of weaving

A fiber structure made as a single piece by multilayer weaving using a method including weaving warp yarns of at least a first set of layers of warp yarns with weft yarns including at least some that are woven with extra length so as to have warp yarn end portions available that extend beyond the zone of weaving, the warp yarn end portions being returned to be woven with warp yarns by being reinserted in layers of warp yarns, and a hollow, or tubular, portion being formed by looping the first woven set of layers of warp yarns back onto itself and applying traction to the ends of the reinserted weft yarns so that a fiber preform for a part including a hollow portion can be obtained as a single piece.

Multilayer woven fibrous structure including a hollow tubular part, production method thereof and composite part comprising same

A method of fabricating a part, for example a reinforcing edge for a turbomachine blade, the method including: making at least one fiber structure by three-dimensionally weaving metal yarns; and subjecting the fiber structure to hot isostatic pressing to cause the metal yarns to agglomerate so as to obtain a solid part. A composite solid part, for example a reinforcing edge for a turbomachine blade, includes a reinforcing structure of three-dimensionally woven ceramic fibers and a metal or metal alloy matrix.

Method of fabricating a part and a composite solid part obtained by the method

A method for manufacturing a cylindrical part from composite material, and a molding device to implement the method, the method including: installation of a fibrous structure on a horizontal mandrel; formation of an annular enclosure for molding around the fibrous structure and the mandrel; supply of the enclosure with resin via a first axial end, while keeping a second axial end of the enclosure at a pressure lower than a supply pressure of the resin. The second end includes at least two sectors of vents in a form of ring sectors, each being independently kept at a pressure lower than the supply pressure.

Method and device for manufacturing a cylindrical part from composite material

A reinforcing fiber structure woven as a single piece for fabricating a composite material part and including: first and second fiber substructures, each fiber substructure including at least one independent portion obtained by multilayer weaving between a plurality of layers of warp yarns and a plurality of layers of weft yarns that are independent from the other substructure; and an assembly portion between the least first and second fiber substructures in which a plurality of adjacent layers of warp yarns of the first fiber substructure are interlinked by at least some of the warp yarns of the second fiber substructure.

Fibrous structure for a part made of a composite material and having a complex shape

A reinforcing fiber structure for a composite material part is woven as a single piece by multilayer weaving between plural layers of weft yarns and plural layers of warp yarns arranged in adjacent manner between two faces of the structure. The fiber structure includes at least one arcuate portion extending over one of the faces of the fiber structure, the arcuate portion including at least some of the warp yarns continuous with at least two adjacent warp yarn layers present on one of the faces of the structure. The warp yarns of the arcuate portion are of a length that is longer than the warp yarns of at least two underlying warp yarn layers of the structure. In addition, the warp yarns of the arcuate portion are not interlinked with other warp yarns of the fiber structure.

Fibrous structure for a part made of composite material having one or more archshaped portions

A method for producing a metal component such as a metal turbomachine blade reinforcement, includes positioning a plurality of metal staples in a forming tool having a die and a punch; and hot isostatic pressing the plurality of metal staples causing the agglomeration of the metal staples so as to obtain a solid component.

Process for manufacturing a metal part, such as turbine engine blade reinforcement

A process for manufacturing a metal part such as a metal reinforcement for the blade of a turbine engine, which includes: manufacturing a three-dimensional metal structure made up of an insert which exhibits properties which allow superplastic forming and diffusion welding to be carried out, and of multiple metal wires encircling the periphery of the insert, where the metal structure forms a preform of the metal part; positioning the metal structure in a forming tool and hot-pressing the three-dimensional metal structure which causes agglomeration of the metal structure so as to obtain the compact metal part.

Process for making a metal part such as a turbine engine blade reinforcement

A method for producing a metal reinforcement for the leading edge or trailing edge of a turbomachine blade, the method including cutting a plurality of metal foils from a flexible metal sheet, corresponding substantially to the developed length of the leading or trailing edge metal reinforcement; producing a plurality of metal pockets, each pocket being produced from two of the metal foils obtained during the cutting; stacking the metal pockets one inside the other, such as to form a preform of the leading or trailing edge metal reinforcement; and hot isostatic pressing the preform, causing the metal pockets to bond to one another, so as to produce the leading or trailing edge metal reinforcement.

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Sevran, France

Thierry Godon