EP2191029A2 - Mechanical part including an insert made of a composite material - Google Patents

Mechanical part including an insert made of a composite material

Info

Publication number
EP2191029A2
EP2191029A2 EP08830741A EP08830741A EP2191029A2 EP 2191029 A2 EP2191029 A2 EP 2191029A2 EP 08830741 A EP08830741 A EP 08830741A EP 08830741 A EP08830741 A EP 08830741A EP 2191029 A2 EP2191029 A2 EP 2191029A2
Authority
EP
European Patent Office
Prior art keywords
mechanical part
revolution
winding
insert
manufacturing
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP08830741A
Other languages
German (de)
French (fr)
Other versions
EP2191029B1 (en
Inventor
Patrick Dunleavy
Jean-Michel Franchet
Gilles Klein
Richard Masson
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Safran Aircraft Engines SAS
Safran Landing Systems SAS
Original Assignee
Messier Dowty SA
SNECMA SAS
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Messier Dowty SA, SNECMA SAS filed Critical Messier Dowty SA
Publication of EP2191029A2 publication Critical patent/EP2191029A2/en
Application granted granted Critical
Publication of EP2191029B1 publication Critical patent/EP2191029B1/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Classifications

    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C47/00—Making alloys containing metallic or non-metallic fibres or filaments
    • C22C47/02—Pretreatment of the fibres or filaments
    • C22C47/06—Pretreatment of the fibres or filaments by forming the fibres or filaments into a preformed structure, e.g. using a temporary binder to form a mat-like element
    • C22C47/062—Pretreatment of the fibres or filaments by forming the fibres or filaments into a preformed structure, e.g. using a temporary binder to form a mat-like element from wires or filaments only
    • C22C47/064—Winding wires
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C47/00—Making alloys containing metallic or non-metallic fibres or filaments
    • C22C47/02—Pretreatment of the fibres or filaments
    • C22C47/04—Pretreatment of the fibres or filaments by coating, e.g. with a protective or activated covering
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C47/00—Making alloys containing metallic or non-metallic fibres or filaments
    • C22C47/14—Making alloys containing metallic or non-metallic fibres or filaments by powder metallurgy, i.e. by processing mixtures of metal powder and fibres or filaments
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C49/00—Alloys containing metallic or non-metallic fibres or filaments
    • C22C49/02—Alloys containing metallic or non-metallic fibres or filaments characterised by the matrix material
    • C22C49/04—Light metals
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
    • B22F2999/00—Aspects linked to processes or compositions used in powder metallurgy
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/4998—Combined manufacture including applying or shaping of fluent material
    • Y10T29/49982—Coating
    • Y10T29/49986—Subsequent to metal working
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/12—All metal or with adjacent metals
    • Y10T428/12486—Laterally noncoextensive components [e.g., embedded, etc.]

Definitions

  • the present invention relates to a mechanical part comprising an insert of composite material of the type consisting of ceramic fibers in a metal matrix, as well as a method of manufacturing this mechanical part and a winding device designed for implementing the manufacturing process. .
  • the invention applies to any type of mechanical part whose function is to transmit a traction force and / or compression mainly unidirectional.
  • some mechanical parts may comprise an insert made of composite material with a metal matrix, such parts being able to be monobloc.
  • a composite material comprises a matrix of metal alloy, for example titanium alloy Ti, within which fibers extend, for example ceramic fibers of SiC silicon carbide.
  • Such fibers have a much higher tensile and compressive strength than titanium. It is therefore mainly the fibers that take up the efforts, the metal alloy matrix ensuring a binder function with the rest of the part, as well as protection and insulation of the fibers, which must not come into contact with each other. others.
  • the ceramic fibers are resistant to erosion, but must necessarily be reinforced with metal.
  • the composite materials as described above are known to be used, in the aeronautical field, for the manufacture of disks, shafts, bodies of jacks, housings, spacers or as reinforcements of single-piece parts such as blades.
  • a technique for manufacturing these parts is described in document FR 2886290, representative of the technological background of the invention, in which one of the essential manufacturing steps consists in winding a beam or a sheet of threads coated around a piece of circular revolution perpendicular to the axis of rotation thereof.
  • the described parts thus obtained are of circular type and are particularly suitable for producing circular parts such as shafts, cylinder bodies, housings or discs.
  • connecting rods essentially oblong shape, whose function is to transmit a tensile force and / or unidirectional compression.
  • the invention particularly relates to a method of manufacturing a mechanical part comprising at least one composite material insert of the type consisting of ceramic fibers in a metal matrix capable of transmitting tensile forces and / or unidirectional compression between its ends .
  • the invention relates to a method of manufacturing a mechanical part comprising at least one insert made of metal matrix composite material within which ceramic fibers extend, the composite material insert being obtained from a plurality of coated wires each having a ceramic fiber coated with a metallic sheath, the method comprising the manufacture of at least one insert with a step of winding a bundle or a bonded layer of wires coated around a piece of revolution.
  • at least part of the winding is carried out in a rectilinear direction.
  • the mechanical part thus obtained for example a connecting rod, advantageously makes it possible to transmit unidirectional traction and / or compression forces.
  • the invention also relates to a winding device specially designed for implementing the manufacturing method according to the invention.
  • FIG. 1 represents a perspective view of an example of a mechanical part according to the prior art
  • FIG. 2 represents a perspective view of an exemplary winding device according to the invention
  • FIG. 3 represents a perspective view of an example of an insert obtained according to the manufacturing method of the invention.
  • Fig. 4 shows an example of an insert, container for receiving and a metal cover for sealingly covering the container and the insert;
  • FIG. 5 represents a perspective view of an example of a mechanical part obtained according to the manufacturing method of the invention
  • FIG. 6 represents a variant of the manufacturing method of the invention
  • FIG. 7 represents a sectional view of another example of a mechanical part obtained according to the variant of the manufacturing method of the invention.
  • FIG. 8 represents a perspective view of the example of a mechanical part obtained according to the variant of the manufacturing method of the invention.
  • FIG. 1 represents an example of a mechanical part such as a rod 1 whose shape is generally oblong, that is to say of elongated shape. It has two ends 13 and 14.
  • the function of a connecting rod 1 is to transmit a movement, and / or tensile forces T and / or compression C, between two parts articulated at its ends along parallel axes Z1 and Z2 .
  • the connecting rod 1 has at each of its ends 13 and 14 a cylindrical recess 11 or 12 whose axes correspond to the parallel axes Z1 and Z2.
  • This type of rod 1 can be used, for example, in the design of the undercarriages or in that of turbomachines comprising rods for taking up thrust force.
  • FIG. 2 represents an example of a winding device 20 according to the invention.
  • the winding device 20 is particularly suitable for producing an insert for a mechanical part such as a connecting rod.
  • This winding device 20 comprises a hollow part of revolution 2 hollow oblong playing the role of mandrel and two flanges 21 and 22 oblong and substantially identical.
  • the piece of revolution 2 has a geometry of revolution, that is to say a geometry describing a closed structure most often curved.
  • the dimensions of the flanges 21 and 22 are greater than the dimensions of the part of revolution 2 so that the periphery 27 of each flange 21 and 22 extends beyond the periphery of the part of revolution 2.
  • the piece of revolution 2 is sandwiched between the flanges 21 and 22.
  • the son 32 are wound on the part of revolution 2 when the winding device 20 is rotated along the winding axis Z.
  • the flanges 21 and 22 retain axially the son coatings 32 and guide them.
  • the winding device 20 belongs to an assembly forming a winding system.
  • the winding system further comprises means for rotating the winding device 20 and means for providing a bundle or a bonded sheet of coated threads 32.
  • the piece of revolution 2 comprises two rectilinear winding portions
  • These rectilinear winding portions 24 are oriented perpendicularly to the winding axis Z.
  • the winding of the coated wires 32 is carried out perpendicularly to the winding axis Z, in other words, the coated wires 32 are substantially oriented perpendicularly to the winding axis Z.
  • these rectilinear winding portions 24 are parallel and interposed between two circular portions.
  • the part of revolution 2 it is possible to vary the dimensions of the part of revolution 2, in particular its thickness in the axial direction Z, the length of the rectilinear winding portions 24 and the radius of curvature of the circular pieces 25, depending on the dimensions of the desired insert 3.
  • the circular pieces 25 may also have different radii.
  • the portions of rectilinear windings 24 may not be parallel.
  • the winding around the part of revolution 2 having rectilinear winding portions 24 makes it possible to generate in a short time an insert 3 comprising at least one rectilinear generatrix constituted by a large number of parallel and unidirectional coiled wires 32.
  • the insert 3 once wound, can be removed from the winding device 20 by separating the flanges 21 and 22 from one another.
  • the shape of the insert 3 thus formed must be fixed to prevent the son 32 lose their orientation. Several techniques can be implemented for this purpose.
  • a first technique for maintaining the shape of the insert 3 consists in providing, at the beginning of winding, a step of winding a first metal foil for hooking up the inner part of the insert 3 and, at the end of winding, a step of winding a second metal foil 28 for hooking the outer part of the insert 3.
  • the first metallic foil constitutes the part of revolution 2.
  • the coated wires 32 are thus between the foils 2 and 28, as shown in FIG.
  • each flange 21 and 22 has notches 23 on its periphery 27.
  • Each notch 23 of the flange 21 is disposed opposite a notch 23 of the flange 22, thus forming a pair of notches 23.
  • Attaching the metal straps 31 is facilitated by the dimensions of the notches 23 extending inwardly of the flanges 21 and 22 to a depth d.
  • the depth d of the notches 23 must be such that it is possible to access the hollow interior 29 of the part of revolution 2 which is arranged around a hub of the winding device 20, not visible in FIG. 2, comprising an alternation of notches and teeth, the notches of the hub being in phase with the notches 23 of the flanges 21 and 22.
  • the depth d extends beyond the winding surface of the part of revolution 2.
  • Each pair of notches 23 is intended to allow the attachment of a metal strap 31.
  • the metal straps 31 are made of a metallic material identical to that of the container 4, described in connection with Figure 4, and the piece of revolution 2.
  • the metal straps 31 are fixed around the insert 3 by a contact welding process.
  • the metal straps 31 are arranged at regular intervals on the wound insert 3.
  • insert 3 coiled and the metal straps 31 put in place, it can be removed from the winding device 20 by separating the flanges 21 and 22 from one another.
  • An example of insert 3 thus obtained is shown in FIG. 3. It consists of a piece of revolution of oblong shape comprising two rectilinear and parallel portions 34 interposed between two circular portions 35.
  • a second technique for maintaining the shape of the insert 3, which does not require the use of straps 31, consists in providing a part of revolution 2 forming an oblong mandrel comprising at least one radial flange, for example of L-shaped cross-section or in U, on which the wires 32 are wound.
  • a bonded sheet of coated son 32 it is possible to secure it to the part of revolution 2 on which it is wound and to the sheet of the lower layer by means of a method by contact welding between two electrodes and passage of a medium frequency current.
  • the wires 32 are thus welded as winding progresses so that, when the insert 3 is extracted from the winding device 20, it forms a part integral with the part of revolution 2.
  • the insert 3 is then inserted into a container 4, as shown in FIG. 4.
  • the container 4 comprises for this purpose a groove 41 of shape complementary to the insert 3 and in which the insert 3 is housed.
  • the container 4 constitutes the preform of the metal alloy matrix, preferably titanium Ti.
  • a lid 5 is attached to the container 4 by electron beam welding, evacuated, and then compacted by a hot isostatic compaction process.
  • the assembly is then machined to obtain the final mechanical part 10: a connecting rod 10, shown in FIG. 5.
  • the connecting rod 10, of identical shape to the connecting rod 1 of FIG. 1, further comprises an insert of composite material 3, with geometry of revolution, whose son 32 are partly oriented in a rectilinear direction.
  • This rectilinear direction is perpendicular to the axes Z1 and Z2.
  • This link 10 advantageously allows to transmit the unidirectional traction and / or compression forces.
  • the rectilinear portions 34 of the inserts 3 comprise son all oriented in the same rectilinear direction.
  • the invention applies to any type of mechanical part whose function is to transmit a traction force and / or compression mainly unidirectional and is therefore not limited only to connecting rods that are only an example of application.
  • the mechanical part may be of more complex shape and comprise a plurality of inserts 3 each of which may be of geometry of revolution, that is to say a geometry describing a closed structure most often curved .
  • the manufacturing method is modified by using a container 4 comprising, on either side of two of its opposite faces 42, grooves 41 intended to receive inserts 3.
  • the mechanical part 110 obtained is that represented in FIG. 7 and thus comprises inserts 3.
  • the inserts 3 are positioned on either side of a median plane P1 of the mechanical part 110. They are positioned in P2 planes and P3 forming an angle ⁇ not zero between them.
  • Figure 8 shows, in perspective, a mechanical part 110 thus obtained.
  • This mechanical part 110 may also include recesses 15 intended to reduce the mass.
  • Such mechanical parts 10 or 110 are perfectly suitable for aeronautical applications, for example for undercarriages or for turbomachines intended for an aircraft.

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  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Crystallography & Structural Chemistry (AREA)
  • Manufacture Of Alloys Or Alloy Compounds (AREA)
  • Pressure Welding/Diffusion-Bonding (AREA)
  • Moulding By Coating Moulds (AREA)
  • Manufacturing Of Tubular Articles Or Embedded Moulded Articles (AREA)

Abstract

The invention relates to a method for making a mechanical part (10) that comprises at least one insert (3) made of a composite material with a metal matrix in which extend ceramic fibres, the composite material insert (3) being obtained from a plurality of coated threads (32) each comprising a ceramic fibre coated with a metal sheath, wherein said method comprises the production of at least one insert (3) with the step of winding a bundle or a bonded web of coated threads (32) around a revolution part (2). According to the invention, at least a portion of the winding is carried out in a rectilinear direction. The invention also relates to a mechanical part (10) thus obtained and to a winding device (20) adapted for implementing the production method of the invention.

Description

Pièce mécanique comportant un insert en matériau composite Mechanical part comprising a composite material insert
La présente invention concerne une pièce mécanique comportant un insert en matériau composite du type constitué de fibres céramiques dans une matrice métallique, ainsi qu'un procédé de fabrication de cette pièce mécanique et un dispositif de bobinage conçu pour la mise en œuvre du procédé de fabrication. L'invention s'applique à tout type de pièce mécanique dont la fonction est de transmettre un effort de traction et/ou de compression principalement unidirectionnel.The present invention relates to a mechanical part comprising an insert of composite material of the type consisting of ceramic fibers in a metal matrix, as well as a method of manufacturing this mechanical part and a winding device designed for implementing the manufacturing process. . The invention applies to any type of mechanical part whose function is to transmit a traction force and / or compression mainly unidirectional.
Dans le domaine aéronautique, notamment, un objectif constant est l'optimisation de la résistance des pièces mécaniques pour une masse et un encombrement minimaux. Ainsi, certaines pièces mécaniques peuvent comporter un insert en matériau composite à matrice métallique, de telles pièces pouvant être monoblocs. Un tel matériau composite comporte une matrice d'alliage métallique, par exemple d'alliage de titane Ti, au sein de laquelle s'étendent des fibres, par exemple des fibres céramiques de carbure de silicium SiC. De telles fibres présentent une résistance en traction et en compression bien supérieure à celle du titane. Ce sont donc principalement les fibres qui reprennent les efforts, la matrice d'alliage métallique assurant une fonction de liant avec le reste de la pièce, ainsi que de protection et d'isolation des fibres, qui ne doivent pas entrer en contact les unes avec les autres. En outre, les fibres céramiques sont résistantes à l'érosion, mais doivent nécessairement être renforcées par du métal.In the aeronautical field, in particular, a constant objective is the optimization of the resistance of mechanical parts for a minimum mass and size. Thus, some mechanical parts may comprise an insert made of composite material with a metal matrix, such parts being able to be monobloc. Such a composite material comprises a matrix of metal alloy, for example titanium alloy Ti, within which fibers extend, for example ceramic fibers of SiC silicon carbide. Such fibers have a much higher tensile and compressive strength than titanium. It is therefore mainly the fibers that take up the efforts, the metal alloy matrix ensuring a binder function with the rest of the part, as well as protection and insulation of the fibers, which must not come into contact with each other. others. In addition, the ceramic fibers are resistant to erosion, but must necessarily be reinforced with metal.
Les matériaux composites tels que décrits ci-dessus sont connus pour être utilisés, dans le domaine aéronautique, pour la fabrication de disques, d'arbres, de corps de vérins, de carters, d'entretoises ou comme renforts de pièces monoblocs telles que des aubes. Une technique de fabrication de ces pièces est décrite dans le document FR 2886290, représentatif de l'arrière plan technologique de l'invention, dans lequel une des étapes essentielles de fabrication consiste à effectuer un bobinage d'un faisceau ou d'une nappe de fils enduits autour d'une pièce de révolution circulaire perpendiculairement à l'axe de rotation de celle-ci. Les pièces décrites ainsi obtenues sont de type circulaire et conviennent particulièrement pour la réalisation de pièces circulaires telles que des arbres, des corps de vérins, des carters ou des disques.The composite materials as described above are known to be used, in the aeronautical field, for the manufacture of disks, shafts, bodies of jacks, housings, spacers or as reinforcements of single-piece parts such as blades. A technique for manufacturing these parts is described in document FR 2886290, representative of the technological background of the invention, in which one of the essential manufacturing steps consists in winding a beam or a sheet of threads coated around a piece of circular revolution perpendicular to the axis of rotation thereof. The described parts thus obtained are of circular type and are particularly suitable for producing circular parts such as shafts, cylinder bodies, housings or discs.
Toutefois, certaines pièces mécaniques requièrent des propriétés différentes de celles présentées par les pièces circulaires. C'est le cas notamment des bielles, de forme essentiellement oblongue, dont la fonction est de transmettre un effort de traction et/ou de compression unidirectionnel.However, some mechanical parts require properties different from those presented by the circular parts. This is the case in particular connecting rods, essentially oblong shape, whose function is to transmit a tensile force and / or unidirectional compression.
L'invention a notamment pour objet un procédé de fabrication d'une pièce mécanique comportant au moins un insert en matériau composite du type constitué de fibres céramiques dans une matrice métallique capable de transmettre des efforts de traction et/ou de compression unidirectionnels entre ses extrémités.The invention particularly relates to a method of manufacturing a mechanical part comprising at least one composite material insert of the type consisting of ceramic fibers in a metal matrix capable of transmitting tensile forces and / or unidirectional compression between its ends .
A cet effet, l'invention concerne un procédé de fabrication d'une pièce mécanique comportant au moins un insert en matériau composite à matrice métallique au sein de laquelle s'étendent des fibres céramiques, l'insert en matériau composite étant obtenu à partir d'une pluralité de fils enduits comportant chacun une fibre céramique enrobée d'une gaine métallique, le procédé comprenant la fabrication d'au moins un insert avec une étape de bobinage d'un faisceau ou d'une nappe liée de fils enduits autour d'une pièce de révolution. Selon l'invention, au moins une partie du bobinage s'effectue selon une direction rectiligne. La pièce mécanique ainsi obtenue, par exemple une bielle, permet avantageusement de transmettre des efforts de traction et/ou de compression unidirectionnels.For this purpose, the invention relates to a method of manufacturing a mechanical part comprising at least one insert made of metal matrix composite material within which ceramic fibers extend, the composite material insert being obtained from a plurality of coated wires each having a ceramic fiber coated with a metallic sheath, the method comprising the manufacture of at least one insert with a step of winding a bundle or a bonded layer of wires coated around a piece of revolution. According to the invention, at least part of the winding is carried out in a rectilinear direction. The mechanical part thus obtained, for example a connecting rod, advantageously makes it possible to transmit unidirectional traction and / or compression forces.
L'invention se rapporte également à un dispositif de bobinage spécialement conçu pour la mise en œuvre du procédé de fabrication selon l'invention.The invention also relates to a winding device specially designed for implementing the manufacturing method according to the invention.
D'autres avantages et caractéristiques de l'invention ressortiront à la lecture de la description détaillée qui suit en référence aux figures annexées sur lesquelles :Other advantages and characteristics of the invention will emerge on reading the detailed description which follows with reference to the appended figures in which:
• la figure 1 représente une vue en perspective d'un exemple de pièce mécanique selon l'art antérieur ; • la figure 2 représente une vue en perspective d'un exemple de dispositif de bobinage selon l'invention ;FIG. 1 represents a perspective view of an example of a mechanical part according to the prior art; FIG. 2 represents a perspective view of an exemplary winding device according to the invention;
• la figure 3 représente une vue en perspective d'un exemple d'insert obtenu selon le procédé de fabrication de l'invention ;FIG. 3 represents a perspective view of an example of an insert obtained according to the manufacturing method of the invention;
• la figure 4 représente un exemple d'insert, de conteneur destiné à accueillir rïnsert et de couvercle métallique destiné à recouvrir de manière étanche le conteneur et l'insert ;Fig. 4 shows an example of an insert, container for receiving and a metal cover for sealingly covering the container and the insert;
• la figure 5 représente une vue en perspective d'un exemple de pièce mécanique obtenue selon le procédé de fabrication de l'invention ; • la figure 6 représente une variante du procédé de fabrication de l'invention ;FIG. 5 represents a perspective view of an example of a mechanical part obtained according to the manufacturing method of the invention; FIG. 6 represents a variant of the manufacturing method of the invention;
• la figure 7 représente une vue en coupe d'un autre exemple de pièce mécanique obtenue selon la variante du procédé de fabrication de l'invention ; et • la figure 8 représente une vue en perspective de l'exemple de pièce mécanique obtenue selon la variante du procédé de fabrication de l'invention.FIG. 7 represents a sectional view of another example of a mechanical part obtained according to the variant of the manufacturing method of the invention; and FIG. 8 represents a perspective view of the example of a mechanical part obtained according to the variant of the manufacturing method of the invention.
Les techniques de fabrication d'une pièce mécanique, comportant un insert en matériau composite, décrites dans le document FR 2886290 sont utilisables dans le cadre de la présente invention. Ainsi, l'enseignement de ce document doit être considéré comme étant incorporé dans la présente demande, par exemple, et de manière non limitative, la structure des fils enduits, leur fabrication, la fabrication d'une nappe liée de fils enduits, la solidarisation de cette nappe soit sur le support métallique sur lequel elle est enroulée soit à la nappe de couche inférieure, le soudage des fils par laser ou par contact entre deux électrodes, la compaction isostatique à chaud et l'usinage.The techniques for manufacturing a mechanical part, comprising an insert made of composite material, described in document FR 2886290 can be used in the context of the present invention. Thus, the teaching of this document must be considered as incorporated in the present application, for example, and without limitation, the structure of the coated wires, their manufacture, the manufacture of a bonded ply of coated wires, the joining together of this web is on the metal support on which it is wound or to the lower layer ply, the welding of the son by laser or by contact between two electrodes, hot isostatic compaction and machining.
La figure 1 représente un exemple de pièce mécanique telle qu'une bielle 1 dont la forme est généralement oblongue, c'est-à-dire de forme allongée. Elle comporte deux extrémités 13 et 14. La fonction d'une bielle 1 est de transmettre un mouvement, et/ou des efforts de traction T et/ou de compression C, entre deux pièces articulées à ses extrémités suivant des axes parallèles Zl et Z2. La bielle 1 comporte à chacune de ses extrémités 13 et 14 un évidement cylindrique 11 ou 12 dont les axes correspondent aux axes parallèles Zl et Z2. Ce type de bielle 1 peut être utilisé, par exemple, dans la conception des atterrisseurs ou dans celle des turbomachines comportant des bielles de reprise d'effort de poussée.FIG. 1 represents an example of a mechanical part such as a rod 1 whose shape is generally oblong, that is to say of elongated shape. It has two ends 13 and 14. The function of a connecting rod 1 is to transmit a movement, and / or tensile forces T and / or compression C, between two parts articulated at its ends along parallel axes Z1 and Z2 . The connecting rod 1 has at each of its ends 13 and 14 a cylindrical recess 11 or 12 whose axes correspond to the parallel axes Z1 and Z2. This type of rod 1 can be used, for example, in the design of the undercarriages or in that of turbomachines comprising rods for taking up thrust force.
La figure 2 représente un exemple de dispositif de bobinage 20 selon l'invention. Dans cet exemple, le dispositif de bobinage 20 est particulièrement adapté pour la réalisation d'un insert pour une pièce mécanique telle qu'une bielle. Ce dispositif de bobinage 20 comporte une pièce de révolution 2 creuse de forme oblongue jouant le rôle de mandrin et deux flasques 21 et 22 de forme oblongue et sensiblement identiques. La pièce de révolution 2 est à géométrie de révolution, c'est-à-dire une géométrie décrivant une structure fermée le plus souvent courbe. Les dimensions des flasques 21 et 22 sont supérieures aux dimensions de la pièce de révolution 2 de sorte que la périphérie 27 de chaque flasque 21 et 22 s'étende au-delà de la périphérie de la pièce de révolution 2. La pièce de révolution 2 est prise en sandwich entre les flasques 21 et 22. Les fils 32 s'enroulent sur la pièce de révolution 2 lorsque le dispositif de bobinage 20 est mis en rotation selon l'axe de bobinage Z. Les flasques 21 et 22 retiennent axialement les fils enduits 32 et les guident.FIG. 2 represents an example of a winding device 20 according to the invention. In this example, the winding device 20 is particularly suitable for producing an insert for a mechanical part such as a connecting rod. This winding device 20 comprises a hollow part of revolution 2 hollow oblong playing the role of mandrel and two flanges 21 and 22 oblong and substantially identical. The piece of revolution 2 has a geometry of revolution, that is to say a geometry describing a closed structure most often curved. The dimensions of the flanges 21 and 22 are greater than the dimensions of the part of revolution 2 so that the periphery 27 of each flange 21 and 22 extends beyond the periphery of the part of revolution 2. The piece of revolution 2 is sandwiched between the flanges 21 and 22. The son 32 are wound on the part of revolution 2 when the winding device 20 is rotated along the winding axis Z. The flanges 21 and 22 retain axially the son coatings 32 and guide them.
Le dispositif de bobinage 20 appartient à un ensemble formant un système de bobinage. Le système de bobinage comprend en outre des moyens pour mettre en rotation le dispositif de bobinage 20 et des moyens de fourniture d'un faisceau ou d'une nappe liée de fils enduits 32.The winding device 20 belongs to an assembly forming a winding system. The winding system further comprises means for rotating the winding device 20 and means for providing a bundle or a bonded sheet of coated threads 32.
La pièce de révolution 2 comporte deux portions de bobinage rectilignesThe piece of revolution 2 comprises two rectilinear winding portions
24. Ces portions de bobinage rectilignes 24 sont orientées perpendiculairement à l'axe de bobinage Z. Ainsi, au moins une partie du bobinage des fils 32 autour de la pièce de révolution 2 s'effectue selon une direction rectiligne. Le bobinage des fils enduits 32 s'effectue de manière perpendiculaire à l'axe de bobinage Z, autrement dit, les fils enduits 32 sont sensiblement orientés perpendiculairement à l'axe de bobinage Z.24. These rectilinear winding portions 24 are oriented perpendicularly to the winding axis Z. Thus, at least a portion of the winding son 32 around the part of revolution 2 is carried out in a rectilinear direction. The winding of the coated wires 32 is carried out perpendicularly to the winding axis Z, in other words, the coated wires 32 are substantially oriented perpendicularly to the winding axis Z.
Dans l'exemple représenté sur la figure 2, ces portions de bobinage rectilignes 24 sont parallèles et intercalées entre deux portions circulairesIn the example shown in FIG. 2, these rectilinear winding portions 24 are parallel and interposed between two circular portions.
25. Il est possible de faire varier les dimensions de la pièce de révolution 2, notamment son épaisseur selon la direction axiale Z, la longueur des portions de bobinage rectilignes 24 et le rayon de courbure des pièces circulaires 25, en fonction des dimensions de l'insert 3 souhaité. Les pièces circulaires 25 peuvent également comporter des rayons différents. Ainsi, les portions de bobinages rectilignes 24 peuvent ne pas être parallèles.25. It is possible to vary the dimensions of the part of revolution 2, in particular its thickness in the axial direction Z, the length of the rectilinear winding portions 24 and the radius of curvature of the circular pieces 25, depending on the dimensions of the desired insert 3. The circular pieces 25 may also have different radii. Thus, the portions of rectilinear windings 24 may not be parallel.
Le bobinage autour de la pièce de révolution 2 comportant des portions de bobinage rectilignes 24 permet de générer en peu de temps un insert 3 comportant au moins une génératrice rectiligne constituée d'un grand nombre de fils enduits 32 parallèles et unidirectionnels.The winding around the part of revolution 2 having rectilinear winding portions 24 makes it possible to generate in a short time an insert 3 comprising at least one rectilinear generatrix constituted by a large number of parallel and unidirectional coiled wires 32.
L'insert 3, une fois bobiné, peut être retiré du dispositif de bobinage 20 en désolidarisant les flasques 21 et 22 l'un de l'autre. La forme de l'insert 3 ainsi formé doit être figée pour éviter que les fils 32 perdent leur orientation. Plusieurs techniques peuvent être mises en œuvre dans ce but.The insert 3, once wound, can be removed from the winding device 20 by separating the flanges 21 and 22 from one another. The shape of the insert 3 thus formed must be fixed to prevent the son 32 lose their orientation. Several techniques can be implemented for this purpose.
Une première technique de maintien en forme de l'insert 3 consiste à prévoir, en début de bobinage, une étape de bobinage d'un premier clinquant métallique d'accrochage de la partie interne de l'insert 3 et, en fin de bobinage, une étape de bobinage d'un second clinquant 28 métallique d'accrochage de la partie externe de l'insert 3. Dans cet exemple, le premier clinquant métallique constitue la pièce de révolution 2. Les fils enduits 32 se trouvent donc ainsi entre les clinquants 2 et 28, comme représenté sur la figure 3.A first technique for maintaining the shape of the insert 3 consists in providing, at the beginning of winding, a step of winding a first metal foil for hooking up the inner part of the insert 3 and, at the end of winding, a step of winding a second metal foil 28 for hooking the outer part of the insert 3. In this example, the first metallic foil constitutes the part of revolution 2. The coated wires 32 are thus between the foils 2 and 28, as shown in FIG.
Par ailleurs, comme illustré sur la figure 2, chaque flasque 21 et 22 comporte des encoches 23 sur sa périphérie 27. Chaque encoche 23 du flasque 21 est disposée en vis-à-vis d'une encoche 23 du flasque 22, formant ainsi une paire d'encoches 23. La fixation des sangles métalliques 31 est facilitée par les dimensions des encoches 23 s'étendant vers l'intérieur des flasques 21 et 22 sur une profondeur d. La profondeur d des encoches 23 doit être telle qu'il soit possible d'accéder à l'intérieur creux 29 de la pièce de révolution 2 laquelle est disposée autour d'un moyeu du dispositif de bobinage 20, non visible sur la figure 2, comprenant une alternance d'encoches et de dents, les encoches du moyeu étant en phase avec les encoches 23 des flasques 21 et 22. La profondeur d s'étend au-delà de la surface de bobinage de la pièce de révolution 2.Moreover, as illustrated in FIG. 2, each flange 21 and 22 has notches 23 on its periphery 27. Each notch 23 of the flange 21 is disposed opposite a notch 23 of the flange 22, thus forming a pair of notches 23. Attaching the metal straps 31 is facilitated by the dimensions of the notches 23 extending inwardly of the flanges 21 and 22 to a depth d. The depth d of the notches 23 must be such that it is possible to access the hollow interior 29 of the part of revolution 2 which is arranged around a hub of the winding device 20, not visible in FIG. 2, comprising an alternation of notches and teeth, the notches of the hub being in phase with the notches 23 of the flanges 21 and 22. The depth d extends beyond the winding surface of the part of revolution 2.
Chaque paire d'encoches 23 est destinée à permettre la fixation d'une sangle métallique 31. Les sangles métalliques 31 sont constituées d'un matériau métallique identique à celui du conteneur 4, décrit en liaison avec la figure 4, et de la pièce de révolution 2. Les sangles métalliques 31 sont fixées autour de l'insert 3 par un procédé de soudage par contact. Les sangles métalliques 31 sont disposées à intervalles réguliers sur l'insert 3 bobiné.Each pair of notches 23 is intended to allow the attachment of a metal strap 31. The metal straps 31 are made of a metallic material identical to that of the container 4, described in connection with Figure 4, and the piece of revolution 2. The metal straps 31 are fixed around the insert 3 by a contact welding process. The metal straps 31 are arranged at regular intervals on the wound insert 3.
Une fois l'insert 3 bobiné et les sangles métalliques 31 mises en place, celui-ci peut être retiré du dispositif de bobinage 20 en désolidarisant les flasques 21 et 22 l'un de l'autre. Un exemple d'insert 3 ainsi obtenu est représenté en figure 3. Il consiste en une pièce de révolution de forme oblongue comportant deux portions rectilignes 34 et parallèles intercalées entre deux portions circulaires 35.Once the insert 3 coiled and the metal straps 31 put in place, it can be removed from the winding device 20 by separating the flanges 21 and 22 from one another. An example of insert 3 thus obtained is shown in FIG. 3. It consists of a piece of revolution of oblong shape comprising two rectilinear and parallel portions 34 interposed between two circular portions 35.
Une deuxième technique de maintien en forme de l'insert 3, ne nécessitant pas l'utilisation de sangles 31, consiste à prévoir une pièce de révolution 2 formant un mandrin oblong comportant au moins un rebord radial, par exemple à section transversale en L ou en U, sur lequel s'enroulent les fils 32. Lorsqu'une nappe liée de fils enduits 32 est utilisée, il est possible de la solidariser à la pièce de révolution 2 sur laquelle elle est enroulée et à la nappe de la couche inférieure au moyen d'un procédé par soudage par contact entre deux électrodes et passage d'un courant moyenne fréquence. Les fils 32 sont ainsi soudés au fur et à mesure du bobinage de sorte que, lorsque l'insert 3 est extrait du dispositif de bobinage 20, il forme une pièce solidaire avec la pièce de révolution 2.A second technique for maintaining the shape of the insert 3, which does not require the use of straps 31, consists in providing a part of revolution 2 forming an oblong mandrel comprising at least one radial flange, for example of L-shaped cross-section or in U, on which the wires 32 are wound. When a bonded sheet of coated son 32 is used, it is possible to secure it to the part of revolution 2 on which it is wound and to the sheet of the lower layer by means of a method by contact welding between two electrodes and passage of a medium frequency current. The wires 32 are thus welded as winding progresses so that, when the insert 3 is extracted from the winding device 20, it forms a part integral with the part of revolution 2.
L'insert 3 est ensuite inséré dans un conteneur 4, comme représenté sur la figure 4. Le conteneur 4 comporte à cet effet une rainure 41 de forme complémentaire à l'insert 3 et dans laquelle vient se loger l'insert 3. Le conteneur 4 constitue la préforme de la matrice d'alliage métallique, de préférence en titane Ti. Un couvercle 5 est rapporté sur le conteneur 4 par soudage par faisceau d'électrons, mis sous vide, puis compacté par un procédé de compaction isostatique à chaud.The insert 3 is then inserted into a container 4, as shown in FIG. 4. The container 4 comprises for this purpose a groove 41 of shape complementary to the insert 3 and in which the insert 3 is housed. The container 4 constitutes the preform of the metal alloy matrix, preferably titanium Ti. A lid 5 is attached to the container 4 by electron beam welding, evacuated, and then compacted by a hot isostatic compaction process.
L'ensemble est ensuite usiné pour obtenir la pièce mécanique 10 finale : une bielle 10, représentée sur la figure 5. La bielle 10, de forme identique à la bielle 1 de la figure 1, comporte en outre un insert en matériau composite 3, à géométrie de révolution, dont les fils 32 sont en partie orientés selon une direction rectiligne. Cette direction rectiligne est perpendiculaire aux axes Zl et Z2. Cette bielle 10 permet avantageusement de transmettre les efforts de traction et/ou de compression unidirectionnels. Les portions rectilignes 34 des inserts 3 comportent des fils tous orientés selon une même direction rectiligne.The assembly is then machined to obtain the final mechanical part 10: a connecting rod 10, shown in FIG. 5. The connecting rod 10, of identical shape to the connecting rod 1 of FIG. 1, further comprises an insert of composite material 3, with geometry of revolution, whose son 32 are partly oriented in a rectilinear direction. This rectilinear direction is perpendicular to the axes Z1 and Z2. This link 10 advantageously allows to transmit the unidirectional traction and / or compression forces. The rectilinear portions 34 of the inserts 3 comprise son all oriented in the same rectilinear direction.
L'invention s'applique à tout type de pièce mécanique dont la fonction est de transmettre un effort de traction et/ou de compression principalement unidirectionnel et ne se limite donc pas uniquement aux bielles qui ne constituent qu'un exemple d'application. Selon une variante de l'invention, la pièce mécanique peut être de forme plus complexe et comporter une pluralité d'inserts 3 pouvant chacun être à géométrie de révolution, c'est-à-dire une géométrie décrivant une structure fermée le plus souvent courbe. Dans l'exemple représenté en figure 6, le procédé de fabrication est modifié en utilisant un conteneur 4 comportant de part et d'autre de deux de ses faces opposées 42 des rainures 41 destinées à accueillir des inserts 3. Après compaction isostatique à chaud et usinage, la pièce mécanique 110 obtenue est celle représentée en figure 7 et comporte ainsi des inserts 3. Les inserts 3 sont positionnés de part et d'autre d'un plan médian Pl de la pièce mécanique 110. Ils sont positionnés dans des plans P2 et P3 formant un angle α non nul entre eux. La figure 8 montre, en perspective, une pièce mécanique 110 ainsi obtenue. Cette pièce mécanique 110 peut également comporter des évidements 15 destinés à en diminuer la masse.The invention applies to any type of mechanical part whose function is to transmit a traction force and / or compression mainly unidirectional and is therefore not limited only to connecting rods that are only an example of application. According to a variant of the invention, the mechanical part may be of more complex shape and comprise a plurality of inserts 3 each of which may be of geometry of revolution, that is to say a geometry describing a closed structure most often curved . In the example shown in FIG. 6, the manufacturing method is modified by using a container 4 comprising, on either side of two of its opposite faces 42, grooves 41 intended to receive inserts 3. After hot isostatic compaction and machining, the mechanical part 110 obtained is that represented in FIG. 7 and thus comprises inserts 3. The inserts 3 are positioned on either side of a median plane P1 of the mechanical part 110. They are positioned in P2 planes and P3 forming an angle α not zero between them. Figure 8 shows, in perspective, a mechanical part 110 thus obtained. This mechanical part 110 may also include recesses 15 intended to reduce the mass.
De telles pièces mécaniques 10 ou 110 conviennent parfaitement pour les applications aéronautiques, par exemple pour les atterrisseurs ou pour les turbomachines destinés à un aéronef. Such mechanical parts 10 or 110 are perfectly suitable for aeronautical applications, for example for undercarriages or for turbomachines intended for an aircraft.

Claims

REVENDICATIONS
1. Procédé de fabrication d'une pièce mécanique (10, 110) comportant au moins un insert (3) en matériau composite à matrice métallique au sein de laquelle s'étendent des fibres céramiques, l'insert (3) en matériau composite étant obtenu à partir d'une pluralité de fils enduits (32) comportant chacun une fibre céramique enrobée d'une gaine métallique, le procédé comprenant la fabrication d'au moins un insert (3) avec une étape de bobinage d'un faisceau ou d'une nappe liée de fils enduits (32) autour d'une pièce de révolution (2), caractérisé en ce que au moins une partie du bobinage s'effectue selon une direction rectiligne.1. A method of manufacturing a mechanical part (10, 110) comprising at least one insert (3) of metal matrix composite material within which ceramic fibers extend, the insert (3) of composite material being obtained from a plurality of coated yarns (32) each comprising a ceramic fiber coated with a metallic sheath, the method comprising the manufacture of at least one insert (3) with a step of winding a bundle or a ply bonded with coated threads (32) around a piece of revolution (2), characterized in that at least a part of the winding is carried out in a rectilinear direction.
2. Procédé de fabrication d'une pièce mécanique (10, 110) selon la revendication 1, caractérisé en ce que la pièce de révolution (2) comporte au moins une portion de bobinage rectiligne (24).2. A method of manufacturing a mechanical part (10, 110) according to claim 1, characterized in that the part of revolution (2) comprises at least one rectilinear winding portion (24).
3. Procédé de fabrication d'une pièce mécanique (10, 110) selon la revendication 1 ou 2, caractérisé en ce que la pièce de révolution (2) comporte deux portions de bobinage rectilignes (24).3. A method of manufacturing a mechanical part (10, 110) according to claim 1 or 2, characterized in that the part of revolution (2) comprises two rectilinear winding portions (24).
4. Procédé de fabrication d'une pièce mécanique (10, 110) selon la revendication 3, caractérisé en ce que les deux portions rectilignes (24) sont intercalées entre deux portions circulaires (25). 4. A method of manufacturing a mechanical part (10, 110) according to claim 3, characterized in that the two rectilinear portions (24) are interposed between two circular portions (25).
5. Procédé de fabrication d'une pièce mécanique (10, 110) selon la revendication 4, caractérisé en ce que les deux portions circulaires (25) ont des rayons différents.5. A method of manufacturing a mechanical part (10, 110) according to claim 4, characterized in that the two circular portions (25) have different radii.
6. Procédé de fabrication d'une pièce mécanique (10, 110) selon la revendication 3 ou 4, caractérisé en ce que les deux portions rectilignes (24) sont parallèles.6. A method of manufacturing a mechanical part (10, 110) according to claim 3 or 4, characterized in that the two rectilinear portions (24) are parallel.
7. Procédé de fabrication d'une pièce mécanique (10, 110) selon l'une des revendications précédentes, caractérisé en ce que au moins un insert (3) est inséré dans un conteneur (4) pour subir une compaction isostatique à chaud.7. A method of manufacturing a mechanical part (10, 110) according to one of the preceding claims, characterized in that at least one insert (3) is inserted into a container (4) to undergo hot isostatic compaction.
8. Procédé de fabrication d'une pièce mécanique (110) selon la revendication précédente, caractérisé en ce que deux inserts (3) sont insérés de part et d'autre de deux faces opposées (42) du conteneur (4) pour subir une compaction isostatique à chaud.8. A method of manufacturing a mechanical part (110) according to the preceding claim, characterized in that two inserts (3) are inserted on either side of two opposite faces (42) of the container (4) to undergo a hot isostatic compaction.
9. Procédé de fabrication d'une pièce mécanique (110) selon la revendication précédente, caractérisé en ce que les inserts (3) sont positionnés dans des plans (P2, P3) formant un angle (α) non nul.9. A method of manufacturing a mechanical part (110) according to the preceding claim, characterized in that the inserts (3) are positioned in planes (P2, P3) forming a non-zero angle (α).
10. Pièce mécanique (10, 110) comportant au moins un insert (3) en matériau composite à matrice métallique, au sein de laquelle s'étendent des fibres céramiques, l'insert (3) en matériau composite étant obtenu à partir d'une pluralité de fils (32) enduits comportant chacun une fibre céramique enrobée d'une gaine métallique, caractérisée en ce que l'insert (3) est à géométrie de révolution et comporte les fils (32) en partie orientés selon au moins une direction rectiligne. 10. Mechanical part (10, 110) comprising at least one insert (3) of metal matrix composite material, within which ceramic fibers extend, the composite material insert (3) being obtained from a plurality of coated wires (32) each comprising a ceramic fiber coated with a metallic sheath, characterized in that the insert (3) is of a geometry of revolution and comprises the wires (32) partially oriented in at least one direction straight.
11. Pièce mécanique (110) selon la revendication 10, caractérisée en ce qu'elle comporte au moins deux inserts (3) positionnés de part et d'autre d'un plan médian (Pl) de la pièce mécanique (10).11. Mechanical part (110) according to claim 10, characterized in that it comprises at least two inserts (3) positioned on either side of a median plane (Pl) of the mechanical part (10).
12. Pièce mécanique (110) selon la revendication 11, caractérisée en ce que les deux inserts (3) sont positionnés dans des plans (P2, P3) formant un angle (α) entre eux.12. Mechanical part (110) according to claim 11, characterized in that the two inserts (3) are positioned in planes (P2, P3) forming an angle (α) between them.
13. Pièce mécanique (10, 110) selon l'une des revendications 10 à 12 caractérisé en ce qu'elle constitue une bielle.13. Mechanical part (10, 110) according to one of claims 10 to 12 characterized in that it constitutes a connecting rod.
14. Atterrisseur comportant au moins une pièce mécanique (10, 110) selon l'une des revendications 10 à 13.14. Landing gear comprising at least one mechanical part (10, 110) according to one of claims 10 to 13.
15. Turbomachine comportant au moins une pièce mécanique (10, 110) selon l'une des revendications 10 à 13.15. Turbomachine comprising at least one mechanical part (10, 110) according to one of claims 10 to 13.
16. Aéronef comportant une pièce mécanique selon l'une des revendications 10 à 13, un atterrisseur selon la revendication 14 ou une turbomachine selon la revendication 15.16. Aircraft having a mechanical part according to one of claims 10 to 13, an undercarriage according to claim 14 or a turbomachine according to claim 15.
17. Dispositif de bobinage (20) comportant une pièce de révolution (2) d'axe (Z) autour de laquelle peuvent s'enrouler des fils (32) caractérisé en ce que la pièce de révolution (2) comporte au moins une portion de bobinage rectiligne (24) perpendiculaire à l'axe de bobinage (Z).17. A winding device (20) comprising a part of revolution (2) of axis (Z) around which wires (32) can be wound, characterized in that the part of revolution (2) comprises at least one portion straight winding (24) perpendicular to the winding axis (Z).
18. Dispositif de bobinage (20) selon la revendication 17 caractérisé en ce que la pièce de révolution (2) comporte deux portions de bobinage rectilignes (24) intercalées entre deux portions circulaires (25).18. Winding device (20) according to claim 17 characterized in that the piece of revolution (2) comprises two portions of rectilinear winding (24) interposed between two circular portions (25).
19. Dispositif de bobinage (20) selon la revendication 17 ou 18 caractérisé en ce qu'il comporte deux flasques (21, 22) de forme oblongue, la pièce de révolution (2) étant prise en sandwich entre les deux flasques (21, 22).19. Winding device (20) according to claim 17 or 18 characterized in that it comprises two flanges (21, 22) of oblong shape, the piece of revolution (2) being sandwiched between the two flanges (21, 22).
20. Dispositif de bobinage (20) selon la revendication 19 caractérisé en ce que chaque flasque (21, 22) comporte des encoches (23) sur sa périphérie (27).20. A winding device (20) according to claim 19 characterized in that each flange (21, 22) has notches (23) on its periphery (27).
21. Dispositif de bobinage (20) selon l'une des revendications 17 à 20 caractérisé en ce que la pièce de révolution (2) comporte un intérieur creux (29), la profondeur des encoches (23) permettant d'accéder à l'intérieur creux (29) de la pièce de révolution (2). 21. Winding device (20) according to one of claims 17 to 20 characterized in that the piece of revolution (2) has a hollow interior (29), the depth of the notches (23) for accessing the hollow interior (29) of the piece of revolution (2).
EP08830741A 2007-07-26 2008-07-10 Mechanical part including an insert made of a composite material Active EP2191029B1 (en)

Applications Claiming Priority (2)

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FR0705453A FR2919283B1 (en) 2007-07-26 2007-07-26 MECHANICAL PIECE COMPRISING AN INSERT IN COMPOSITE MATERIAL.
PCT/FR2008/001014 WO2009034263A2 (en) 2007-07-26 2008-07-10 Mechanical part including an insert made of a composite material

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CN (1) CN101999010B (en)
BR (1) BRPI0814322A2 (en)
CA (1) CA2694370C (en)
FR (1) FR2919283B1 (en)
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FR2911524B1 (en) * 2007-01-23 2009-08-21 Snecma Sa TUBULAR PIECE COMPRISING A METALLIC MATRIX COMPOSITE INSERT.
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US8920935B2 (en) 2014-12-30
FR2919283A1 (en) 2009-01-30
WO2009034263A2 (en) 2009-03-19
IL203453A (en) 2014-08-31
JP2010534763A (en) 2010-11-11
WO2009034263A3 (en) 2009-10-22
CN101999010B (en) 2014-07-30
RU2490355C2 (en) 2013-08-20
CA2694370A1 (en) 2009-03-19
CN101999010A (en) 2011-03-30
US20100291339A1 (en) 2010-11-18
BRPI0814322A2 (en) 2015-01-20
CA2694370C (en) 2016-10-18
EP2191029B1 (en) 2013-01-23
FR2919283B1 (en) 2010-09-17
RU2010107049A (en) 2011-09-10

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