EP2680991A1 - Method for manufacturing an integral rotationally symmetrical metal part including a reinforcement consisting of ceramic fibbers - Google Patents

Method for manufacturing an integral rotationally symmetrical metal part including a reinforcement consisting of ceramic fibbers

Info

Publication number
EP2680991A1
EP2680991A1 EP12712320.6A EP12712320A EP2680991A1 EP 2680991 A1 EP2680991 A1 EP 2680991A1 EP 12712320 A EP12712320 A EP 12712320A EP 2680991 A1 EP2680991 A1 EP 2680991A1
Authority
EP
European Patent Office
Prior art keywords
blank
wire
fibers
mandrel
composite
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
EP12712320.6A
Other languages
German (de)
French (fr)
Other versions
EP2680991B1 (en
Inventor
Bruno Jacques Gérard DAMBRINE
Thierry Godon
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
Original Assignee
SNECMA Services 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 SNECMA Services SA, SNECMA SAS filed Critical SNECMA Services SA
Publication of EP2680991A1 publication Critical patent/EP2680991A1/en
Application granted granted Critical
Publication of EP2680991B1 publication Critical patent/EP2680991B1/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
    • 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
    • B22F3/00—Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sintering; Apparatus specially adapted therefor ; Presses and furnaces
    • B22F3/12—Both compacting and sintering
    • B22F3/14—Both compacting and sintering simultaneously
    • B22F3/15—Hot isostatic pressing
    • 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
    • C22C47/02—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
    • 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
    • Y10T29/49799—Providing transitory integral holding or handling portion
    • 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
    • Y10T29/49801—Shaping fiber or fibered material

Definitions

  • the present invention relates to a method for manufacturing a one-piece hollow metal piece of revolution, such as a torque transmission shaft, from a composite fibrous structure in the form of fibers, fiber sheets, fiber fabric and analogous, said fibers being coated with metal.
  • such a fibrous structure of composite material comprises a metal alloy matrix, for example of titanium alloy Ti, within which fibers extend, for example ceramic fibers of SiC silicon carbide.
  • a metal alloy matrix for example of titanium alloy Ti
  • fibers for example ceramic fibers of SiC silicon carbide.
  • Such fibers have a tensile strength much higher than that of titanium (typically 4000 MPa against 1000 MPa). It is therefore the fibers that take up the efforts, the alloy matrix metal providing a binder function for the part, as well as protection and insulation of the fibers, which must not come into contact with each other.
  • the ceramic fibers are resistant to erosion, but must necessarily be coated with metal.
  • composite materials can be used to produce annular turbine engine revolution parts or other industrial applications, such as rings, shafts, cylinder bodies, housings, spacers, reinforcements of monolithic parts such as blades, etc. ....
  • a known method for manufacturing hollow revolution parts with a monobloc structure consists in superimposing, around a cylindrical mandrel, fibrous structures (fibers, sheet of fibers or fiber fabric) in succession and then arranging the composite fibrous structures wound in a tool specific reception to compact and bind them by diffusion welding and finally obtain the revolution piece of composite material.
  • a method of manufacturing a piece of revolution by layering a sheet of fibers is described in the patent application EP1726678, in the name of the applicant.
  • Another known method is to wind ceramic fibers, but not coated around a mandrel by interposing metal son between the ceramic fibers. This process has been patented by the applicant FR 2.713.212
  • the applicant has set as an objective the development of a method for producing parts of revolution whose diameter may be very small, of the order of the diameter of the son used, but also be high being limited only by the size of the tooling and whose length depends on the only means used.
  • the subject of the invention is a method for manufacturing a part of one-piece revolution comprising producing a blank of the part around a cylindrical mandrel, the blank comprising at least one fibrous structure formed of composite fibers. metal-coated ceramics, then the welding treatment diffusion of the blank by hot isostatic compaction, and optionally machining the blank thus treated to obtain the workpiece, and the method is characterized in that the blank comprises at least a first layer of wire between the mandrel and said composite fibrous structure and at least a second layer of wire around said composite fibrous structure so as to coat it.
  • the method of the invention thus makes it possible to obtain a part having a sufficient stiffness without increasing its density and in the case of a torque transmission shaft such as the one reported above to increase the Young's modulus ratio on density, to ascend the eigenvalues of vibratory frequencies of the part and thus possibly to realize a shaft without intermediate bearing.
  • the mandrel is in two frustoconical parts separable from one another and forming a diabolo. In this way the roughing after compaction can be demolded without difficulty.
  • the first layer of metal wire is preferably shaped so as to have after compaction of the blank a cylindrical portion forming after machining the inner wall of the workpiece.
  • the wire layer may be formed by winding one or more wires around the mandrel.
  • the wire is for example obtained by drawing and is of the same nature as that which coats the composite fibers; in this way, after passing through the tooling, a homogeneous metal layer having an appropriate thickness on the fibers of the reinforcing structures is obtained.
  • the method of the invention also has the advantage of being able to perform cold, at room temperature, the superposed layers of wire and the fibrous structure.
  • the fibers coated with the fibrous structure are arranged in the same direction, preferably the axial direction of the part.
  • the composite fibrous structure is formed by winding plies or fabric of metal composite fibers.
  • the layers are at least partly bonded together by gluing, welding or by means of foils.
  • transverse radial ribs are formed in particular at the longitudinal ends of the piece, by winding wire. These transverse ribs can be machined and form gear gears for example. According to an alternative embodiment, is incorporated in said transverse ribs a ceramic fiber reinforcement.
  • the metal son used may have different diameters, and multilayered superimposed layers of these son may be provided alternately with the superimposed fibrous structures whose number may be greater than two.
  • Figure 1 shows schematically an example of a cylindrical piece that can be obtained with the method of the invention
  • Figure 2 shows the step of forming the first wire layer of the part blank according to one embodiment of the invention
  • Figure 3 shows the step of forming the fibrous structure layer of coated ceramic fibers
  • Figure 4 shows the step of forming the second layer of wire
  • FIG. 5 schematically shows the step of hot isostatic compaction of the blank
  • FIG. 6 and 7 show an alternative embodiment of the method of the invention.
  • FIG. 8 shows another alternative embodiment of the method of the invention for producing a part having a transverse radial rib.
  • the object of the method is to manufacture a piece of annular, one-piece revolution 1 only from elongated elements in the form of threads, fibers or the like, as will be seen hereinafter.
  • the invention more particularly relates to the formation of parts of great length with respect to their diameter.
  • FIG. 1 shows, in longitudinal section, the cylindrical hollow part of metal wall 2, of axis XX, and incorporating reinforcing fibers 3, made of ceramic material, into one or more layers, preferably all the fibers of the same layer having the same orientation as axial.
  • a cylindrical mandrel 10 with a longitudinal axis X around which the part is formed is used.
  • the mandrel is preferably in the form of a diabolo, in two frustoconical parts 10a and 10b which are fixed to each other by their top, removably so as to be able to separate them from one another.
  • the half-angle alpha at the top of the two cones, exaggerated in the figure, is of the order of 6 to 7 °.
  • the diabolo shape is intended to allow the release of the piece after compaction son and fibers as will be seen later.
  • a wire 4 is wound around the cylinder so as to form a first layer of wire.
  • the wire 4 is made in particular of a titanium alloy of TiA6V or ⁇ 6242 type ensuring thermomechanical resistance and lightness, and it is obtained in particular by wire drawing so as to be available in the form of a reel or reel from which the thread is drawn.
  • Means other than wire drawing are conceivable. Dimensionally, its diameter depends on the part to be obtained and may be of the order of a few tenths of a millimeter to several millimeters.
  • the wire drawn wire 4 is derived from a not shown spool and is driven, substantially perpendicular to the axis X, around the cylindrical mandrel 10 over a predetermined extent corresponding to the length that it is desired to obtain, after manufacture, for the part of revolution 1, thus forming several contiguous turns, and on one or more superimposed thicknesses so as to form the first layer of wire 6. It could also be used several metal wires or one or more metal wires with a different diameter of the wire 4. Due to the taper of the cylinder 10, the first layer has a triangular longitudinal section. One of the functions of the layer 6 is to fill the demoulding portion to the inside diameter of the finished part, after its machining.
  • the method continues with a second step shown in FIG. 3 and consisting in arranging a composite fibrous structure 7 around the first layer 6 of wire 4.
  • the composite fibrous structure 7 may be in the form of a fabric of coated ceramic fibers 9 associated in parallel with each other and made of ceramic (SiC) or of a similar material coated with metal.
  • the latter and the metal of the drawn wire are preferably identical in nature (in TiA6V or in 6242 for example) to optimize the subsequent step of the process relating to the hot isostatic compaction operation.
  • the fabric of the fibrous structure 7 is wound around the winding of the first layer 6 of wire 4 so that the fibers 9 are all arranged in the same orientation, for example and preferably parallel to the longitudinal axis X of the mandrel 10.
  • a single layer of the fabric is formed around the first layer of yarn 4.
  • a multi-layer winding could be provided from the same fabric, or even from one or more other distinct, coiled-up fabrics.
  • the fabrics may be of different species, of different diameters of coated yarn.
  • the length of the composite fibrous structure 7 is less than or equal to the length of the outer surface of the first layer 6 of wire. It should be noted that the outer surface of the latter may be curved to take account of the compaction of the layer 6 by the hot isostatic compression treatment. After this treatment this surface should preferably be straight cylindrical.
  • a wire for example drawn, which comes from a not shown spool and which is brought substantially orthogonally. to the longitudinal axis X of the rotating cylindrical mandrel 10.
  • the wire 5 forms a second layer 8 of contiguous turns around the fabric of the fibrous structure 7.
  • the second layer 8 may comprise a winding of several thicknesses.
  • the first layer instead of winding a wire, one can set up a plurality of metal son or a sheet of metal son. When using multiple wires these can be of the same diameter or different diameters.
  • the wires may also be pre-assembled metal wires in the form of cables.
  • Foil layers can also be rolled up with the second layer.
  • the metal wire (s) 5 are wound so as to completely coat the composite fibers of the underlying fibrous structure 7.
  • the second layer 8 covers the part of the first layer 6 of wire which is not itself covered by the fibrous structure 7.
  • a blank E is obtained from the part of revolution to be produced, which consists solely of metal wires 4 and 5 and of a composite fiber structure 7 in individual, sheet, fabric or other form.
  • the blank E is subjected to hot isostatic compression treatment (CIC) in an isothermal press or bag in an autoclave (the choice depending in particular on the number of parts to be produced).
  • CIC hot isostatic compression treatment
  • a lid system is put in place on the blank of complementary shape.
  • the lid in several parts, forms a cylindrical envelope around the blank.
  • the metal of the metal wires and the coating of the fibers of the structures becomes pasty and flue eliminating all the spaces voids between the turns and layers, and then their diffusion densifying welding in the end the piece.
  • the assembly is placed in a deformable pouch of mild steel which is then introduced into an autoclave.
  • This autoclave is brought to an isostatic pressure of 1000 bar and a temperature of 940 ° C (for TiA6V), so that the whole of the bag is deformed by retracting by the evacuation of the air and is applied against the mandrel and the cover which, in turn, compress under a uniform pressure the windings of wire and fiber until the creep of the metal constituting them with diffusion bonding bonding.
  • several pockets can thus be introduced into the autoclave to simultaneously produce the parts, reducing manufacturing costs.
  • the blank is machined to obtain the piece of composite monobloc revolution 1, shown in Figure 1, which is made of metal with the core fibers forming reinforcement inserts.
  • the tooling formed by the cylindrical mandrel 10 and the cover system is preferably made of a material that allows its use again for the manufacture of another part. This is for example a superalloy that withstands the temperature and pressure of the treatment while maintaining its integrity.
  • the coated composite fibers may be, in addition to SiC / Ti as described above, SiC / Al, SiC / SiC, SiC / B, etc.
  • the minimum radius of the mandrel is a function of the diameter of the wire and must be greater than the latter.
  • the length of the piece it can reach several meters if necessary.
  • the flanges 13a and 14b are attached to the mandrel, on the free ends side of the half mandrels 10'a and 10'b, so as to complete the support of the second layer 8 'of wire when it has a diameter greater than that of the mandrel 10'a, 10'b.
  • the thickness of the different layers applied takes into account their proliferation, in view of the result that is desired after CIC treatment.
  • the cover system 12 'as shown in FIG. 7 is adapted to the external geometry of the blank.
  • the method of the invention makes it possible to manufacture dumbbell-shaped parts, that is to say with transverse radial ribs. It is sufficient to obtain them to adapt the geometry of the second layer so as to form these ribs. The thickness of this second layer is increased for this purpose to the desired location.
  • the second layer 8 "of wire is formed by winding wire so as to have a portion forming a transverse rib 8" a.
  • this rib after CIC treatment forms a transverse radial rib on the workpiece.
  • the function of this rib may be a terminal fastening flange or a pinion after machining radial teeth.
  • reinforcing fibers 8 "b of length adapted to the width of the rib after CIC If the reinforcing fibers are oriented transversely to the axis of the piece, then they may be wound up as metal wires are, if the chosen orientation of the reinforcing fibers is to be axial, then they will be placed in the form of webs or fabric such as the reinforcing layer 7.

Abstract

The invention relates to a method for manufacturing an integral rotationally symmetrical part, which includes producing a blank of the part around a cylindrical mandrel, the blank including at least one fibrous structure made of composite ceramic fibres coated with metal, followed by the diffusion-welding treatment of the blank by hot isostatic pressing, and optionally machining the thus-treated blank in order to obtain the part. According to the invention, the method is characterised in that the blank includes at least a first metal-wire layer (6) between the mandrel (10) and said composite fibrous structure (7), and at least a second metal-wire layer (8) arranged around said composite fibrous structure so as to cover the latter.

Description

PROCEDE POUR FABRIQUER UNE PIECE METALLIQUE DE REVOLUTION MONOBLOC INCORPORANT UN RENFORT DE FIBRES CERAMIQUES  PROCESS FOR MANUFACTURING A MONOBLOC REVOLUTION METAL PIECE INCORPORATING A CERAMIC FIBER REINFORCEMENT
Domaine technique de l'invention Technical field of the invention
La présente invention concerne un procédé de fabrication d'une pièce métallique creuse de révolution, monobloc, telle qu'un arbre de transmission de couple, à partir d'une structure fibreuse composite sous forme de fibres, nappe de fibres, tissu de fibres et analogues, lesdites fibres étant enduites de métal. The present invention relates to a method for manufacturing a one-piece hollow metal piece of revolution, such as a torque transmission shaft, from a composite fibrous structure in the form of fibers, fiber sheets, fiber fabric and analogous, said fibers being coated with metal.
Art antérieur Prior art
Dans le but de répondre aux contraintes permanentes de réduction de consommation spécifique, on cherche à remplacer certaines pièces forgées dans une turbomachine par des pièces plus légères et de structure plus simple. C'est le cas de l'arbre de transmission de puissance entre l'arbre principal d'un turboréacteur et son boîtier à engrenage d'entraînement des machines accessoires du moteur, désigné par l'acronyme AGB dans le domaine. Il s'agit d'un arbre fin relativement long, de l'ordre du mètre, pour les moteurs de grand diamètre et pour lequel il est nécessaire de prévoir en plus des extrémités un palier intermédiaire assurant son soutien et le passage des modes propres de fréquences vibratoires In order to meet the permanent constraints of reducing specific consumption, we seek to replace some forged parts in a turbomachine with lighter parts and simpler structure. This is the case of the power transmission shaft between the main shaft of a turbojet engine and its accessory gearbox motor gearbox, designated by the acronym AGB in the field. It is a relatively long shaft, of the order of one meter, for large-diameter engines and for which it is necessary to provide in addition to the ends an intermediate bearing ensuring its support and the passage of clean modes of vibratory frequencies
Ces dernières années ont mis en évidence dans de nombreux domaines techniques, notamment aéronautique, spatial, militaire, automobile, etc...., l'importance des matériaux composites dans la réalisation partielle ou totale de pièces en raison de l'optimisation de la résistance de celles-ci, pour une masse et un encombrement minimaux. Pour rappel, une telle structure fibreuse en 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 bien supérieure à celle du titane (typiquement, 4000 MPa contre 1000 MPa). Ce sont donc les fibres qui reprennent les efforts, la matrice d'alliage métallique assurant une fonction de liant pour 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 revêtues de métal. In recent years have highlighted in many technical fields, including aeronautics, space, military, automotive, etc ...., the importance of composite materials in the partial or total realization of parts due to the optimization of the resistance of these, for a minimum mass and size. As a reminder, such a fibrous structure of composite material comprises a metal alloy matrix, for example of titanium alloy Ti, within which fibers extend, for example ceramic fibers of SiC silicon carbide. Such fibers have a tensile strength much higher than that of titanium (typically 4000 MPa against 1000 MPa). It is therefore the fibers that take up the efforts, the alloy matrix metal providing a binder function for the part, as well as protection and insulation of the fibers, which must not come into contact with each other. In addition, the ceramic fibers are resistant to erosion, but must necessarily be coated with metal.
Ces matériaux composites peuvent être utilisés pour réaliser des pièces de révolution annulaires de turbomachine pour aéronef ou autre application industrielle, comme des bagues, des arbres, des corps de vérin, des carters, des entretoises, des renforts de pièces monolithiques telles des aubes, etc....  These composite materials can be used to produce annular turbine engine revolution parts or other industrial applications, such as rings, shafts, cylinder bodies, housings, spacers, reinforcements of monolithic parts such as blades, etc. ....
Un procédé connu pour fabriquer des pièces de révolution creuses à structure monobloc consiste à superposer, autour d'un mandrin cylindrique, des structures fibreuses (fibres, nappe de fibres ou tissu de fibres) successives puis à disposer les structures fibreuses composites enroulées dans un outillage de réception spécifique pour compacter et lier celles-ci par soudage diffusion et obtenir au final la pièce de révolution en matériau composite. Un procédé de fabrication d'une pièce de révolution par drapage d'une nappe de fibres est décrit dans la demande de brevet EP1726 678, au nom de la demanderesse.  A known method for manufacturing hollow revolution parts with a monobloc structure consists in superimposing, around a cylindrical mandrel, fibrous structures (fibers, sheet of fibers or fiber fabric) in succession and then arranging the composite fibrous structures wound in a tool specific reception to compact and bind them by diffusion welding and finally obtain the revolution piece of composite material. A method of manufacturing a piece of revolution by layering a sheet of fibers is described in the patent application EP1726678, in the name of the applicant.
Un autre procédé connu consiste à enrouler des fibres céramiques, mais non enduites, autour d'un mandrin en interposant des fils métalliques entre les fibres céramiques. Ce procédé a été breveté par la demanderesse FR 2.713.212  Another known method is to wind ceramic fibers, but not coated around a mandrel by interposing metal son between the ceramic fibers. This process has been patented by the applicant FR 2.713.212
Présentation de l'invention Presentation of the invention
La demanderesse s'est fixé comme objectif la mise au point d'un procédé permettant de réaliser des pièces de révolution dont le diamètre peut être très faible, de l'ordre du diamètre des fils utilisés, mais aussi être élevé en étant limité seulement par l'encombrement de l'outillage et dont la longueur dépend des seuls moyens utilisés. The applicant has set as an objective the development of a method for producing parts of revolution whose diameter may be very small, of the order of the diameter of the son used, but also be high being limited only by the size of the tooling and whose length depends on the only means used.
C'est ainsi que l'invention a pour objet un procédé pour fabriquer une pièce de révolution monobloc comprenant la réalisation d'une ébauche de la pièce autour d'un mandrin cylindrique, l'ébauche comprenant au moins une structure fibreuse formée de fibres composites céramiques enduites de métal, puis le traitement de soudage diffusion de l'ébauche par compaction isostatique à chaud, et l'usinage éventuel de l'ébauche ainsi traitée pour obtenir la pièce, et le procédé est caractérisé par le fait que l'ébauche comprend au moins une première couche de fil métallique entre le mandrin et ladite structure fibreuse composite et au moins une deuxième couche de fil métallique autour de ladite structure fibreuse composite de manière à enrober celle-ci. Thus, the subject of the invention is a method for manufacturing a part of one-piece revolution comprising producing a blank of the part around a cylindrical mandrel, the blank comprising at least one fibrous structure formed of composite fibers. metal-coated ceramics, then the welding treatment diffusion of the blank by hot isostatic compaction, and optionally machining the blank thus treated to obtain the workpiece, and the method is characterized in that the blank comprises at least a first layer of wire between the mandrel and said composite fibrous structure and at least a second layer of wire around said composite fibrous structure so as to coat it.
Le procédé de l'invention permet ainsi d'obtenir une pièce présentant une raideur suffisante sans augmenter sa masse volumique et dans le cas d'un arbre de transmission de couple tel que celui rapporté plus haut d'augmenter le rapport module d'Young sur masse volumique, de remonter les modes propres de fréquences vibratoires de la pièce et donc éventuellement de réaliser un arbre sans palier intermédiaire. The method of the invention thus makes it possible to obtain a part having a sufficient stiffness without increasing its density and in the case of a torque transmission shaft such as the one reported above to increase the Young's modulus ratio on density, to ascend the eigenvalues of vibratory frequencies of the part and thus possibly to realize a shaft without intermediate bearing.
Avantageusement le mandrin est en deux parties tronconiques séparables l'une de l'autre et formant un diabolo. De cette façon l'ébauche après compaction peut être démoulée sans difficulté. La première couche de fil métallique est de préférence conformée de manière à présenter après compaction de l'ébauche une portion cylindrique formant après usinage la paroi intérieure de la pièce. La couche de fil métallique peut être formée par enroulement d'un ou plusieurs fils métalliques autour du mandrin.  Advantageously the mandrel is in two frustoconical parts separable from one another and forming a diabolo. In this way the roughing after compaction can be demolded without difficulty. The first layer of metal wire is preferably shaped so as to have after compaction of the blank a cylindrical portion forming after machining the inner wall of the workpiece. The wire layer may be formed by winding one or more wires around the mandrel.
Le fil métallique est par exemple obtenu par tréfilage et est de même nature que celui qui enduit les fibres composites ; de la sorte on obtient, après passage dans l'outillage, une couche métallique homogène ayant une épaisseur appropriée sur les fibres des structures de renfort.  The wire is for example obtained by drawing and is of the same nature as that which coats the composite fibers; in this way, after passing through the tooling, a homogeneous metal layer having an appropriate thickness on the fibers of the reinforcing structures is obtained.
Le procédé de l'invention présente aussi l'avantage de pouvoir effectuer à froid, à la température ambiante, les couches superposées de fil métallique et de la structure fibreuse.  The method of the invention also has the advantage of being able to perform cold, at room temperature, the superposed layers of wire and the fibrous structure.
Conformément à une autre caractéristique du procédé on dispose les fibres enduites de la structure fibreuse selon une même direction, de préférence la direction axiale de la pièce.  According to another characteristic of the process, the fibers coated with the fibrous structure are arranged in the same direction, preferably the axial direction of the part.
Plus particulièrement, la structure fibreuse composite est formée par enroulement de nappes ou de tissu de fibres composites métalliques. Conformément à une autre caractéristique, on lie au moins en partie les couches entre elles par collage, soudage ou au moyen de clinquants. More particularly, the composite fibrous structure is formed by winding plies or fabric of metal composite fibers. According to another characteristic, the layers are at least partly bonded together by gluing, welding or by means of foils.
Conformément à un mode de réalisation particulier, on forme notamment aux extrémités longitudinales de la pièce, par enroulement de fil métallique, des nervures radiales transversales. Ces nervures transversales peuvent être usinées et former des pignons d'engrenage par exemple. Selon une variante de réalisation, on incorpore dans lesdites nervures transversales un renfort de fibres céramiques.  According to a particular embodiment, transverse radial ribs are formed in particular at the longitudinal ends of the piece, by winding wire. These transverse ribs can be machined and form gear gears for example. According to an alternative embodiment, is incorporated in said transverse ribs a ceramic fiber reinforcement.
Par ailleurs, les fils métalliques utilisés peuvent avoir des diamètres différents, et des couches à plusieurs enroulements superposés de ces fils peuvent être prévues en alternance avec les structures fibreuses superposées dont le nombre peut être supérieur à deux.  Furthermore, the metal son used may have different diameters, and multilayered superimposed layers of these son may be provided alternately with the superimposed fibrous structures whose number may be greater than two.
Brève description des dessins Brief description of the drawings
Les figures du dessin annexé feront bien comprendre comment l'invention peut être réalisée. Sur ces figures, des références identiques désignent des éléments semblables. The figures of the appended drawing will make it clear how the invention can be realized. In these figures, identical references designate similar elements.
La figure 1 montre schématiquement un exemple de pièce cylindrique que l'on peut obtenir avec le procédé de l'invention ; Figure 1 shows schematically an example of a cylindrical piece that can be obtained with the method of the invention;
La figure 2 montre l'étape de formation de la première couche de fil métallique de l'ébauche de pièce selon un mode de réalisation de l'invention ;  Figure 2 shows the step of forming the first wire layer of the part blank according to one embodiment of the invention;
La figure 3 montre l'étape de formation de la couche de structure fibreuse en fibres céramiques enduites ;  Figure 3 shows the step of forming the fibrous structure layer of coated ceramic fibers;
La figure 4 montre l'étape de formation de la deuxième couche de fil métallique ;  Figure 4 shows the step of forming the second layer of wire;
La figure 5 montre schématiquement l'étape de compaction isostatique à chaud de l'ébauche  FIG. 5 schematically shows the step of hot isostatic compaction of the blank
Les figures 6 et 7 montrent une variante de mise en œuvre du procédé de l'invention. La figure 8 montre une autre variante de mise en œuvre du procédé de l'invention pour la réalisation d'une pièce présentant une nervure radiale transversale. Figures 6 and 7 show an alternative embodiment of the method of the invention. FIG. 8 shows another alternative embodiment of the method of the invention for producing a part having a transverse radial rib.
Description détaillée de l'invention. Detailed description of the invention.
Le procédé a pour but la fabrication d'une pièce de révolution monobloc, annulaire 1 , uniquement à partir d'éléments allongés se présentant sous la forme de fils, fibres ou analogues, comme on le verra ci-après. L'invention vise plus particulièrement la formation de pièces de grande longueur par rapport à leur diamètre. La figure 1 montre en coupe longitudinale la pièce creuse cylindrique de paroi 2 métallique, d'axe XX, et incorporant des fibres de renfort 3, en matériau céramique, en une ou plusieurs couches, de préférence toutes les fibres d'une même couche ayant une même orientation telle qu'axiale. The object of the method is to manufacture a piece of annular, one-piece revolution 1 only from elongated elements in the form of threads, fibers or the like, as will be seen hereinafter. The invention more particularly relates to the formation of parts of great length with respect to their diameter. FIG. 1 shows, in longitudinal section, the cylindrical hollow part of metal wall 2, of axis XX, and incorporating reinforcing fibers 3, made of ceramic material, into one or more layers, preferably all the fibers of the same layer having the same orientation as axial.
Pour obtenir ce type de pièce, on utilise un mandrin cylindrique 10 d'axe longitudinal X autour duquel on forme la pièce. Le mandrin est de préférence en forme de diabolo, en deux parties tronconiques 10a et 10b qui sont fixées l'une à l'autre par leur sommet, de manière amovible de façon à pouvoir les séparer l'une de l'autre. Le demi-angle alpha au sommet des deux cônes, exagéré sur la figure, est de l'ordre de 6 à 7°. La forme diabolo a pour but de permettre le démoulage de la pièce après compaction des fils et fibres comme on le verra par la suite. On enroule, dans une première étape, un fil métallique 4 autour du cylindre de manière à former une première couche de fil métallique. Compte tenu de l'application de la pièce 1 au domaine aéronautique, le fil métallique 4 est réalisé notamment en un alliage de titane de type TiA6V ou ΤΊ6242 assurant résistance thermomécanique et légèreté, et il est obtenu notamment par tréfilage de manière à pouvoir être disponible sous forme de bobine ou de dévidoir duquel est tiré le fil.  To obtain this type of part, a cylindrical mandrel 10 with a longitudinal axis X around which the part is formed is used. The mandrel is preferably in the form of a diabolo, in two frustoconical parts 10a and 10b which are fixed to each other by their top, removably so as to be able to separate them from one another. The half-angle alpha at the top of the two cones, exaggerated in the figure, is of the order of 6 to 7 °. The diabolo shape is intended to allow the release of the piece after compaction son and fibers as will be seen later. In a first step, a wire 4 is wound around the cylinder so as to form a first layer of wire. Taking into account the application of the part 1 to the aeronautical field, the wire 4 is made in particular of a titanium alloy of TiA6V or ΤΊ6242 type ensuring thermomechanical resistance and lightness, and it is obtained in particular by wire drawing so as to be available in the form of a reel or reel from which the thread is drawn.
Des moyens autres que le tréfilage sont envisageables. Dimensionnellement, son diamètre dépend de la pièce à obtenir et peut-être de l'ordre de quelques dixièmes de millimètre à plusieurs millimètres. Means other than wire drawing are conceivable. Dimensionally, its diameter depends on the part to be obtained and may be of the order of a few tenths of a millimeter to several millimeters.
Dans l'exemple illustré sur la figure 2, le fil tréfilé métallique 4 est issu d'une bobine non représentée et est entraîné, de façon sensiblement perpendiculaire à l'axe X, autour du mandrin cylindrique 10 sur une étendue prédéterminée correspondant à la longueur que l'on souhaite obtenir, après fabrication, pour la pièce de révolution 1 , en formant ainsi plusieurs spires jointives, et sur une ou plusieurs épaisseurs superposées de manière à former la première couche de fil métallique 6. On pourrait également utiliser plusieurs fils métalliques ou un ou plusieurs fils métalliques avec un diamètre différent du fil métallique 4. En raison de la conicité du cylindre 10, la première couche a une section longitudinale triangulaire. Une des fonctions de la couche 6 est de combler la partie de démoulage jusqu'au diamètre intérieur de la pièce finie, après son usinage.  In the example illustrated in FIG. 2, the wire drawn wire 4 is derived from a not shown spool and is driven, substantially perpendicular to the axis X, around the cylindrical mandrel 10 over a predetermined extent corresponding to the length that it is desired to obtain, after manufacture, for the part of revolution 1, thus forming several contiguous turns, and on one or more superimposed thicknesses so as to form the first layer of wire 6. It could also be used several metal wires or one or more metal wires with a different diameter of the wire 4. Due to the taper of the cylinder 10, the first layer has a triangular longitudinal section. One of the functions of the layer 6 is to fill the demoulding portion to the inside diameter of the finished part, after its machining.
Le procédé se poursuit par une deuxième étape montrée sur la figure 3 et consistant à disposer une structure fibreuse composite 7 autour de la première couche 6 de fil métallique 4.  The method continues with a second step shown in FIG. 3 and consisting in arranging a composite fibrous structure 7 around the first layer 6 of wire 4.
La structure fibreuse composite 7 peut se présenter sous la forme d'un tissu de fibres céramiques enduites 9 associées parallèlement entre elles et réalisées en céramique (SiC) ou en un matériau analogue enduit de métal. Ce dernier et le métal du fil tréfilé sont de préférence de nature identique (en TiA6V ou en 6242 par exemple) pour optimiser l'étape ultérieure du procédé relative à l'opération de compaction isostatique à chaud. Le tissu de la structure fibreuse 7 est enroulé autour du bobinage de la première couche 6 de fil métallique 4 de façon que les fibres 9 soient disposées toutes selon la même orientation par exemple et de préférence parallèlement à l'axe longitudinal X du mandrin 10. The composite fibrous structure 7 may be in the form of a fabric of coated ceramic fibers 9 associated in parallel with each other and made of ceramic (SiC) or of a similar material coated with metal. The latter and the metal of the drawn wire are preferably identical in nature (in TiA6V or in 6242 for example) to optimize the subsequent step of the process relating to the hot isostatic compaction operation. The fabric of the fibrous structure 7 is wound around the winding of the first layer 6 of wire 4 so that the fibers 9 are all arranged in the same orientation, for example and preferably parallel to the longitudinal axis X of the mandrel 10.
Une seule couche du tissu est formée autour de la première couche de fil 4. Bien entendu, un enroulement de plusieurs couches pourrait être prévu à partir du même tissu, voire à partir d'un ou de plusieurs autres tissus distincts enroulés concentriquement. Les tissus peuvent être de différentes espèces, de différents diamètres de fil enduits. La longueur de la structure fibreuse composite 7 est inférieure ou égale à la longueur de la surface extérieure de la première couche 6 de fil métallique. Il est à noter que la surface extérieure de cette dernière peut être bombée pour tenir compte de la compaction de la couche 6 par le traitement de compression isostatique à chaud. Après ce traitement cette surface doit de préférence être cylindrique droit. A single layer of the fabric is formed around the first layer of yarn 4. Of course, a multi-layer winding could be provided from the same fabric, or even from one or more other distinct, coiled-up fabrics. The fabrics may be of different species, of different diameters of coated yarn. The length of the composite fibrous structure 7 is less than or equal to the length of the outer surface of the first layer 6 of wire. It should be noted that the outer surface of the latter may be curved to take account of the compaction of the layer 6 by the hot isostatic compression treatment. After this treatment this surface should preferably be straight cylindrical.
Selon une troisième étape du procédé illustrée en regard de la figure 4, on dispose, autour du tissu de la structure fibreuse composite 7, un fil métallique, par exemple tréfilé, 5 qui provient d'une bobine non représentée et qui est amené sensiblement orthogonalement à l'axe longitudinal X du mandrin cylindrique rotatif 10. Le fil métallique 5 forme une deuxième couche 8 de spires jointives autour du tissu de la structure fibreuse 7. La deuxième couche 8 peut comprendre un enroulement de plusieurs épaisseurs. Egalement, comme pour la première couche, au lieu de l'enroulement d'un fil métallique, on peut mettre en place une pluralité de fils métalliques ou une nappe de fils métalliques. Lorsqu'on utilise plusieurs fils ceux-ci peuvent être de même diamètre ou de diamètres différents. Les fils peuvent aussi être des fils métalliques pré-assemblés sous la forme de câbles. Des couches de clinquants peuvent aussi être enroulées avec la deuxième couche. Selon une caractéristique du procédé, le ou les fils métalliques 5 sont enroulés de manière à enrober intégralement les fibres composites de la structure fibreuse 7 sous jacente. Comme on le voit sur la figure 4, en particulier la deuxième couche 8 recouvre la partie de la première couche 6 de fil métallique qui n'est elle-même pas recouverte par la structure fibreuse 7.  According to a third step of the method illustrated with reference to FIG. 4, around the fabric of the composite fibrous structure 7 there is disposed a wire, for example drawn, which comes from a not shown spool and which is brought substantially orthogonally. to the longitudinal axis X of the rotating cylindrical mandrel 10. The wire 5 forms a second layer 8 of contiguous turns around the fabric of the fibrous structure 7. The second layer 8 may comprise a winding of several thicknesses. Also, as for the first layer, instead of winding a wire, one can set up a plurality of metal son or a sheet of metal son. When using multiple wires these can be of the same diameter or different diameters. The wires may also be pre-assembled metal wires in the form of cables. Foil layers can also be rolled up with the second layer. According to one characteristic of the process, the metal wire (s) 5 are wound so as to completely coat the composite fibers of the underlying fibrous structure 7. As seen in FIG. 4, in particular the second layer 8 covers the part of the first layer 6 of wire which is not itself covered by the fibrous structure 7.
On obtient une ébauche E de la pièce de révolution à réaliser, qui est constituée uniquement à partir de fils métalliques 4 et 5 et d'une structure 7 à fibres composites sous forme individuelle, en nappe, en tissu ou autre.  A blank E is obtained from the part of revolution to be produced, which consists solely of metal wires 4 and 5 and of a composite fiber structure 7 in individual, sheet, fabric or other form.
Puis, comme le montre la figure 5, l'ébauche E est soumise à traitement de compression isostatique à chaud (CIC) dans une presse isotherme ou sous sac dans un autoclave (le choix dépendant notamment du nombre de pièces à produire). On met en place un système de couvercle sur l'ébauche de forme complémentaire. Comme l'ébauche est cylindrique, le couvercle, en plusieurs parties, forme une enveloppe cylindrique autour de l'ébauche. Sous l'action de la compression exercée (par suite d'une haute pression appliquée selon la flèche F) sous une température élevée appropriée, le métal des fils métalliques et de l'enrobage des fibres des structures devient pâteux et flue supprimant tous les espaces vides entre les spires et couches, puis leur soudage diffusion densifiant au final la pièce. Then, as shown in Figure 5, the blank E is subjected to hot isostatic compression treatment (CIC) in an isothermal press or bag in an autoclave (the choice depending in particular on the number of parts to be produced). A lid system is put in place on the blank of complementary shape. As the blank is cylindrical, the lid, in several parts, forms a cylindrical envelope around the blank. Under the action of the compression exerted (as a result of a high pressure applied according to the arrow F) under a suitable high temperature, the metal of the metal wires and the coating of the fibers of the structures becomes pasty and flue eliminating all the spaces voids between the turns and layers, and then their diffusion densifying welding in the end the piece.
Dans une variante l'ensemble est placé dans une poche déformable en acier doux laquelle est ensuite introduite dans un autoclave. Cet autoclave est porté à une pression isostatique de 1000 bars et une température de 940°C (pour le TiA6V), de sorte que la totalité de la poche se déforme en se rétractant par l'évacuation de l'air et s'applique contre le mandrin et le couvercle qui, à leur tour, compriment sous une pression uniforme les enroulements de fil et fibre jusqu'au fluage du métal les constituant avec liaison par soudage diffusion. Avantageusement, plusieurs poches peuvent être ainsi introduites dans l'autoclave pour réaliser simultanément les pièces, réduisant les coûts de fabrication.  In a variant, the assembly is placed in a deformable pouch of mild steel which is then introduced into an autoclave. This autoclave is brought to an isostatic pressure of 1000 bar and a temperature of 940 ° C (for TiA6V), so that the whole of the bag is deformed by retracting by the evacuation of the air and is applied against the mandrel and the cover which, in turn, compress under a uniform pressure the windings of wire and fiber until the creep of the metal constituting them with diffusion bonding bonding. Advantageously, several pockets can thus be introduced into the autoclave to simultaneously produce the parts, reducing manufacturing costs.
Ainsi, après arrêt du traitement CIC, refroidissement et démoulage, on usine l'ébauche pour obtenir la pièce de révolution monobloc composite 1 , représentée sur la figure 1 , qui est réalisée en métal avec en son cœur les fibres formant des inserts de renfort.  Thus, after stopping the CIC treatment, cooling and demolding, the blank is machined to obtain the piece of composite monobloc revolution 1, shown in Figure 1, which is made of metal with the core fibers forming reinforcement inserts.
L'outillage formé par le mandrin cylindrique 10 et le système de couvercle est de préférence constitué d'un matériau qui permet son utilisation à nouveau pour la fabrication d'une autre pièce. Il s'agit par exemple d'un superalliage qui résiste à la température et à la pression du traitement en conservant son intégrité.  The tooling formed by the cylindrical mandrel 10 and the cover system is preferably made of a material that allows its use again for the manufacture of another part. This is for example a superalloy that withstands the temperature and pressure of the treatment while maintaining its integrity.
Bien évidemment, la direction d'orientation des fibres pourrait être différente de celle décrite ci-dessus (parallèle à l'axe du mandrin), de même que le choix d'un tissu en tant que structure fibreuse interne n'est nullement obligatoire, tout autre choix pouvant être envisagé. Il convient également de préciser que les étapes d'enroulement des fils et des structures fibreuses s'effectuent à la température ambiante sans avoir recours à une installation complexe.  Of course, the direction of orientation of the fibers could be different from that described above (parallel to the axis of the mandrel), just as the choice of a fabric as internal fibrous structure is not mandatory, any other choice that may be considered. It should also be noted that the winding steps son and fibrous structures are carried out at room temperature without resorting to a complex installation.
A titre d'exemples, les fibres composites enduites peuvent être, outre en SiC/Ti comme décrit ci-dessus, en SiC/AI, SiC/SiC, SiC/B, etc.... Dimensionnellement, le rayon minimal du mandrin est fonction du diamètre du fil métallique et doit être supérieur à ce dernier. Concernant la longueur de la pièce, elle peut atteindre plusieurs mètres si nécessaire. By way of example, the coated composite fibers may be, in addition to SiC / Ti as described above, SiC / Al, SiC / SiC, SiC / B, etc. Dimensionally, the minimum radius of the mandrel is a function of the diameter of the wire and must be greater than the latter. Regarding the length of the piece, it can reach several meters if necessary.
Conformément à une variante de mise en œuvre, représentée sur les figures 6 et 7, on adjoint des flasques 13a et14b au mandrin, du côté des extrémités libres des demi mandrins 10'a et 10'b, de manière à compléter le support de la deuxième couche 8' de fil métallique lorsque celle-ci a un diamètre supérieur à celui du mandrin 10'a, 10'b. L'épaisseur des différentes couches appliquées tient compte de leur foisonnement, en vue du résultat que l'on souhaite obtenir après traitement CIC. Le système de couvercle 12' tel que représenté sur la figure 7 est adapté à la géométrie externe de l'ébauche.  According to an alternative embodiment, shown in FIGS. 6 and 7, the flanges 13a and 14b are attached to the mandrel, on the free ends side of the half mandrels 10'a and 10'b, so as to complete the support of the second layer 8 'of wire when it has a diameter greater than that of the mandrel 10'a, 10'b. The thickness of the different layers applied takes into account their proliferation, in view of the result that is desired after CIC treatment. The cover system 12 'as shown in FIG. 7 is adapted to the external geometry of the blank.
Conformément à une autre variante de réalisation, le procédé de l'invention permet de fabriquer des pièces en forme d'haltère, c'est-à-dire avec des nervures radiales transversales. Il suffit pour les obtenir d'adapter la géométrie de la deuxième couche de manière à former ces nervures. L'épaisseur de cette deuxième couche est augmentée dans ce but à l'endroit souhaité. Ainsi sur la figure 8 on voit un détail de l'ébauche réalisée de cette façon. La deuxième couche 8" de fil métallique est formée par enroulement de fil métallique de manière à présenter une partie formant une nervure transversale 8"a. cette nervure après le traitement CIC forme une nervure radiale transversale sur la pièce. La fonction de cette nervure peut être une bride de fixation terminale ou bien un pignon après usinage de dents radiales.  According to another alternative embodiment, the method of the invention makes it possible to manufacture dumbbell-shaped parts, that is to say with transverse radial ribs. It is sufficient to obtain them to adapt the geometry of the second layer so as to form these ribs. The thickness of this second layer is increased for this purpose to the desired location. Thus in Figure 8 we see a detail of the blank made this way. The second layer 8 "of wire is formed by winding wire so as to have a portion forming a transverse rib 8" a. this rib after CIC treatment forms a transverse radial rib on the workpiece. The function of this rib may be a terminal fastening flange or a pinion after machining radial teeth.
Dans le but de renforcer encore la résistance mécanique de cette nervure on peut inclure des fibres céramiques 8"b de longueur adaptée à la largeur de la nervure après CIC. Si les fibres de renfort sont orientées transversalement à l'axe de la pièce alors elles peuvent être mise en place par enroulement comme le sont les fils métalliques. Si l'orientation choisie des fibres de renfort doit être axiale, alors on les mettra en place sous la forme de nappes ou de tissu comme la couche de renfort 7.  In order to further reinforce the mechanical strength of this rib, it is possible to include ceramic fibers 8 "b of length adapted to the width of the rib after CIC If the reinforcing fibers are oriented transversely to the axis of the piece, then they may be wound up as metal wires are, if the chosen orientation of the reinforcing fibers is to be axial, then they will be placed in the form of webs or fabric such as the reinforcing layer 7.
On observe que la forme du couvercle 12" est également adaptée à celle de l'ébauche de pièce réalisée sur le mandrin 10".  It is observed that the shape of the cover 12 "is also adapted to that of the part blank made on the mandrel 10".

Claims

REVENDICATIONS
1 . Procédé pour fabriquer une pièce (1 ) de révolution monobloc comprenant la réalisation d'une ébauche de la pièce autour d'un mandrin cylindrique (10), l'ébauche comprenant au moins une structure fibreuse (7) formée de fibres (9) composites céramiques enduites de métal, puis le traitement de soudage diffusion de l'ébauche par compaction isostatique à chaud, et l'usinage éventuel de l'ébauche ainsi traitée pour obtenir la pièce (1 ), caractérisé par le fait que l'ébauche comprend au moins une première couche (6) de fil métallique (4) entre le mandrin (10) et ladite structure (7) fibreuse composite et au moins une deuxième couche (8) de fil métallique autour de ladite structure (7) fibreuse composite de manière à enrober celle-ci, le mandrin (10) comprenant deux parties (10a, 10b) tronconiques, séparables l'une de l'autre. 1. Process for manufacturing a piece (1) of one-piece revolution comprising producing a blank of the piece around a cylindrical mandrel (10), the blank comprising at least one fibrous structure (7) formed of composite fibers (9) ceramics coated with metal, then the welding treatment diffusion of the blank by hot isostatic compaction, and the possible machining of the blank thus treated to obtain the part (1), characterized in that the blank comprises at at least one first layer (6) of wire (4) between the mandrel (10) and said composite fibrous structure (7) and at least one second layer (8) of wire around said composite fibrous structure (7). to coat the latter, the mandrel (10) comprising two parts (10a, 10b) frustoconical, separable from one another.
2. Procédé selon la revendication précédente selon lequel la première couche (6) de fil métallique est conformée de manière à présenter après compaction de l'ébauche une portion cylindrique susceptible de former après usinage la paroi intérieure de la pièce.  2. Method according to the preceding claim wherein the first layer (6) of wire is shaped so as to have after compaction of the blank a cylindrical portion capable of forming after machining the inner wall of the workpiece.
3. Procédé selon l'une des revendications précédentes, la première couche (6) de fil métallique étant formée par enroulement d'un ou plusieurs fils métalliques (4) autour du mandrin (10).  3. Method according to one of the preceding claims, the first layer (6) of wire being formed by winding one or more wire (4) around the mandrel (10).
4. Procédé selon l'une des revendications précédentes, le fil métallique (4) étant du type obtenu par tréfilage et de même nature que celui qui enduit les fibres composites.  4. Method according to one of the preceding claims, the wire (4) being of the type obtained by wire drawing and of the same nature as that which coats the composite fibers.
5. Procédé selon l'une des revendications précédentes dont la mise en place des différentes couches (6, 7, 8) est effectuée à froid, à la température ambiante.  5. Method according to one of the preceding claims, the establishment of the different layers (6, 7, 8) is performed cold at room temperature.
6. Procédé selon l'une des revendications précédentes, selon lequel on dispose les fibres (9) enduites de la structure fibreuse composite selon une même direction, de préférence la direction axiale de la pièce.  6. Method according to one of the preceding claims, wherein the fibers (9) coated with the composite fiber structure are arranged in the same direction, preferably the axial direction of the workpiece.
7. Procédé selon la revendication précédente, selon lequel la structure fibreuse (7) composite est formée par enroulement d'une ou plusieurs nappes ou tissus de fibres composites métalliques parallèles ou bien de fibres individuelles et parallèles successivement disposées autour du mandrin, 7. Method according to the preceding claim, wherein the composite fibrous structure (7) is formed by winding one or more plies or fabrics of parallel metallic composite fibers or of individual and parallel fibers successively arranged around the mandrel,
8. Procédé selon l'une des revendications précédentes, selon lequel on lie au moins en partie les couches entre elles par collage, soudage ou au moyen de clinquants.  8. Method according to one of the preceding claims, wherein at least partially binds the layers together by gluing, welding or by means of foils.
9. Procédé selon l'une des revendications précédentes selon lequel on forme notamment aux extrémités longitudinales de l'ébauche, par enroulement de fil métallique des nervures (8"a) radiales transversales.  9. Method according to one of the preceding claims, which is formed in particular at the longitudinal ends of the blank, by winding wire transverse ribs (8 "a) radial.
10. Procédé selon la revendication précédente selon lequel on incorpore dans lesdites nervures transversales un renfort (8"b) de fibres céramiques.  10. Method according to the preceding claim wherein incorporating in said transverse ribs a reinforcement (8 "b) of ceramic fibers.
EP12712320.6A 2011-03-02 2012-03-02 Method for manufacturing an integral rotationally symmetrical metal part including a reinforcement consisting of ceramic fibers Active EP2680991B1 (en)

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PCT/FR2012/050448 WO2012117213A1 (en) 2011-03-02 2012-03-02 Method for manufacturing an integral rotationally symmetrical metal part including a reinforcement consisting of ceramic fibbers

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RU2584061C2 (en) 2016-05-20
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US20130340226A1 (en) 2013-12-26
BR112013022288A2 (en) 2017-03-01
FR2972123A1 (en) 2012-09-07
CA2828388C (en) 2018-07-03
BR112013022288B1 (en) 2018-07-03
CN103402675B (en) 2016-03-30
EP2680991B1 (en) 2015-07-22
FR2972123B1 (en) 2014-06-13
US9150948B2 (en) 2015-10-06
CA2828388A1 (en) 2012-09-07
RU2013141409A (en) 2015-04-10

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