EP2686123B1 - Verfahren zur herstellung eines einteiligen axialsymmetrischen metallischen bauteils aus faserverbundstrukturen - Google Patents

Verfahren zur herstellung eines einteiligen axialsymmetrischen metallischen bauteils aus faserverbundstrukturen Download PDF

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Publication number
EP2686123B1
EP2686123B1 EP12714793.2A EP12714793A EP2686123B1 EP 2686123 B1 EP2686123 B1 EP 2686123B1 EP 12714793 A EP12714793 A EP 12714793A EP 2686123 B1 EP2686123 B1 EP 2686123B1
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EP
European Patent Office
Prior art keywords
mandrel
fibrous structure
layer
metal wire
wire
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Active
Application number
EP12714793.2A
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English (en)
French (fr)
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EP2686123A1 (de
Inventor
Thierry Godon
Bruno Jacques Gérard DAMBRINE
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Safran Aircraft Engines SAS
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Safran Aircraft Engines SAS
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Classifications

    • 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
    • B22F7/00—Manufacture of composite layers, workpieces, or articles, comprising metallic powder, by sintering the powder, with or without compacting wherein at least one part is obtained by sintering or compression
    • B22F7/02—Manufacture of composite layers, workpieces, or articles, comprising metallic powder, by sintering the powder, with or without compacting wherein at least one part is obtained by sintering or compression of composite layers
    • B22F7/04—Manufacture of composite layers, workpieces, or articles, comprising metallic powder, by sintering the powder, with or without compacting wherein at least one part is obtained by sintering or compression of composite layers with one or more layers not made from powder, e.g. made from solid metal
    • 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
    • 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
    • B22F3/002—Manufacture of articles essentially made from metallic fibres
    • 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
    • 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
    • Y10T29/4998—Combined manufacture including applying or shaping of fluent material
    • Y10T29/49988—Metal casting
    • Y10T29/49989—Followed by cutting or removing material

Definitions

  • the present invention relates to a method for manufacturing a metal piece of one-piece revolution from composite fiber structures in the form of fibers, fiber webs, fiber fabrics and the like, coated with metal.
  • such a structure comprises metal composite fibers composed of a metal alloy matrix, for example titanium alloy Ti, within which fibers extend, for example ceramic fibers of SiC silicon carbide.
  • a metal alloy matrix for example titanium alloy Ti
  • 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 metal alloy matrix 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 reinforced with metal.
  • composite materials can be used to produce annular parts of gas turbine revolution for aircraft or other industrial application, such as rings, shafts, cylinder bodies, housings, spacers, reinforcements of monolithic parts such as blades. , etc ....
  • the documents JP 06256869 and EP 1 288 324 A2 illustrate such composite materials, their uses, as well as their manufacturing processes.
  • the known methods for producing such pieces of revolution monoblocs consist of superimposing, around a rotary cylindrical mandrel, fibrous structures (fibers, fiber web or fiber fabric) successive and to dispose the composite fibrous structures wound and out of the mandrel , in a specific receiving tooling for thermally treating them and finally obtaining the revolution piece made of composite material.
  • one of the superposed fibrous structures is oriented in a first direction of winding with respect to the longitudinal axis of the mandrel, then the other fibrous structure is wound on the preceding one in a second direction of winding different from the first, so as to obtain two composite fibrous structures having cross winding directions.
  • the present invention aims to overcome these disadvantages.
  • the wire layer acts as an interface between the superposed and crossed fibrous structures and increases the metallic thickness between the structures, so that the over-stresses between the composite fibers of the structures no longer occur.
  • the wire is obtained, for example, by wire drawing and is of the same nature as the metal of the composite fibrous structures, so that after passing through the tooling, an intermediate and homogeneous metallic layer having an appropriate thickness is obtained. between the fibers of the structures.
  • Wire wire means both a continuous wire and a plurality of son put end to end.
  • the wire may also be individual or be in the form of a sheet or ribbon of several parallel or interlaced son, a cable, a fabric of unidirectional son, etc .. without departing from the scope of the invention.
  • the superimposed winding layers of the wire and the fibrous structures are cold-processed at ambient temperature, which does not require complex installation for carrying out the relevant steps of the process.
  • the wire is wound substantially orthogonally to the longitudinal axis of the rotating cylindrical mandrel to form the layer of contiguous turns.
  • At least one layer of wire may be arranged around the outer fibrous structure, so that the part obtained superficially presents an outer and inner layer of metal layers.
  • the first winding direction of the internal fibrous structure is oriented angularly with respect to the longitudinal axis of the cylindrical mandrel, the second winding direction of the outer fibrous structure then being oriented symmetrically to the first by relative to a radial direction of the mandrel, perpendicular to its longitudinal axis.
  • the winding direction of the internal fibrous structure is between 30 ° - 60 ° with respect to the longitudinal axis of the mandrel, the winding direction of the external structure will be between 30 ° - 60 ° + ⁇ / 2.
  • the internal and external fibrous structures may be in the form of individual and parallel fibers successively wound around the mandrel, or in the form of parallel sheets or ribbons of fibers, or in the form of parallel fiber fabrics, said structures being arranged with crosswise on the mandrel.
  • the first winding direction of the internal fibrous structure is parallel to the longitudinal axis of the cylindrical mandrel, the second winding direction of the outer fibrous structure then being oriented angularly with respect to the axis. longitudinal axis of the mandrel.
  • the internal fibrous structure may be in the form of a fabric of fibers parallel to each other and wound around the cylindrical mandrel parallel to its longitudinal axis
  • the external fibrous structure may be any, but, of course, with the oriented fibers. angularly with respect to those of the internal structure which are parallel to the mandrel.
  • 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.
  • FIGS. 4A, 4B, 4C1 and 4C2 proposeing different possibilities of external fibrous structures used after the process step illustrated on the figure 3
  • Figures 6A and 6B schematically represent tools for processing the blank to obtain the part.
  • the object of the method is to produce a piece of annular, one-piece revolution 1 illustrated on FIG. figure 7 , only from elongated elements in the form of son, fibers or the like, as will be seen below.
  • the method consists in using a rotary cylindrical mandrel 2 with a longitudinal axis X and firstly wound around the lateral surface 3 thereof, in a first step illustrated in FIG. figure 1 at least one wire 4.
  • the wire 4 is made in particular of a titanium alloy of TA6V or 6242 type providing thermomechanical resistance and lightness, and it is obtained in this non-limiting example by wire drawing so that it can be available in the form of coil or reel from which the wire is drawn. Dimensionally, its diameter depends on the part to be obtained and perhaps, for example, of the order of a few tenths of a millimeter.
  • the wire drawn wire 4 is derived from a not shown spool and is driven, substantially perpendicular to the axis X, around the lateral surface 3 of the cylindrical mandrel 2 over a predetermined extent corresponding to the length which is wishes to obtain, after manufacture, for the part of revolution 1, thus forming several contiguous turns 5, and on several predetermined superimposed layers 6.
  • the process continues with a second step shown on the figure 2 and consisting in arranging a composite fibrous structure 7 around the wire drawn wire 4.
  • the composite fibrous structure 7 is in the form of a fabric 8 of fibers 9 associated parallel to each other and made of ceramic (SiC) or a similar material coated with metal.
  • the latter and the metal of the drawn wire are identical in nature (for example in TA6V or 6242 type titanium alloy) to optimize the subsequent step of the process relating to the operation of hot isostatic compaction or isothermal forging .
  • a drawn wire 11 which comes from a not shown spool and which is brought substantially orthogonal to the longitudinal axis X of the rotary cylindrical mandrel 2.
  • the wire 11 forms a single layer 12 of contiguous turns 13 around the fabric 8.
  • a winding of several layers is also possible, depending on the diameter of the wire used, and the separation to be given between the fibrous structure internal composite 7 and a then external composite fibrous structure 14 to be superposed as will be seen below.
  • the drawn wire 11 may be the same (diameter, nature) as that used to form the layers 6 on the mandrel 2 and come from the same coil. But, it could also have a different diameter.
  • the outer fibrous structure 14 is composed of ceramic composite fibers coated with metal which may or may not be identical to the preceding fibers.
  • These fibers 15 are wound successively around the turns 13 of the layer 12 of intermediate wire 11, which is according to the invention between the two fibrous structures 7 and 14.
  • the fibers 15 are contiguous and oriented in a second direction D2 relative to to the X axis of the mandrel 2, forming a helix angle A with respect thereto.
  • the wound fibers 15 and the fibers 9 of the fabric 8 have different orientation directions D1 and D2 different and cross to allow the realization of rigid monobloc composite parts revolution. Some of the fibers are only partially represented.
  • the number of coiled fibers 15 is variable and is a function of the helix angle A to be given, which is for example of the order of 30 ° to 60 °, and the diameter of the fibers.
  • a single layer 16 of the fibers 15 is made around the wire 11. Nevertheless, several layers are possible.
  • the two internal and external fibrous structures 7 are not in direct contact with each other, being separated by the winding layer of the intermediate wire drawn metal wire 11 acting as an interface, in order to eliminate any over-stress that may appear between them during the cooling of the blank E formed by the structures and the metal wires.
  • the outer fibrous structure 14 can consist of the successive winding of plies or ribbons 17 each composed of parallel composite fibers 18 (six in this example), that is to say having a core made of ceramic or a similar material coated with metal, preferably identical to drawn wire 11.
  • transverse metallic wires of weaving 19 identical in nature to drawn wire.
  • the number of layers 17 to cover the layer 12 of intermediate wire 11 is a function of the width of the sheet and the helix angle A thereof relative to the winding axis X of the rotary cylindrical mandrel 2.
  • the helix angle A of the plies defines the second direction D2 of the outer fibrous structure 14, crossing the direction D1 of the internal fibrous structure 7.
  • the outer fibrous structure 14 is in the form of a fabric 21 with metal composite fibers 22, assembled parallel to each other.
  • the fibers 22 are oriented obliquely with respect to the perpendicular sides 23, 24 of the fabric 21 in the form of a rectangular strip.
  • the fabric 21 is presented by its corresponding side 23 (short side) parallel to the longitudinal axis X of the cylindrical mandrel 2, it is wound, by the rotation of the latter, on the layer 12 of wire drawn intermediate 11 and these oblique parallel composite fibers 22 form the desired helix angle A defining the second direction D2 of the outer fibrous structure 14, crossed with the first direction D1 of the internal fibrous structure 7.
  • the size of the fabric 21 is sufficient to completely cover the layer of drawn wire.
  • a layer 25 (or more layers if necessary) of fabric 21 is thus wound on the intermediate drawn wire 11.
  • the fibers 22 are parallel to the side 23 of the fabric 21 to be wound and are interconnected by son 27. Also, to have a direction of orientation D2 fibers different from that D1 of the internal structure, the fabric 21 itself The same is obliquely presented by one of its corners 26 with respect to the rotating cylindrical mandrel 2, so as to form the desired helix angle A.
  • the parallel fibers 22 of the fabric 21 wind around the layer 12 of wire drawn wire 11 in the second desired direction D2 crossed with the first direction D1 of the internal fibrous structure 7, parallel to the axis X of the cylindrical mandrel 2.
  • the size of the fabric 21 is such that it allows to cover completely the layer 12 of wire drawn by the winding of said fabric on one or more layers 25.
  • the two fibrous structures 7 and 14 have directions D1, D2 crossed and are separated from each other by at least one layer 12 of contiguous turns 13 of the wire 11 playing the role. interface according to the invention.
  • the successive layers composing the two fibrous structures 7 and 14 their fibers are always parallel from one layer to another with an orientation D1 or D2.
  • a subsequent step of the method consists in winding, on the outer fibrous structure 14, at least one layer 28 of drawn wire 29 which may be from the same feed reel as before.
  • a winding with contiguous turns 30 of the wire 29, made substantially orthogonal to the axis X of the cylindrical mandrel 2 is obtained (as a reminder, wire and / or fabric of metal wires).
  • a blank E is obtained from the piece of revolution to be produced, which consists solely of wire drawn wires 4, 11, 29 and internal and external structures 7, 14 of composite fibers in individual form, in sheets, in fabric or in other.
  • the blank E is transferred to a compaction tool 31, schematically represented, where the hot isostatic pressing (CIC) step is carried out in an isothermal press or in an autoclave (the choice depending in particular on the number of pieces to produce).
  • CIC hot isostatic pressing
  • Figure 6A After the transfer and the placement of the blank E in the vacuum press tooling 31, Figure 6A , more particularly in an open cylindrical receptacle 32 of the press, whose reception volume, defined by its walls 33, corresponds to that of the part to be obtained, the receptacle is closed by a cover 34 of complementary shape to the opening of the receptacle and the transverse face of the blank E facing.
  • this autoclave is brought to an isostatic pressure of 1000 bar and a temperature of 940 ° C (for the TA6V), so that the whole of the pocket 36 is deformed, arrows F1, retracting through the evacuation air expelled via the hole 37 and is applied against the receptacle 32 and the cover 34 which, in turn, compress under a uniform pressure the windings of son and fibers until the creep of the metal constituting them (diffusion welding) , like before.
  • the piece of composite monobloc revolution 1 represented on FIG. figure 7 , which is made of TA6V or 6242 type titanium alloy, with in its core the ceramic matrices (silicon carbon, for example) fibers 9-15 or 18 or 22 forming cross reinforcement inserts, but separated by the metal layer from the intermediate wire, and whose thickness is such that it avoids the appearance of stress between the crossed ceramic fibers, superimposed.
  • the part 1 can of course undergo machining operations subsequent to the CIC treatment.
  • the orientation direction of the fibers of the internal structure could be different from that described above (parallel to the axis of the mandrel), as well as the choice of a fabric as an internal fibrous structure is not mandatory, any other choice may be considered.
  • the winding steps son and fibrous structures are carried out at room temperature without resorting to a complex installation.
  • 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.

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  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Manufacturing & Machinery (AREA)
  • Materials Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Crystallography & Structural Chemistry (AREA)
  • Composite Materials (AREA)
  • Manufacture Of Alloys Or Alloy Compounds (AREA)
  • Laminated Bodies (AREA)
  • Moulding By Coating Moulds (AREA)
  • Powder Metallurgy (AREA)
  • Woven Fabrics (AREA)
  • Yarns And Mechanical Finishing Of Yarns Or Ropes (AREA)

Claims (10)

  1. Verfahren zum Herstellen eines einstückigen Rotationsteils durch Überlagerung von mindestens zwei mit Metall beschichteten Verbundfaserstrukturen, einer inneren (7) bzw. einer äußeren (14) um einen drehbaren zylindrischen Dorn (2), die in einer ersten und zweiten Querrichtung auf den Dorn gewickelt sind, dadurch gekennzeichnet, dass es darin besteht:
    - zumindest eine Schicht von Draht (11) um die innere Faserstruktur (7), die auf dem Dorn (2) angeordnet ist, gemäß der ersten Wickelrichtung (D1) anzubringen,
    - auf die Schicht von Draht (11) die äußere faserige Struktur (14) gemäß der zweiten Wickelrichtung (D2) zu wickeln,
    - den Rohling (E) des Stücks, das durch die Faserstrukturen (7, 14) und die Drahtschicht (11) gebildet ist, in einem Aufnahmewerkzeug (31) aufzunehmen, um auf den Rohling eine isostatische Kompaktierungsbearbeitung unter Wärme oder eine isothermische Schmiedebearbeitung anzuwenden, und
    - den bearbeiteten Rohling aus dem Werkzeug herauszunehmen, gegebenenfalls den bearbeiteten Rohling weiterzuverarbeiten, um das Teil (1) zu erhalten.
  2. Verfahren nach Anspruch 1, wobei der Draht (11) durch Drahtziehen erhalten wird und von der gleichen Art wie diejenige der inneren (7) und äußeren (14) Verbundfaserstruktur ist.
  3. Verfahren nach einem der vorhergehenden Ansprüche, wobei die überlagerten Wicklungsschichten des Drahtes (11) und der Faserstrukturen (7, 14) im Kalten bei Raumtemperatur realisiert werden.
  4. Verfahren nach einem der vorhergehenden Ansprüche, wobei die Schicht (12) aus Draht (11) im Wesentlichen orthogonal zur Längsachse des drehbaren zylindrischen Dorns (2) gewickelt wird.
  5. Verfahren nach einem der vorhergehenden Ansprüche, wobei mindestens eine Schicht aus Draht (4), auf die anschließend die innere Faserstruktur (7) gewickelt wird, um den zylindrischen Dorn (2) vor dem Anordnen der inneren Faserstruktur (7) angebracht wird.
  6. Verfahren nach einem der vorhergehenden Ansprüche, wobei um die äußere Faserstruktur (14) mindestens eine Schicht von Draht (29) angebracht wird.
  7. Verfahren nach einem der vorhergehenden Ansprüche, wobei die erste Wicklungsrichtung (D1) der inneren Faserstruktur (7) im Winkel in Bezug auf die Längsachse (X) des zylindrischen Dorns (2) ausgerichtet ist, wobei die zweite Wicklungsrichtung (D2) der äußeren Faserstruktur (14) symmetrisch zu der ersten in Bezug auf eine Richtung ausgerichtet ist, die senkrecht zur Längsachse des Dorns ist.
  8. Verfahren nach dem vorhergehenden Anspruch, wobei die innere (7) und äußere (14) Faserstruktur in Form von einzelnen und parallelen Fasern (15), die nacheinander um den Dorn gewickelt werden, oder in Form von Tüchern oder Streifen (17) aus parallelen Fasern oder in Form von Geweben (21) aus parallelen Fasern sind, wobei die Strukturen quer auf dem Dorn angeordnet sind.
  9. Verfahren nach einem der Ansprüche 1 bis 6, wobei die erste Wicklungsrichtung (D1) der inneren Faserstruktur (7) parallel zu der Längsachse (X) des zylindrischen Dorns (2) ist, wobei die zweite Wicklungsrichtung (D2) der äußeren Faserstruktur (14) in einem Winkel in Bezug auf die Längsachse des Dorns ausgerichtet ist.
  10. Verfahren nach dem vorhergehenden Anspruch, wobei die innere Faserstruktur (7) in der Form eines Gewebes von zueinander parallelen Fasern und um den zylindrischen Dorn (2) parallel zu seiner Längsachse gewickelt ist, wobei die äußere Faserstruktur (14) Fasern hat, die in einem Winkel in Bezug auf jene der inneren Fasernstruktur ausgerichtet sind, die zu dem Dorn parallel sind.
EP12714793.2A 2011-03-15 2012-03-15 Verfahren zur herstellung eines einteiligen axialsymmetrischen metallischen bauteils aus faserverbundstrukturen Active EP2686123B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1152129A FR2972661B1 (fr) 2011-03-15 2011-03-15 Procede pour fabriquer une piece metallique de revolution monobloc a partir de structures fibreuses composites
PCT/FR2012/050550 WO2012123686A1 (fr) 2011-03-15 2012-03-15 Procede pour fabriquer une piece metallique de revolution monobloc a partir de structures fibreuses composites

Publications (2)

Publication Number Publication Date
EP2686123A1 EP2686123A1 (de) 2014-01-22
EP2686123B1 true EP2686123B1 (de) 2017-11-01

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EP12714793.2A Active EP2686123B1 (de) 2011-03-15 2012-03-15 Verfahren zur herstellung eines einteiligen axialsymmetrischen metallischen bauteils aus faserverbundstrukturen

Country Status (8)

Country Link
US (1) US9321106B2 (de)
EP (1) EP2686123B1 (de)
CN (1) CN103459067B (de)
BR (1) BR112013023463B8 (de)
CA (1) CA2829012C (de)
FR (1) FR2972661B1 (de)
RU (1) RU2584106C2 (de)
WO (1) WO2012123686A1 (de)

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FR2970715B1 (fr) * 2011-01-21 2014-10-17 Snecma Structure fibreuse tissee multicouches ayant une partie tubulaire creuse, procede de fabrication et piece composite la comportant
RU2542221C2 (ru) * 2013-06-25 2015-02-20 Федеральное государственное автономное образовательное учреждение высшего профессионального образования "Уральский федеральный университет имени первого Президента России Б.Н. Ельцина" Способ получения цилиндрической заготовки в виде прутка из металлического армированного композиционного материала

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US5762843A (en) * 1994-12-23 1998-06-09 Kennametal Inc. Method of making composite cermet articles
ATE322560T1 (de) * 1999-11-04 2006-04-15 Avio Spa Verfahren zur herstellung eines bauteiles aus verbundwerkstoff
GB0119636D0 (en) * 2001-08-11 2001-10-03 Rolls Royce Plc a method of manufacturing a fibre reinforced metal component
RU2215816C2 (ru) * 2001-12-26 2003-11-10 Федеральное государственное унитарное предприятие "Всероссийский научно-исследовательский институт авиационных материалов" Способ получения композиционного материала на основе интерметаллида титана и изделие, полученное этим способом
FR2886181B1 (fr) * 2005-05-27 2008-12-26 Snecma Moteurs Sa Procede de fabrication d'une piece tubulaire avec un insert en materiau composite a matrice metallique
FR2913053B1 (fr) * 2007-02-23 2009-05-22 Snecma Sa Procede de fabrication d'un carter de turbine a gaz en materiau composite et carter ainsi obtenu
FR2925895B1 (fr) * 2007-12-28 2010-02-05 Messier Dowty Sa Procede de fabrication d'une piece metallique renforcee de fibres ceramiques

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Publication number Publication date
CN103459067A (zh) 2013-12-18
RU2013142130A (ru) 2015-04-20
FR2972661B1 (fr) 2013-04-12
US20130340241A1 (en) 2013-12-26
US9321106B2 (en) 2016-04-26
BR112013023463A2 (pt) 2017-08-08
WO2012123686A1 (fr) 2012-09-20
CA2829012C (fr) 2018-10-16
FR2972661A1 (fr) 2012-09-21
EP2686123A1 (de) 2014-01-22
BR112013023463B1 (pt) 2019-01-02
RU2584106C2 (ru) 2016-05-20
CA2829012A1 (fr) 2012-09-20
BR112013023463B8 (pt) 2019-10-08
CN103459067B (zh) 2016-10-12

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