EP2504462B1 - Verfahren zur herstellung eines verbundmetallteils mit inneren verstärkungselementen in faserform - Google Patents

Verfahren zur herstellung eines verbundmetallteils mit inneren verstärkungselementen in faserform Download PDF

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Publication number
EP2504462B1
EP2504462B1 EP10784770.9A EP10784770A EP2504462B1 EP 2504462 B1 EP2504462 B1 EP 2504462B1 EP 10784770 A EP10784770 A EP 10784770A EP 2504462 B1 EP2504462 B1 EP 2504462B1
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EP
European Patent Office
Prior art keywords
insert
container
cavity
cover
production method
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.)
Active
Application number
EP10784770.9A
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English (en)
French (fr)
Other versions
EP2504462A1 (de
Inventor
Richard Masson
Patrick Dunleavy
Jean-Michel Franchet
Gilles Klein
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
Safran Aircraft Engines SAS
Safran Landing Systems SAS
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Publication date
Application filed by Safran Aircraft Engines SAS, Safran Landing Systems SAS filed Critical Safran Aircraft Engines SAS
Publication of EP2504462A1 publication Critical patent/EP2504462A1/de
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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
    • 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
    • C22C47/20—Making alloys containing metallic or non-metallic fibres or filaments by subjecting to pressure and heat an assembly comprising at least one metal layer or sheet and one layer of fibres or filaments
    • 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
    • Y10T29/49229—Prime mover or fluid pump making
    • Y10T29/49288—Connecting rod making
    • Y10T29/4929—Connecting rod making including metallurgical bonding
    • 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
    • Y10T29/49616—Structural member making
    • Y10T29/49622—Vehicular structural member making
    • 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 invention relates to a method for manufacturing composite metal parts by incorporating internal reinforcements formed of fibers, in particular ceramic fibers, and also relates to the preform used during the implementation of the method as well as the composite metal part obtained.
  • the invention relates to the field of metal matrix composite materials, abbreviated CMM.
  • Ceramic fibers in particular SiC silicon carbide fibers, are in particular used for high-tech high-temperature applications that require the fields of aviation or aerospace or in the field of safety, for example for braking (ceramic brakes).
  • a known method for manufacturing such parts with reinforcement comprises forming a coil of coated wires around a mandrel.
  • the coil is then incorporated into a metal container or main body in which a cavity has been pre-machined to form a housing for the insert.
  • the depth of the cavity is greater than the height of the coil and is shaped to insert a cover pin.
  • the lid is vacuum welded at the periphery of the cavity to ensure the seal during the hot isostatic compaction step, during which the cover is deformed and the winding is compressed by the tenon.
  • the hot isostatic compaction technique consists of placing the part in a chamber where it is subjected to a high pressure, of the order of 1000 bar, and at a temperature which is also high, of the order of 1000.degree. hours.
  • the inter-son voids coated creep disappear, the metal sheaths of the coated son are welded together and with the walls of the cavity, by diffusion bonding, to form a dense set composed of a metal alloy to within which the ceramic fibers extend. The resulting part is then machined to the desired shape.
  • the method allows the manufacture of axisymmetric aeronautical parts, such as rotor discs or monobloc blade discs, but also non-axisymmetric, such as connecting rods, shafts, cylinder bodies, housings.
  • the machining of the cavity in the main body is a difficult operation to achieve especially because of the small connection radii in the bottom of the cavity between the bottom surface and the side walls.
  • This small radius of connection is necessary to allow housing, with a game as low as possible, the insert which has a rectangular section and which is formed of son of small rays. Machining the corresponding post in the cover is not easy either because of the non-opening angles and because it must have a shape perfectly complementary to the cavity.
  • the machining of the main body of the container with its lid represents a significant fraction of the total cost of the parts.
  • the applicant has developed a manufacturing process in which wherein the cavity houses a rectilinear insert and the lid whose dimensions are adjusted to allow positioning on this insert.
  • the sealing of the cavity is then ensured by shrinking by reducing the dimensions of the cold cover, for example by diving in liquid nitrogen, and then expanding in the cavity so as to achieve a tight fit.
  • the solution thus provides a seal that simplifies the shape of the cavity.
  • This operation consists in subjecting the container - insert - lid assembly to a double cycle of temperature rise and pressure.
  • the pressure is exerted by a gaseous fluid of compaction, generally argon.
  • the invention proposes a pre-welding treatment of the lid on the container prior to the compaction phase.
  • the subject of the present invention is a process for manufacturing composite metal parts by incorporating internal reinforcements formed of fibers, comprising the steps of machining in a metal body or container of at least one housing cavity for an insert of corresponding form comprising reinforcing fibers for introducing a lid on the insert into the cavity of the container, the lid having walls held in pressure against the walls of the facing container, the hot isostatic compaction cycle of the container assembly - insert - cover, and machining said assembly to obtain said part.
  • This step of pressurizing the lid against the container is then continued by a pre-diffusion diffusion heat treatment consisting of a rise and a temperature maintenance of the container-insert-lid assembly solidarisant the lid and the container.
  • the isostatic compaction is optimized and no longer requires external closure of the container by the lid with a specific weld, which leads to a reduction in costs, while ensuring quality compaction due to the absence of gas leakage in the insert by the internal pre-welding.
  • the pre-treatment is integrated in the hot isostatic compaction cycle in which a first thermal phase only is followed by an external hot pressurization phase.
  • the positioning terms of the "superior” or “inferior” type designate locations with respect to objects in the sense of universal gravity.
  • the metal body shown or container 10 is for example intended to form a connecting rod of a landing gear.
  • a cavity 12 has been machined in the container 10 from its upper face Fs. This cavity accommodates an insert 14 in its lower part and a cover 16 in its upper part, the cover covering the insert.
  • the cover 16 is projecting, in the example shown on the figure 1a , relative to the upper face Fs of the container 10 for material compensation issues as mentioned below in the isostatic compaction phase.
  • the cavity 12, the insert 14 and the cover 16 are of complementary shape and machined in such a way as to have no clearance or minimal clearance between them, the lowest possible considering technological constraints.
  • the lid 16 and the container 10 have walls 16a and 10a bearing against each other by pressurization.
  • a hooping between the walls of the lid and the container facing is performed by prior cooling of the lid in liquid nitrogen.
  • the lid then shrinks in size and is positioned in the cavity on the insert.
  • the lid expands in size and the walls of the lid and the container opposite then come into pressure against each other by a tight fit.
  • the metal is a titanium alloy and the temperature of Welding is between 850 and 1000 ° C.
  • the temperature keeping time for titanium alloys is at least 30 minutes.
  • This pre-welding integrally or at least partially solidifies the container and the lid.
  • the container and the lid are advantageously made of the same metal, a titanium alloy in the example. After this bonding treatment, the container 10 and the lid 16 form no more than a single entity surrounding the fiber insert 14, as schematically illustrated by the figure 1b , the cover always forming a projection 16s of upper face Fc.
  • the dimensions of the lid are previously calculated so that the upper face 16s of the lid 16 comes, during the pressurization, at the upper face Fs of the container 10, knowing that the volume of the insert decreases from about 15 to 20%.
  • the container, the lid and the fibers are compacted, as indicated by the shrinkage volumes 18 and 19 appearing in hatched section on the figure 1c .
  • the blank of the piece is thus reinforced by the wires imprisoned in the mass. Final machining makes it possible to obtain the desired shaped part.
  • FIG. 2a and 2b Concretely illustrate the assembly of the components to achieve a preform 20.
  • the components comprise the container 10 of elongated shape, having the cavity 12 also in elongated form, the insert 14 rectilinear and the cover 16 in the form of pavers.
  • the machined cavity 12 is rectilinear with a flat bottom and walls perpendicular to the bottom.
  • the connecting surface between the bottom and the walls has a small radius of curvature to allow an adjustment of the insert 14 with a game as low as possible.
  • the cavity comprises a central portion 12c and two annular end portions 12e and 12e ', in longitudinal extension on either side of the central portion.
  • the central portion 12c is intended to serve as a housing for the rectilinear insert 14 by adjustment.
  • the insert is formed of an assembly of ceramic fibers coated with metal, titanium in the embodiment.
  • the shape of the cover 16 makes it possible to wrap the insert 14 once disposed in its housing.
  • the cover 16 has an overall block shape and dimensions adjusted as close to those of the cavity 12, with a central portion 16c and end portions 16e and 16e 'in the longitudinal extensions of the central portion.
  • the end portions allow the cover to wrap the insert on its upper face Fi and on its end faces Fe and Fe ', in three different planes.
  • the height H of the end portions 16e and 16e 'of the cover corresponds to the height 16h of its central portion 16c increased by that of the insert 14, and is slightly greater than the depth of the cavity 12.
  • the end portions 16e and 16e 'of the lid each have a cutaway 16p and 16p' providing a space with the bottom of the cavity on the side of the insert. These sections define free spaces that will facilitate the deformation of the lid during compaction.
  • connection between the lid and the container to obtain the preform 20 is advantageously preceded by a hooping.
  • the lid 12 is lowered suddenly in temperature to cause a shrinkage of its dimensions.
  • a simple way is to immerse it in liquid nitrogen.
  • the lid is then easily placed in the cavity after being cooled. As it expands, the lid comes in a snug fit against the side walls of the container.
  • the isostatic compaction chamber (not shown) conventionally comprises heating control means in a wide range of temperatures, up to 1000 ° C and beyond, means for evacuation and means for putting under high pressure, up to 1000 bar and above.
  • the temperature of the diffusion welding cycle is the conventional welding temperature of the metal constituting the container and the lid, here the titanium alloy.
  • the heat treatment phases in particular pre-welding, are performed in the compaction plant. Pre-welding and compaction are thus chained continuously.
  • the upper face Fc of the cover 16 collapses during compression up to 1000 bars to finalize the hot isostatic compaction of the preform 20.
  • the insert is formed of a fiber bundle coated with a titanium alloy.
  • the blank thus obtained is ready to be machined to produce the desired metal part.
  • Pressurizing the lid on the container can be achieved by any means within the reach of the skilled person: by the introduction of an elastic blade, a mechanical spacer, etc.
  • inserts were compacted according to the method of the invention in each of the straight portions 31 and 31 'of each non-parallel branches 33 and 33', before machining the recesses 34, 35, 35 'and 36.
  • the inserts ensure the transmission of forces in traction and compression.
  • the process of the invention makes it possible under these conditions to make any part incorporating one or more inserts in longitudinal parts of this part.
  • the shapes of the lid can vary and wrap the insert partially or totally.
  • several lids can envelop the insert, providing for example a through cavity, an insert being disposed in the middle of the cavity and two lids disposed on either side of the insert from the two opposite faces of the container.

Landscapes

  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Manufacture Of Alloys Or Alloy Compounds (AREA)
  • Pressure Welding/Diffusion-Bonding (AREA)
  • Powder Metallurgy (AREA)

Claims (10)

  1. Herstellungsverfahren von Metallverbundteilen (30) durch Einbringen von inneren Verstärkungen aus Fasern (14), umfassend die Schritte: Bearbeiten mindestens eines Aufnahmehohlraums (12) für einen Einsatz (14) entsprechender Form mit Verstärkungsfasern in einem Metallkörper oder -behälter (10), Einbringen eines Deckels (16) auf den Einsatz (14) in den Hohlraum (12) des Behälters, wobei der Deckel Wände (16a) aufweist, die unter Druck gegen die ihnen gegenüberliegenden Wände (10a) des Behälters gehalten werden, einen heißisostatischen Presszyklus einer solchen Behälter-Einsatz-Deckel-Anordnung und eine Bearbeitung der Anordnung, um das Teil (30) zu erhalten, dadurch gekennzeichnet, dass er darin besteht, den Schritt der Druckbeaufschlagung des Deckels und des Behälters durch eine Wärmebehandlung vor dem Diffusionsschweißen fortzusetzen, die darin besteht, die Temperatur der Behälter-Einsatz-Deckel-Anordnung, anzuheben und aufrechtzuerhalten, wobei der Deckel (16) und der Behälter (10) fest verbunden werden.
  2. Herstellungsverfahren nach Anspruch 1, bei dem die Vorbehandlung in den heißisostatischen Presszyklus integriert ist, wobei auf eine erste nur thermische Phase eine heiße externe Druckbeaufschlagung folgt.
  3. Herstellungsverfahren nach Anspruch 1 oder 2, wobei zwischen den Wänden (16a, 10a) des Deckels (16) und den gegenüberliegenden des Behälters (10) ein Schrumpfen vor dem Schweißvorgang durchgeführt wird, um eine formschlüssige Druckverbindung zwischen den Wänden zu erzielen.
  4. Herstellungsverfahren nach dem vorstehenden Anspruch, bei dem das Schrumpfen durchgeführt wird, indem der Deckel (16) abgekühlt wird, um seine Abmessungen zu reduzieren, bevor er in den Hohlraum eingeführt wird, und dann seine Ausdehnung durch Wiedererlangen der Umgebungstemperatur bewirkt wird und/oder indem der Behälter (10) während dieses Temperaturanstiegs erhitzt wird, um die Abmessungen seines Hohlraums (12) durch Ausdehnung vor Einführen des Deckels (16) zu vergrößern.
  5. Herstellungsverfahren nach einem der vorstehenden Ansprüche, wobei der Hohlraum (12) einen ersten langen Hauptabschnitt (12c), der den Einsatz (14) aufnimmt, und mindestens einen zweiten Abschnitt (12e, 12e') in Verlängerung des ersten Abschnitts umfasst, wobei der Deckel (16) einen zentralen Abschnitt (16c), der den Einsatz (14) abdeckt, und mindestens eine Verlängerung (16e, 16e') mit einer dem zweiten Abschnitt (12e, 12e') des Hohlraums (12) entsprechenden Form umfasst, sodass der Einsatz (14) auf mindestens zwei Ebenen teilweise umhüllt ist.
  6. Herstellungsverfahren nach dem vorstehenden Anspruch, wobei der Deckel (16) einen Bereich progressiver Verformung (16p, 16p') zwischen dem Mittelteil (16c) und mindestens einer Verlängerung (16e, 16e') aufweist.
  7. Herstellungsverfahren nach einem der Ansprüche 4 bis 6, wobei der Einsatz (14) und der Hohlraum (12) geradlinig sind.
  8. Herstellungsverfahren nach dem vorstehenden Anspruch, wobei der Querschnitt des Einsatzes (14) nach Wahl polygonal, oval oder kreisförmig ist.
  9. Herstellungsverfahren nach einem der Ansprüche 5 bis 8, bei dem der Einsatz (14) aus zu Bündeln zusammengefassten und mit Metall, insbesondere Titan, beschichteten Fasern gebildet wird.
  10. Herstellungsverfahren nach einem der Ansprüche 4 bis 9, wobei mindestens ein länglicher Hohlraum (12) einen oder mehrere Einsätze (14) entsprechender Form aufnimmt, wobei der Hohlraum beziehungsweise die Hohlräume entsprechend einem oder mehreren geraden Abschnitten angeordnet ist beziehungsweise sind.
EP10784770.9A 2009-11-25 2010-11-24 Verfahren zur herstellung eines verbundmetallteils mit inneren verstärkungselementen in faserform Active EP2504462B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0958350A FR2952944B1 (fr) 2009-11-25 2009-11-25 Procede de fabrication d'une piece metallique composite a renforts internes en fibres, preforme de mise en oeuvre et piece metallique obtenue
PCT/EP2010/068120 WO2011064251A1 (fr) 2009-11-25 2010-11-24 Procédé de fabrication d'une pièce métallique composite à renforts internes en fibres, préforme de mise en oeuvre et pièce métallique obtenue

Publications (2)

Publication Number Publication Date
EP2504462A1 EP2504462A1 (de) 2012-10-03
EP2504462B1 true EP2504462B1 (de) 2018-07-11

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EP10784770.9A Active EP2504462B1 (de) 2009-11-25 2010-11-24 Verfahren zur herstellung eines verbundmetallteils mit inneren verstärkungselementen in faserform

Country Status (9)

Country Link
US (1) US8776343B2 (de)
EP (1) EP2504462B1 (de)
JP (1) JP5858925B2 (de)
CN (1) CN102770573B (de)
BR (1) BR112012011974A2 (de)
CA (1) CA2793463C (de)
FR (1) FR2952944B1 (de)
RU (1) RU2550053C2 (de)
WO (1) WO2011064251A1 (de)

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2925896B1 (fr) * 2007-12-28 2010-02-05 Messier Dowty Sa Procede de fabrication d'une piece metallique renforcee de fibres ceramiques
FR2933422B1 (fr) * 2008-07-04 2011-05-13 Messier Dowty Sa Procede de fabrication d'une piece metallique comportant des renforts internes formes de fibres ceramiques
EP2703622B1 (de) * 2012-08-31 2014-12-31 Caterpillar Motoren GmbH & Co. KG Zylinderkopf mit Sensorhülle
CN103131928B (zh) * 2013-02-06 2015-04-08 西南交通大学 一种具有微纳米结构的超细晶多孔铁合金的制备方法
GB2510894B (en) * 2013-02-18 2015-01-14 Messier Dowty Ltd A method of manufacture of an aircraft landing gear component

Family Cites Families (8)

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Publication number Priority date Publication date Assignee Title
FR854589A (fr) 1939-01-06 1940-04-18 Bombe incendiaire
GB0324810D0 (en) * 2003-10-24 2003-11-26 Rolls Royce Plc A method of manufacturing a fibre reinforced metal matrix composite article
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
FR2886290B1 (fr) 2005-05-27 2007-07-13 Snecma Moteurs Sa Procede de fabrication d'une piece avec un insert en materiau composite a matrice metallique et fibres ceramiques
GB0515211D0 (en) * 2005-07-23 2005-08-31 Rolls Royce Plc A method of making titanium components
FR2919284B1 (fr) * 2007-07-26 2010-09-24 Snecma Piece mecanique comportant un insert en materiau composite.
FR2925896B1 (fr) 2007-12-28 2010-02-05 Messier Dowty Sa Procede de fabrication d'une piece metallique renforcee de fibres ceramiques
US7739794B2 (en) * 2008-02-29 2010-06-22 General Electric Company Method for repair of rail wheels

Non-Patent Citations (1)

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Also Published As

Publication number Publication date
JP2013512334A (ja) 2013-04-11
CN102770573B (zh) 2015-07-22
EP2504462A1 (de) 2012-10-03
FR2952944A1 (fr) 2011-05-27
FR2952944B1 (fr) 2014-05-02
BR112012011974A2 (pt) 2017-10-10
CN102770573A (zh) 2012-11-07
US8776343B2 (en) 2014-07-15
JP5858925B2 (ja) 2016-02-10
CA2793463A1 (fr) 2011-06-03
RU2012126107A (ru) 2013-12-27
US20120255961A1 (en) 2012-10-11
WO2011064251A1 (fr) 2011-06-03
CA2793463C (fr) 2017-05-16
RU2550053C2 (ru) 2015-05-10

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