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EP2245204B1 - Verfahren zur herstellung von teilen mit einem einsatz aus einem metallmatrixverbundmaterial - Google Patents

Verfahren zur herstellung von teilen mit einem einsatz aus einem metallmatrixverbundmaterial Download PDF

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Publication number
EP2245204B1
EP2245204B1 EP08867160A EP08867160A EP2245204B1 EP 2245204 B1 EP2245204 B1 EP 2245204B1 EP 08867160 A EP08867160 A EP 08867160A EP 08867160 A EP08867160 A EP 08867160A EP 2245204 B1 EP2245204 B1 EP 2245204B1
Authority
EP
European Patent Office
Prior art keywords
insert
mould
metal
mold
coated
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
EP08867160A
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English (en)
French (fr)
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EP2245204A1 (de
Inventor
Richard Masson
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Safran Landing Systems SAS
Original Assignee
Messier Bugatti Dowty SA
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Publication date
Application filed by Messier Bugatti Dowty SA filed Critical Messier Bugatti Dowty SA
Publication of EP2245204A1 publication Critical patent/EP2245204A1/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
    • 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
    • C22C47/14—Making alloys containing metallic or non-metallic fibres or filaments by powder metallurgy, i.e. by processing mixtures of metal powder and fibres or filaments
    • 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
    • B22F2998/00—Supplementary information concerning processes or compositions relating to powder metallurgy

Definitions

  • the present invention relates to a method of manufacturing a metal part having a reinforcement of metal matrix composite material of the ceramic fiber type in a metal matrix.
  • an insert made of composite material with a metal matrix is incorporated in some parts an insert made of composite material with a metal matrix.
  • This material comprises ceramic fibers, of silicon carbide for example, embedded in a metal matrix, such as a titanium alloy. Ceramic fibers have the property of a very high tensile strength and compression greater than the metal.
  • the metal matrix provides a binder function with the part as well as protection and insulation of the fibers.
  • a known method of manufacturing such parts with reinforcement comprises producing a coil of wire coated around a mandrel.
  • the coil is then incorporated in a container or metal main body in which a groove forming a housing has been previously machined.
  • the depth of the groove is greater than the height of the winding.
  • a lid is placed on the container and welded to its periphery.
  • the cover has a post complementary shape to that of the groove, and its height is adapted to that of the coil placed in the groove so as to fill the groove.
  • a hot isostatic pressing step is then carried out during which the winding is compacted by the tenon.
  • the metallic sheaths of the coated wires are welded together and with the walls of the groove by diffusion to form a dense set composed of metal alloy in which the ceramic fibers extend annularly.
  • the resulting part is then machined to the desired shape.
  • the patent FR 2886290 on behalf of Snecma proposes to carry out the winding directly on the main body. Instead of a groove, there are two shoulders in it. The first has a bearing surface for the direct winding of a coated wire. This surface is parallel to the winding direction. When the winding is completed, the groove is reconstructed by placing a piece on the main body which is shaped complementary to that of a second shoulder forming a step relative to the first shoulder. Then we have the cover with the pin on the insert that has just wound and compacts the whole.
  • the present invention therefore aims to improve the manufacture of a part with a reinforcement of this type so as to reduce the cost.
  • parts can be produced directly: having both high dimensional accuracy, high mechanical performance, and excellent metallurgical homogeneity.
  • the geometry of the piece resulting from the process can be chosen so that it is closer to the final piece, requiring no or little machining operation.
  • the method allows the use of one or more inserts of various shapes depending on the shape of the piece and the desired reinforcement.
  • Each insert can thus be annular. It may be more particularly axisymmetric or have at least one rectilinear portion.
  • the insert is rectilinear, in the form of a straight segment, it has preferably been formed from coated yarns subjected to hot isostatic compression treatment together.
  • pads are provided inside the mold which reduce the volume to be filled by the metal powder in the areas where the material will be removed by machining. These studs delimit cavities in said metal part between the reinforced zones: by the ceramic fibers.
  • EP 1,669,144 which relates to the manufacture of a metal article, such as a hollow fan blade with an internal reinforcement by powder metallurgy as well.
  • the process involves the production of a preform: then the shaping of the latter to make the hollow article.
  • Such a method is not suitable for the implementation of the invention.
  • FIG. 1 there is shown a container 4 of the prior art, of elongate shape, for producing a piece with a metal matrix composite insert.
  • a groove 41 has been machined in the container to receive an insert 3.
  • the groove and the insert are of complementary shape so that the insert is fit without play in the groove.
  • a cover 5 covers the assembly and has a projecting surface not visible in the figure to form a bearing on the insert in the groove.
  • the assembly is evacuated, the lid is electron beam welded for example. Then the assembly is placed in a suitable chamber where it is carried out isostatic hot pressing by subjecting it to a high pressure and a high temperature (1000 ° C and 1000 bar).
  • the manufacturing techniques with an insert comprising at least one rectilinear portion are described in the patent applications FR 07/05453 and FR 07/05454 of July 26, 2007 in the name of the plaintiff.
  • the blank thus produced is then machined to obtain the desired shape.
  • parts having complex shapes such as aircraft landing gear elements can be obtained.
  • a steel mold is prepared with a hollow shape close to that of the part to be manufactured.
  • the Figures 2 and 3 show such a mold 10 for producing a generally elongate piece.
  • This mold is hollow with a flat bottom 10a and a wall 10b of determined thickness and height corresponding to the thickness of the finished part. It comprises studs 11, 12 and 13 inside the cavity. According to the example of this figure the pads are at a height that allows them to come into contact with a lid 14 closing the mold. The height may however be less as shown on the figure 5 .
  • This insert here comprises two rectilinear portions between two half-circle portions.
  • the straight portions may be parallel or not and the semicircular portions may be of the same diameter or not.
  • the insert is made, without limitation, according to one of the methods taught by the FR 2886290 .
  • the insert comprises at least one rectilinear portion, it is more particularly made according to one of the methods presented in the FR 07/05453 or FR 07/05454 of July 26, 2007 in the name of the plaintiff.
  • the insert can be obtained from a plurality of coated wires each comprising a ceramic fiber coated with a metal sheath with a winding step around a part of revolution, a part of the winding being effected in one direction. straight.
  • the insert forms a rectilinear segment, it can be obtained from an insert blank with a rectilinear portion which is compacted and then cut into straight segments.
  • the insert is positioned inside the cavity being spaced apart from the walls of the mold.
  • One way to hold the insert in the mold is to arrange it on a support 16 which, if necessary, is of width corresponding to that of the insert and over the entire length of the latter or on pawns distributed under the insert.
  • This support is preferably in the same metal as the powder.
  • the support may consist of a L-shaped section piece 16 'as shown in FIG. figure 4 .
  • the support is advantageously constituted by the mandrel on which the coated wire has been wound to form the insert as described in the patent. FR2886920 which is not part of this invention.
  • the mold is filled with metal powder 18.
  • the metal may be a titanium alloy such as TA6V alloy or a nickel alloy such as the unknown 625 or a stainless steel. It is an alloy in a granulometric form suitable for use in powder metallurgy.
  • the powder can be introduced into the mold in part before the introduction of the insert, with pre-compaction if necessary. Then the mold is filled.
  • the lid 14 is placed on the mold thus filled and the cavity is evacuated. The enclosure is finally sealed tightly by welding.
  • the mold thus prepared is placed in a hot isostatic compression chamber.
  • the chamber thus makes it possible to maintain the workpiece at a temperature of 1000 ° C. and a pressure of 1000 bars for several hours. Under these conditions the mold is deformed due to the volume reduction between 20 and 25% of both the insert and the powder.
  • the powder is completely densified and no porosity remains. All the parts in contact are welded by soldering diffusion.
  • the coated wires are welded together forming a matrix within which the ceramic fibers are contained.
  • the metal constituting the matrix of the insert is the same as that constituting the powder. It may be distinct, however.
  • the mold is then removed by selective acid or mechanical dissolution. If necessary, the workpiece is machined to obtain the desired shape.
  • the pads 51, 52, 53 of the mold 50 extend only in part over the height of the mold cavity.
  • the insert is visible by transparency in the figure
  • a mold 70 and its associated cover 71 are used which have symmetrical pads 72, 73 with respect to a median wall 74.
  • the molding 70 'of the figure 8 is symmetrical.

Landscapes

  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Crystallography & Structural Chemistry (AREA)
  • Manufacture Of Alloys Or Alloy Compounds (AREA)
  • Powder Metallurgy (AREA)

Claims (9)

  1. Verfahren zur Herstellung eines mit Keramikfasern verstärkten Metallteils (20; 50'; 70'), das folgende aufeinanderfolgende Schritte umfasst:
    - Formen mindestens eines Einsatzes (15) durch Zusammenfügen von metallbeschichteten Keramikfasern zu einem Bündel,
    - Einbringen des Einsatzes (15) in eine Metallform (10; 50; 70) auf eine solche Weise, dass der Einsatz (15) in dem Hohlraum mit einem Abstand zu den Wänden (10a, 10b) der Form angeordnet ist,
    - Füllen der Form (10; 50; 70) mit einem Metallpulver (18),
    - Platzieren eines Deckels, der die Form verschließt,
    - Evakuieren des Raums und dichtes Verschließen der Form (10; 50; 70) durch Schweißen,
    - isostatisches Heißpressen der Einheit bei einer Temperatur und einem Druck, die ausreichen, um die Pulverpartikel und die beschichteten Fasern des Einsatzes (15) zu verbinden,
    - Entfernen der Form (10; 50; 70) und gegebenenfalls Verarbeitung zur gewünschten Form.
  2. Verfahren nach dem vorhergehenden Anspruch, wobei der Einsatz (15) ringförmig, insbesondere achsensymmetrisch ist.
  3. Verfahren nach Anspruch 1, wobei der Einsatz (15) mindestens einen geraden Abschnitt aufweist.
  4. Verfahren nach Anspruch 1, wobei der Einsatz (15) gerade ist und aus beschichteten Drähten geformt wurde, die gemeinsam isostatisch heißgepresst wurden.
  5. Verfahren nach einem der vorhergehenden Ansprüche, wobei der Einsatz (15) mittels eines Trägers (16, 16') in der Form (10) angeordnet wird.
  6. Verfahren nach dem vorhergehenden Anspruch, wobei der Träger (16') der Wickeldorn des Einsatzes ist.
  7. Verfahren nach einem der vorhergehenden Ansprüche, wobei mindestens zwei Einsätze in der Form angeordnet werden.
  8. Verfahren nach dem vorhergehenden Anspruch, wobei die beiden Einsätze so angeordnet werden, dass sie übereinanderliegen.
  9. Verfahren nach einem der vorhergehenden Ansprüche, wobei in der Form (10, 50, 70) Erhebungen (11, 12, 13; 51, 52, 53; 72, 73) vorgesehen werden, wobei die Erhebungen die Hohlräume in dem Metallteil zwischen den Bereichen, die mit Keramikfasern verstärkt sind, begrenzen.
EP08867160A 2007-12-28 2008-12-24 Verfahren zur herstellung von teilen mit einem einsatz aus einem metallmatrixverbundmaterial Active EP2245204B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0709173A FR2925897B1 (fr) 2007-12-28 2007-12-28 Procede de fabrication de pieces avec insert en materiau composite a matrice metallique
PCT/EP2008/068292 WO2009083571A1 (fr) 2007-12-28 2008-12-24 Procede de fabrication de pieces avec insert en materiau composite a matrice metallique

Publications (2)

Publication Number Publication Date
EP2245204A1 EP2245204A1 (de) 2010-11-03
EP2245204B1 true EP2245204B1 (de) 2012-06-06

Family

ID=39620313

Family Applications (1)

Application Number Title Priority Date Filing Date
EP08867160A Active EP2245204B1 (de) 2007-12-28 2008-12-24 Verfahren zur herstellung von teilen mit einem einsatz aus einem metallmatrixverbundmaterial

Country Status (11)

Country Link
US (1) US8557175B2 (de)
EP (1) EP2245204B1 (de)
JP (1) JP5657392B2 (de)
CN (1) CN101918609B (de)
BR (1) BRPI0821414A8 (de)
CA (1) CA2710455C (de)
ES (1) ES2388887T3 (de)
FR (1) FR2925897B1 (de)
IL (1) IL206629A0 (de)
RU (1) RU2492273C2 (de)
WO (1) WO2009083571A1 (de)

Families Citing this family (16)

* 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
FR2933423B1 (fr) * 2008-07-04 2010-09-17 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
RU2571680C2 (ru) 2009-07-28 2015-12-20 Снекма Балка подвески турбинного двигателя к конструкции летательного аппарата
FR2950077B1 (fr) * 2009-09-11 2014-07-18 Messier Dowty Sa Procede de fabrication d'une bielle metallique renforcee par des fibres, et bielle ainsi obtenue
GB201007570D0 (en) * 2010-05-06 2010-06-23 Rolls Royce Plc A mould assembly
FR2970266B1 (fr) * 2011-01-10 2013-12-06 Snecma Procede de fabrication d'une piece metallique annulaire monobloc a insert de renfort en materiau composite, et piece obtenue
FR2975317B1 (fr) * 2011-05-18 2013-05-31 Snecma Procede de fabrication par soudage diffusion d'une piece monobloc pour une turbomachine
DE102012221990A1 (de) * 2012-11-30 2014-06-05 Robert Bosch Gmbh Verbindungsmittel zum Verbinden von wenigstens zwei Komponenten unter Verwendung eines Sinterprozesses
GB2510894B (en) * 2013-02-18 2015-01-14 Messier Dowty Ltd A method of manufacture of an aircraft landing gear component
CN106660125B (zh) * 2014-05-30 2023-03-17 诺沃皮尼奥内技术股份有限公司 制造涡轮机构件的方法、涡轮机构件和涡轮机
KR20170004160A (ko) * 2015-07-01 2017-01-11 엘지전자 주식회사 이동단말기 및 그 제어방법
FR3039839B1 (fr) 2015-08-06 2019-12-20 Safran Aircraft Engines Procede de fabrication d'une piece en materiau composite
FR3039838B1 (fr) * 2015-08-06 2019-05-10 Safran Aircraft Engines Procede de fabrication d'une piece en materiau composite
FR3105039B1 (fr) * 2019-12-20 2021-12-10 Safran Procédé de fabrication d’une roue aubagée de turbomachine composite à renfort céramique
RU2761530C1 (ru) * 2020-12-10 2021-12-09 Федеральное государственное автономное образовательное учреждение высшего образования "Национальный исследовательский технологический университет "МИСиС" Способ получения цилиндрических армированных элементов для изготовления деталей моноколеса газотурбинного двигателя

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JPS62167830A (ja) * 1986-01-20 1987-07-24 Toshiba Corp 耐熱性金属基複合材料の製造方法
PL164448B1 (pl) * 1988-11-10 1994-07-29 Lanxide Technology Co Ltd Sposób wytwarzania kompozytu z osnową metalową
DE4324755C1 (de) * 1993-07-23 1994-09-22 Mtu Muenchen Gmbh Verfahren zur Herstellung faserverstärkter Triebwerkskomponenten
DE4335557C1 (de) * 1993-10-19 1995-02-02 Deutsche Forsch Luft Raumfahrt Verfahren zum Herstellen von langfaserverstärkten Bauteilen
FR2713662B1 (fr) * 1993-12-08 1996-01-12 Snecma Procédé d'obtention d'une pièce circulaire métallique renforcée par des fibres.
JPH10330865A (ja) * 1997-05-28 1998-12-15 Hitachi Ltd 複合体の製造方法及び複合体
DE59911362D1 (de) * 1998-10-31 2005-02-03 Deutsch Zentr Luft & Raumfahrt Verfahren zum Herstellen eines langfaserverstärkten Bauteils
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
GB0515211D0 (en) * 2005-07-23 2005-08-31 Rolls Royce Plc A method of making titanium components

Also Published As

Publication number Publication date
EP2245204A1 (de) 2010-11-03
US20110027119A1 (en) 2011-02-03
CN101918609B (zh) 2013-04-10
BRPI0821414A2 (pt) 2015-06-16
CA2710455A1 (fr) 2009-07-09
FR2925897A1 (fr) 2009-07-03
BRPI0821414A8 (pt) 2016-02-10
IL206629A0 (en) 2010-12-30
CA2710455C (fr) 2016-12-20
JP5657392B2 (ja) 2015-01-21
RU2492273C2 (ru) 2013-09-10
WO2009083571A1 (fr) 2009-07-09
JP2011508083A (ja) 2011-03-10
ES2388887T3 (es) 2012-10-19
CN101918609A (zh) 2010-12-15
FR2925897B1 (fr) 2010-07-30
RU2010131478A (ru) 2012-02-10
US8557175B2 (en) 2013-10-15

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