EP0997549B1 - Procédé pour produire des composants renforcés par des fibres longues - Google Patents

Procédé pour produire des composants renforcés par des fibres longues Download PDF

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Publication number
EP0997549B1
EP0997549B1 EP99118781A EP99118781A EP0997549B1 EP 0997549 B1 EP0997549 B1 EP 0997549B1 EP 99118781 A EP99118781 A EP 99118781A EP 99118781 A EP99118781 A EP 99118781A EP 0997549 B1 EP0997549 B1 EP 0997549B1
Authority
EP
European Patent Office
Prior art keywords
structural member
matrix material
component
fiber
reinforced
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.)
Expired - Lifetime
Application number
EP99118781A
Other languages
German (de)
English (en)
Other versions
EP0997549A1 (fr
Inventor
Klaus Weber
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.)
Deutsches Zentrum fuer Luft und Raumfahrt eV
Original Assignee
Deutsches Zentrum fuer Luft und Raumfahrt eV
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 Deutsches Zentrum fuer Luft und Raumfahrt eV filed Critical Deutsches Zentrum fuer Luft und Raumfahrt eV
Publication of EP0997549A1 publication Critical patent/EP0997549A1/fr
Application granted granted Critical
Publication of EP0997549B1 publication Critical patent/EP0997549B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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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
    • C22C47/06—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
    • C22C47/068—Aligning wires
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C47/00—Making alloys containing metallic or non-metallic fibres or filaments
    • 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
    • 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 invention relates to a method for producing a long fiber reinforced component which has a matrix material with at least one group of essentially parallel long fibers coated with matrix material embedded therein.
  • the fiber reinforcement material advantageously consists of fibers coated with a matrix material; this has the advantage that adjacent fibers do not touch each other but rather are surrounded by a material which is surrounded by matrix material. Titanium-based alloys are preferably used as the matrix material, while the fiber itself consists of silicon carbide (SiC).
  • SiC silicon carbide
  • the term “fiber” means a monofiber which consists of fiber material on the inside and has a coating of matrix material on the outside.
  • a method for producing long fiber reinforced components in which a cavity is made in a workpiece made of, in particular, matrix material, which is then filled by individual long fibers lying next to one another and essentially parallel to one another.
  • a hot isostatic pressing process takes place, in which the workpiece is exposed to extremely high temperatures and pressures.
  • the component or workpiece deforms because of the gaps be closed between the individual fibers. This means that the workpiece must be reworked in any case in order to ultimately be able to produce the component with the desired outer contour. This post-processing is usually very difficult and costly.
  • DE 29 15 412 C2 discloses a method for producing a molded body from fiber-reinforced metal material, in which a prefabricated tube is inserted into a cavity and is filled with individual fibers that are parallel to one another.
  • this known method also has the disadvantage that the shaped body provided with the fiber-filled tubes is exposed to relatively strong shrinkage during the hot isostatic pressing process.
  • the invention has for its object to provide a method for producing a long fiber reinforced component, with which the component can be manufactured close to the contour and dimensionally stable without any significant post-treatment.
  • the fiber-reinforced component is first produced with the desired outer contour from a metal material, in particular, which is preferably the matrix material. Then at least one cavity is introduced into this component, which is already produced close to the contour and is still provided without fiber reinforcement. This cavity is accessible from the outside of the component, namely to introduce a long-fiber-reinforced reinforcing element into it.
  • This reinforcing element is prefabricated according to the invention and exists from the matrix material of the long fiber coating in which the long fibers are embedded. This prefabricated reinforcing element is then hot isostatically pressed with the component.
  • the cavities that may still remain before the hot isostatic pressing process are reduced solely to the very small space between the reinforcing element and the component, there is hardly any change in shape or shrinkage of the component after the hot isostatic pressing process. This means that, in particular, no post-processing of the component is required in order to give it the desired outer contour. Machining of the component is only necessary in the areas of the access (s) to the at least one cavity. Because in the hot isostatic pressing process, the component or the spaces or gaps still remaining in it must be evacuated so that these gaps or spaces are filled with matrix material or fibers after the hot isostatic pressing process.
  • the advantage to be achieved according to the invention of the extremely low shrinkage of the hot isostatically pressed component therefore makes it possible to give the component the desired outer contour even before the fiber reinforcement is introduced, so that manufacturing techniques can be used to create the component with the desired outer contour, which are much cheaper than machining a fiber-reinforced workpiece in order to give it a desired outer contour.
  • the cavity is introduced from outside the component, in particular by spark erosion or by drilling.
  • Chemical or mechanical techniques can be used for drilling.
  • the cavities extend along straight lines and come out of the component on one side (blind hole formation) or on two opposite sides of the component (through hole).
  • the reinforcing elements are rod-shaped. Round, but also polygonal bars are conceivable here.
  • the "access" to such a cavity can, for example, be regarded as extending along the adjoining interfaces of the component halves.
  • the gas-tight closure of the access is carried out in particular by electron beam welding.
  • This welding technique can only be carried out in a vacuum. Exactly a vacuum is required, however, to evacuate the remaining free spaces between the reinforcing element and the remaining part of the component.
  • FIG. 1 shows, as an example of a long-fiber-reinforced component, a fan blade 10 which is provided with a multiplicity of rod-shaped long-fiber-reinforced reinforcing elements 12 (hereinafter referred to as fiber-reinforced rods).
  • the fiber-reinforced rods 12 extend straight from the blade tip 14 to the blade root 16 through the fan blade 10.
  • the fiber-reinforced rods 12 have been introduced as prefabricated reinforcing elements in cavities 18 introduced into the fan blade and fill them completely in the finished state of the fan blade 10.
  • long fibers 22 parallel to one another are embedded in the material 20 of the fiber-reinforced rods 12 (see also FIG. 2).
  • These reinforcing elements 12 are produced, for example, by introducing the long fibers 22 coated with a matrix material into a tube or tube of matrix material. Subsequently, the tube filled with long fibers 22 in this way, after evacuation and gas-tight closure, is subjected to a hot isostatic pressing process for several hours at temperatures of 1000 ° C. to 1300 ° C. and pressures of 150 MPa to 230 Mpa. This hot isostatic pressing process causes the matrix material of the long fibers to fuse 22 with each other and the matrix material of the tube. After the hot isostatic pressing process, there is a reinforcing element 12 which no longer has any cavities; If such a reinforcement element 12 is exposed to a hot isostatic pressing process again at a later point in time, there is no shrinkage or change in shape.
  • the fan blade 10 is produced in the desired shape from a suitable material, for example the matrix material of the coating of the long fibers 22 or a material compatible therewith.
  • a suitable material for example the matrix material of the coating of the long fibers 22 or a material compatible therewith.
  • the fan blade 10 is thus available with its final outer contour, although the fiber reinforcement is still missing (see FIG. 3).
  • the cavities 18 are now introduced into the fan blade 10.
  • the prefabricated fiber-reinforced rods 12 are now introduced into the cavities 18.
  • the outer diameter of the fiber-reinforced rods 12 is adjusted to the inner diameter of the cavities 18 in such a way that the fiber-reinforced rods 12 can be inserted into the cavities 18. It cannot be avoided here that the smallest spaces 24 (see FIG. 7) are formed between the fiber-reinforced rods 12 and the fan blade 10.
  • the fiber-reinforced rods 12 For the intimate connection of the fiber-reinforced rods 12 to the fan blade 10, the latter is subjected to a hot isostatic pressing process, for example under the conditions specified above. For this purpose, it is necessary to evacuate the spaces 24 between the fiber-reinforced rods 12 and the fan blade 10 and then to seal these spaces 24 in a gas-tight manner with respect to the surroundings of the fan blade 10. In the exemplary embodiment described here, this takes place in that foil-like cover plates 26 made of the material of the fan blade 10 are welded onto the blade tip 14 and onto the blade root 16 (see FIG. 6). If electron beam welding is used as the welding technique, this has the advantage that the fan blade 10 is automatically evacuated during welding, since electron beam welding is only possible in a vacuum.
  • FIG. 7 The situation after the insertion of the reinforcing elements 12 into the fan blade 10 and before the hot isostatic pressing process is shown in FIG. 7.
  • the spaces 24 are shown in Fig. 7 larger than technologically necessary for clarification.
  • Fig. 8 shows the situation after the hot isostatic pressing process.
  • the spaces 24 are filled with matrix material 20 or the material of the fan blade 10, this matrix material 20 intimately connecting with the material of the fan blade 10. Since the spaces 24 are extremely small, there is no significant shrinkage or shape changes of the fan blade 10 during hot isostatic pressing of the fan blade 10 provided with the reinforcing elements 12, so that the fan blade 10 retains its outer contour imparted before the hot isostatic pressing process.
  • This has the decisive advantage that after the hot isostatic pressing process, no further processing of the fan blade is required to give it its outer contour. Conversely, this means that the outer contour of the fiber-reinforced component is essentially already fixed at a point in time before the hot isostatic pressing process.

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)

Claims (5)

  1. Procédé de fabrication d'un composant renforcé par des fibres longues, qui comprend un matériau de matrice dans lequel est noyé au moins un groupe de fibres longues sensiblement parallèles, revêtues de matériau de matrice,
    procédé selon lequel
    - on fabrique le composant (10) avec sensiblement le contour extérieur souhaité, en matériau de matrice,
    - dans le composant (10) ainsi fabriqué, on réalise au moins une cavité (18) qui présente une forme pouvant être prédéterminée et qui est accessible à partir de l'extérieur du composant,
    - on insère dans ladite au moins une cavité (18), au moins un élément de renfort (12) préfabriqué et renforcé de fibres longues, qui présente plusieurs fibres longues noyées dans du matériau de matrice, les espaces intermédiaires entre les fibres longues étant comblés avec du matériau de matrice, et
    - on soumet le composant (10), y compris ledit au moins un élément de renfort (12), à une compression isostatique à chaud.
  2. Procédé selon la revendication 1, caractérisé en ce que ladite au moins une cavité (18) est réalisée dans le composant (10) à partir de l'extérieur, par érosion ou par perçage chimique ou mécanique.
  3. Procédé selon la revendication 1 ou 2, caractérisé en ce que le composant (10) est en deux parties et en ce que la cavité (18) s'étend à travers les deux parties du composant (10).
  4. Procédé selon l'une des revendications 1 à 3, caractérisé en ce que le composant (10), avant l'opération de compression isostatique à chaud, est soumis à un vide et l'accès à ladite au moins une cavité (18) est fermé de manière étanche aux gaz.
  5. Procédé selon l'une des revendications 1 à 4, caractérisé en ce que ledit au moins un élément de renfort (12) présente une forme de tige.
EP99118781A 1998-10-31 1999-09-23 Procédé pour produire des composants renforcés par des fibres longues Expired - Lifetime EP0997549B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19850252 1998-10-31
DE19850252 1998-10-31

Publications (2)

Publication Number Publication Date
EP0997549A1 EP0997549A1 (fr) 2000-05-03
EP0997549B1 true EP0997549B1 (fr) 2004-12-29

Family

ID=7886273

Family Applications (1)

Application Number Title Priority Date Filing Date
EP99118781A Expired - Lifetime EP0997549B1 (fr) 1998-10-31 1999-09-23 Procédé pour produire des composants renforcés par des fibres longues

Country Status (2)

Country Link
EP (1) EP0997549B1 (fr)
DE (1) DE59911362D1 (fr)

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102006040120B3 (de) * 2006-08-26 2008-04-24 Deutsches Zentrum für Luft- und Raumfahrt e.V. Verbundwerkstoff und Verfahren zu seiner Herstellung
FR2925897B1 (fr) * 2007-12-28 2010-07-30 Messier Dowty Sa Procede de fabrication de pieces avec insert en materiau composite a matrice metallique
FR2925896B1 (fr) * 2007-12-28 2010-02-05 Messier Dowty Sa Procede de fabrication d'une piece metallique renforcee de fibres ceramiques
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

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS589822B2 (ja) * 1976-11-26 1983-02-23 東邦ベスロン株式会社 炭素繊維強化金属複合材料プリプレグ
SE411051B (sv) * 1978-04-17 1979-11-26 Volvo Flygmotor Ab Forfarande for framstellning av ett foremal av fiberforsterkt metallmaterial
DE4021547A1 (de) * 1990-07-06 1992-01-16 Deutsche Forsch Luft Raumfahrt Verfahren zum herstellen von faserverstaerkten bauteilen
DE4335557C1 (de) * 1993-10-19 1995-02-02 Deutsche Forsch Luft Raumfahrt Verfahren zum Herstellen von langfaserverstärkten Bauteilen
DE4335558A1 (de) * 1993-10-19 1995-04-20 Deutsche Forsch Luft Raumfahrt Verfahren zum Herstellen von langfaserverstärkten Bauteilen

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Publication number Publication date
DE59911362D1 (de) 2005-02-03
EP0997549A1 (fr) 2000-05-03

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