EP0775754A1 - Verfahren zur Herstellung eines Metallmatrixverbundrotors - Google Patents

Verfahren zur Herstellung eines Metallmatrixverbundrotors Download PDF

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Publication number
EP0775754A1
EP0775754A1 EP96402499A EP96402499A EP0775754A1 EP 0775754 A1 EP0775754 A1 EP 0775754A1 EP 96402499 A EP96402499 A EP 96402499A EP 96402499 A EP96402499 A EP 96402499A EP 0775754 A1 EP0775754 A1 EP 0775754A1
Authority
EP
European Patent Office
Prior art keywords
disc
metal
crown
plate
sleeve
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
EP96402499A
Other languages
English (en)
French (fr)
Other versions
EP0775754B1 (de
Inventor
Yves Christian Louis Honnorat
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
Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
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 Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA, SNECMA SAS filed Critical Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
Publication of EP0775754A1 publication Critical patent/EP0775754A1/de
Application granted granted Critical
Publication of EP0775754B1 publication Critical patent/EP0775754B1/de
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
    • C22C47/064—Winding 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
    • 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
    • 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
    • Y10T29/49316—Impeller making
    • Y10T29/49318—Repairing or disassembling
    • 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
    • Y10T29/49316—Impeller making
    • Y10T29/4932—Turbomachine making

Definitions

  • the invention relates to a method for manufacturing a composite rotor with a metal matrix.
  • These fibers make it possible to build resistant rotors, with high performance and whose weight is not very high. They are generally wrapped around a hub of the rotor and embedded in the metal matrix. Metallic material of composition identical to that of the matrix is added between the windings of the fiber to give good cohesion.
  • the manufacturing method therefore requires forming the windings of the fibers, placing these windings in the material of the matrix and uniting the assembly by hot compression which produces agglomeration between the fibers and the matrix while eliminating the interstices. between the windings and the metallic material added. It is however necessary to guard against the proliferation of the fiber, that is to say irregular displacements of the windings which disturb the regularity of their position in the finished part.
  • the characteristic of the invention is to avoid these contractions in diameter of the turns and their consequences, thanks to an improved hot compression, which is exerted only in the axial direction.
  • the metal matrix rotor including fiber windings which are finally obtained forms a unitary and compact mass with the fiber windings much more regularly arranged.
  • the block is therefore formed by agglomeration resulting from isothermal forging of the hub, the sleeve, the crown and the coating of the fibers, which are normally formed of the same material of the matrix and form a single block with the end of the process.
  • the fibers continue to adhere to their coating and are therefore perfectly integrated into the formed part.
  • the metal matrix is initially formed from four pieces, three of which are visible in FIG. 1: a hub 1, a crown 2 and a disc 3.
  • the hub 1 is formed by a lower circular plate 4 from the center of which stands a rod 5 cylindrical.
  • the crown 2 has a slightly larger diameter than the rod 5 and an external diameter identical to that of the plate 4.
  • a motor 8 rotates the axis 7.
  • a fiber 9 has been prepared. It is unwound from a reel 10 rotating at will, and it is passed through a pulley 11 freely rotating on a frame 12 itself movable in translation along two vertical and parallel slides 13 and 14.
  • the frame 12 is connected by a connecting rod 15 at an intermediate point 16 of a lever 17, one end of which is articulated at a fixed point 18 and the other end to a nut 19 movable along an Archimedes screw 20 vertical and movable under the action of a motor 21.
  • Two switches 22 and 23 sensitive to the contact of the connecting rod 17 are provided against the Archimedes screw 20 to provide limit switches.
  • the advance of the fiber 9 is produced by rotating the motor 8, which unwinds it from the coil 10 by forming windings around the rod 5. Simultaneously, the motor 21 is started to gradually lower the connecting rod 17 and therefore the pulley 11 from the upper switch 22 to the lower switch 23. The pulley 11 gradually drives the fiber 9 downwards and contributes to forming windings over the entire height of the rod 5, between the disc 3 and the tray. In this embodiment, the end of the fiber 9 is wedged between the disc 3 and the upper surface of the rod 5, but other ways of entraining the fiber by binding it to pieces 1, 2 and 3 of the matrix can be considered.
  • the crown 2 has a height greater than that of the disc 3 and is held so as to project around it upwards by a wedging pin 24 housed in a cavity formed both in the crown 2 and the disc 3, at their lower side.
  • Another pin 30 is used to center the disc 3 on the rod 5; it is housed in a cavity formed on the axis of these parts.
  • the centering pin 30 can be chosen with a diameter sufficient for the drive in rotation of the disc 3 to be ensured.
  • the axis 7 is replaced by a thinner axis on which the hub 1 and the disc 2, drilled in their center, are threaded. This process guarantees very regular windings without imposing any dexterity, unlike the previous delicate processes to accomplish. Crown 2 serves as coil side during winding and therefore prevents any displacement of the wound layers.
  • Fiber 9 is cut when the windings are made. We then proceed to arrive at the state illustrated in FIG. 2.
  • the centering pin 24 is removed and a sleeve 26, which is the fourth piece of the metallic matrix, is slid around the crown 2, the windings 25 and of plate 4; then a hermetic sheath 27 is formed around the entire matrix, however making provision to pierce it with a degassing conduit 28 leading to a pump 29. It can be seen that, when the sleeve 26 is placed at the level of the plate 4, its top arrives at the height of the disc 3 but the crown 2 projects upwards.
  • Hot isostatic compression is then undertaken in order, according to the diagram in FIG. 3, to obtain a compact mass in the sheath 27.
  • the hot isostatic compression methods are now well known and will not be discussed further.
  • the main effect obtained is an agglomeration of the windings 25 which results in a reduction in the volume which they occupy and in a progressive collapse of the crown 2.
  • the isostatic compression becomes a purely axial compression of the windings 25 to because of the continuity of the sleeve 26, which replaces a circle of cores used in previous methods and which contracts radially until the cores touch.
  • the proliferation of the fiber is much smaller with the invention.
  • the height of the crown 2 is calculated so that its upper surface is flush with the upper surfaces of the disc 3 and the sleeve 26 when a satisfactory agglomeration of the windings 25 has been obtained, which is shown in FIG. 3.
  • the compression can then be stopped.
  • the sheath 27 is removed by machining and the metal matrix corresponding to the old pieces 1, 2, 3 and 26 can be machined at will to form the desired part.
  • the part 1, 2, 3 and 26 can be provided from the start with an external surface similar to that of the piece in the final state; the sheath 27 then has the consequent shape.
  • An effective manufacturing example concerns a TAGV alloy matrix and SIC silicon carbide fibers also coated with titanium.
  • the coatings of the windings 25 form a compact mass during compression. Perfect cohesion of the part is thus obtained.

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)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Press Drives And Press Lines (AREA)
EP96402499A 1995-11-22 1996-11-21 Verfahren zur Herstellung eines Metallmatrixverbundrotors Expired - Lifetime EP0775754B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR9513832A FR2741383B1 (fr) 1995-11-22 1995-11-22 Procede de fabrication d'un rotor composite a matrice metallique
FR9513832 1995-11-22

Publications (2)

Publication Number Publication Date
EP0775754A1 true EP0775754A1 (de) 1997-05-28
EP0775754B1 EP0775754B1 (de) 2000-02-02

Family

ID=9484795

Family Applications (1)

Application Number Title Priority Date Filing Date
EP96402499A Expired - Lifetime EP0775754B1 (de) 1995-11-22 1996-11-21 Verfahren zur Herstellung eines Metallmatrixverbundrotors

Country Status (6)

Country Link
US (1) US5745994A (de)
EP (1) EP0775754B1 (de)
JP (1) JP3308174B2 (de)
CA (1) CA2190567C (de)
DE (1) DE69606502T2 (de)
FR (1) FR2741383B1 (de)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2901497A1 (fr) * 2006-05-24 2007-11-30 Snecma Sa Procede de fabrication d'un disque de rotor de turbomachine

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2784616B1 (fr) * 1998-10-15 2000-11-17 Snecma Procede d'obtention de pieces metalliques minces, legeres et rigides
US6158102A (en) * 1999-03-24 2000-12-12 General Electric Co. Apparatus and methods for aligning holes through wheels and spacers and stacking the wheels and spacers to form a turbine rotor
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

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2289425A1 (fr) * 1974-10-30 1976-05-28 Snecma Procede de realisation de frettes bobinees
FR2607071A1 (fr) 1986-11-21 1988-05-27 Textron Inc Procede de formage d'articles renforces par filaments et articles ainsi formes
FR2684578A1 (fr) 1991-12-04 1993-06-11 Snecma Procede de fabrication de pieces en materiau composite a matrice metallique.
EP0657554A1 (de) * 1993-12-08 1995-06-14 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Verfahren zur Herstellung eines ringförmigenfaserverstärkten Metallkörpers

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4831707A (en) * 1980-11-14 1989-05-23 Fiber Materials, Inc. Method of preparing metal matrix composite materials using metallo-organic solutions for fiber pre-treatment
US4900599A (en) * 1986-11-21 1990-02-13 Airfoil Textron Inc. Filament reinforced article
US4809903A (en) * 1986-11-26 1989-03-07 United States Of America As Represented By The Secretary Of The Air Force Method to produce metal matrix composite articles from rich metastable-beta titanium alloys
US5305520A (en) * 1990-09-01 1994-04-26 Rolls-Royce Plc Method of making fibre reinforced metal component
US5217770A (en) * 1991-08-15 1993-06-08 The B. F. Goodrich Company Braided shaped filamentary structures and methods of making
DE4208100C2 (de) * 1992-03-13 1994-05-26 Mtu Muenchen Gmbh Rohling zur Herstellung von faserverstärkten Beschichtungen oder Metallbauteilen

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2289425A1 (fr) * 1974-10-30 1976-05-28 Snecma Procede de realisation de frettes bobinees
FR2607071A1 (fr) 1986-11-21 1988-05-27 Textron Inc Procede de formage d'articles renforces par filaments et articles ainsi formes
FR2684578A1 (fr) 1991-12-04 1993-06-11 Snecma Procede de fabrication de pieces en materiau composite a matrice metallique.
EP0657554A1 (de) * 1993-12-08 1995-06-14 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Verfahren zur Herstellung eines ringförmigenfaserverstärkten Metallkörpers

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2901497A1 (fr) * 2006-05-24 2007-11-30 Snecma Sa Procede de fabrication d'un disque de rotor de turbomachine
US8065799B2 (en) 2006-05-24 2011-11-29 Snecma Method of fabricating a turbomachine rotor disk

Also Published As

Publication number Publication date
FR2741383B1 (fr) 1997-12-12
JP3308174B2 (ja) 2002-07-29
CA2190567A1 (en) 1997-05-23
JPH09192892A (ja) 1997-07-29
EP0775754B1 (de) 2000-02-02
US5745994A (en) 1998-05-05
CA2190567C (en) 2004-08-03
DE69606502T2 (de) 2000-06-21
FR2741383A1 (fr) 1997-05-23
DE69606502D1 (de) 2000-03-09

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