EP3036057B1 - Insert de renfort composite et procede de fabrication - Google Patents

Insert de renfort composite et procede de fabrication Download PDF

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Publication number
EP3036057B1
EP3036057B1 EP14786966.3A EP14786966A EP3036057B1 EP 3036057 B1 EP3036057 B1 EP 3036057B1 EP 14786966 A EP14786966 A EP 14786966A EP 3036057 B1 EP3036057 B1 EP 3036057B1
Authority
EP
European Patent Office
Prior art keywords
strand
strands
metal
filaments
reinforcement insert
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
EP14786966.3A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP3036057A1 (fr
Inventor
Gilles Charles Casimir Klein
Germain Marcel SANCHEZ
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.)
FSP-ONE
Safran Aircraft Engines SAS
Original Assignee
SNECMA Services SA
SNECMA SAS
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Filing date
Publication date
Application filed by SNECMA Services SA, SNECMA SAS filed Critical SNECMA Services SA
Publication of EP3036057A1 publication Critical patent/EP3036057A1/fr
Application granted granted Critical
Publication of EP3036057B1 publication Critical patent/EP3036057B1/fr
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Classifications

    • D—TEXTILES; PAPER
    • D02—YARNS; MECHANICAL FINISHING OF YARNS OR ROPES; WARPING OR BEAMING
    • D02G—CRIMPING OR CURLING FIBRES, FILAMENTS, THREADS, OR YARNS; YARNS OR THREADS
    • D02G3/00—Yarns or threads, e.g. fancy yarns; Processes or apparatus for the production thereof, not otherwise provided for
    • D02G3/22—Yarns or threads characterised by constructional features, e.g. blending, filament/fibre
    • D02G3/38—Threads in which fibres, filaments, or yarns are wound with other yarns or filaments, e.g. wrap yarns, i.e. strands of filaments or staple fibres are wrapped by a helically wound binder yarn
    • 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
    • B22F5/00—Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product
    • B22F5/009—Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product of turbine components other than turbine blades
    • 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
    • B22F5/00—Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product
    • B22F5/04—Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product of turbine blades
    • 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
    • C22C49/00—Alloys containing metallic or non-metallic fibres or filaments
    • C22C49/02—Alloys containing metallic or non-metallic fibres or filaments characterised by the matrix material
    • C22C49/04—Light metals
    • C22C49/06—Aluminium
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C49/00—Alloys containing metallic or non-metallic fibres or filaments
    • C22C49/02—Alloys containing metallic or non-metallic fibres or filaments characterised by the matrix material
    • C22C49/08—Iron group metals
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C49/00—Alloys containing metallic or non-metallic fibres or filaments
    • C22C49/02—Alloys containing metallic or non-metallic fibres or filaments characterised by the matrix material
    • C22C49/10—Refractory metals
    • C22C49/11—Titanium
    • D—TEXTILES; PAPER
    • D02—YARNS; MECHANICAL FINISHING OF YARNS OR ROPES; WARPING OR BEAMING
    • D02G—CRIMPING OR CURLING FIBRES, FILAMENTS, THREADS, OR YARNS; YARNS OR THREADS
    • D02G3/00—Yarns or threads, e.g. fancy yarns; Processes or apparatus for the production thereof, not otherwise provided for
    • D02G3/02—Yarns or threads characterised by the material or by the materials from which they are made
    • D02G3/12—Threads containing metallic filaments or strips
    • D—TEXTILES; PAPER
    • D07—ROPES; CABLES OTHER THAN ELECTRIC
    • D07B—ROPES OR CABLES IN GENERAL
    • D07B1/00—Constructional features of ropes or cables
    • D07B1/06—Ropes or cables built-up from metal wires, e.g. of section wires around a hemp core
    • D07B1/0606—Reinforcing cords for rubber or plastic articles
    • D07B1/062—Reinforcing cords for rubber or plastic articles the reinforcing cords being characterised by the strand configuration
    • D07B1/0633—Reinforcing cords for rubber or plastic articles the reinforcing cords being characterised by the strand configuration having a multiple-layer configuration

Definitions

  • the present invention relates to a reinforcing insert, preferably for a turbomachine part, as well as to a method of manufacturing such a reinforcing insert.
  • a reinforcement insert made of composite material with a metal matrix.
  • a composite material generally comprises a metal alloy matrix, for example of titanium alloy Ti, nickel Ni or aluminum Al, in which fibers extend, for example ceramic fibers of SiC silicon carbide.
  • Such fibers have a tensile strength much greater than that of titanium (typically 4000 MPa against 1000 MPa) and a rigidity typically three times higher.
  • the fibers that take up the forces the metal alloy matrix ensuring the transfer of charges between the fibers, a binder function with the rest of the part, as well as a function of protection and separation of the fibers, which must not come into contact with each other.
  • the ceramic fibers are strong, but fragile and must necessarily be protected by metal.
  • These composite materials can be used in the manufacture of disks, shafts, cylinder bodies, housings, spacers, as reinforcements of monolithic parts such as blades, etc. They may also find application in other fields where a field of voluminal forces applies to a part, for example a pressure envelope such as a gun or a pressure fluid reservoir.
  • coated son comprising a frame formed of a ceramic fiber, coated with a metal sheath.
  • the metal coating gives the wire a greater stiffness but a better toughness, useful for its handling.
  • the coating of silicon carbide (SiC) fibers is most often carried out by a physical gas phase deposition method EBPVC (Electron Beam Physical Vapor Deposition).
  • EBPVC Electro Beam Physical Vapor Deposition
  • the prior art also proposes to perform the coating of SiC fibers by a direct coating process of the SiC fiber in a molten metal bath levitation.
  • a coating process is for example described in the document EP0931846 .
  • This document proposes to keep the liquid metal levitated in a suitable crucible, so as to at least partially remove the contact with the walls of the latter, at an appropriate temperature.
  • Levitation is achieved by electromagnetic means surrounding the crucible.
  • the ceramic fiber, held taut by means of pre-emption, is drawn through the metal bath.
  • the rate of passage of the fiber into the metal bath is set according to the desired metal thickness on the fiber. This process is faster than the previous one, but it produces an off-center fiber.
  • it does not allow to easily adjust the ratio between the percentage of SiC fiber and the percentage of metal matrix.
  • destabilizations may appear in the inserts manufactured according to this method.
  • the invention aims to overcome the drawbacks of the state of the art by providing a reinforcing insert according to claim 1 which has a reinforced strength and whose composition can be chosen.
  • a "strand” is an assembly whose strands or fibers are arranged in concentric layers around a strand or central fiber.
  • the invention proposes to previously wind the metal alloy fibers around the central fiber, and then to coat the assembly obtained with a metal reinforcement layer.
  • the reinforcement insert thus obtained has improved strength. It also has the advantage of having a central fiber centered relative to the metal part surrounding it.
  • such a reinforcing insert is particularly advantageous because it is possible to choose the ratio between the percentage of ceramic material and the percentage of metal alloy easily.
  • the reinforcing insert according to the invention may also have one or more of the following features taken individually or in any technically possible combination.
  • the strand may comprise N strands of metal alloy with N greater than or equal to 6.
  • N is preferably equal to 7, 19 or 37.
  • the diameter of the metal strands and their number N are determined so that the insert has a chosen number Vf.
  • the number Vf corresponds to the surface ratio between the ceramic fiber and the surrounding metal alloy strands.
  • these strands are preferably arranged to form a single layer around the central fiber.
  • Vf is then equal to 1/7 or 14.3%.
  • constructions with Vf of less than 14% are selected, the strand has number of strands beyond 18 or 19 around the core fiber and these strands are preferably arranged to form a plurality of concentric layers around the core fiber.
  • the central fiber is preferably made of silicon carbide, which has good mechanical properties.
  • the strands are made of a metal alloy based on titanium, nickel or aluminum so that the reinforcing insert has a good ratio strength / weight.
  • the metal reinforcing layer is preferably made of the same metallic base material as the metal alloy forming the strands.
  • Such a method is simple and fast, and it allows to obtain reinforcement inserts whose composition can be chosen.
  • the ceramic fiber of the insert thus produced is centered.
  • the method may also comprise a step (b) of fixing the strands by welding points.
  • This step can be performed by laser or electron beam.
  • this fixing step is not essential if the strand has a mechanical strength without expansion of the strands.
  • the coating step preferably comprises a step of passage of the strand in a liquid molten metal bath levitation.
  • the levitated liquid molten metal preferably comprises a filler of the same material as the base material of the strands.
  • the method may also comprise, between steps (b) and (c), a step of coating of the strand by a protective layer against oxidation.
  • This protective layer is particularly useful when the metal alloy of the strands is sensitive to oxidation. This is for example the case when the strands are made of an aluminum alloy.
  • the strand can then be covered with a protective layer, which is preferably a copper nanolayer. This protective layer disappears during the passage of the strand in the liquid metal bath.
  • Another aspect of the invention also relates to a metal part for a turbomachine comprising an insert according to the first aspect of the invention or made according to a method according to the second aspect of the invention.
  • the reinforcing insert is made from a central fiber 1 ceramic.
  • This central fiber 1 is made of silicon carbide.
  • the method comprises a first step (a) of making a strand by winding strands 2 of metal alloy around the central fiber 1.
  • the strands are preferably made of a metal alloy based on titanium, nickel or aluminum. aluminum.
  • the strands are helically wrapped around the core fiber to form a helix around the core fiber.
  • the strand may comprise more or fewer strands 2.
  • the number Vf is defined as the surface ratio between the central fiber and the metal strands.
  • a central fiber 1 of 140 ⁇ m in diameter has a section of 15400 ⁇ m 2 .
  • the evolution of the number Vf as a function of the number of strands in the case of a single layer stranding is represented on the figure 5 , as well as the evolution of the ratio R2 / R1 in depending on the number of strands at the periphery.
  • a silicon carbide fiber of 140 ⁇ m in diameter surrounded by 7 strands of 107 ⁇ m in diameter and coated with a protective layer of 3 ⁇ m gives a percentage of silicon carbide fiber SiC of 20%.
  • the pulleys used to wind the central fiber during the stranding operation must be large enough not to generate bending radii in the core fiber less than 20 mm.
  • the strand exhibits expansion phenomena around the central fiber, it is possible to perform small spot welding of the strands in line with the stranding machine.
  • a technique by laser welding or electron beams can be used
  • the method may comprise a step (c) of coating the strand with a protective layer.
  • a protective layer may be a copper nanolayer. This protective layer disappears in the next step.
  • the method then comprises a step (c) of coating the strand by a metal reinforcement layer 3.
  • the strand is passed through a molten liquid metal bath levitation of a charge of the same material as the strands placed helically around the central fiber 1.
  • the charge of the liquid metal bath preferably comprises titanium.
  • the load preferably comprises aluminum.
  • the method then comprises a step of solidification of the reinforcing insert, during which the reinforcing insert becomes rigid.
  • the reinforcement insert thus obtained is easy to manufacture, very resistant. In addition, its composition can easily be modified.
  • the reinforcement insert thus obtained can then be used to reinforce parts, particularly in the field of aeronautics.
  • the reinforcing insert can then be shaped by tran-canning around a turbomachine part, and especially around a casing or a turbomachine disc.
  • the reinforcement insert is placed in the part to be reinforced.
  • the resulting assembly can then be compacted by hot isostatic pressing. In order to obtain a totally compact composite part.

Landscapes

  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Materials Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Manufacturing & Machinery (AREA)
  • Textile Engineering (AREA)
  • Crystallography & Structural Chemistry (AREA)
  • Manufacture Of Alloys Or Alloy Compounds (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Ropes Or Cables (AREA)
EP14786966.3A 2013-08-21 2014-08-19 Insert de renfort composite et procede de fabrication Active EP3036057B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1358105A FR3009832B1 (fr) 2013-08-21 2013-08-21 Insert de renfort composite et procede de fabrication
PCT/FR2014/052100 WO2015025107A1 (fr) 2013-08-21 2014-08-19 Insert de renfort composite et procede de fabrication

Publications (2)

Publication Number Publication Date
EP3036057A1 EP3036057A1 (fr) 2016-06-29
EP3036057B1 true EP3036057B1 (fr) 2017-07-19

Family

ID=49911618

Family Applications (1)

Application Number Title Priority Date Filing Date
EP14786966.3A Active EP3036057B1 (fr) 2013-08-21 2014-08-19 Insert de renfort composite et procede de fabrication

Country Status (9)

Country Link
US (1) US10119205B2 (pt)
EP (1) EP3036057B1 (pt)
JP (1) JP6410272B2 (pt)
CN (1) CN105492147B (pt)
BR (1) BR112016003482B8 (pt)
CA (1) CA2921534C (pt)
FR (1) FR3009832B1 (pt)
RU (1) RU2676547C2 (pt)
WO (1) WO2015025107A1 (pt)

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10184194B2 (en) * 2014-07-28 2019-01-22 The Boeing Company Multi-material integrated knit thermal protection for industrial and vehicle applications
JP2018053604A (ja) * 2016-09-29 2018-04-05 株式会社ハイレックスコーポレーション 柵構造体
US20190059476A1 (en) * 2017-08-29 2019-02-28 Wells Lamont Industry Group Llc Thermal and cut resistant glove
US11478028B2 (en) 2019-04-05 2022-10-25 Wells Lamont Industry Group Llc Disposable cut-resistant glove
FR3105039B1 (fr) * 2019-12-20 2021-12-10 Safran Procédé de fabrication d’une roue aubagée de turbomachine composite à renfort céramique
US20230191528A1 (en) * 2021-12-22 2023-06-22 Spirit Aerosystems, Inc. Method for manufacturing metal matrix composite parts

Family Cites Families (18)

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US4375779A (en) * 1981-04-24 1983-03-08 Minnesota Mining And Manufacturing Company Composite sewing thread of ceramic fibers
US4430851A (en) * 1982-01-29 1984-02-14 Minnesota Mining And Manufacturing Company Twisted ceramic fiber sewing thread
NL8302366A (nl) * 1983-07-04 1985-02-01 Hoogovens Groep Bv Vuurvast afdichtkoord.
FR2684578B1 (fr) * 1991-12-04 1996-04-12 Snecma Procede de fabrication de pieces en materiau composite a matrice metallique
FR2710635B1 (fr) * 1993-09-27 1996-02-09 Europ Propulsion Procédé de fabrication d'un matériau composite à interphase lamellaire entre fibres de renfort et matrice, et matériau tel qu'obtenu par le procédé.
RU2078217C1 (ru) * 1993-12-30 1997-04-27 Яков Петрович Гохштейн Турбинная лопатка с тепловой защитой
CA2164080C (en) * 1995-04-15 2004-07-06 Takeo Munakata Overhead cable and low sag, low wind load cable
FR2773820B1 (fr) * 1998-01-22 2000-02-25 Snecma Procede d'enduction metallique de fibres par voie liquide
AU2001262195A1 (en) * 2000-04-17 2001-10-30 N V. Bekaert S.A. A textile fabric for use as a gas burner membrane
WO2004018718A1 (en) * 2002-08-20 2004-03-04 3M Innovative Properties Company Metal matrix composites, and methods for making the same
US7100352B2 (en) * 2004-01-21 2006-09-05 Robins Steven D Protective composite yarn
US7093416B2 (en) * 2004-06-17 2006-08-22 3M Innovative Properties Company Cable and method of making the same
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
FR2891541B1 (fr) * 2005-10-05 2008-01-11 Snecma Sa Procede d'enduction metallique de fibres par voie liquide
FR2916453B1 (fr) * 2007-05-22 2009-09-04 Snecma Sa Procede et un dispositif d'enduction metallique de fibres par voie liquide
FR2945823B1 (fr) * 2009-05-25 2011-10-14 Snecma Procede et dispositif d'enduction metallique par voie liquide de fibres en materiau ceramique
CN201553934U (zh) * 2009-11-26 2010-08-18 江苏法尔胜股份有限公司 一种复合绳芯钢丝绳
FR2962483B1 (fr) * 2010-07-12 2012-07-13 Snecma Procede de realisation d?un renfort metallique creux d?aube de turbomachine

Also Published As

Publication number Publication date
EP3036057A1 (fr) 2016-06-29
US20160201260A1 (en) 2016-07-14
CA2921534C (fr) 2021-04-06
RU2016109799A3 (pt) 2018-06-28
CN105492147B (zh) 2018-06-26
JP6410272B2 (ja) 2018-10-24
BR112016003482B8 (pt) 2024-01-30
WO2015025107A1 (fr) 2015-02-26
BR112016003482A8 (pt) 2018-06-12
JP2016536479A (ja) 2016-11-24
FR3009832A1 (fr) 2015-02-27
CN105492147A (zh) 2016-04-13
US10119205B2 (en) 2018-11-06
FR3009832B1 (fr) 2015-08-28
RU2016109799A (ru) 2017-09-26
BR112016003482A2 (pt) 2017-08-01
BR112016003482B1 (pt) 2024-01-16
CA2921534A1 (fr) 2015-02-26
RU2676547C2 (ru) 2019-01-09

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