WO2015025107A1 - Insert de renfort composite et procede de fabrication - Google Patents
Insert de renfort composite et procede de fabrication Download PDFInfo
- Publication number
- WO2015025107A1 WO2015025107A1 PCT/FR2014/052100 FR2014052100W WO2015025107A1 WO 2015025107 A1 WO2015025107 A1 WO 2015025107A1 FR 2014052100 W FR2014052100 W FR 2014052100W WO 2015025107 A1 WO2015025107 A1 WO 2015025107A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- strands
- strand
- metal
- fiber
- reinforcement insert
- Prior art date
Links
- 230000002787 reinforcement Effects 0.000 title claims abstract description 19
- 239000002131 composite material Substances 0.000 title claims abstract description 11
- 238000004519 manufacturing process Methods 0.000 title claims description 8
- 239000000835 fiber Substances 0.000 claims abstract description 65
- 229910052751 metal Inorganic materials 0.000 claims abstract description 29
- 239000002184 metal Substances 0.000 claims abstract description 29
- 229910001092 metal group alloy Inorganic materials 0.000 claims abstract description 24
- 229910010293 ceramic material Inorganic materials 0.000 claims abstract description 4
- 230000003014 reinforcing effect Effects 0.000 claims description 28
- 238000000034 method Methods 0.000 claims description 22
- 238000000576 coating method Methods 0.000 claims description 17
- 239000010410 layer Substances 0.000 claims description 16
- 239000011248 coating agent Substances 0.000 claims description 14
- 239000000919 ceramic Substances 0.000 claims description 13
- HBMJWWWQQXIZIP-UHFFFAOYSA-N silicon carbide Chemical compound [Si+]#[C-] HBMJWWWQQXIZIP-UHFFFAOYSA-N 0.000 claims description 13
- 229910010271 silicon carbide Inorganic materials 0.000 claims description 12
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 claims description 9
- 239000000463 material Substances 0.000 claims description 9
- 239000011241 protective layer Substances 0.000 claims description 9
- 229910052782 aluminium Inorganic materials 0.000 claims description 8
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims description 7
- 239000010936 titanium Substances 0.000 claims description 7
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 claims description 6
- 238000005339 levitation Methods 0.000 claims description 6
- 229910052719 titanium Inorganic materials 0.000 claims description 6
- 239000007788 liquid Substances 0.000 claims description 4
- 229910052759 nickel Inorganic materials 0.000 claims description 4
- 230000003647 oxidation Effects 0.000 claims description 4
- 238000007254 oxidation reaction Methods 0.000 claims description 4
- 238000003466 welding Methods 0.000 claims description 4
- 229910045601 alloy Inorganic materials 0.000 claims description 2
- 239000000956 alloy Substances 0.000 claims description 2
- 229910001338 liquidmetal Inorganic materials 0.000 description 5
- 239000011159 matrix material Substances 0.000 description 4
- 239000000203 mixture Substances 0.000 description 3
- 239000002356 single layer Substances 0.000 description 3
- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical compound [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 description 2
- 238000010276 construction Methods 0.000 description 2
- 229910052802 copper Inorganic materials 0.000 description 2
- 239000010949 copper Substances 0.000 description 2
- 238000000151 deposition Methods 0.000 description 2
- 238000005328 electron beam physical vapour deposition Methods 0.000 description 2
- 238000010894 electron beam technology Methods 0.000 description 2
- 239000002052 molecular layer Substances 0.000 description 2
- 229910000838 Al alloy Inorganic materials 0.000 description 1
- 229910001069 Ti alloy Inorganic materials 0.000 description 1
- 238000005452 bending Methods 0.000 description 1
- 239000011230 binding agent Substances 0.000 description 1
- 238000009924 canning Methods 0.000 description 1
- 238000005056 compaction Methods 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 230000008021 deposition Effects 0.000 description 1
- 230000001687 destabilization Effects 0.000 description 1
- 239000000945 filler Substances 0.000 description 1
- 239000012530 fluid Substances 0.000 description 1
- 238000001513 hot isostatic pressing Methods 0.000 description 1
- 238000005457 optimization Methods 0.000 description 1
- 230000001681 protective effect Effects 0.000 description 1
- 238000000926 separation method Methods 0.000 description 1
- 238000007711 solidification Methods 0.000 description 1
- 230000008023 solidification Effects 0.000 description 1
- 125000006850 spacer group Chemical group 0.000 description 1
- 238000004804 winding Methods 0.000 description 1
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
- 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.
- 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 method is for example described in 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 occur in inserts made by this method.
- the invention aims to overcome the disadvantages of the state of the art by providing a reinforcing insert which has a reinforced strength and whose composition can be chosen.
- a composite reinforcing insert preferably for a turbomachine, comprising: a strand formed by a central fiber made of ceramic material surrounded by metal alloy strands wound helically around the 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.
- a second aspect of the invention also relates to a method for producing a reinforcing insert, preferably for a turbomachine, from a ceramic core fiber, the method comprising the following steps:
- 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 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 invention also relates to a method for producing a metal part for a turbomachine comprising the following steps:
- FIG. 5 gives the evolution of the ratio of the radius of the metal strands and that of the fiber, as well as the Vf obtained as a function of the number of strands for monolayer constructions.
- the reinforcing insert is made from a ceramic central fiber 1.
- This central fiber 1 is made of silicon carbide.
- the method comprises a first step (a) of forming a strand by winding metal alloy strands 2 around the central fiber 1.
- the strands are preferably made of a metal alloy based on titanium, nickel or 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 ⁇ in diameter has a section of 15400 ⁇ 2 .
- the strand generally comprises N strands with N greater than or equal to 6.
- the strands 2 are arranged in concentric layer (s) around the central fiber 1. It is also possible to vary the diameter of the central fiber 1 and the diameter of the strands 2 as a function of the desired ratio Vf between the percentage of silicon carbide fiber with respect to the percentage of material of the strand.
- the evolution of the number Vf as a function of the number of strands in the case of a single layer stranding is represented in FIG. 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 ⁇ in diameter surrounded by 7 strands of 107 ⁇ in diameter and coated with a protective layer of 3 ⁇ 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 load 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.
- a strand comprising:
- 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)
- Ropes Or Cables (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
Claims
Priority Applications (7)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP14786966.3A EP3036057B1 (fr) | 2013-08-21 | 2014-08-19 | Insert de renfort composite et procede de fabrication |
RU2016109799A RU2676547C2 (ru) | 2013-08-21 | 2014-08-19 | Упрочняющая композитная вставка и способ ее изготовления |
CN201480046349.7A CN105492147B (zh) | 2013-08-21 | 2014-08-19 | 复合加强插件和制造方法 |
US14/912,694 US10119205B2 (en) | 2013-08-21 | 2014-08-19 | Composite reinforcing insert and manufacturing method |
CA2921534A CA2921534C (fr) | 2013-08-21 | 2014-08-19 | Insert de renfort composite et procede de fabrication |
BR112016003482A BR112016003482B8 (pt) | 2013-08-21 | 2014-08-19 | Inserto de reforço compósito, peça de turbomáquina contendo um tal inserto de reforço e método de fabricação de um inserto de reforço compósito |
JP2016535516A JP6410272B2 (ja) | 2013-08-21 | 2014-08-19 | 複合体強化インサートおよび製造方法 |
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 |
FR1358105 | 2013-08-21 |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2015025107A1 true WO2015025107A1 (fr) | 2015-02-26 |
Family
ID=49911618
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/FR2014/052100 WO2015025107A1 (fr) | 2013-08-21 | 2014-08-19 | Insert de renfort composite et procede de fabrication |
Country Status (9)
Country | Link |
---|---|
US (1) | US10119205B2 (fr) |
EP (1) | EP3036057B1 (fr) |
JP (1) | JP6410272B2 (fr) |
CN (1) | CN105492147B (fr) |
BR (1) | BR112016003482B8 (fr) |
CA (1) | CA2921534C (fr) |
FR (1) | FR3009832B1 (fr) |
RU (1) | RU2676547C2 (fr) |
WO (1) | WO2015025107A1 (fr) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20230191528A1 (en) * | 2021-12-22 | 2023-06-22 | Spirit Aerosystems, Inc. | Method for manufacturing metal matrix composite parts |
Families Citing this family (5)
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 |
Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2684578A1 (fr) * | 1991-12-04 | 1993-06-11 | Snecma | Procede de fabrication de pieces en materiau composite a matrice metallique. |
EP0931846A1 (fr) | 1998-01-22 | 1999-07-28 | SOCIETE NATIONALE D'ETUDE ET DE CONSTRUCTION DE MOTEURS D'AVIATION -Snecma | Procédé d'enduction métallique de fibres par voie liquide |
EP1995342A1 (fr) | 2007-05-22 | 2008-11-26 | Snecma | Procédé et un dispositif d'enduction métallique de fibres par voie liquide |
FR2962483A1 (fr) * | 2010-07-12 | 2012-01-13 | Snecma | Procede de realisation d’un renfort metallique creux d’aube de turbomachine |
Family Cites Families (14)
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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. |
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 (fr) * | 1995-04-15 | 2004-07-06 | Takeo Munakata | Cable aerien a faible fleche et a faible prise au vent |
AU2001262195A1 (en) * | 2000-04-17 | 2001-10-30 | N V. Bekaert S.A. | A textile fabric for use as a gas burner membrane |
WO2004018718A1 (fr) * | 2002-08-20 | 2004-03-04 | 3M Innovative Properties Company | Composites a matrice metallique et leurs procedes de production |
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 |
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 |
-
2013
- 2013-08-21 FR FR1358105A patent/FR3009832B1/fr active Active
-
2014
- 2014-08-19 WO PCT/FR2014/052100 patent/WO2015025107A1/fr active Application Filing
- 2014-08-19 BR BR112016003482A patent/BR112016003482B8/pt active IP Right Grant
- 2014-08-19 CN CN201480046349.7A patent/CN105492147B/zh active Active
- 2014-08-19 CA CA2921534A patent/CA2921534C/fr active Active
- 2014-08-19 JP JP2016535516A patent/JP6410272B2/ja active Active
- 2014-08-19 US US14/912,694 patent/US10119205B2/en active Active
- 2014-08-19 EP EP14786966.3A patent/EP3036057B1/fr active Active
- 2014-08-19 RU RU2016109799A patent/RU2676547C2/ru active
Patent Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2684578A1 (fr) * | 1991-12-04 | 1993-06-11 | Snecma | Procede de fabrication de pieces en materiau composite a matrice metallique. |
EP0931846A1 (fr) | 1998-01-22 | 1999-07-28 | SOCIETE NATIONALE D'ETUDE ET DE CONSTRUCTION DE MOTEURS D'AVIATION -Snecma | Procédé d'enduction métallique de fibres par voie liquide |
EP1995342A1 (fr) | 2007-05-22 | 2008-11-26 | Snecma | Procédé et un dispositif d'enduction métallique de fibres par voie liquide |
FR2962483A1 (fr) * | 2010-07-12 | 2012-01-13 | Snecma | Procede de realisation d’un renfort metallique creux d’aube de turbomachine |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20230191528A1 (en) * | 2021-12-22 | 2023-06-22 | Spirit Aerosystems, Inc. | Method for manufacturing metal matrix composite parts |
Also Published As
Publication number | Publication date |
---|---|
FR3009832B1 (fr) | 2015-08-28 |
CA2921534C (fr) | 2021-04-06 |
FR3009832A1 (fr) | 2015-02-27 |
CN105492147A (zh) | 2016-04-13 |
JP2016536479A (ja) | 2016-11-24 |
EP3036057B1 (fr) | 2017-07-19 |
RU2676547C2 (ru) | 2019-01-09 |
CA2921534A1 (fr) | 2015-02-26 |
BR112016003482A2 (pt) | 2017-08-01 |
BR112016003482B1 (pt) | 2024-01-16 |
BR112016003482A8 (pt) | 2018-06-12 |
RU2016109799A (ru) | 2017-09-26 |
RU2016109799A3 (fr) | 2018-06-28 |
JP6410272B2 (ja) | 2018-10-24 |
CN105492147B (zh) | 2018-06-26 |
EP3036057A1 (fr) | 2016-06-29 |
US20160201260A1 (en) | 2016-07-14 |
US10119205B2 (en) | 2018-11-06 |
BR112016003482B8 (pt) | 2024-01-30 |
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