WO2010031930A1 - Procede de fabrication d'une piece en materiau composite a matrice metallique - Google Patents
Procede de fabrication d'une piece en materiau composite a matrice metallique Download PDFInfo
- Publication number
- WO2010031930A1 WO2010031930A1 PCT/FR2009/050575 FR2009050575W WO2010031930A1 WO 2010031930 A1 WO2010031930 A1 WO 2010031930A1 FR 2009050575 W FR2009050575 W FR 2009050575W WO 2010031930 A1 WO2010031930 A1 WO 2010031930A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- fibers
- preform
- metal
- metal matrix
- composite material
- Prior art date
Links
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
- C22C47/20—Making alloys containing metallic or non-metallic fibres or filaments by subjecting to pressure and heat an assembly comprising at least one metal layer or sheet and one layer of fibres or filaments
-
- 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
- C22C49/14—Alloys containing metallic or non-metallic fibres or filaments characterised by the 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
- B22F2998/10—Processes characterised by the sequence of their steps
-
- 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
- Y10T156/00—Adhesive bonding and miscellaneous chemical manufacture
- Y10T156/10—Methods of surface bonding and/or assembly therefor
-
- 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
- Y10T428/00—Stock material or miscellaneous articles
- Y10T428/12—All metal or with adjacent metals
- Y10T428/12493—Composite; i.e., plural, adjacent, spatially distinct metal components [e.g., layers, joint, etc.]
-
- 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
- Y10T442/00—Fabric [woven, knitted, or nonwoven textile or cloth, etc.]
- Y10T442/20—Coated or impregnated woven, knit, or nonwoven fabric which is not [a] associated with another preformed layer or fiber layer or, [b] with respect to woven and knit, characterized, respectively, by a particular or differential weave or knit, wherein the coating or impregnation is neither a foamed material nor a free metal or alloy layer
- Y10T442/2033—Coating or impregnation formed in situ [e.g., by interfacial condensation, coagulation, precipitation, etc.]
Definitions
- the present invention relates to a method of manufacturing a piece of metal matrix composite material.
- the high temperatures at the turbojet outlet require the use of metal materials resistant to high temperatures.
- temperatures above 600 ° C. the use of nickel-based alloys becomes necessary to support the thermal and mechanical loadings. Indeed, most other metal alloys have their mechanical strength greatly reduced in these temperature ranges.
- Mass saving is a major objective of aerospace construction and there is still a need for materials that combine low density with high thermal and mechanical properties.
- One solution is to use metal matrix composite materials.
- ceramic fillers such as long or short fibers, particulate fillers, etc.
- these ceramic fillers also make it possible to extend the ranges of use of certain metallic materials such as titanium alloys by a few tens of degrees.
- CMM metal matrix composite materials
- JP 2004-192792 also discloses a CMM plate.
- the shaping of the plates to make the final piece, such as an ejection nozzle, for example, remains difficult.
- US 2005/0136256 discloses a CMM having a particular composition made, in particular, in the form of sheets.
- WO 2005/054536 discloses a CMM using glass fibers but does not describe a method of making a part.
- GB 2 324 102 describes a method of manufacturing a CMM element, said element having an axis of symmetry of revolution. To do this, the ceramic fibers are wound on a mandrel before projection of molten metal. This method is, however, limited to parts having an axis of symmetry of revolution, the mandrel being rotated. The mandrel to be rotated, such a process has limitations in the production of large parts, such as nozzles for example.
- the amount of metal on the fibers, their spacing and the final porosity are difficult to control.
- the orientation of the fibers can not also be controlled since they are necessarily wrapped around the mandrel.
- many mechanical properties of the composite materials depend on the orientation of the fibers.
- the present invention relates to a method of manufacturing a piece of metal matrix composite material characterized in that it comprises the steps of:
- the metal coatings of the various fibers can be easily brought into contact, which gives a better homogeneity of the metal matrix after its heat treatment and reduces the risks of porosity and zones without metal. that should be corrected in a subsequent step.
- the process comprises a step of pre-coating the fibers.
- This pre-coating may, for example, be achieved by passing the fibers in a bath of the desired metal or molten alloy.
- the method comprises a compression step between the mold and the preform of the molten metal.
- the compression forces to ensure good diffusion of the metal after melting are reduced.
- the compression step takes place during the diffusion step of the metal.
- the compression step carried out by thermal expansion of the preform, in particular as a replacement for hot isostatic compaction (CIC). This is made possible by the fact that the necessary compression forces are greatly reduced.
- CIC hot isostatic compaction
- At least a portion of the fibers are in the form of at least one braided strip, the strip may comprise particulate fillers.
- the preform is provided with pins so as to produce a skin made of a perforated metal matrix composite material.
- the formatting may give rise to a full pierced structure later, for example by water jet, laser, punching ...
- spikes may in particular be retractable or dissolvable thermally or chemically.
- materials that can be used for the fibers there may be mentioned in particular silicon carbide (SiC), carbon, alumina and boron nitride (BN). It will also be possible to use metal fibers, such as boron fibers, for example.
- the metal matrix may be, for example, made of alloys of aluminum, titanium, steels or superalloys.
- FIG. 1 is a schematic cross-sectional representation of a pre-coated fiber
- FIG. 2 is a schematic representation of an example of arrangement of pre-coated fibers
- FIG. 3 is a schematic representation of a preform of an element of a jet engine nacelle nozzle, said preform being in accordance with the process according to the invention coated with pre-coated fibers as represented in FIG. the example arrangement of Figure 2.
- a method according to the invention is used for the manufacture of a piece of composite metal matrix material, such as a turbojet nozzle or a nozzle portion, for example.
- a set of fibers 1 intended to constitute a reinforcing load of the metal matrix composite material are pre-coated with the metal alloy or the metal in question.
- Fibers 1 can be in many forms and materials.
- Fibers 1 may be in the form of long fibers, braided mattresses, loaded strips and strips, for example.
- the reinforcing fibers 1 are arranged on a preform 2 of the final piece.
- Long fibers 1 may be positioned by winding on the preform 2.
- Short fibers or braided fire may be positioned by stacking on the preform.
- the coating of the fibers 1 may be carried out by passing the fibers in a bath of the desired metal or alloy.
- the coated fibers 1 thus disposed on the preform 2 the cohesion of the final structure is provided by heat treatment for melting and diffusion of the metal elements. This operation takes place inside a mold of complementary shape to the preform 2.
- the preform 2 is kept in contact against the mold and compressive forces are applied.
- the compression forces required are greatly reduced compared to the prior art.
- the compression forces can therefore advantageously be applied by the preform 2 itself by virtue of its thermal expansion.
- the preform 2 will be made from a material whose thermal expansion is greater than that of the metal matrix of the workpiece.
- Applicable pressures are determined based on geomethics and relative thermal properties of the part and tooling.
- a press can replace differential expansion tooling.
- the skins of the part produced can be stiffened by adding profiles that can be soldered by diffusion or soldered during the heat treatment of the metal matrix composite material.
- the preform 2 may be provided with pins 3, retractable or not depending on the geometry of the part, around which the coated fibers 1 may be positioned. Depending on the positioning capacity of the fibers 1, a free placement may be sufficient to define a fiber-free space 1 between two rows of fibers 1.
- the shaping of the piece may give rise to a full skin which will be pierced later, for example by water jet, laser or punching.
- the pins 3 may be retractable or made from a thermally or chemically soluble material.
Landscapes
- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Materials Engineering (AREA)
- Mechanical Engineering (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- Manufacture Of Alloys Or Alloy Compounds (AREA)
Abstract
Description
Claims
Priority Applications (5)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
CN2009801353582A CN102149843A (zh) | 2008-09-17 | 2009-04-03 | 一种由含金属基质的复合材料制成的部件的制备方法 |
BRPI0917218A BRPI0917218A2 (pt) | 2008-09-17 | 2009-04-03 | método para fazer peça a partir de material compsoto com uma matriz de metal, método de prodrução e peça |
EP09784372A EP2331721A1 (fr) | 2008-09-17 | 2009-04-03 | Procede de fabrication d'une piece en materiau composite a matrice metallique |
CA 2734083 CA2734083A1 (fr) | 2008-09-17 | 2009-04-03 | Procede de fabrication d'une piece en materiau composite a matrice metallique |
US13/119,203 US20110171487A1 (en) | 2008-09-17 | 2009-04-03 | Method for making a part made of a composite material with a metal matrix |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR08/05096 | 2008-09-17 | ||
FR0805096A FR2935990B1 (fr) | 2008-09-17 | 2008-09-17 | Procede de fabrication d'une piece en materiau composite a matrice metallique |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2010031930A1 true WO2010031930A1 (fr) | 2010-03-25 |
Family
ID=40149661
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/FR2009/050575 WO2010031930A1 (fr) | 2008-09-17 | 2009-04-03 | Procede de fabrication d'une piece en materiau composite a matrice metallique |
Country Status (8)
Country | Link |
---|---|
US (1) | US20110171487A1 (fr) |
EP (1) | EP2331721A1 (fr) |
CN (1) | CN102149843A (fr) |
BR (1) | BRPI0917218A2 (fr) |
CA (1) | CA2734083A1 (fr) |
FR (1) | FR2935990B1 (fr) |
RU (1) | RU2011114627A (fr) |
WO (1) | WO2010031930A1 (fr) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN103402691A (zh) * | 2011-03-01 | 2013-11-20 | 斯奈克玛 | 用于制造金属部件,诸如涡轮发动机叶片加强件的方法 |
Families Citing this family (9)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2988407B1 (fr) * | 2012-03-22 | 2014-10-31 | Aircelle Sa | Procede de fabrication d'une preforme monobloc pour structure composite |
FR2995557A1 (fr) * | 2012-09-18 | 2014-03-21 | Aircelle Sa | Procede de fabrication de pieces composites, installation de fabrication mettant en oeuvre un tel procede, et pieces composites ainsi fabriquees |
CN102901552B (zh) * | 2012-10-25 | 2014-06-04 | 梅特勒-托利多(常州)精密仪器有限公司 | 称重传感器无线套件 |
CN102965601B (zh) * | 2012-12-20 | 2014-04-16 | 重庆市科学技术研究院 | 一种含wc纤维晶增强硬质合金的制备方法 |
CN105644066A (zh) * | 2014-10-22 | 2016-06-08 | 廖树汉 | 重量比铝轻价格降低过半代替钢板的钢玻复合板 |
CN105882017A (zh) * | 2014-10-28 | 2016-08-24 | 廖树汉 | 重量比铝轻价格低几倍代替铝板的铝瓷复合板 |
CN105538796A (zh) * | 2014-11-03 | 2016-05-04 | 廖树汉 | 比铝轻价低几倍代替不锈钢板的不锈钢玻复合瓦楞板 |
CN105599366A (zh) * | 2014-11-05 | 2016-05-25 | 廖树汉 | 比铝轻价低几倍代替铝板的铝瓷复合瓦楞板 |
FR3039839B1 (fr) * | 2015-08-06 | 2019-12-20 | Safran Aircraft Engines | Procede de fabrication d'une piece en materiau composite |
Citations (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB2263483A (en) * | 1992-01-09 | 1993-07-28 | Secr Defence | Ceramic fibre reinforcements precoated with alternating layers of matrix material; reinforced composites |
FR2709134A1 (fr) * | 1991-03-11 | 1995-02-24 | Minnesota Mining & Mfg | Composites de matrice métallique. |
WO1998011265A1 (fr) * | 1996-09-12 | 1998-03-19 | Minnesota Mining And Manufacturing Company | Bande de materiau composite a matrice metallique |
EP0921202A2 (fr) * | 1997-12-01 | 1999-06-09 | Inco Limited | Procédé de préparation de matériaux composites à matrice métallique contenant des fibres |
DE10326818A1 (de) * | 2003-06-15 | 2004-12-30 | Mtu Aero Engines Gmbh | Verbundwerkstoff, Verfahren zur Herstellung eines Verbundwerkstoffs und Verwendung desselben |
EP1527842A1 (fr) * | 2003-10-24 | 2005-05-04 | ROLLS-ROYCE plc | Procédé de fabrication d'un article composite métallique renforcé par de fibres |
EP1533067A1 (fr) * | 2003-11-20 | 2005-05-25 | Rolls-Royce Plc | Procédé de fabrication d'un article composite metallique renforcé par des fibres |
EP1533393A2 (fr) * | 2003-11-18 | 2005-05-25 | ROLLS-ROYCE plc | Procédé de préparation d'un article métallique à matrice composite renforcé de fibres et cassette à utiliser dans cette préparation |
Family Cites Families (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5439750A (en) * | 1993-06-15 | 1995-08-08 | General Electric Company | Titanium metal matrix composite inserts for stiffening turbine engine components |
CN1273636C (zh) * | 2002-09-05 | 2006-09-06 | 费维栋 | 硼酸镁晶须增强铝基复合材料及制备工艺 |
DE10360808B4 (de) * | 2003-12-19 | 2005-10-27 | Airbus Deutschland Gmbh | Faserverstärkter metallischer Verbundwerkstoff |
CN100587859C (zh) * | 2007-08-30 | 2010-02-03 | 中国科学院电工研究所 | 一种Fe/Cu包套结构二硼化镁多芯超导线的制备方法 |
-
2008
- 2008-09-17 FR FR0805096A patent/FR2935990B1/fr not_active Expired - Fee Related
-
2009
- 2009-04-03 BR BRPI0917218A patent/BRPI0917218A2/pt not_active Application Discontinuation
- 2009-04-03 CN CN2009801353582A patent/CN102149843A/zh active Pending
- 2009-04-03 RU RU2011114627/02A patent/RU2011114627A/ru unknown
- 2009-04-03 EP EP09784372A patent/EP2331721A1/fr not_active Withdrawn
- 2009-04-03 WO PCT/FR2009/050575 patent/WO2010031930A1/fr active Application Filing
- 2009-04-03 CA CA 2734083 patent/CA2734083A1/fr not_active Abandoned
- 2009-04-03 US US13/119,203 patent/US20110171487A1/en not_active Abandoned
Patent Citations (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2709134A1 (fr) * | 1991-03-11 | 1995-02-24 | Minnesota Mining & Mfg | Composites de matrice métallique. |
GB2263483A (en) * | 1992-01-09 | 1993-07-28 | Secr Defence | Ceramic fibre reinforcements precoated with alternating layers of matrix material; reinforced composites |
WO1998011265A1 (fr) * | 1996-09-12 | 1998-03-19 | Minnesota Mining And Manufacturing Company | Bande de materiau composite a matrice metallique |
EP0921202A2 (fr) * | 1997-12-01 | 1999-06-09 | Inco Limited | Procédé de préparation de matériaux composites à matrice métallique contenant des fibres |
DE10326818A1 (de) * | 2003-06-15 | 2004-12-30 | Mtu Aero Engines Gmbh | Verbundwerkstoff, Verfahren zur Herstellung eines Verbundwerkstoffs und Verwendung desselben |
EP1527842A1 (fr) * | 2003-10-24 | 2005-05-04 | ROLLS-ROYCE plc | Procédé de fabrication d'un article composite métallique renforcé par de fibres |
EP1533393A2 (fr) * | 2003-11-18 | 2005-05-25 | ROLLS-ROYCE plc | Procédé de préparation d'un article métallique à matrice composite renforcé de fibres et cassette à utiliser dans cette préparation |
EP1533067A1 (fr) * | 2003-11-20 | 2005-05-25 | Rolls-Royce Plc | Procédé de fabrication d'un article composite metallique renforcé par des fibres |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN103402691A (zh) * | 2011-03-01 | 2013-11-20 | 斯奈克玛 | 用于制造金属部件,诸如涡轮发动机叶片加强件的方法 |
CN103402691B (zh) * | 2011-03-01 | 2016-09-14 | 斯奈克玛 | 用于制造金属部件,诸如涡轮发动机叶片加强件的方法 |
Also Published As
Publication number | Publication date |
---|---|
CA2734083A1 (fr) | 2010-03-25 |
FR2935990B1 (fr) | 2011-05-13 |
EP2331721A1 (fr) | 2011-06-15 |
CN102149843A (zh) | 2011-08-10 |
US20110171487A1 (en) | 2011-07-14 |
RU2011114627A (ru) | 2012-10-27 |
FR2935990A1 (fr) | 2010-03-19 |
BRPI0917218A2 (pt) | 2015-11-24 |
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