EP1384539A1 - Pièce composite à matrice métallique, et son procédé de fabrication - Google Patents
Pièce composite à matrice métallique, et son procédé de fabrication Download PDFInfo
- Publication number
- EP1384539A1 EP1384539A1 EP03291800A EP03291800A EP1384539A1 EP 1384539 A1 EP1384539 A1 EP 1384539A1 EP 03291800 A EP03291800 A EP 03291800A EP 03291800 A EP03291800 A EP 03291800A EP 1384539 A1 EP1384539 A1 EP 1384539A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- metal matrix
- mechanical part
- core
- metal
- reinforcing elements
- 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
Links
- 238000004519 manufacturing process Methods 0.000 title claims abstract description 18
- 238000000034 method Methods 0.000 title claims abstract description 16
- 239000011156 metal matrix composite Substances 0.000 title claims description 33
- 239000000463 material Substances 0.000 claims abstract description 90
- 229910052751 metal Inorganic materials 0.000 claims abstract description 58
- 239000002184 metal Substances 0.000 claims abstract description 58
- 239000011159 matrix material Substances 0.000 claims abstract description 50
- 230000003014 reinforcing effect Effects 0.000 claims abstract description 34
- 229910052782 aluminium Inorganic materials 0.000 claims abstract description 23
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims abstract description 23
- 239000010953 base metal Substances 0.000 claims abstract description 16
- 230000002093 peripheral effect Effects 0.000 claims abstract description 4
- 239000000203 mixture Substances 0.000 claims description 24
- 229910045601 alloy Inorganic materials 0.000 claims description 17
- 239000000956 alloy Substances 0.000 claims description 17
- 239000002245 particle Substances 0.000 claims description 10
- 238000005242 forging Methods 0.000 claims description 9
- HBMJWWWQQXIZIP-UHFFFAOYSA-N silicon carbide Chemical compound [Si+]#[C-] HBMJWWWQQXIZIP-UHFFFAOYSA-N 0.000 claims description 8
- 238000009987 spinning Methods 0.000 claims description 8
- 239000000047 product Substances 0.000 claims description 7
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 claims description 5
- PNEYBMLMFCGWSK-UHFFFAOYSA-N aluminium oxide Inorganic materials [O-2].[O-2].[O-2].[Al+3].[Al+3] PNEYBMLMFCGWSK-UHFFFAOYSA-N 0.000 claims description 4
- 230000000750 progressive effect Effects 0.000 claims description 4
- 230000002829 reductive effect Effects 0.000 claims description 4
- 239000011265 semifinished product Substances 0.000 claims description 4
- 239000010936 titanium Substances 0.000 claims description 4
- 229910052719 titanium Inorganic materials 0.000 claims description 4
- UONOETXJSWQNOL-UHFFFAOYSA-N tungsten carbide Chemical compound [W+]#[C-] UONOETXJSWQNOL-UHFFFAOYSA-N 0.000 claims description 4
- 229910018072 Al 2 O 3 Inorganic materials 0.000 claims description 3
- 239000000843 powder Substances 0.000 claims description 3
- 238000005096 rolling process Methods 0.000 claims description 3
- ZOXJGFHDIHLPTG-UHFFFAOYSA-N Boron Chemical compound [B] ZOXJGFHDIHLPTG-UHFFFAOYSA-N 0.000 claims description 2
- 229910052796 boron Inorganic materials 0.000 claims description 2
- 238000005272 metallurgy Methods 0.000 claims 1
- 239000002131 composite material Substances 0.000 abstract description 17
- XUIMIQQOPSSXEZ-UHFFFAOYSA-N Silicon Chemical compound [Si] XUIMIQQOPSSXEZ-UHFFFAOYSA-N 0.000 description 10
- 230000002787 reinforcement Effects 0.000 description 8
- 229910000838 Al alloy Inorganic materials 0.000 description 6
- 239000004411 aluminium Substances 0.000 description 5
- 230000008901 benefit Effects 0.000 description 5
- 230000000670 limiting effect Effects 0.000 description 4
- 230000009467 reduction Effects 0.000 description 4
- 229910001069 Ti alloy Inorganic materials 0.000 description 3
- 229910010271 silicon carbide Inorganic materials 0.000 description 3
- 230000015572 biosynthetic process Effects 0.000 description 2
- 230000003628 erosive effect Effects 0.000 description 2
- 230000036961 partial effect Effects 0.000 description 2
- 238000004663 powder metallurgy Methods 0.000 description 2
- 239000002994 raw material Substances 0.000 description 2
- 229910052580 B4C Inorganic materials 0.000 description 1
- 241000287107 Passer Species 0.000 description 1
- 241001494479 Pecora Species 0.000 description 1
- HIGRAKVNKLCVCA-UHFFFAOYSA-N alumine Chemical compound C1=CC=[Al]C=C1 HIGRAKVNKLCVCA-UHFFFAOYSA-N 0.000 description 1
- 238000005452 bending Methods 0.000 description 1
- INAHAJYZKVIDIZ-UHFFFAOYSA-N boron carbide Chemical compound B12B3B4C32B41 INAHAJYZKVIDIZ-UHFFFAOYSA-N 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
- 238000005056 compaction Methods 0.000 description 1
- 150000001875 compounds Chemical class 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 238000007796 conventional method Methods 0.000 description 1
- 230000007797 corrosion Effects 0.000 description 1
- 238000005260 corrosion Methods 0.000 description 1
- 229910052593 corundum Inorganic materials 0.000 description 1
- 230000003247 decreasing effect Effects 0.000 description 1
- 230000001627 detrimental effect Effects 0.000 description 1
- 238000009826 distribution Methods 0.000 description 1
- 239000012530 fluid Substances 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
- 238000001513 hot isostatic pressing Methods 0.000 description 1
- 230000003993 interaction Effects 0.000 description 1
- 238000000462 isostatic pressing Methods 0.000 description 1
- 150000001247 metal acetylides Chemical class 0.000 description 1
- 229910001092 metal group alloy Inorganic materials 0.000 description 1
- 230000037361 pathway Effects 0.000 description 1
- 238000009497 press forging Methods 0.000 description 1
- 230000035939 shock Effects 0.000 description 1
- 238000005245 sintering Methods 0.000 description 1
- 239000000126 substance Substances 0.000 description 1
- MTPVUVINMAGMJL-UHFFFAOYSA-N trimethyl(1,1,2,2,2-pentafluoroethyl)silane Chemical compound C[Si](C)(C)C(F)(F)C(F)(F)F MTPVUVINMAGMJL-UHFFFAOYSA-N 0.000 description 1
- 238000011144 upstream manufacturing Methods 0.000 description 1
- 229910001845 yogo sapphire Inorganic materials 0.000 description 1
Images
Classifications
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- 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
- B22F7/00—Manufacture of composite layers, workpieces, or articles, comprising metallic powder, by sintering the powder, with or without compacting wherein at least one part is obtained by sintering or compression
- B22F7/06—Manufacture of composite layers, workpieces, or articles, comprising metallic powder, by sintering the powder, with or without compacting wherein at least one part is obtained by sintering or compression of composite workpieces or articles from parts, e.g. to form tipped tools
- B22F7/062—Manufacture of composite layers, workpieces, or articles, comprising metallic powder, by sintering the powder, with or without compacting wherein at least one part is obtained by sintering or compression of composite workpieces or articles from parts, e.g. to form tipped tools involving the connection or repairing of preformed parts
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C32/00—Non-ferrous alloys containing at least 5% by weight but less than 50% by weight of oxides, carbides, borides, nitrides, silicides or other metal compounds, e.g. oxynitrides, sulfides, whether added as such or formed in situ
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C2204/00—End product comprising different layers, coatings or parts of cermet
-
- 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
- Y10T29/49826—Assembling or joining
- Y10T29/49908—Joining by deforming
-
- 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
- Y10T29/49826—Assembling or joining
- Y10T29/49908—Joining by deforming
- Y10T29/49909—Securing cup or tube between axially extending concentric annuli
- Y10T29/49913—Securing cup or tube between axially extending concentric annuli by constricting outer annulus
-
- 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.]
- Y10T428/12736—Al-base component
Definitions
- the present invention relates to obtaining a coin having a main direction along which extend a heart zone forming a core and a peripheral zone forming an envelope surrounding said core, said core and said envelope having a metallurgical bond between them, said core being made of a first material having at least one matrix metal and said envelope being made of a second material having at least one metal matrix.
- the present invention relates to obtaining a mechanical part for which the matrix of the first material and / or the second material aluminum as base metal.
- the invention relates to a mechanical part used in the sector aeronautics, particularly as a moving or fixed blade of a compressor, especially low pressure, or as a dawn blower ("fan”) of turbojet.
- the present invention is not intended to be limited to the realization of blades or to be applied only to the sector aeronautics: other types of mechanical parts may be envisaged, in particular in the machine tool sectors or in the automotive sector, such as crankcases, tubes, cylinders or wearing parts in the field of braking.
- titanium alloys are widely used in This has the disadvantages of significant costs of raw material as well as a weight sometimes still considered too important.
- the present invention aims to overcome the disadvantages of these techniques of the prior art by proposing a piece mechanics and its manufacturing process using techniques metallurgical simple to implement.
- the present invention thus relates to a mechanical part with a main direction along which extend a heart zone forming a core and a zone peripheral forming an envelope surrounding said core, said core and said envelope having a metallurgical bond between them, said core being made of a first material having at least one metal matrix and said envelope being made in a second material having at least one metal matrix.
- said metal matrices of first and second materials have the same base metal and at least one of said first and second materials is formed of a metal matrix composite comprising elements of reinforcement dispersed in said metal matrix.
- the characteristics of the interface between two materials forming a room, which can therefore be described as complex, are of great importance, especially when at least one of these materials is a metal matrix composite: the identity between the re-entrant base metal in the composition of the first and second materials is in this regard of great importance in obtaining a core and an envelope forming between them a metallurgical bond presenting a great mechanical resistance.
- this arrangement allows, by the presence of reinforcement elements, in at least one of the first material and the second material, to improve the strength properties mechanical and, possibly, withstand temperature, of the piece in the part that we wish to strengthen, while at the same time density similar to that of the metal matrix.
- both the first material and the second material (core and shell) is (are) made up of a metal matrix composite comprising elements of reinforcement dispersed in said metal matrix.
- the composition of the first material is different from that of the second material, at least as far as the proportion of reinforcement elements.
- a blade consisting of said mechanical part.
- Such a dawn can belong to a compressor, especially low pressure, whether as a fixed dawn or as dawn mobile.
- the present invention relates to the manufacturing process which makes it possible, by means of its implementation, to obtain said aforesaid mechanical part.
- said step a) consists in forming jointly the core and the envelope by the metallurgical technique of powders.
- this technique which implements the compression of a powder in a matrix, followed by a heat treatment called "sintering", it is thus possible to obtain a metal part forming directly the semi-finished product.
- This first solution is particularly well adapted to the situation in which one wishes to obtain a mechanical part where said reinforcement elements represent a percentage by weight of the composition of said progressive metal matrix composite in said first material (core) and in said second material (envelope), from the center of said core to the periphery of said envelope, or decreasing from the center, either increasing from the center, entering through example, a minimum of 0% to 10% and a maximum less than or equal to 50% by weight.
- This second solution is particularly well adapted to situation in which one wishes to obtain a mechanical part where said reinforcing elements are only present in one of the first and second materials, the other of said first and second materials being formed only of said metal matrix.
- Sub-step a4) of the second solution of step a), consists of preferably rolling or spinning all, that is to say by successive passages, in force and hot, between pairs of cylinders more and more close together or in sectors of section smaller and smaller.
- this step a) uses a technique performing the compaction, in particular the pressurization between the core and envelope, at the time of their joint formation (first solution), either at the moment of their initial training as a separate parts (second solution), so as to create between materials constituting a metallurgical type connection generating a good interface.
- forging generally consists of metallurgical operation whose purpose is to convert ingots into shaped blanks by deformation of a metal carried to a temperature where it is sufficiently malleable, the deformation being obtained either by shock (pestle, sheep) or by pressure (presses with closed matrix) between two tools.
- this forging step consists of stamping or stamping.
- Other forging possibilities can also be used alone, or in combination with the stamping: press forging, pestle ...
- the manufacturing method according to the present invention applies to a first material which is formed only of said metal matrix which comprises aluminum as base metal and a second material which is formed of said matrix composite metal comprising said reinforcing elements dispersed in said metal matrix, said metal matrix having aluminum as base metal and said reinforcing elements being formed of silicon carbide particles (SiC): this preferential choice makes it possible to benefit from a very good interaction between an aluminum alloy and SiC particles, as explained in US 6,135,195, for a material whose price is lower than that of titanium.
- SiC silicon carbide particles
- step a) the choice of aluminum as base metal allows benefit from its good elongation properties, especially for the forging step and also, in the case of the second solution of step a), during step a4) of passage in a more sectional orifice reduced (rolling or spinning), as well as its good resistance to corrosion.
- Figure 1 An example of the possible applications of the mechanical part according to the present invention is shown in Figure 1 in the form of a double-flow turbojet engine 100.
- This turbojet engine 100 comprises a conventional structure which comprises different elements arranged axially around the axis longitudinal 102, in fluid communication with each other, namely in particular a blower 104 and an accelerator 106.
- turbojet engine includes the others conventional elements of such a structure, namely a compressor high pressure, a combustion chamber, a high pressure turbine and a low pressure turbine, these different additional elements not represented for the sake of clarity.
- the fan 104 and the accelerator 106 are rotated by the low pressure turbine thanks to the rotor axis 108.
- the blower 104 comprises a series of blades 110 extending radially mounted on an annular disc 112: only one of these vanes appear in Figure 1. It is understood that the disc 112 and the blades 110 are rotatably mounted about the axis 102 of the motor 100.
- the motor 100 further comprises a fan casing 114.
- the accelerator 106 includes several sets of blades 116 in rotation mounted on a disc 118 and between which are mounted series of vanes 120.
- the present invention relates to obtaining a coin mechanics that can constitute in particular each of the blades 110 of the blower 104 and / or each of the blades 116 and / or vanes 120 of the accelerator 106.
- the mechanical part according to the present invention can also constitute the blades and / or mobiles of other elements of a turbojet engine, identical or different from that illustrated in FIG. a compressor, in particular a low pressure compressor.
- the mechanical part according to the present invention can also find application in areas other than that of aeronautics for the formation of structural elements to resist mechanically while having a relatively light structure.
- an aluminum rod 10 is first formed an aluminum rod 10 by conventional techniques for manufacturing aluminum alloys.
- the next step is to introduce the rod 10 inside of the sleeve 20 to form an assembly 30: it is clear that at this stage it there is a clearance, or even a space between the outer surface of the rod 10 and the inner surface of the wall of the sleeve 20.
- the assembly 30 appears to be introduced in the input 40 of a die 42.
- This input 40 has a shape of truncated cone with an angle at the center ⁇ forming the angle of reduction.
- This inlet 40 has an upstream diameter greater than the diameter outside the sleeve 20, while the downstream diameter of the inlet 40 has a diameter smaller than the diameter of the rod 10.
- the assembly 30 is, during the passage in force and at the inlet 40 of the die 42, reduced in section by lengthening, an interface being created between the rod 10 and the sleeve 20 which together form in this way a complex semi-product 32 at the exit 44 of the die 42.
- the reduction angle ⁇ is equal to 30 °, this reduction angle being able to vary in a general way between 1 ° and 45 ° and preferably between 5 and 35 °.
- this spinning technique in particular when it is carried out by the successive passage in series dies, allows, by the pressure exerted between the surfaces in contact by friction, good cohesion between the materials constituting the core and the envelope.
- This embodiment has been realized with a rod 10 having a diameter of 30 mm made of an aluminum alloy of 2024 T4 series, while the sleeve 20 had an outer diameter of 70 mm and an inside diameter of 40 mm being realized in a second material forming a metal matrix composite, the matrix metal alloy being a 2024 T4 series aluminum alloy and the reinforcement being composed of silicon carbide particles of a average size of 5 ⁇ m to 15% by weight.
- Such spinning can be carried out at room temperature or hot, especially with a temperature of the order of 400 ° C.
- the subsequent step of the exemplary embodiment described in detail is to perform forging by stamping to give the almost definitive shape of dawn.
- This mastering is achieved by successive steps in matrices gradually tending to present the final shape of dawn under pressure and temperature conditions adapted to materials to maintain a good interface and good adhesion between the core and the envelope: a temperature of the order of 430 ° C and a pressure of the order of 100 MPa have been used in particular.
- a blank (not shown) is obtained which is then machined to lead to a finished product forming the mechanical part according to the invention, in particular a blade such as those represented in Figures 3 to 5.
- the blade 50 which is represented according to different shapes has a core 52 made of the first material initially constituting the rod 10, while the envelope 54 surrounding the core 52 is made in the second material initially forming the sleeve 20 of the assembly 30 of FIG.
- dawn 50 has a regular distribution of the first material and the second material between the core 52 and the casing 54.
- the present invention is not limited to the use of reinforcing elements in the form of silicon carbide particles, alumina particles (Al 2 O 3 ) or metal carbides, such as tungsten carbide, tungsten carbide, boron carbide or titanium carbide can also be used.
- the present invention also applies to the production of a part mechanical made entirely of a metal matrix composite, which has a progressive composition of reinforcing elements from the center of the nucleus to the periphery of the envelope.
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- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Materials Engineering (AREA)
- Mechanical Engineering (AREA)
- Composite Materials (AREA)
- Manufacturing & Machinery (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- Powder Metallurgy (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Manufacture Of Alloys Or Alloy Compounds (AREA)
Abstract
Description
- une pièce mécanique réalisée avec deux parties formées d'un noyau réalisé dans un premier matériau présentant au moins une matrice métallique et d'une enveloppe réalisée dans un deuxième matériau présentant au moins une matrice métallique; et
- un procédé de fabrication qui permet l'obtention, par sa mise en oeuvre, de ladite pièce mécanique précitée.
- ledit métal de base est l'aluminium ;
- lesdites matrices métalliques du premier et du deuxième matériaux sont respectivement formées d'un premier alliage et d'un deuxième alliage, ledit premier alliage et ledit deuxième alliage appartenant aux alliages à base d'aluminium des séries 2000, 5000, 6000 ou 7000 selon les normes ASTM ; de préférence, ledit premier alliage et ledit deuxième alliage appartiennent à la même série d'alliage à base d'aluminium parmi lesdites séries 2000, 5000, 6000 ou 7000 selon les normes ASTM, en particulier à la série 2000 ;
- éléments de renforcement sont des particules de carbure de silicium (SiC), d'alumine (Al2O3) ou de carbure métallique tel que carbure de tungstène, de bore ou de titane ;
- lesdits éléments de renforcement représentent au plus 50% en poids de la composition dudit composite à matrice métallique ; de préférence, lesdits éléments de renforcement représentent entre 5 et 35%, de préférence entre 10 et 20%, et de préférence de l'ordre de 15% en poids de la composition dudit composite à matrice métallique ;
- l'un parmi lesdits premier et deuxième matériaux est formé dudit composite à matrice métallique comprenant lesdits éléments de renforcement dispersés dans ladite matrice métallique, l'autre parmi lesdits premier et deuxième matériaux étant formé seulement de ladite matrice métallique ;
- ledit premier matériau est formé seulement de ladite matrice métallique qui comporte l'aluminium comme métal de base et ledit deuxième matériau est formé dudit composite à matrice métallique comprenant lesdits éléments de renforcement dispersés dans ladite matrice métallique, ladite matrice métallique ayant l'aluminium comme métal de base et lesdits éléments de renforcement étant formés de particules de carbure de silicium (SiC) : ce choix préférentiel permet de bénéficier de la bonne tenue à l'érosion et à l'impact de l'Al/SiC et de sa rigidité plus importante ;
- lesdits premier et deuxième matériaux sont formés dudit composite à matrice métallique comprenant lesdits éléments de renforcement dispersés dans ladite matrice métallique, lesdits éléments de renforcement représentant un pourcentage en poids de la composition dudit composite à matrice métallique différent dans ledit noyau et dans ladite enveloppe ;
- lesdits éléments de renforcement représentent un pourcentage en poids de la composition dudit composite à matrice métallique progressif dans ledit premier matériau et dans ledit deuxième matériau, depuis le centre dudit noyau vers la périphérie de ladite enveloppe ;
- ledit premier matériau présente, pour lesdits éléments de renforcement, un pourcentage en poids de la composition dudit composite à matrice métallique plus important que dans ledit deuxième matériau;
- ledit deuxième matériau présente, pour lesdits éléments de renforcement, un pourcentage en poids de la composition dudit composite à matrice métallique plus important que dans ledit premier matériau.
- lesdits premier et deuxième matériaux sont formés dudit composite à matrice métallique comprenant lesdits éléments de renforcement dispersés dans ladite matrice métallique, lesdits éléments de renforcement représentant un pourcentage en poids de la composition dudit composite à matrice métallique différent dans ledit noyau et dans ladite enveloppe,
- l'un parmi lesdits premier et deuxième matériaux est formé dudit composite à matrice métallique comprenant lesdits éléments de renforcement dispersés dans ladite matrice métallique, l'autre parmi lesdits premier et deuxième matériaux étant formé seulement de ladite matrice métallique.
- la figure 1 est une vue en section longitudinale partielle d'un turboréacteur double-flux montrant une soufflante et un accélérateur illustrant à titre d'exemple des applications possibles de la pièce mécanique selon la présente invention,
- la figure 2 est une vue en coupe longitudinale de l'agencement permettant la réalisation de l'une des étapes du procédé de fabrication selon la présente invention selon l'une des solutions possibles,
- les figures 3 et 4 sont des vues en perspective d'aubes tronquées à leur extrémité radialement externe qui illustrent des applications possibles de la pièce mécanique selon la présente invention, et
- la figure 5 est une vue en perspective partielle avec coupe selon la direction longitudinale d'une autre aube pouvant former la pièce mécanique selon la présente invention.
Claims (21)
- Pièce mécanique (50, 110) présentant une direction principale le long de laquelle s'étendent une zone de coeur formant un noyau (52) et une zone périphérique formant une enveloppe (54) qui entoure ledit noyau (52), ledit noyau (52) et ladite enveloppe (54) présentant entre eux une liaison métallurgique, ledit noyau (52) étant réalisé dans un premier matériau présentant au moins une matrice métallique et ladite enveloppe (54) étant réalisée dans un deuxième matériau présentant au moins une matrice métallique, caractérisée en ce que lesdites matrices métalliques du premier et du deuxième matériaux présentent le même métal de base et en ce que l'un au moins parmi lesdits premier et deuxième matériaux est formé d'un composite à matrice métallique comprenant des éléments de renforcement dispersés dans ladite matrice métallique.
- Pièce mécanique (50, 110) selon la revendication 1, caractérisée en ce que ledit métal de base est l'aluminium.
- Pièce mécanique (50, 110) selon la revendication 2, caractérisée en ce que lesdites matrices métalliques du premier et du deuxième matériaux sont respectivement formées d'un premier alliage et d'un deuxième alliage, ledit premier alliage et ledit deuxième alliage appartenant aux alliages à base d'aluminium des séries 2000, 5000, 6000 ou 7000 selon les normes ASTM.
- Pièce mécanique (50, 110) selon la revendication 3, caractérisée en ce que ledit premier alliage et ledit deuxième alliage appartiennent à la même série d'alliage à base d'aluminium parmi lesdites séries 2000, 5000, 6000 ou 7000 selon les normes ASTM, en particulier à la série 2000.
- Pièce mécanique (50, 110) selon l'une quelconque des revendications 1 à 4, caractérisée en ce que lesdits éléments de renforcement sont des particules de carbure de silicium (SiC), d'alumine (Al2O3) ou de carbure métallique tel que carbure de tungstène, de bore ou de titane.
- Pièce mécanique (50, 110) selon la revendication 5, caractérisée en ce que lesdits éléments de renforcement représentent au plus 50% en poids de la composition dudit composite à matrice métallique.
- Pièce mécanique (50, 110) selon la revendication 6, caractérisée en ce que lesdits éléments de renforcement représentent entre 5 et 35%, de préférence entre 10 et 20%, et de préférence de l'ordre de 15% en poids de la composition dudit composite à matrice métallique.
- Pièce mécanique (50, 110) selon l'une quelconque des revendications 1 à 7, caractérisée en ce que l'un parmi lesdits premier et deuxième matériaux est formé dudit composite à matrice métallique comprenant lesdits éléments de renforcement dispersés dans ladite matrice métallique, l'autre parmi lesdits premier et deuxième matériaux étant formé seulement de ladite matrice métallique.
- Pièce mécanique (50, 110) selon la revendication 8, caractérisée en ce que ledit premier matériau est formé seulement de ladite matrice métallique qui comporte l'aluminium comme métal de base et en ce que ledit deuxième matériau est formé dudit composite à matrice métallique comprenant lesdits éléments de renforcement dispersés dans ladite matrice métallique, ladite matrice métallique ayant l'aluminium comme métal de base et lesdits éléments de renforcement étant formés de particules de carbure de silicium (SiC).
- Pièce mécanique (50, 110) selon l'une quelconque des revendications 1 à 7, caractérisée en ce que lesdits premier et deuxième matériaux sont formés dudit composite à matrice métallique comprenant lesdits éléments de renforcement dispersés dans ladite matrice métallique, lesdits éléments de renforcement représentant un pourcentage en poids de la composition dudit composite à matrice métallique différent dans ledit noyau (52) et dans ladite enveloppe (54).
- Pièce mécanique (50, 110) selon la revendication 10, caractérisée en ce que lesdits éléments de renforcement représentent un pourcentage en poids de la composition dudit composite à matrice métallique progressif dans ledit premier matériau et dans ledit deuxième matériau, depuis le centre dudit noyau (52) vers la périphérie de ladite enveloppe (54).
- Pièce mécanique (50, 110) selon la revendication 10 ou 11, caractérisée en ce que ledit premier matériau présente, pour lesdits éléments de renforcement, un pourcentage en poids de la composition dudit composite à matrice métallique plus important que dans ledit deuxième matériau.
- Pièce mécanique (50, 110) selon la revendication 10 ou 11, caractérisée en ce que ledit deuxième matériau présente, pour lesdits éléments de renforcement, un pourcentage en poids de la composition dudit composite à matrice métallique plus important que dans ledit premier matériau.
- Aube (50, 110) constituée d'une pièce mécanique selon l'une quelconque des revendications 1 à 13.
- Compresseur basse pression comprenant des aubes fixes et/ou mobiles selon la revendication 14.
- Soufflante (104) de turboréacteur comprenant des aubes (110) selon la revendication 14.
- Procédé de fabrication d'une pièce mécanique (50, 110) selon l'une quelconque des revendications 1 à 13, caractérisé en ce qu'il comporte successivement les étapes suivantes :a) on réalise par compactage un demi-produit contenant un noyau (52) et une enveloppe (54), ledit noyau (52) et ladite enveloppe (54) présentant entre eux une liaison métallurgique, ledit noyau (52) étant réalisé dans un premier matériau présentant au moins une matrice métallique et ladite enveloppe (54) étant réalisée dans un deuxième matériau présentant au moins une matrice métallique, lesdites matrices métalliques du premier et du deuxième matériaux présentant le même métal de base et l'un au moins parmi lesdits premier et deuxième matériaux étant formé d'un composite à matrice métallique comprenant des éléments de renforcement dispersés dans ladite matrice métallique,b) on réalise le forgeage du demi-produit pour obtenir une ébauche, etc) on usine ladite ébauche pour aboutir à un produit fini formant ladite pièce mécanique .
- Procédé de fabrication selon la revendication 17 en vue de l'obtention d'une pièce mécanique selon la revendication 11, caractérisé en ce que ladite étape a) consiste à former conjointement le noyau (52) et l'enveloppe (54) par la technique de métallurgie des poudres.
- Procédé de fabrication selon la revendication 17 en vue de l'obtention d'une pièce mécanique selon l'une quelconque des revendications 1 à 10, caractérisé en ce que ladite étape a) consiste à réaliser successivement les sous-étapes suivantes :a1) former une tige (10) s'étendant selon une direction longitudinale dans ledit premier matériau, ladite tige (10) étant destinée à former ledit noyau (52) placé au coeur de la pièce mécanique ;a2) former un manchon (20) s'étendant selon une direction longitudinale dans ledit deuxième matériau, ledit manchon (20) étant destinée à former l'enveloppe (54) de la pièce mécanique en entourant ledit noyau (52) ;a3) introduire la tige (10) dans le manchon (20) pour former un ensemble (30), eta4) passer à travers un orifice de section réduite ledit ensemble (30) pour diminuer au moins une dimension dudit ensemble selon une direction perpendiculaire à ladite direction longitudinale et afin de créer une liaison métallurgique entre ladite tige (10) et le dit manchon (20).
- Procédé selon l'une quelconque des revendications 17 à 19, caractérisé en ce que ladite sous-étape a4) consister à effectuer un laminage ou un filage.
- Procédé selon l'une quelconque des revendications 17 à 20, caractérisé en ce que ladite étape b) consister à effectuer un matriçage.
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR0209444 | 2002-07-25 | ||
FR0209444A FR2842828B1 (fr) | 2002-07-25 | 2002-07-25 | Piece mecanique, et procede de fabrication d'une telle piece mecanique |
Publications (2)
Publication Number | Publication Date |
---|---|
EP1384539A1 true EP1384539A1 (fr) | 2004-01-28 |
EP1384539B1 EP1384539B1 (fr) | 2010-02-10 |
Family
ID=29797665
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP03291800A Expired - Lifetime EP1384539B1 (fr) | 2002-07-25 | 2003-07-21 | Aube composite à matrice métallique et son procédé de fabrication |
Country Status (12)
Country | Link |
---|---|
US (1) | US7749342B2 (fr) |
EP (1) | EP1384539B1 (fr) |
JP (1) | JP2005533931A (fr) |
CN (1) | CN1671498B (fr) |
AU (1) | AU2003269058A1 (fr) |
CA (1) | CA2493445C (fr) |
DE (1) | DE60331206D1 (fr) |
ES (1) | ES2340372T3 (fr) |
FR (1) | FR2842828B1 (fr) |
RU (1) | RU2347648C2 (fr) |
UA (1) | UA82069C2 (fr) |
WO (1) | WO2004011687A2 (fr) |
Cited By (3)
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US7510778B2 (en) * | 2005-04-15 | 2009-03-31 | Snecma | Part for protecting the leading edge of a blade |
EP3460188A1 (fr) * | 2017-09-22 | 2019-03-27 | Rolls-Royce plc | Composant de surface portante et procédé |
WO2020007916A1 (fr) * | 2018-07-04 | 2020-01-09 | Rolls-Royce Plc | Procédé et ensemble d'outils pour la fabrication d'un élément composite |
Families Citing this family (17)
Publication number | Priority date | Publication date | Assignee | Title |
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US6701998B2 (en) * | 2002-03-29 | 2004-03-09 | Water Gremlin Company | Multiple casting apparatus and method |
US7338539B2 (en) | 2004-01-02 | 2008-03-04 | Water Gremlin Company | Die cast battery terminal and a method of making |
US8701743B2 (en) | 2004-01-02 | 2014-04-22 | Water Gremlin Company | Battery parts and associated systems and methods |
US7617582B2 (en) * | 2005-07-05 | 2009-11-17 | Honeywell International Inc. | Method of manufacturing composite generator rotor shaft |
ES2746292T3 (es) * | 2009-04-30 | 2020-03-05 | Water Gremlin Co | Piezas de bateria que tienen elementos de retención y sellado |
US8272085B2 (en) * | 2009-10-13 | 2012-09-25 | Justin Finch | Boat hammock installation system |
FR2963806B1 (fr) * | 2010-08-10 | 2013-05-03 | Snecma | Dispositif de blocage d'un pied d'une aube de rotor |
DE102010034014B4 (de) * | 2010-08-11 | 2015-06-25 | Schwäbische Hüttenwerke Automotive GmbH | Sinterverbund und Verfahren zu seiner Herstellung |
CN102455249B (zh) * | 2010-11-03 | 2014-02-19 | 上海微电子装备有限公司 | 气浮轴承的刚度测试装置 |
US9748551B2 (en) | 2011-06-29 | 2017-08-29 | Water Gremlin Company | Battery parts having retaining and sealing features and associated methods of manufacture and use |
FR2982518B1 (fr) * | 2011-11-15 | 2013-12-20 | Snecma | Conception d'une piece en materiau composite tisse 3d |
US20130192982A1 (en) * | 2012-02-01 | 2013-08-01 | United Technologies Corporation | Surface implantation for corrosion protection of aluminum components |
FR2993577B1 (fr) * | 2012-07-20 | 2016-03-11 | Snecma | Revetement abradable resistant a la corrosion |
US9954214B2 (en) | 2013-03-15 | 2018-04-24 | Water Gremlin Company | Systems and methods for manufacturing battery parts |
RU2528926C1 (ru) * | 2013-04-30 | 2014-09-20 | Федеральное государственное бюджетное учреждение науки Институт машиноведения Уральского отделения Российской академии наук (ИМАШ УрО РАН) | Способ получения металломатричного композиционного материала |
FR3037097B1 (fr) * | 2015-06-03 | 2017-06-23 | Snecma | Aube composite comprenant une plateforme munie d'un raidisseur |
US11283141B2 (en) | 2018-12-07 | 2022-03-22 | Water Gremlin Company | Battery parts having solventless acid barriers and associated systems and methods |
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EP0019569A1 (fr) * | 1979-05-16 | 1980-11-26 | Cegedur Societe De Transformation De L'aluminium Pechiney | Corps creux composite et procédé de fabrication |
US4314007A (en) * | 1976-08-26 | 1982-02-02 | Bbc Brown, Boveri & Company Limited | Composite shaped articles |
DE4137839A1 (de) * | 1991-11-16 | 1993-05-19 | Asea Brown Boveri | Verfahren zum anbringen einer erosionsschutzschicht |
EP0809050A1 (fr) * | 1996-05-20 | 1997-11-26 | Yamaha Hatsudoki Kabushiki Kaisha | Piston pour un moteur à combustion interne et son procédé de fabrication |
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- 2002-07-25 FR FR0209444A patent/FR2842828B1/fr not_active Expired - Lifetime
-
2003
- 2003-07-21 ES ES03291800T patent/ES2340372T3/es not_active Expired - Lifetime
- 2003-07-21 EP EP03291800A patent/EP1384539B1/fr not_active Expired - Lifetime
- 2003-07-21 DE DE60331206T patent/DE60331206D1/de not_active Expired - Lifetime
- 2003-07-25 AU AU2003269058A patent/AU2003269058A1/en not_active Abandoned
- 2003-07-25 UA UAA200500660A patent/UA82069C2/uk unknown
- 2003-07-25 US US10/522,182 patent/US7749342B2/en not_active Expired - Fee Related
- 2003-07-25 WO PCT/FR2003/002350 patent/WO2004011687A2/fr active Application Filing
- 2003-07-25 CN CN03817892.3A patent/CN1671498B/zh not_active Expired - Fee Related
- 2003-07-25 JP JP2004523882A patent/JP2005533931A/ja active Pending
- 2003-07-25 RU RU2005105069/02A patent/RU2347648C2/ru active
- 2003-07-25 CA CA2493445A patent/CA2493445C/fr not_active Expired - Lifetime
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EP0019569A1 (fr) * | 1979-05-16 | 1980-11-26 | Cegedur Societe De Transformation De L'aluminium Pechiney | Corps creux composite et procédé de fabrication |
DE4137839A1 (de) * | 1991-11-16 | 1993-05-19 | Asea Brown Boveri | Verfahren zum anbringen einer erosionsschutzschicht |
EP0809050A1 (fr) * | 1996-05-20 | 1997-11-26 | Yamaha Hatsudoki Kabushiki Kaisha | Piston pour un moteur à combustion interne et son procédé de fabrication |
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Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US7510778B2 (en) * | 2005-04-15 | 2009-03-31 | Snecma | Part for protecting the leading edge of a blade |
EP3460188A1 (fr) * | 2017-09-22 | 2019-03-27 | Rolls-Royce plc | Composant de surface portante et procédé |
WO2020007916A1 (fr) * | 2018-07-04 | 2020-01-09 | Rolls-Royce Plc | Procédé et ensemble d'outils pour la fabrication d'un élément composite |
Also Published As
Publication number | Publication date |
---|---|
AU2003269058A8 (en) | 2004-02-16 |
AU2003269058A1 (en) | 2004-02-16 |
CN1671498B (zh) | 2010-09-01 |
DE60331206D1 (de) | 2010-03-25 |
ES2340372T3 (es) | 2010-06-02 |
US7749342B2 (en) | 2010-07-06 |
UA82069C2 (uk) | 2008-03-11 |
CN1671498A (zh) | 2005-09-21 |
WO2004011687A3 (fr) | 2004-04-15 |
RU2347648C2 (ru) | 2009-02-27 |
EP1384539B1 (fr) | 2010-02-10 |
RU2005105069A (ru) | 2005-07-20 |
FR2842828B1 (fr) | 2005-04-29 |
CA2493445A1 (fr) | 2004-02-05 |
WO2004011687A2 (fr) | 2004-02-05 |
CA2493445C (fr) | 2011-06-14 |
FR2842828A1 (fr) | 2004-01-30 |
JP2005533931A (ja) | 2005-11-10 |
US20060127693A1 (en) | 2006-06-15 |
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