EP1384539B1 - Aube composite à matrice métallique et son procédé de fabrication - Google Patents

Aube composite à matrice métallique et son procédé de fabrication Download PDF

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Publication number
EP1384539B1
EP1384539B1 EP03291800A EP03291800A EP1384539B1 EP 1384539 B1 EP1384539 B1 EP 1384539B1 EP 03291800 A EP03291800 A EP 03291800A EP 03291800 A EP03291800 A EP 03291800A EP 1384539 B1 EP1384539 B1 EP 1384539B1
Authority
EP
European Patent Office
Prior art keywords
metal matrix
blade
core
reinforcing elements
casing
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.)
Expired - Lifetime
Application number
EP03291800A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP1384539A1 (fr
Inventor
Isabelle Peslerbe
Jacques Tschofen
Anne Thenaisie
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Safran Aircraft Engines SAS
Forges de Bologne
Original Assignee
Forges de Bologne
SNECMA SAS
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Forges de Bologne, SNECMA SAS filed Critical Forges de Bologne
Publication of EP1384539A1 publication Critical patent/EP1384539A1/fr
Application granted granted Critical
Publication of EP1384539B1 publication Critical patent/EP1384539B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • 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 blade having a main direction along which extends a heart zone forming a core and a peripheral zone forming an envelope which surrounds said core, said core and said envelope having between them a metallurgical bond, said core being made of a first material having at least one metal matrix and said envelope being made of a second material having at least one metal matrix.
  • the present invention relates to obtaining a blade for which the metal matrix of the first material and / or the second material has aluminum as the base metal.
  • the present invention relates to a blade used in the aeronautical sector, in particular as a blade or a fixed blade of a compressor, particularly low pressure, or as a fan blade ("fan") of a jet engine .
  • titanium alloys are widely used for this purpose, which has the disadvantage of particular costs of raw material and a weight sometimes still considered too important.
  • DE-A-4137839 discloses the manufacture of a turbine blade by compression and forging of an aluminum alloy core, possibly reinforced with carbon fibers, and an erosion-resistant steel casing.
  • the present invention aims to overcome the disadvantages of these techniques of the prior art by providing a blade and its manufacturing process using metallurgical techniques simple to implement.
  • the present invention therefore relates to a blade according to claim 1.
  • said metal matrices of the 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 reinforcing elements dispersed in said metal matrix.
  • the characteristics of the interface between two materials forming a part, 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 In this respect, the identity of the base metal forming part of the composition of the first and second materials is of great importance in obtaining a core and an envelope forming between them a metallurgical bond having a high mechanical strength.
  • this arrangement makes it possible, by the presence of reinforcing elements, in at least one of the first material and the second material, to improve the properties of mechanical strength and, optionally, temperature resistance, of the part in which the part that is to be reinforced, while generally maintaining a density similar to that of the metal matrix.
  • first material (core) and the second material (envelope), or both the first material and the second material (core and envelope) is (are) constituted of a metal matrix composite comprising reinforcement elements dispersed in said metal matrix.
  • composition of the first material is different from that of the second material, at least as regards the proportion of the reinforcing elements.
  • the blade according to the invention can belong to a compressor, in particular low pressure, whether as a fixed blade or as a mobile blade.
  • Such a blade can be applied to the realization of a turbojet fan.
  • the present invention relates to the manufacturing process which makes it possible, by its implementation, to obtain said blade.
  • said step a) consists of jointly forming the core and the envelope by the powder metallurgy technique.
  • 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 directly forming the semi-finished product.
  • This first solution is particularly well suited to the situation in which it is desired to obtain a blade where said reinforcing 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, either decreasing from the center, or increasing from the center, between for example, a minimum of 0% to 10% and a maximum less than or equal to 50% in weight.
  • the sub-step a4) of the second solution of step a), consists in carrying out, preferably, a rolling or spinning of the assembly, that is to say by successive passages, in force and hot , between pairs of cylinders more and more close together or in dies of smaller and smaller section.
  • this step a) uses a technique that performs the compaction, in particular the pressurization between the core and the envelope, either at the time of their joint formation (first solution), or at the time of their initial formation. as separate pieces (second solution), so as to create between the materials constituting them a metallurgical type connection generating a good interface.
  • this metallurgical bond forms a more intimate contact than a mechanical bond, the first and second materials being so close that the inter-atomic forces come into play. Such an interface will allow the dawn to withstand satisfactory to the different constraints to which it is subjected.
  • the forging generally consists of a metallurgical operation whose object is to transform the ingots into blanks of determined shape by deformation of a metal brought to a temperature where it is sufficiently malleable, the deformation being obtained either by shock (pestle, sheep), or by pressure (presses with closed die) between two tools.
  • this forging step consists of stamping or stamping.
  • Other forging possibilities can also be used alone, or in combination with 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 the base metal and to a second material which is formed of said metal matrix composite comprising said reinforcing elements dispersed in said metal matrix, said metal matrix having aluminum as the base metal and said reinforcing elements being formed of silicon carbide (SiC) particles: 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
  • step a4 passing through a smaller section orifice (rolling or spinning), as well as its good resistance to corrosion.
  • FIG. figure 1 An example of the possible applications of the blade according to the present invention is shown in FIG. figure 1 in the form of a double-flow turbojet engine 100.
  • This turbojet engine 100 comprises a conventional structure which comprises various elements arranged axially around the longitudinal axis 102, in fluid communication with each other, namely in particular a fan 104 and an accelerator 106.
  • turbojet comprises the other conventional elements of such a structure, namely a high pressure compressor, a combustion chamber, a high pressure turbine and a low pressure turbine, these various additional elements not being represented. for the sake of clarity.
  • the fan 104 and the accelerator 106 are rotated by the low-pressure turbine through the rotor axis 108.
  • the fan 104 comprises a series of radially extending blades 110 which are mounted on an annular disc 112: only one of these vanes appears on the 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 comprises several series of rotating blades 116 rotatably mounted on a disk 118 and between which are mounted series of blades 120.
  • the present invention relates to obtaining a blade that can constitute in particular each blade 110 of the blower 104 and / or each of the blades 116 and / or vanes 120 of the accelerator 106.
  • the blade according to the present invention can also constitute the blades and / or mobile blades of other elements of a turbojet, identical or different from that illustrated on the figure 1 , such as a compressor, in particular a low pressure compressor.
  • the blade according to the present invention can also find application in fields other than aeronautics for the formation of structural elements having to withstand mechanically while having a relatively lightly.
  • a blade composed of a core made of a first material formed of an aluminum-based alloy and of an envelope made of a second material formed of a metal matrix composite wherein the metal matrix is an aluminum alloy and the reinforcing elements are silicon carbide (SiC) particles.
  • an aluminum rod 10 is first formed by conventional techniques for manufacturing aluminum alloys.
  • the next step is to introduce the rod 10 inside the sleeve 20 to form an assembly 30: it is clear that at this stage there is a clearance, or even a space between the outer surface of the rod 10 and the surface inside the wall of the sleeve 20.
  • the assembly 30 appears as being introduced into the inlet 40 of a die 42.
  • This inlet 40 has a truncated cone shape with an angle at the center ⁇ forming the reduction angle.
  • This inlet 40 has an upstream diameter greater than the outside diameter of 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 of force and hot at the inlet 40 of the die 42, reduced in section by elongation, an interface being created between the rod 10 and the sleeve 20 which form jointly in this way a complex semi-product 32 at the outlet 44 of the die 42.
  • spinning step illustrated on the figure 2 may comprise several successive passages in dies with smaller and smaller diameters.
  • the reduction angle ⁇ is equal to 30 °, this reduction angle can vary generally between 1 ° and 45 ° and preferably between 5 and 35 °.
  • this spinning technique in particular when it is carried out by successively passing through series dies, makes it possible, by the pressure exerted between the surfaces in contact by friction, a good cohesion between the materials constituting the core and the 'envelope.
  • This exemplary embodiment was made with a rod 10 having a diameter of 30 mm made of an aluminum alloy of series 2024 T4, while the sleeve 20 had an outer diameter of 70 mm and an internal diameter of 40 mm while being made in a second material forming a metal matrix composite, the metal matrix being an aluminum alloy of series 2024 T4 and the reinforcing element being composed of silicon carbide particles having a mean size of 5 ⁇ m at 15% by weight.
  • Such spinning can be carried out at room temperature or hot, in particular with a temperature of the order of 400 ° C.
  • the subsequent step of the embodiment described in detail is to perform forging by stamping to give the almost final shape of the blade.
  • This stamping is performed by successive steps in matrices progressively tending to present the final shape of the blade under conditions of pressure and temperature adapted to the materials to maintain a good interface and a 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 were used in particular.
  • a blank (not shown) is obtained which is then machined to produce a finished product forming the blade according to the invention, in particular a blade such that those represented on the Figures 3 to 5 .
  • the blade 50 which is represented according to different shapes comprises a core 52 made in the first material initially constituting the rod 10, while the casing 54 surrounding the core 52 is made in the second material initially forming the sleeve. 20 of the whole 30 of the figure 2 .
  • the blade 50 has a regular distribution of the first material and the second material between the core 52 and the casing 54.
  • the aluminum alloy has been placed in the central part of the blade, which makes it possible to benefit from the bending properties of aluminum while at the surface, the matrix composite Al / SiC metal allows greater rigidity and better resistance to impact and erosion.
  • 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 realization of a blade made entirely of a metal matrix composite, which has a progressive composition of reinforcing elements from the center of the core towards 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)
EP03291800A 2002-07-25 2003-07-21 Aube composite à matrice métallique et son procédé de fabrication Expired - Lifetime EP1384539B1 (fr)

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 EP1384539A1 (fr) 2004-01-28
EP1384539B1 true 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 (ru)
EP (1) EP1384539B1 (ru)
JP (1) JP2005533931A (ru)
CN (1) CN1671498B (ru)
AU (1) AU2003269058A1 (ru)
CA (1) CA2493445C (ru)
DE (1) DE60331206D1 (ru)
ES (1) ES2340372T3 (ru)
FR (1) FR2842828B1 (ru)
RU (1) RU2347648C2 (ru)
UA (1) UA82069C2 (ru)
WO (1) WO2004011687A2 (ru)

Families Citing this family (20)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
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
FR2884550B1 (fr) * 2005-04-15 2010-09-17 Snecma Moteurs Piece pour proteger le bord d'attaque d'une pale
US7617582B2 (en) * 2005-07-05 2009-11-17 Honeywell International Inc. Method of manufacturing composite generator rotor shaft
PL3059785T3 (pl) 2009-04-30 2020-03-31 Water Gremlin Company Części akumulatora mające cechy utrzymujące i uszczelniające
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
US20190093488A1 (en) * 2017-09-22 2019-03-28 Rolls-Royce Plc Aerofoil component and method
GB201811019D0 (en) * 2018-07-04 2018-08-15 Rolls Royce Plc Methos and Tool Set For Manufacturing A Composite Component
MX2021006454A (es) 2018-12-07 2021-07-02 Water Gremlin Co Partes de bateria que tienen barreras contra acidos sin solventes y sistemas y metodos asociados.

Family Cites Families (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH602330A5 (ru) * 1976-08-26 1978-07-31 Bbc Brown Boveri & Cie
FR2456783A1 (fr) * 1979-05-16 1980-12-12 Cegedur Corps creux composite et procede de fabrication
JPS5662956A (en) * 1979-10-15 1981-05-29 United Technologies Corp Corrosion and abrasion resistant coating material
AU6744381A (en) * 1980-02-27 1981-09-03 British Internal Combustion Engine Research Institute Limited, The Sintered piston
US4850802A (en) * 1983-04-21 1989-07-25 Allied-Signal Inc. Composite compressor wheel for turbochargers
JPH01180927A (ja) * 1988-01-13 1989-07-18 Toyota Motor Corp ピストン製造方法
GB2242848A (en) * 1990-04-12 1991-10-16 Frictec Ltd Depositing coating on materials
DE4137839A1 (de) * 1991-11-16 1993-05-19 Asea Brown Boveri Verfahren zum anbringen einer erosionsschutzschicht
US5439750A (en) * 1993-06-15 1995-08-08 General Electric Company Titanium metal matrix composite inserts for stiffening turbine engine components
US6203897B1 (en) * 1993-09-24 2001-03-20 The Ishizuka Research Institute, Ltd. Sintered composites containing superabrasive particles
US5669059A (en) * 1994-01-19 1997-09-16 Alyn Corporation Metal matrix compositions and method of manufacturing thereof
US5490764A (en) * 1994-05-23 1996-02-13 General Electric Company Unshrouded blading for high bypass turbofan engines
EP0809050B1 (en) * 1996-05-20 2003-08-13 Yamaha Hatsudoki Kabushiki Kaisha Method of making a piston for an internal combustion engine
US6190133B1 (en) * 1998-08-14 2001-02-20 Allison Engine Company High stiffness airoil and method of manufacture
FR2784616B1 (fr) * 1998-10-15 2000-11-17 Snecma Procede d'obtention de pieces metalliques minces, legeres et rigides
DE19859477B4 (de) * 1998-12-22 2005-06-23 Mtu Aero Engines Gmbh Verschleißschutzschicht
DE19959598A1 (de) * 1999-12-10 2001-06-13 Rolls Royce Deutschland Verfahren zum Herstellen einer Schaufel einer Strömungsmaschine
FR2884550B1 (fr) * 2005-04-15 2010-09-17 Snecma Moteurs Piece pour proteger le bord d'attaque d'une pale

Also Published As

Publication number Publication date
AU2003269058A8 (en) 2004-02-16
WO2004011687A3 (fr) 2004-04-15
EP1384539A1 (fr) 2004-01-28
UA82069C2 (ru) 2008-03-11
CA2493445C (fr) 2011-06-14
WO2004011687A2 (fr) 2004-02-05
CN1671498B (zh) 2010-09-01
RU2347648C2 (ru) 2009-02-27
ES2340372T3 (es) 2010-06-02
FR2842828A1 (fr) 2004-01-30
JP2005533931A (ja) 2005-11-10
DE60331206D1 (de) 2010-03-25
RU2005105069A (ru) 2005-07-20
AU2003269058A1 (en) 2004-02-16
US20060127693A1 (en) 2006-06-15
CA2493445A1 (fr) 2004-02-05
FR2842828B1 (fr) 2005-04-29
US7749342B2 (en) 2010-07-06
CN1671498A (zh) 2005-09-21

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