EP2553131B1 - Alliage d'aluminium stable à haute température - Google Patents

Alliage d'aluminium stable à haute température Download PDF

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Publication number
EP2553131B1
EP2553131B1 EP11763104.4A EP11763104A EP2553131B1 EP 2553131 B1 EP2553131 B1 EP 2553131B1 EP 11763104 A EP11763104 A EP 11763104A EP 2553131 B1 EP2553131 B1 EP 2553131B1
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Prior art keywords
alloy
alloys
exposure
precipitate
hardness
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EP11763104.4A
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German (de)
English (en)
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EP2553131A4 (fr
EP2553131A1 (fr
Inventor
Calin Daniel Marioara
Sigmund Jarle Andersen
Sverre Gulbrandsen-Dahl
Jon Holmestad
Randi Holmestad
Tor-Erik Nicolaisen
Inge-Erland Opheim
Oddvin Reiso
Jostein RØYSET
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Norsk Hydro ASA
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Norsk Hydro ASA
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    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C21/00—Alloys based on aluminium
    • C22C21/06—Alloys based on aluminium with magnesium as the next major constituent
    • C22C21/08—Alloys based on aluminium with magnesium as the next major constituent with silicon

Definitions

  • the present invention relates to Al-Mg-Si-Cu alloy optimised for high temperature stability.
  • Alloys of the Al-Mg-Si system have an attractive combination of processability, mechanical strength and response to surface finishing treatments, thus making them the alloys of choice for several applications within the building industry and the automotive industry. Some of the automotive applications require that the alloy should maintain a certain mechanical strength after defined thermal exposures. Requirements for thermal exposure are expected to increase in the future. There is therefore a strong drive in the aluminium industry for developing aluminium alloys that can meet the current and the future requirements.
  • a common aluminium alloy for structural applications in the European market is the standard 6082 alloy.
  • This alloy contains sufficient amounts of Mg and Si for obtaining tensile strength of typically 300-320 MPa under common industrial practices.
  • the alloy contains a substantial amount of Mn.
  • the Mn forms dispersoids during homogenisation of the alloy.
  • the purpose of the dispersoids is to control the microstructure during thermo-mechanical processing, such as for example obtaining a fibrous grain structure after extrusion of the alloy.
  • the 6082 alloys do, however, lose strength after prolonged temperature exposure at for instance 200°C.
  • Document JP2009084698A discloses an aluminum alloy that has the components of, by mass, 0.3 to 1.0% Si, 0.2 to 0.6% Cu, 0.8 to 1.5% Mg, 0.05 to 0.5% Cr, 0.05 to 0.15% Mn and 0.18 to 0.40% Fe, and the balance Al with inevitable impurities.
  • Document US6248189B1 discloses an alloy that includes, in weight %, 0.50 to 0.70% Si, up to 0.30% Fe, 0.20 to 0.40% Cu, up to 0.03% Mn, 0.80 to 1.10% Mg, up to 0.03% Cr, balance Al and impurities.
  • the alloy is characterized by the features as defined in the independent claim 1.
  • Al-Mg-Si alloys gain their strength from precipitation hardening (also commonly denoted artificial age hardening), a heat treatment by which a fine dispersion of precipitates is formed. The precipitates strengthen the alloy by impeding dislocation movements.
  • the common temperatures used for precipitation hardening of 6xxx alloys for structural applications lie in the range 150-190°C.
  • the hardness of the alloy will increase to a maximum level and thereafter decrease.
  • the condition of the alloy is referred to as "overaged”.
  • Exposure of the alloy to temperatues higher than the normal age hardening temperatures gives an acceleration of the mechanisms that lead to overageing
  • the L-phase can be found to in highest number density, i.e. it is "dominating", in the overaged state for some alloy compositions and thermomechanical treatments.
  • a commonly known aluminium alloy for structural applications in the European market is the standard 6082 alloy.
  • This alloy contains sufficient amounts of Mg and Si for obtaining tensile strength of typically 300-320 MPa under common industrial practices.
  • the alloy contains a substantial amount of Mn.
  • the Mn forms dispersoids during homogenisation of the alloy.
  • the purpose of the dispersoids is to control the microstructure during thermo-mechanical processing, such as for example obtaining a fibrous grain structure after extrusion of the alloy.
  • the 6082 alloys do, however, lose strength after prolonged temperature exposure at for instance 200°C.
  • a Mn-level typical for 6082-alloys was chosen for all alloy compositions.
  • Zr and Cr serve the same purpose as Mn in this type of alloys and could have been used as partial or complete replacements of Mn.
  • the alloys were cast as ⁇ 95mm logs (extrusion ingots), homogenised at a temperature in the range 520 - 600°C for a length of time between 1 and 10 hours, and pre-cut to extrusion billets of 200mm length.
  • the extrusion billets were preheated in an induction furnace, and extruded to cylindrical rods of 20mm diameter. Samples of the extruded rods were solution heat treated in the range 520 - 600°C, water-quenched, stored 4 hour at roomtemperature, and then precipitation hardened at 155°C for 12h, corresponding approximately to maximum hardness of the alloy.
  • Fig. 1 shows the development in Vickers hardness as a function of exposure time at 200°C for an alloy of composition 1 in Table 1 above.
  • This alloy represents a typical composition for a 6082-alloy.
  • the hardness declines rapidly, and after a day the hardness is down to approx. 2/3 of that of the starting condition. Further exposure at 200°C reduces the hardness to 50% of that the starting condition after 1 week.
  • the types of precipitates are different in the two alloys.
  • the Cu-free alloy 1 one finds a combination of B', ⁇ ', U2 and U1 precipitates.
  • the dominating precipitate type is the Q'-phase. It seems that Q' is more stable against precipitate coarsening than B', ⁇ ', U2 and U1.
  • TEM investigations reveal that this is due to an even smaller precipitate size than in alloy 2.
  • Fig. 2 c shows a TEM image of equal magnification as for alloys 1 and 2, after exposure at 200°C for 7 days.
  • Q' is the dominating precipitate type in alloy 2
  • alloy 3 contains mostly L-type precipitates. These precipitate types are even more stable against coarsening than the Q'-type, and the features of these precipitates (crystal structure and orientation relationship with the aluminium crystal lattice) are preferred for alloys designed for high temperature stability.
  • the L-phase is the dominating precipitate type.
  • a flat rectangular cross-section with a well-defined long edge aligned in the [100] direction of the aluminium lattice This is the precipitate type that is most resistant to coarsening, and the key to successfully make a high-temperature stable alloy is that this precipitate type becomes dominant upon high-temperature exposure.
  • alloy 8 which has approximately 10% higher content of Mg+Si+Cu than alloy 3
  • alloy 9 which has approximately 10% lower content of Mg+Si+Cu than alloy 3, see Table 1 for full composition.
  • Fig. 6 shows the results of the development in Vickers hardness as a function of exposure time at 200°C for these alloys.
  • the hardness of alloy 3 mostly lies in between those of alloy 8 an 9.
  • the hardness of alloy 9 is clearly lower. This indicates that the sum of alloying elements Mg+Si+Cu chosen for alloy 3 is fairly optimal.
  • Figure 7 shows the precipitate statistics as measured in TEM for alloy 3, 8 and 9 after 1 week exposure at 200°C.
  • the L-type precipitate was dominating for all alloys in this condition.
  • Alloy 8 with the highest Mg+Si+Cu content, has the highest number densitiy of precipitates, but also the smallest precipitate size, of the alloys. These two differences seem to nearly cancel out on the effect of strength compared to alloy 3
  • Alloy 9 with the lowest Mg+Si+Cu content has slightly lower number density of precipitates, slightly lower volume fraction, and slightly lower precipitate size than alloy 3. These differences all have a negative effect on strength, and in sum they give a significantly lower strength in alloy 9 than in alloy 3.
  • Cu is a critical element in the sense that a high Cu content may be detrimental for processing and fabrication characteristics, such as castability and extrudability of the alloys, as well as for corrosion properties of components.
  • a certain Cu content is necessary to achieve the desired precipitate types in the alloys, namely the precipitate types that have been proven to be most resistant to coarsening during high temperature exposure.
  • alloy 10 was prepared, which is similar to alloy 6 (Mg/Si ratio is 3) except for the Cu content, which is 0.30 wt.%.
  • the development in Vickers hardness as a function of exposure time at 200°C for alloy 6 and alloy 10 is shown in Fig. 8 .
  • the results show that the lower Cu content has a significant negative effect on the strength, and possibly also a slight negative effect on the softening rate of the alloy.
  • the recommended Cu level of the alloy will therefore be dictated by the strength requirement for the desired application.
  • Fig. 9 compares the development in Vickers hardness as a function of exposure time at 200°C of the alloys 11, 12 and 13 to that of alloy 6. It is seen that the substitution of a fraction of Si with Ge (alloy 6 vs alloy 12) enhances the temperature stability of the alloy somewhat. Just adding Ag to the alloy does lower the temperature stability (alloy 11 vs alloy 6), but when used in combination with the Ge it seems to further enhance the temperature stability of the alloy (alloy 13 vs alloy 12)
  • Fig. 10 compares the development in Vickers hardness as a function of exposure time at 200°C of alloy 14 to that of alloy 10.
  • the substitution of a fraction of Si with Ge leads to a considerable increase in the hardness, and by comparing Fig. 10 with Fig. 8 one finds that the Ge/Si substitution compensates for the lower level of Cu in alloy 10 compared to alloy 6.
  • Figure 11 shows a TEM image of alloy 12 after exposure to 200°C for 1 week. The condition of the material and magnification of the image is identic to those of Figure 2 , and can be compared directly. It is evident that the Ge-modification leads to a finer precipitate structure.
  • Figure 12 shows the development in hardness of alloy 3, 6, 15 and 16 during high-temperature exposure at 250°C. Alloys 3 and 6, which lie within the optimal alloy window revealed in this application, have a much better temperature stability than alloys 15 and 16, which are outside this optimal window. It is worthwhile to note that the temperature stability of alloys 3 and 6 at 250°C is much better than that of alloy 2 at 200°C (compare Figs. 1 and 12 ). This illustrates the great advantage in temperature stability of alloys according to the present invention in comparison with the common 6082-alloy.
  • Alloys 3 and 6 were also subjected to a high temperature exposure of 350°C for 5h. After this heat treatment there has been a change in dominating precipitate type from L to Q'.
  • Fig. 13 shows an Mg-Si chart illustrating polygons defined by the coordinates in the Mg-Si diagram visualizing as rectangles the Mg and Si contents as defined in claims 1 through 6.

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  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Materials For Medical Uses (AREA)
  • Conductive Materials (AREA)

Claims (6)

  1. Alliage de Al-Mg-Si-Cu possédant une bonne stabilité thermique, dans lequel sa teneur en Mg et en Si se situe à l'intérieur d'un polygone défini par les coordonnées suivantes d'un diagramme de Mg-Si :
    a1 - a2 - a3 - a4 - a1
    dans lequel en termes de pourcentage massique, a1 = 0,60 Mg, 0,60 Si, a2 = 0,90 Mg, 0,90 Si, a3 = 1,30 Mg, 0,60 Si et a4 = 1,00 Mg, 0,30 Si, et dans lequel Mn est compris entre 0,40 et 0,80 % en poids à des fins d'ajustement de la structure de grains pendant le traitement de l'alliage,
    et avec les éléments d'alliages suivants :
    - Cu compris entre 0,20 et 0,50 % en poids
    - Fe compris entre 0,08 et 0,40 % en poids,
    et où éventuellement au moins un des éléments suivants est ajouté à des fins d'ajustement de la structure de grains pendant le traitement de l'alliage
    - Cr compris entre 0 et 0,30 % en poids
    - Zr compris entre 0 et 0,30 % en poids,
    et jusqu'à éventuellement 0,1 % en poids de Ti et jusqu'à 0,1 % en poids de B en tant qu'éléments de raffinage de grains,
    et où Ge est encore éventuellement compris entre 0 et 0,20 % en poids et Ag est compris entre 0 et 0,20 % en poids, le reste étant Al comprenant des impuretés fortuites.
  2. Alliage de Al-Mg-Si-Cu selon la revendication 1,
    caractérisé en ce que la phase L constitue le type de précipité dominant par rapport à la densité en nombre au sur-vieillissement.
  3. Alliage de Al-Mg-Si-Cu selon la revendication 1 ou la revendication 2,
    caractérisé en ce que sa teneur en Mg et en Si se situe à l'intérieur d'un polygone défini par les coordonnées suivantes d'un diagramme de Mg-Si :
    b1 - b2 - b3 - b4 - b1
    dans lequel en termes de pourcentage massique b1 = 0,70 Mg, 0,60 Si, b2 = 0,90 Mg, 0,80 Si, b3 = 1,20 Mg, 0,60 Si et b4 = 0,98 Mg, 0,37 Si.
  4. Alliage de Al-Mg-Si-Cu selon l'une quelconque des revendications 1 à 3,
    caractérisé en ce que sa teneur en Mg et en Si se situe à l'intérieur d'un polygone défini par les coordonnées suivantes d'un diagramme de Mg-Si :
    c1 - c2 - c3 - c4 - c1
    dans lequel en termes de pourcentage massique c1 = 0,75 Mg, 0,62 Si, c2 = 0,90 Mg, 0,75 Si, c3 = 1,15 Mg, 0,58 Si et c4 = 0,98 Mg, 0,42 Si.
  5. Alliage de Al-Mg-Si-Cu selon l'une quelconque des revendications 1 à 4,
    caractérisé en ce que
    Ge est compris entre 0,004 et 0,20 % en poids.
  6. Alliage de Al-Mg-Si-Cu selon l'une quelconque des revendications 1 à 5,
    caractérisé en ce que
    le rapport Mg/Si est compris entre 1,5 et 4.
EP11763104.4A 2010-03-30 2011-03-30 Alliage d'aluminium stable à haute température Revoked EP2553131B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
NO20100474 2010-03-30
PCT/NO2011/000111 WO2011122958A1 (fr) 2010-03-30 2011-03-30 Alliage d'aluminium stable à haute température

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EP2553131A1 EP2553131A1 (fr) 2013-02-06
EP2553131A4 EP2553131A4 (fr) 2017-04-05
EP2553131B1 true EP2553131B1 (fr) 2019-05-08

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Cited By (2)

* Cited by examiner, † Cited by third party
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US10633725B2 (en) * 2015-10-14 2020-04-28 NaneAL LLC Aluminum-iron-zirconium alloys
EP3122912B1 (fr) * 2014-03-24 2024-05-15 Constellium Extrusion Decin S.r.o. Produit filé en alliage 6xxx apte au décolletage et présentant une faible rugosité après anodisation

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PL3339457T3 (pl) * 2012-04-25 2020-12-14 Norsk Hydro Asa Wyciskany profil stopu aluminium al-mg-si o polepszonych właściwościach
WO2014201565A1 (fr) 2013-06-19 2014-12-24 Rio Tinto Alcan International Limited Composition d'alliage d'aluminium présentant des propriétés mécaniques améliorées, à température élevée
CN107743526B (zh) 2015-06-15 2020-08-25 肯联铝业辛根有限责任公司 用于获得由6xxx铝合金制成的用于牵引孔眼的高强度固体挤出产品的制造方法
SI25352A (sl) 2017-09-13 2018-07-31 UNIVERZA V MARIBORU Fakulteta za Strojništvo Izdelava visokotrdnostnih in temperaturnoobstojnih aluminijevih zlitin utrjenih z dvojnimi izločki
CN111014332B (zh) * 2019-12-31 2021-05-28 辽宁忠旺集团有限公司 具有高长期热稳定性的6系高合金成分及其制备方法
CN113564433B (zh) * 2021-08-10 2022-06-03 江苏亚太航空科技有限公司 一种耐腐蚀的6082铝合金材料及其熔铸工艺

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FR1602294A (fr) 1967-02-27 1970-11-02
DE2103614A1 (de) 1970-02-25 1971-09-09 Olin Corp Warmverformbare Alumimumlegierungen und Verfahren zu deren Verarbeitung
US3717512A (en) 1971-10-28 1973-02-20 Olin Corp Aluminum base alloys
US4082578A (en) 1976-08-05 1978-04-04 Aluminum Company Of America Aluminum structural members for vehicles
JPS58167575A (ja) 1982-03-16 1983-10-03 バイエル・アクチエンゲゼルシヤフト フエノキシプロピルトリアゾリル−ケトン及びカルビノ−ル、その製法並びに利用
JPS58167757A (ja) 1982-03-29 1983-10-04 Nippon Light Metal Co Ltd 耐食性，溶接性および焼入性のすぐれた加工用Ａｌ−Ｍｇ−Ｓｉ系合金の製造法
DE4421744A1 (de) 1993-07-02 1995-01-12 Fuchs Fa Otto Verwendung einer Knetlegierung des Types AlMgSiCu zur Herstellung von hochfesten und korrosionsbeständigen Teilen
EP0676480A1 (fr) 1994-04-07 1995-10-11 Northwest Aluminum Company Alliage d'aluminium du type MG-Si à haute résistance mécanique
WO1995027091A1 (fr) 1994-03-30 1995-10-12 Reynolds Metals Company Procede de fabrication de pieces extrudees d'alliage d'aluminium
EP0687743A1 (fr) 1994-06-16 1995-12-20 The Furukawa Electric Co., Ltd. Matériau de renforcement en alliage d'aluminium pour pare-choc et procédé de fabrication
JPH086161B2 (ja) 1988-03-07 1996-01-24 日本軽金属株式会社 高強度Ａ１‐Ｍｇ‐Ｓｉ系合金部材の製造法
US5888320A (en) 1995-05-11 1999-03-30 Kaiser Aluminum & Chemical Corporation Aluminum alloy having improved damage tolerant characteristics
EP0936278A1 (fr) 1998-02-17 1999-08-18 Hoogovens Aluminium Profiltechnik Bonn GmbH Alliage d'aluminium et procédé pour sa fabrication
EP0987344A1 (fr) 1998-08-25 2000-03-22 Kabushiki Kaisha Kobe Seiko Sho Pièces forgées en alliage d'aluminium à haute résistance mécanique
EP0997547A1 (fr) 1998-10-27 2000-05-03 Kabushiki Kaisha Kobe Seiko Sho Extrusion d'un alliage de Al-Mg-Si à base d'aluminium
EP1041165A1 (fr) 1999-04-02 2000-10-04 Kabushiki Kaisha Kobe Seiko Sho Matériau amortissant les chocs
EP1104815A1 (fr) 1999-12-02 2001-06-06 Alusuisse Technology & Management AG Alliage d'aluminium et produit extrudé de celui-ci
US6248189B1 (en) 1998-12-09 2001-06-19 Kaiser Aluminum & Chemical Corporation Aluminum alloy useful for driveshaft assemblies and method of manufacturing extruded tube of such alloy
US6258465B1 (en) 1997-07-09 2001-07-10 Kabushiki Kaisha Kobe Seiko Sho Energy absorbing member
WO2002099151A2 (fr) 2001-06-01 2002-12-12 Alcoa Inc. Procede d'amelioration des alliages de la serie 6xxx par la reduction des sites de densite alteres
JP2003155535A (ja) 2001-11-16 2003-05-30 Nippon Light Metal Co Ltd 自動車ブラケット用アルミニウム合金押出材およびその製造方法
JP2003181530A (ja) 2001-12-20 2003-07-02 Mitsubishi Alum Co Ltd 曲げ加工性およびエネルギー吸収特性に優れたアルミニウム合金押出し材の製造方法
JP2004292937A (ja) 2003-03-28 2004-10-21 Kobe Steel Ltd 輸送機構造材用アルミニウム合金鍛造材およびその製造方法
EP1614760A1 (fr) 2003-04-15 2006-01-11 Nippon Light Metal Company Ltd. Plaque d'alliage d'aluminium presentant une excellente formabilite de pressage et une excellente soudabilite par points presentant une resistance continue, ainsi que methode pour sa production
EP1715067A1 (fr) 2003-12-26 2006-10-25 Nippon Light Metal, Co., Ltd. Procede de production de plaques d'alliage d'al-mg-si presentant une excellente capacite de durcissement thermique
DE102005060297A1 (de) 2005-11-14 2007-05-16 Fuchs Kg Otto Energieabsorbtionsbauteil
WO2007094686A1 (fr) 2006-02-17 2007-08-23 Norsk Hydro Asa Alliage en aluminium presentant des proprietes d'ecrasement ameliorees
EP2003219A2 (fr) 2006-03-31 2008-12-17 Kabushiki Kaisha Kobe Seiko Sho Element forge d'alliage d'aluminium et son procede de production
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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1602294A (fr) 1967-02-27 1970-11-02
DE2103614A1 (de) 1970-02-25 1971-09-09 Olin Corp Warmverformbare Alumimumlegierungen und Verfahren zu deren Verarbeitung
US3717512A (en) 1971-10-28 1973-02-20 Olin Corp Aluminum base alloys
US4082578A (en) 1976-08-05 1978-04-04 Aluminum Company Of America Aluminum structural members for vehicles
JPS58167575A (ja) 1982-03-16 1983-10-03 バイエル・アクチエンゲゼルシヤフト フエノキシプロピルトリアゾリル−ケトン及びカルビノ−ル、その製法並びに利用
JPS58167757A (ja) 1982-03-29 1983-10-04 Nippon Light Metal Co Ltd 耐食性，溶接性および焼入性のすぐれた加工用Ａｌ−Ｍｇ−Ｓｉ系合金の製造法
JPH086161B2 (ja) 1988-03-07 1996-01-24 日本軽金属株式会社 高強度Ａ１‐Ｍｇ‐Ｓｉ系合金部材の製造法
DE4421744A1 (de) 1993-07-02 1995-01-12 Fuchs Fa Otto Verwendung einer Knetlegierung des Types AlMgSiCu zur Herstellung von hochfesten und korrosionsbeständigen Teilen
WO1995027091A1 (fr) 1994-03-30 1995-10-12 Reynolds Metals Company Procede de fabrication de pieces extrudees d'alliage d'aluminium
EP0676480A1 (fr) 1994-04-07 1995-10-11 Northwest Aluminum Company Alliage d'aluminium du type MG-Si à haute résistance mécanique
EP0687743A1 (fr) 1994-06-16 1995-12-20 The Furukawa Electric Co., Ltd. Matériau de renforcement en alliage d'aluminium pour pare-choc et procédé de fabrication
US5888320A (en) 1995-05-11 1999-03-30 Kaiser Aluminum & Chemical Corporation Aluminum alloy having improved damage tolerant characteristics
US6258465B1 (en) 1997-07-09 2001-07-10 Kabushiki Kaisha Kobe Seiko Sho Energy absorbing member
EP0936278A1 (fr) 1998-02-17 1999-08-18 Hoogovens Aluminium Profiltechnik Bonn GmbH Alliage d'aluminium et procédé pour sa fabrication
EP0987344A1 (fr) 1998-08-25 2000-03-22 Kabushiki Kaisha Kobe Seiko Sho Pièces forgées en alliage d'aluminium à haute résistance mécanique
EP0997547A1 (fr) 1998-10-27 2000-05-03 Kabushiki Kaisha Kobe Seiko Sho Extrusion d'un alliage de Al-Mg-Si à base d'aluminium
US6248189B1 (en) 1998-12-09 2001-06-19 Kaiser Aluminum & Chemical Corporation Aluminum alloy useful for driveshaft assemblies and method of manufacturing extruded tube of such alloy
EP1041165A1 (fr) 1999-04-02 2000-10-04 Kabushiki Kaisha Kobe Seiko Sho Matériau amortissant les chocs
EP1104815A1 (fr) 1999-12-02 2001-06-06 Alusuisse Technology & Management AG Alliage d'aluminium et produit extrudé de celui-ci
WO2002099151A2 (fr) 2001-06-01 2002-12-12 Alcoa Inc. Procede d'amelioration des alliages de la serie 6xxx par la reduction des sites de densite alteres
JP2003155535A (ja) 2001-11-16 2003-05-30 Nippon Light Metal Co Ltd 自動車ブラケット用アルミニウム合金押出材およびその製造方法
JP2003181530A (ja) 2001-12-20 2003-07-02 Mitsubishi Alum Co Ltd 曲げ加工性およびエネルギー吸収特性に優れたアルミニウム合金押出し材の製造方法
JP2004292937A (ja) 2003-03-28 2004-10-21 Kobe Steel Ltd 輸送機構造材用アルミニウム合金鍛造材およびその製造方法
EP1614760A1 (fr) 2003-04-15 2006-01-11 Nippon Light Metal Company Ltd. Plaque d'alliage d'aluminium presentant une excellente formabilite de pressage et une excellente soudabilite par points presentant une resistance continue, ainsi que methode pour sa production
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