EP1045043B1 - Verfahren zur Herstellung von Formteilen aus Aluminiumlegierung vom Typ 2024 - Google Patents

Verfahren zur Herstellung von Formteilen aus Aluminiumlegierung vom Typ 2024 Download PDF

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Publication number
EP1045043B1
EP1045043B1 EP00420071A EP00420071A EP1045043B1 EP 1045043 B1 EP1045043 B1 EP 1045043B1 EP 00420071 A EP00420071 A EP 00420071A EP 00420071 A EP00420071 A EP 00420071A EP 1045043 B1 EP1045043 B1 EP 1045043B1
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EP
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Prior art keywords
process according
temperature
content
less
quenching
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EP00420071A
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English (en)
French (fr)
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EP1045043A1 (de
Inventor
Hervé Ribes
Guy-Michel Raynaud
Ronan Dif
Martin Peter Schmidt
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Constellium Issoire SAS
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Pechiney Rhenalu SAS
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Classifications

    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22F—CHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS AND NON-FERROUS ALLOYS
    • C22F1/00—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
    • C22F1/04—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon
    • C22F1/057—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon of alloys with copper as the next major constituent
    • 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
    • C22C21/12—Alloys based on aluminium with copper as the next major constituent
    • C22C21/16—Alloys based on aluminium with copper as the next major constituent with magnesium

Definitions

  • the invention relates to a method of manufacturing highly deformed parts, intended for mechanical engineering and in particular for aeronautical construction, using AlCuMg type 2024 aluminum alloy sheets according to the nomenclature of the Aluminum Association.
  • Alloy 2024 is widely used in aircraft construction and its composition registered in the Aluminum Association is as follows (% by weight): If ⁇ 0.5 Fe ⁇ 0.5 Cu: 3.8 - 4.9 Mn: 0.3 - 0.9 Mg: 1.2 - 1.8 Zn ⁇ 0.25 Cr ⁇ 0.10 Ti ⁇ 0 15 Certain parts, made in particular by stretch-forming (the term “stretch-forming" is often used), stamping, spinning, bending or rolling, require, in addition to the properties usually required for aircraft construction, such as high strength. mechanics, toughness, resistance to the propagation of cracks etc, sheets having a good formability.
  • EP 0473122 discloses a method for manufacturing alloy steel sheets.
  • Patent Application EP 0731185 discloses sheets of modified alloy 2024, later registered with the Aluminum Association under the designation 2024A, having a reduced level of residual stresses and improved toughness for heavy plates, and improved elongation for thin sheets. This application limits the content of Mn to 0.55% and that in Fe to 0.25%, with the relation: 0 ⁇ Mn - 2 Fe ⁇ 0.2 (the contents Mn and Fe being expressed in%).
  • the patent application WO 96/29440 describes a method of manufacturing a product in type 2024 aluminum alloy, having a hot rolling, an annealing, a cold rolling, dissolving, quenching and cold forming minimum, which may be traction, straightening or leveling, a process intended improve formability.
  • the request recommends a preferential composition of the alloy: Cu: 4.0 - 4.4, Mg: 1.25 - 1.5, Mn: 0.35 - 0.5, Si ⁇ 0.12, Fe ⁇ 0.08, Ti ⁇ 0.06.
  • Intermediate annealing between hot rolling and cold rolling is presented as favorable for strength and toughness.
  • This step the additional and unusual process has disadvantages economic. Nor does it solve the problem posed by the market, namely provide plates with characteristics such that their shaping is simplified.
  • the sheets are in a state characterized by good formability, but this state is unstable (state "W"), and the shaping must occur on fresh quenching, c that is to say within a short time after quenching, of the order of a few tens of minutes to a few hours. If this is not possible for reasons of production management, the sheet must be stored in a cold room at a sufficiently low temperature and for a sufficiently short duration so as to avoid natural ripening.
  • this solution heat treatment requires large furnaces, which makes the operation inconvenient, including with respect to the same operation performed on flat sheet.
  • the possible need for a cold room adds to the costs and disadvantages of the state of the art. For highly deformed parts, this operation must possibly be repeated, if the material does not have, in the metallurgical state in which it is, sufficient formability to achieve the desired shape in a single operation.
  • the only possible formatting is a rolling.
  • the rolled sheet is then dissolved and quenched, and a second shaping is done either on fresh quenching or after storage in a cold room. In all other cases, the sheet is directly dissolved and quenched before shaping.
  • a first shaping operation is carried out from this state, and a second shaping after dissolution and quenching.
  • This variant is used when the shaping referred to is too important to be carried out in a single operation from a state W, but can however be performed in two passes from the state O. In this state, the The sheet is certainly less formable, but the state O is easier to use than the state W, which is unstable, and requires additional heat treatment.
  • the manufacture of the sheet in state O involves a final annealing of the raw sheet rolling, and therefore an additional manufacturing step, which is contrary to the purpose of simplification targeted by the present invention.
  • a sheet in the W state which generally has the best formability
  • the object of the invention is therefore to simplify the process for manufacturing formed parts, and in particular parts that are highly deformed by one or more processes such as stretch-forming, stamping, spinning or bending, by the combination of an optimized chemical composition and particular manufacturing processes, to avoid as much as possible the setting in solution on formed sheet metal. It goes without saying that any new manufacturing process of highly deformed parts must lead to parts having mechanical characteristics and use at least as good as existing products. Another object of the invention is to obtain parts whose properties of damage tolerance do not degrade after deformation.
  • the alloy has a copper content of between 3.9 and 4.3% (and even more preferably between 3.9 and 4.2%), a magnesium content of between 1.2 and 1.4% (and still preferably between 1.25 and 1.35%), a manganese content between 0.3 and 0.45% iron content ⁇ 0.10%, silicon content ⁇ 0.10% (and preferably ⁇ 0.08%), titanium, chromium and zirconium content ⁇ 0.07% (preferably ⁇ 0.05%).
  • the method according to the invention makes it possible to optionally use plated sheets, for example examples of sheets covered with an alloy plating more resistant to corrosion, as is usually the case for aircraft fuselage liner plates.
  • a first feature of the invention is to use a modified alloy compared to the traditional 2024.
  • the first modification consists in reducing the Si and Fe contents respectively below 0.25 and 0.20%, and preferably below 0.10%.
  • the Mn content is also reduced below 0.5% and preferably below 0.45%.
  • the Cu content is also slightly reduced and maintained below 4.5%, and preferably below 4.3%, or even 4.2%.
  • the Mg content is also slightly reduced, and kept below 1.5%, preferably between 1.2 and 1.4%, or even between 1.25 and 1.35%. The applicant has observed that this composition, suggested by the prior art, does not by itself to achieve the required formability.
  • the alloy is cast into plates, which are homogenized at a temperature between 460 and 510 ° C (preferably between 470 and 500 ° C) for 2 to 12 hours (preferably 3 to 6 hours).
  • the plates may be scalped.
  • the hot rolling is carried out with an inlet temperature of between 430 and 470 ° C, and preferably between 440 and 460 ° C.
  • the outlet temperature of the strips is at a temperature higher than the usual temperature,> 300 ° C., and preferably> 310 ° C.
  • the strips are wound. They present at this stage an elongation of more than 13.5%, and most often greater than 15% in the L and TL directions.
  • the strips are then cut into sheets.
  • a first variant of the invention consists in shaping, by stretch-forming, stamping, spinning or bending, directly on this state F without annealing or other prior treatment.
  • the partially shaped sheet is then dissolved at a temperature between 480 and 500 ° C for a period of between 5 minutes and 1 hour, then quenched, usually with cold water.
  • the formatting is done in two or more passes.
  • the freshly hardened part (less than one hour) can undergo a new shaping immediately, or it is transferred to a cold room at a temperature below 10 ° C and preferably below 0 ° C, and shaped to the exit of the cold room.
  • One or two sided plates can be used, which is the most common case for aircraft fuselage panels plated with a 1000 series alloy, for example 1050, 1100, 1200, 1135 alloys. , 1145, 1170, 1175, 1180, 1185, 1188, 1199, 1230, 1235, 1250, 1285, 1350 or 1435.
  • the distributed elongation is the difference in elongation between the beginning and the end of the plastic deformation domain, that is to say the deformation domain permanent before necking, of the deformation curve.
  • a cold rolled strip has an LDH value greater than 42 mm and preferably higher at 44 mm, while a hot-rolled strip has an LDH value greater than 73 and preferably greater than 75 mm.
  • the preferred composition gives a better formability than the traditional composition.
  • the mechanical properties of the intermediate product do not matter in this situation, provided that the finished product at the end of the whole process has at least one mechanical characteristics. as high as the product resulting from the process according to the prior art.
  • the two products In the state T42, as defined by the draft standard prEN 4211 of July 1995, for a thickness of 6 mm and with an identical manufacturing range, the two products have equivalent mechanical properties.
  • Examples 3s, 3t, 3u, 3v, 3w correspond to the prior art.
  • Examples 3a, 3c, 3d correspond to Examples 2h, 2L and 2m of Example 2; they are shown here for comparison to represent a 2024 W state according to the prior art.
  • T3-optimized composition plates are compared to the plates used in the processes according to the prior art, that is to say a 2024 alloy in the T3 state (Examples 3s, 3t, 3u, 3v, 3w) or W (Examples 3a, 3b, 3c, 3d)), it can be seen that for a given thickness, the process leads to a better formability, as evidenced by the elongation at break and especially the LDH values. and CLF.
  • the springback is lower than in the prior art. More particularly, when the chemical composition is in the preferred range, the process leads to an improvement of the formability as it is characterized by the parameters which have just been enumerated.
  • the process does not lead, after forming by stretching, to a significant decrease in the properties of damage tolerance, unlike the method according to the prior art. It is even noted that the method improves the damage tolerance on a stretched state, ie the state in which the piece is in the finished state.

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  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Physics & Mathematics (AREA)
  • Thermal Sciences (AREA)
  • Crystallography & Structural Chemistry (AREA)
  • Heat Treatment Of Sheet Steel (AREA)
  • Shaping Metal By Deep-Drawing, Or The Like (AREA)
  • Metal Rolling (AREA)

Claims (13)

  1. Verfahren zur Herstellung stark verformter Teile aus AlCuMg-Legierung mit folgenden aufeinanderfolgenden Schritten:
    a) Gießen einer Platte der Zusammensetzung (Gew.-%):
    Cu: 3,8 - 4,5   Mg: 1,2 - 1,5   Mn: 0,3 - 0,5   Si < 0,25   Fe < 0,20 Zn < 0,20   Cr < 0,10   Zr < 0,10   Ti < 0,10, Rest Al und Verunreinigungen,
    b) Homogenisierung bei einer Temperatur von 460 bis 510°C während 2 bis 12 h und vorzugsweise bei einer Temperatur von 470 bis 500°C während 3 bis 6 h,
    c) Warmwalzen mit einer Eingangstemperatur von 430 bis 470°C, vorzugsweise 440 bis 460°C, und mit einer Ausgangstemperatur des Bandes von mehr als 300°C,
    d) Zuschneiden des in Schritt c) gewonnenen Bandes zu Blechen,
    e) Formen der zugeschnittenen Bleche durch ein oder mehrere Verfahren, gewählt unter Ziehformen, Tiefziehen, Drückwalzen oder Biegen,
    f) Lösungsglühen zwischen 480 und 500°C für eine Dauer von 5 min bis 1 h,
    g) Abschrecken.
  2. Verfahren nach Anspruch 1, dadurch gekennzeichnet, dass das geformte Teil nach Lösungsglühen und Abschrecken folgendem Verfahren unterzogen wird:
    a) eventuell sofortige Überführung des frisch abgeschreckten Teils in einen Kälteraum mit einer Temperatur unterhalb 10°C und vorzugsweise unterhalb 0°C,
    b) weniger als 1 Stunde nach Abschrecken und Herausnehmen des Teils aus dem Kälteraum erneutes Formen des Blechs durch ein oder mehrere Verfahren, gewählt unter Ziehformen, Tiefziehen, Drückwalzen oder Biegen.
  3. Verfahren zur Herstellung stark verformter Teile aus AlCuMg-Legierung nach Anspruch 1, bei dem die Bleche nach erfolgtem Zuschneiden in Längs- und Längs-Querrichtung eine Bruchdehnung A von mehr als 13,5 % und vorzugsweise mehr als 15 % aufweisen.
  4. Verfahren nach einem der Ansprüche 1 bis 3, dadurch gekennzeichnet, dass das Blech auf einer oder beiden Seiten mit einem anderen Blech aus Aluminiumlegierung plattiert ist.
  5. Verfahren nach einem der Ansprüche 3 oder 4, dadurch gekennzeichnet, dass die Austrittstemperatur beim Warmwalzen mehr als 300°C und vorzugsweise mehr als 310°C beträgt.
  6. Verfahren nach irgendeinem der Ansprüche 1 bis 5, dadurch gekennzeichnet, dass der Cu-Gehalt 3,9 bis 4,3 % und vorzugsweise 3,9 bis 4,2 % beträgt.
  7. Verfahren nach irgendeinem der Ansprüche 1 bis 6, dadurch gekennzeichnet, dass der Mg-Gehalt 1,2 bis 1,4 % und vorzugsweise 1,25 bis 1,35 % beträgt.
  8. Verfahren nach irgendeinem der Ansprüche 1 bis 7, dadurch gekennzeichnet, dass der Mn-Gehalt 0,30 bis 0,45 % beträgt.
  9. Verfahren nach irgendeinem der Ansprüche 1 bis 8, dadurch gekennzeichnet, dass der Si-Gehalt weniger als 0,10 und vorzugsweise weniger als 0,08 % beträgt.
  10. Verfahren nach irgendeinem der Ansprüche 1 bis 9, dadurch gekennzeichnet, dass der Fe-Gehalt weniger als 0,10 % beträgt.
  11. Verfahren nach irgendeinem der Ansprüche 1 bis 10, dadurch gekennzeichnet, dass Cr < 0,07 % und vorzugsweise < 0,05 %, Zr < 0,07 % und vorzugsweise < 0,05 %, Ti 0,07 % und vorzugsweise < 0,05 %.
  12. Verfahren nach irgendeinem der Ansprüche 1 bis 11, dadurch gekennzeichnet, dass Cu 3,9 - 4,3 Mg 1,2 - 1,4 Mn 0,30 - 0,45 Si < 0,10 Fe < 0,10 und dass das warmgewalzte Blech einen LDH-Wert größer 73 mm aufweist.
  13. Verfahren nach Anspruch 12, dadurch gekennzeichnet, dass das warmgewalzte Blech einen LDH-Wert größer 75 mm aufweist.
EP00420071A 1999-04-12 2000-04-10 Verfahren zur Herstellung von Formteilen aus Aluminiumlegierung vom Typ 2024 Expired - Lifetime EP1045043B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR9904685A FR2792001B1 (fr) 1999-04-12 1999-04-12 Procede de fabrication de pieces de forme en alliage d'aluminium type 2024
FR9904685 1999-04-12

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Publication Number Publication Date
EP1045043A1 EP1045043A1 (de) 2000-10-18
EP1045043B1 true EP1045043B1 (de) 2005-05-18

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US (1) US20030140990A1 (de)
EP (1) EP1045043B1 (de)
JP (1) JP2000328211A (de)
BR (1) BR0001563A (de)
DE (2) DE60020188T2 (de)
FR (1) FR2792001B1 (de)
GB (1) GB2352453A (de)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7883591B2 (en) 2004-10-05 2011-02-08 Aleris Aluminum Koblenz Gmbh High-strength, high toughness Al-Zn alloy product and method for producing such product
US8002913B2 (en) 2006-07-07 2011-08-23 Aleris Aluminum Koblenz Gmbh AA7000-series aluminum alloy products and a method of manufacturing thereof
CN102489971A (zh) * 2011-12-21 2012-06-13 西南铝业（集团）有限责任公司 一种铝合金板材生产方法
US8608876B2 (en) 2006-07-07 2013-12-17 Aleris Aluminum Koblenz Gmbh AA7000-series aluminum alloy products and a method of manufacturing thereof
US10968501B2 (en) 2011-10-14 2021-04-06 Constellium France Transformation process of Al—Cu—Li alloy sheets

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US7494552B2 (en) 2002-08-20 2009-02-24 Aleris Aluminum Koblenz Gmbh Al-Cu alloy with high toughness
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US7604704B2 (en) 2002-08-20 2009-10-20 Aleris Aluminum Koblenz Gmbh Balanced Al-Cu-Mg-Si alloy product
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US20070151637A1 (en) * 2005-10-28 2007-07-05 Aleris Aluminum Koblenz Gmbh Al-Cu-Mg ALLOY SUITABLE FOR AEROSPACE APPLICATION
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FR3004464B1 (fr) * 2013-04-12 2015-03-27 Constellium France Procede de transformation de toles en alliage al-cu-li ameliorant la formabilite et la resistance a la corrosion
CN105543596B (zh) * 2015-12-22 2017-06-20 马鞍山市新马精密铝业股份有限公司 一种航空用铝合金棒材的制造方法
JP6898254B2 (ja) * 2015-12-25 2021-07-07 株式会社Uacj 缶ボディ用アルミニウム合金板及びその製造方法
CN106513638B (zh) * 2016-11-18 2019-07-12 喀左金牛铸造有限公司 2a12铝合金铸造工艺
CN109825748B (zh) * 2019-02-26 2021-08-27 中铝材料应用研究院有限公司 一种提高Al-Cu-Mg系铝合金晶间腐蚀性能的方法
CN110218921A (zh) * 2019-06-21 2019-09-10 天津忠旺铝业有限公司 一种t4态2024铝合金薄板的加工方法
CN111014327A (zh) * 2019-12-31 2020-04-17 营口忠旺铝业有限公司 2024铝合金挤压棒材生产工艺
CN112725671B (zh) * 2020-12-22 2022-08-26 东北轻合金有限责任公司 一种Al-Cu-Mg铝合金线材及其制备方法
CN114134376A (zh) * 2021-12-08 2022-03-04 无锡市世达精密焊管制造有限公司 一种Mg-Cu铝合金及其制备方法

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Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7883591B2 (en) 2004-10-05 2011-02-08 Aleris Aluminum Koblenz Gmbh High-strength, high toughness Al-Zn alloy product and method for producing such product
US8002913B2 (en) 2006-07-07 2011-08-23 Aleris Aluminum Koblenz Gmbh AA7000-series aluminum alloy products and a method of manufacturing thereof
US8088234B2 (en) 2006-07-07 2012-01-03 Aleris Aluminum Koblenz Gmbh AA2000-series aluminum alloy products and a method of manufacturing thereof
US8608876B2 (en) 2006-07-07 2013-12-17 Aleris Aluminum Koblenz Gmbh AA7000-series aluminum alloy products and a method of manufacturing thereof
US10968501B2 (en) 2011-10-14 2021-04-06 Constellium France Transformation process of Al—Cu—Li alloy sheets
US11667994B2 (en) 2011-10-14 2023-06-06 Constellium Issoire Transformation process of Al—Cu—Li alloy sheets
CN102489971A (zh) * 2011-12-21 2012-06-13 西南铝业（集团）有限责任公司 一种铝合金板材生产方法

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Publication number Publication date
EP1045043A1 (de) 2000-10-18
DE00420071T1 (de) 2004-04-22
DE60020188T2 (de) 2006-01-12
DE60020188D1 (de) 2005-06-23
GB0008506D0 (en) 2000-05-24
JP2000328211A (ja) 2000-11-28
FR2792001A1 (fr) 2000-10-13
GB2352453A (en) 2001-01-31
FR2792001B1 (fr) 2001-05-18
US20030140990A1 (en) 2003-07-31
BR0001563A (pt) 2000-10-31

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