EP1458898A1 - Alliage d'aluminium deformable a chaud et a froid - Google Patents

Alliage d'aluminium deformable a chaud et a froid

Info

Publication number
EP1458898A1
EP1458898A1 EP02787956A EP02787956A EP1458898A1 EP 1458898 A1 EP1458898 A1 EP 1458898A1 EP 02787956 A EP02787956 A EP 02787956A EP 02787956 A EP02787956 A EP 02787956A EP 1458898 A1 EP1458898 A1 EP 1458898A1
Authority
EP
European Patent Office
Prior art keywords
semi
component
finished product
less
silicon
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
Application number
EP02787956A
Other languages
German (de)
English (en)
Other versions
EP1458898B1 (fr
Inventor
Andreas Barth
Patrick Laevers
Arne Mulkers
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.)
Alvance Aluminium Duffel BV
Mercedes Benz Group AG
Original Assignee
Corus Aluminium NV
DaimlerChrysler AG
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 Corus Aluminium NV, DaimlerChrysler AG filed Critical Corus Aluminium NV
Publication of EP1458898A1 publication Critical patent/EP1458898A1/fr
Application granted granted Critical
Publication of EP1458898B1 publication Critical patent/EP1458898B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

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
    • C22F1/043—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 silicon 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
    • C22C21/02—Alloys based on aluminium with silicon 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
    • C22C21/06—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
    • 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
    • C22F1/05—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 of the Al-Si-Mg type, i.e. containing silicon and magnesium in approximately equal proportions

Definitions

  • the invention relates to a hot and cold formable aluminum alloy according to claim 1 and a method for producing an aluminum component according to claim 5 and the use of an aluminum alloy according to claim 9.
  • High-strength Cu e.g. Al Mg Si 1 Cu 0.5
  • Zn-containing, heat-treated Al semi-finished products and Al forgings have high static strength values, but their elongation at break is low. In the case of a notch effect (e.g. stone chips), this results in a low dynamic strength.
  • These alloys are also susceptible to corrosion, so that expensive corrosion protection is necessary to avoid notch-causing corrosion scars. Because e.g. highly stressed, forged aluminum chassis parts are always exposed to stone chips (notches) and corrosion, in these areas only in exceptional cases Cu / Zn-containing AI materials are used. More ductile or notch-sensitive AI Mg Si 1 alloys such. B. the EN-AW 6082 are corrosion-resistant due to their very low Cu and Zn content, but these alloys do not achieve sufficient strength values.
  • German Offenlegungsschriften DE OS 2 103 614 and DE OS 2 213 136 each describe an aluminum-silicon-magnesium alloy which reacts to inhibit recrystallization, but these alloys are too weak in strength, and the tendency to recrystallize this alloy is for multi-formed or cold formed components still too high. The same applies to the well-known alloy according to EN-AW 6082.
  • the object of the invention is to provide a component and a method for producing a component which have a better recrystallization-inhibiting effect compared to the prior art and lead to a higher strength and corrosion resistance of the components.
  • the object is achieved in a component or semi-finished product according to claim 1 and in a method according to claim 9.
  • the component or semi-finished product according to the invention consists of an aluminum alloy with the following composition:
  • Titan serves to refine the grain, zinc can contribute to increasing the strength.
  • the alloy contains unavoidable impurities that are due to the manufacturing process.
  • the alloy has a silicon content between 0.9 and 1.7% by weight.
  • the invention is also characterized in that the alloy elements manganese, chromium and zirconium and / or hafnium together have a proportion of at least 0.4% by weight. The proportion of these is preferably Elements higher than 0.6% by weight. These elements act as recrystallization inhibitors.
  • intermetallic dispersoids with the aluminum during homogenization annealing, which anchor the grain boundaries and do not dissolve or only dissolve to a small extent during further temperature treatments. By anchoring the dispersoids to the grain boundaries, the growth of the grains to coarse grains is prevented, so that recrystallization is sustainably suppressed.
  • Zirconium and hafnium-containing dispersoids are particularly temperature-stable, which has an inhibiting effect on recrystallization at high temperatures.
  • the alloy has a silicon content of 0.9 to 1.3%. It has been found that a lower silicon content does not lead to the required strength values.
  • the silicon works in combination with the magnesium in the form of precipitation hardening (heat treatment), which occurs in the form of Mg2S ⁇ deposits. Higher levels of manganese and chromium also lead to hardening of the precipitate or increase in strengthening.
  • the ratio of silicon to magnesium is therefore preferably between 1.1 to 1.3 to 1, particularly preferably between 1.16 to 1.24 to 1.
  • the alloy is particularly resistant to recrystallization in both hot and cold forming. Almost independent of a manufacturing process, it exhibits high strength and a low tendency to corrode. The minor The tendency to corrode is mainly due to the low proportion of copper and zinc.
  • the process is characterized in that the cast raw material of the alloy is homogenized at temperatures between 420 ° C and 540 ° C, preferably between 460 ° C and 500 ° C.
  • the alloy components magnesium and silicon are finely distributed in the aluminum matrix and the dispersoids are formed, which, as described, are based on zirconium or hafnium, manganese, chromium and / or iron.
  • the raw material is formed into semi-finished products at a temperature between 450 ° C and 560 ° C (e.g. extrusion or rolling of sheets) and optionally quenched.
  • the semi-finished product is preferably formed between 500 ° C and 560 ° C, with the highest possible temperature being selected in order to
  • the semi-finished products are separated into workpieces that are suitable for forming and either cold-formed once or several times or, if necessary, formed several times hot into components or other semi-finished products. Machining the semi-finished products, e.g. B. by turning or milling is also useful. The hot or cold forming or the machining can take place within the scope of the professional ability and, if necessary, include the usual heat treatments.
  • the hot forming of the semi-finished product follows at temperatures which are in the range of the usual solution annealing (between 440 ° C and 560 ° C). During the forming process, especially during several forming steps, it must be ensured that the The temperature of the workpiece does not fall below the specified temperature, which has resulted in coarse deposits in the component structure. The forming process therefore replaces the process step of solution annealing, which has a significant impact on process costs and process duration.
  • the forming temperatures according to the invention which also include solution annealing, are higher than the usual forming temperatures, which results in less solidification and thus less recrystallization nucleation in the structure.
  • the recrystallization is thus sustainably suppressed.
  • the result is higher strength values and, above all, significantly higher elongation at break in highly formed areas.
  • the workpiece is preferably quenched in water, which freezes the structure. Subsequent hot curing between 160 ° C and 240 ° C results in the desired increase in strength.
  • the aluminum component according to the invention has a tensile strength of at least 400 MPa and a minimum elongation at break (A5) of 10% with a composition corresponding to the alloy specifications.
  • Components of this type are preferably used as tension struts or other chassis parts, profiles, bolts, screws or wheels.
  • the bars are poured into bars.
  • the bars are homogenized at a temperature of 480 ° C for 12 h.
  • the round bars are quenched and separated into approximately 20 cm long workpieces.
  • the tension struts are quenched in water and aged at 200 ° C for 4 hours.
  • the tensile struts have a tensile strength of more than 400 MPa and an elongation at break (A5) of more than 13% both in the area of a central strut and in the area of a large eye, which usually has a high degree of recrystallization due to the high degree of deformation.

Landscapes

  • Chemical & Material Sciences (AREA)
  • Mechanical Engineering (AREA)
  • Organic Chemistry (AREA)
  • Metallurgy (AREA)
  • Engineering & Computer Science (AREA)
  • Materials Engineering (AREA)
  • Crystallography & Structural Chemistry (AREA)
  • Physics & Mathematics (AREA)
  • Thermal Sciences (AREA)
  • Forging (AREA)
  • Powder Metallurgy (AREA)
  • Conductive Materials (AREA)
  • Cookers (AREA)
EP02787956A 2001-12-21 2002-12-18 Procede de fabrication d'un article en alliage d'aluminium deformable a chaud et a froid Expired - Lifetime EP1458898B1 (fr)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
DE10163039 2001-12-21
DE10163039A DE10163039C1 (de) 2001-12-21 2001-12-21 Warm- und kaltumformbares Bauteil aus einer Aluminiumlegierung und Verfahren zu seiner Herstellung
PCT/EP2002/014452 WO2003054243A1 (fr) 2001-12-21 2002-12-18 Alliage d'aluminium deformable a chaud et a froid

Publications (2)

Publication Number Publication Date
EP1458898A1 true EP1458898A1 (fr) 2004-09-22
EP1458898B1 EP1458898B1 (fr) 2005-04-27

Family

ID=7710217

Family Applications (1)

Application Number Title Priority Date Filing Date
EP02787956A Expired - Lifetime EP1458898B1 (fr) 2001-12-21 2002-12-18 Procede de fabrication d'un article en alliage d'aluminium deformable a chaud et a froid

Country Status (7)

Country Link
US (2) US20050095167A1 (fr)
EP (1) EP1458898B1 (fr)
AT (1) ATE294252T1 (fr)
AU (1) AU2002352255A1 (fr)
DE (2) DE10163039C1 (fr)
ES (1) ES2239261T3 (fr)
WO (1) WO2003054243A1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3214191A1 (fr) 2016-03-04 2017-09-06 Impol 2000, d. d. Alliage d'aluminium al-mg-si à haute résistance et son procédé de fabrication
WO2017207603A1 (fr) * 2016-06-01 2017-12-07 Aleris Aluminum Duffel Bvba Matériau à forger en alliage d'aluminium de série 6xxx et son procédé de fabrication

Families Citing this family (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102005060297A1 (de) * 2005-11-14 2007-05-16 Fuchs Kg Otto Energieabsorbtionsbauteil
JP4944525B2 (ja) * 2006-07-18 2012-06-06 株式会社神戸製鋼所 ボルトの製造方法、ボルト、ボルト用の形材、ボルト用の形材の成形装置及びボルト用の形材の成形方法
DE102007032143A1 (de) * 2007-07-09 2009-01-15 Thyssenkrupp Drauz Nothelfer Gmbh Tür eines Kraftfahrzeuges
EP2149618B1 (fr) * 2008-07-30 2011-10-26 Olab S.r.l. Procédé d'emboutissage à chaud, en particulier pour la fabrication de raccords métalliques pour des circuits hydrauliques, pneumatiques ou contenant des fluides, et raccord obtenu par ce procédé.
DE102009059804A1 (de) 2009-12-21 2011-06-22 Daimler AG, 70327 Verfahren zur Wärmebehandlung von miteinander verschraubbaren Gussbauteilen
WO2013080650A1 (fr) * 2011-12-02 2013-06-06 古河スカイ株式会社 Matériau en alliage d'aluminium et structure en alliage d'aluminium et leur procédé de production
JP5872443B2 (ja) 2012-03-30 2016-03-01 株式会社神戸製鋼所 自動車用アルミニウム合金鍛造材およびその製造方法
WO2014003074A1 (fr) 2012-06-27 2014-01-03 株式会社Uacj Feuille d'alliage d'aluminium pour moulage par soufflage et procédé de production correspondant
JP6557476B2 (ja) * 2015-02-10 2019-08-07 三菱アルミニウム株式会社 アルミニウム合金フィン材
WO2019139724A1 (fr) 2018-01-12 2019-07-18 Accuride Corporation Roues en aluminium et procédés de fabrication
FR3101641B1 (fr) * 2019-10-04 2022-01-21 Constellium Issoire Tôles de précision en alliage d’aluminium
CN112522552B (zh) * 2020-11-04 2022-04-26 佛山科学技术学院 一种耐蚀的铝合金及其制备方法和应用

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CA962172A (en) * 1971-05-05 1975-02-04 Olin Corporation High ductility high strength aluminum base alloys and process for obtaining same
US3945860A (en) * 1971-05-05 1976-03-23 Swiss Aluminium Limited Process for obtaining high ductility high strength aluminum base alloys
US3717512A (en) * 1971-10-28 1973-02-20 Olin Corp Aluminum base alloys
CH624147A5 (fr) * 1976-12-24 1981-07-15 Alusuisse
JPS58156197A (ja) * 1982-03-10 1983-09-17 Sumitomo Light Metal Ind Ltd 超高圧用プレ−トフイン型熱交換器
FR2529578B1 (fr) * 1982-07-02 1986-04-11 Cegedur Procede pour ameliorer a la fois la resistance a la fatigue et la tenacite des alliages d'al a haute resistance
FR2617188B1 (fr) * 1987-06-23 1989-10-20 Cegedur Alliage a base d'al pour boitage et procede d'obtention
US5108519A (en) * 1988-01-28 1992-04-28 Aluminum Company Of America Aluminum-lithium alloys suitable for forgings
JPH03287738A (ja) * 1990-04-03 1991-12-18 Kobe Steel Ltd 真空ろう付け法により組立てられる熱交換器用フィン材及びその製造方法
DE4421744C2 (de) * 1993-07-02 1996-05-23 Fuchs Fa Otto Verwendung einer Knetlegierung des Types AlMgSiCu zur Herstellung von hochfesten und korrosionsbeständigen Teilen
JPH07197219A (ja) * 1993-12-28 1995-08-01 Furukawa Electric Co Ltd:The 成形用アルミニウム合金板材の製造方法
FR2737225B1 (fr) * 1995-07-28 1997-09-05 Pechiney Rhenalu Alliage al-cu-mg a resistance elevee au fluage
FR2744136B1 (fr) * 1996-01-25 1998-03-06 Pechiney Rhenalu Produits epais en alliage alznmgcu a proprietes ameliorees
JPH11310841A (ja) * 1998-04-28 1999-11-09 Nippon Steel Corp 疲労強度に優れたアルミニウム合金押出形材およびその製造方法
US6630037B1 (en) * 1998-08-25 2003-10-07 Kobe Steel, Ltd. High strength aluminum alloy forgings

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See references of WO03054243A1 *

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3214191A1 (fr) 2016-03-04 2017-09-06 Impol 2000, d. d. Alliage d'aluminium al-mg-si à haute résistance et son procédé de fabrication
WO2017207603A1 (fr) * 2016-06-01 2017-12-07 Aleris Aluminum Duffel Bvba Matériau à forger en alliage d'aluminium de série 6xxx et son procédé de fabrication
CN109415780A (zh) * 2016-06-01 2019-03-01 阿莱利斯铝业迪弗尔私人有限公司 6xxx系列铝合金锻造坯料及其制造方法
CN109415780B (zh) * 2016-06-01 2021-02-23 阿莱利斯铝业迪弗尔私人有限公司 6xxx系列铝合金锻造坯料及其制造方法

Also Published As

Publication number Publication date
US20050095167A1 (en) 2005-05-05
DE10163039C1 (de) 2003-07-24
US20080078480A1 (en) 2008-04-03
ATE294252T1 (de) 2005-05-15
ES2239261T3 (es) 2005-09-16
EP1458898B1 (fr) 2005-04-27
WO2003054243A1 (fr) 2003-07-03
AU2002352255A1 (en) 2003-07-09
DE50202955D1 (de) 2005-06-02

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