EP1143027B1 - Verfahren zur Herstellung von Flugzeugstrukturelementen aus Al-Si-Mg-Legierung - Google Patents

Verfahren zur Herstellung von Flugzeugstrukturelementen aus Al-Si-Mg-Legierung Download PDF

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Publication number
EP1143027B1
EP1143027B1 EP01420078A EP01420078A EP1143027B1 EP 1143027 B1 EP1143027 B1 EP 1143027B1 EP 01420078 A EP01420078 A EP 01420078A EP 01420078 A EP01420078 A EP 01420078A EP 1143027 B1 EP1143027 B1 EP 1143027B1
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Prior art keywords
mpa
state
alloy
product
income
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EP01420078A
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English (en)
French (fr)
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EP1143027A1 (de
Inventor
Ronan Dif
Philippe Lequeu
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Constellium Issoire SAS
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Alcan Rhenalu SAS
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    • 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
    • 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

Definitions

  • the invention relates to the field of rolled, extruded or forged aluminum alloy products Al-Si-Mg 6000 series according to the alloy designations of the Aluminum Association, for the manufacture of structural elements of aircraft, including fuselage elements.
  • the fuselages of commercial aircraft are made for the most part from alloy sheets 2024 in the T3 or T351 state, plated on both sides with a low-alloy aluminum alloy, for example an alloy 1050 or 1070, in the aim to improve the resistance to corrosion.
  • a low-alloy aluminum alloy for example an alloy 1050 or 1070
  • the thickness of the plating may be between 2 and 12% of the total thickness.
  • the US Patent 4589932 (Alcoa ) describes the use, for aircraft structural elements, of an alloy, subsequently registered under the designation 6013, of composition (% by weight): If: 0.4 - 1.2 Mg: 0.5 - 1.3 Cu: 0.6 - 1.1 Mn: 0.1 - 1 Fe ⁇ 0.6
  • the EP 0173632 in the name of the applicant, describes an alloy, subsequently registered under the designation 6056, of composition: If: 0.9 - 1.2 Mg: 0.7 - 1.1 Cu: 0.3 - 1.1 Mn: 0.25 - 0.75 Zn: 0.1 - 0.7 Zr: 0.07 - 0.2 Fe ⁇ 0.3
  • the EP 0787217 also in the name of the Applicant, relates to a particular tempering treatment, leading to a T78 state, for an alloy of the type 6056, so as to desensitize it to intercrystalline corrosion, and thus to permit its use without plating for the fuselage of aircraft.
  • This income is defined by a total duration, measured in equivalent time at 175 ° C, between 30 and 300 hours, and preferably between 70 and 120 hours.
  • This development was the subject of a communication from R. Dif, D. Bechet, T. Warner and H. Ribes: "6056 T78: A corrosion resistant copper-rich 6xxx alloy for aerospace applications” at ICAA-6 (July 1998) in Toyohashi (Japan), and published in Congress proceedings, pages 1991-1996 .
  • the forming of the pieces is preferably in the T4 state, in which the alloy 6056 has excellent formability.
  • the income is made on the formed parts and possibly welded.
  • the figure 1 represents, in the form of Wöhler curves, the fatigue life of samples according to example 1 in the T6 and T78 state, before and after prolonged exposure in the marine atmosphere.
  • the figure 2 represents the results of the intercrystalline corrosion tests as a function of the TL yield strength in the T4 state for the samples of Examples 6 and 7.
  • the plate was reheated to 530 ° C, scalped, hot rolled and then cold to 3.2 mm thickness. Samples of the sheet obtained were dissolved at 550 ° C., quenched with water, finished and subjected to an income. For some, the income was 8 h at 175 ° C to obtain the T6 state, that is to say the state corresponding to the maximum mechanical strength; for the others, it was 6 hours at 175 ° C.
  • the toughness was also measured by the R curve method according to ASTM E 561.
  • the curve R also allows, for example by the method of L.
  • the plate was transformed under the same conditions as in Example 1, except for the income at the T78 state.
  • Part of the samples received an income of 6 h at 175 ° C and 5 h at 210 ° C, a total equivalent time at 175 ° C of 105 h, in accordance with the preferential teaching of EP 0787217 .
  • Another part was tempered for 6 hours at 175 ° C. and 13 hours at 190 ° C., a total equivalent time at 175 ° C.
  • Table 7 Three plates of alloys A, B and C were cast, whose compositions (in% by weight), included in the range of composition of the invention, and the final rolling thickness e, are shown in Table 7: Table 7 alloy e (mm) Yes mg Cu mn Fe Zn Si + 2 Mg AT 1.4 to 3.2 0.93 0.75 0.60 0.63 0.10 0.16 2.43 B 4-8 0.91 0.76 0.64 0.59 0.13 0.17 2.43 VS 4,5-6 0.94 0.80 0.64 0.56 0.10 0.13 2.54
  • the plates were transformed identically to those of the preceding examples until the income, except that, for the thicknesses greater than or equal to 4.5 mm, indicated in Table 7, there was no rolling at cold.
  • the same yield was carried out for 6 hours at 175 ° C. for 13 hours at 190 ° C., ie a total equivalent time at 175 ° C. of 55 hours.
  • the same measurements were carried out as in the preceding examples: static mechanical characteristics in the direction of TL R 0.2 (in MPa), Rm (in MPa) and A (in%), sensitivity to intercrystalline corrosion, tenacity in the TL direction (in MPa) ⁇ m), and crack propagation velocity (TL direction). The results are shown in Tables 8, 9 and 10.
  • K R (TL) ⁇ a 20mm
  • K R (TL) ⁇ a 40mm K c0 (TL)
  • K c (TL) At 1.4 mm 90 122.5 85.5 129.7 At 3.2 mm 95.5 125 86.9 125.7 B 8 mm 110 134 93.8 126.1 C 4.5 mm 98.5 121.5 84.9 114.7 -Alloy thickness.
  • a first plate of this alloy was subjected to the manufacturing range A comprising the following steps: homogenization of 4 h at 540 ° C. + 24 h at 565 ° C., scalping, reheating at 530 ° C., hot rolling of a band up to 4.5 mm, debiting of the sheet metal strip, dissolving in an air oven for 40 minutes at 550 ° C., quenching with water, finishing, T6 yield from 8 h to 175 ° C.
  • a second plate has undergone a manufacturing range B comprising the same steps with the exception of the prior homogenization.
  • the grain size (thickness e and length l), at the surface and at the mid-thickness of the sheet, were measured in the T4 state (before tempering) by optical microscopy on a polished section, as well as the distribution of the Al dispersoids. Mn-Si in transmission electron microscopy. This distribution is evaluated by the Equivalent Circle Diameter (ECD) parameter ⁇ 4A / ⁇ in which A is the area of the phases observed on the micrographic section. To characterize the formability, the parameter LDH (Limit Dome Height) is used. This parameter is defined in the request for EP Patent 1045043 in the name of the plaintiff. The results are shown in Table 11: Table 11 Range grain surface ( ⁇ m) 1 grain surface ( ⁇ m) e mid-th grain. (Microns) 1 mid-th grain (Microns) ECD (nm) LDH (mm) AT 27 143 23 140 271 92 B 40 316 30 320 108 73
  • Samples were taken from the sheets of Example 3 and Example 5 at different thicknesses and with different types of finishing, comprising at least one of the following operations: wrinkling (D), roller flattening (P) or traction planing (T).
  • the yield strength R 0.2 was measured in each case in the TL (in MPa) direction at the T4 and T78 state, as well as the T88 intercrystalline corrosion sensitivity. This corrosion has been described as "light” when it shows pits with short intergranular branches.
  • Table 16 Table 16 Ex.-alloy e (mm) Paratroopers.

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  • Chemical & Material Sciences (AREA)
  • Physics & Mathematics (AREA)
  • Thermal Sciences (AREA)
  • Crystallography & Structural Chemistry (AREA)
  • Engineering & Computer Science (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Heat Treatment Of Steel (AREA)
  • Heat Treatment Of Articles (AREA)

Claims (6)

  1. Verfahren zur Herstellung eines Flugzeugstrukturelementes aus Walz-Strangpress- oder Schmiedeprodukten aus Aluminiumlegierung, umfassend
    - das Gießen eines Vormaterials der Zusammensetzung (Gew.-%);
    Si: 0,7 - 1,1 Mg: 0,6 - 0,9 Cu: 0,5 - 0,7 Mn: 0,3 - 0,8 Zn < 0,5 Fe < 0,2 Zr < 0,20 Cr < 0,25 Mg/Si < 1 Si + 2Mg : 2,0 - 2,6 weitere Elemente jeweils < 0,05 und insgesamt < 0,15, Rest Aluminium,
    - das Warm- und eventuell Kaltverarbeiten dieses Vormaterials zu einem Produkt,
    - das Lösungsglühen des Produktes zwischen 540 und 570 °C,
    - das Abschrecken des Produktes,
    - das Herstellen des Strukturelementes durch Formgebung des Produktes und gegebenenfalls Schweißen,
    - das ein- oder mehrstufige Auslagern des Strukturelementes, bei dem die entsprechende Gesamtzeit bei 175 °C, ausgedrückt in Stunden, zwischen 40 und 65 h beträgt.
  2. Verfahren nach Anspruch 1, dadurch gekennzeichnet, dass das Vormaterial bei einer Temperatur zwischen 540 und 570 °C homogenisiert wird.
  3. Verfahren nach einem der Ansprüche 1 oder 2, dadurch gekennzeichnet, dass das abgeschreckte Produkt vor dem Auslagern einer Kaltumformung unterzogen wird, die zu einer bleibenden Dehnung von 1 bis 15 % führt.
  4. Verfahren nach Anspruch 3, dadurch gekennzeichnet, dass die Kaltumformung zu einer bleibenden Dehnung von 2 bis 10 % führt.
  5. Verfahren nach einem der Ansprüche 1 bis 4, dadurch gekennzeichnet, dass Si + 2MG zwischen 2,3 und 2,6 beträgt.
  6. Verfahren zur Herstellung eines Flugzeugstrukturelementes nach einem der Ansprüche 3 bis 5, dadurch gekennzeichnet, dass es das Zusammenfügen von Blechen und Profilen umfasst und die Profile im Vergleich zu den Blechen vor dem Zusammenfügen und Auslagern eine zusätzliche Kaltumformung erfahren, um ihre Beständigkeit gegen interkristalline Korrosion im Wesentlichen auf das gleiche Niveau anzuheben.
EP01420078A 2000-04-07 2001-04-03 Verfahren zur Herstellung von Flugzeugstrukturelementen aus Al-Si-Mg-Legierung Expired - Lifetime EP1143027B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0004456 2000-04-07
FR0004456A FR2807449B1 (fr) 2000-04-07 2000-04-07 Procede de fabrication d'elements de structure d'avions en alliage d'aluminium al-si-mg

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EP1143027A1 EP1143027A1 (de) 2001-10-10
EP1143027B1 true EP1143027B1 (de) 2008-06-11

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EP (1) EP1143027B1 (de)
DE (1) DE60134357D1 (de)
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Cited By (4)

* 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
US8083871B2 (en) 2005-10-28 2011-12-27 Automotive Casting Technology, Inc. High crashworthiness Al-Si-Mg alloy and methods for producing automotive casting
US8608876B2 (en) 2006-07-07 2013-12-17 Aleris Aluminum Koblenz Gmbh AA7000-series aluminum alloy products and a method of manufacturing thereof

Families Citing this family (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2403730B (en) 2002-06-24 2005-07-27 Corus Aluminium Walzprod Gmbh Method of producing high strength balanced Al-Mg-Si alloy and a weldable product of that alloy
GB2398752B (en) * 2003-02-26 2005-01-12 Wuxi Prohandy Tool Co Ltd Paint roller
US7666267B2 (en) 2003-04-10 2010-02-23 Aleris Aluminum Koblenz Gmbh Al-Zn-Mg-Cu alloy with improved damage tolerance-strength combination properties
ES2293813B2 (es) 2003-04-10 2011-06-29 Corus Aluminium Walzprodukte Gmbh Una aleacion de al-zn-mg-cu.
FR2856368B1 (fr) * 2003-06-18 2005-07-22 Pechiney Rhenalu Piece de peau de carrosserie automobile en tole d'alliage ai-si-mg fixee sur structure acier
FR2873717B1 (fr) * 2004-07-27 2006-10-06 Boxal France Soc Par Actions S Procede de fabrication de boitiers d'aerosols.
US20060070686A1 (en) * 2004-10-05 2006-04-06 Corus Aluminium Walzprodukte Gmbh High hardness moulding plate and method for producing said plate
US20070151636A1 (en) * 2005-07-21 2007-07-05 Corus Aluminium Walzprodukte Gmbh Wrought aluminium AA7000-series alloy product and method of producing said product
AU2016369546B2 (en) 2015-12-18 2019-06-13 Novelis Inc. High strength 6xxx aluminum alloys and methods of making the same
CN112831697A (zh) * 2020-12-31 2021-05-25 山东裕航特种合金装备有限公司 一种高强度无粗晶铝合金及其制备方法和应用
CN113265569B (zh) * 2021-05-14 2022-11-11 江苏亚太轻合金科技股份有限公司 一种6系列高强度细晶粒锻造汽车控制臂用铝合金棒材的制备方法
CN113684401B (zh) * 2021-08-25 2022-11-15 航桥新材料科技（滨州）有限公司 一种高服役传动轴用铝合金及其制备方法

Citations (1)

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Publication number Priority date Publication date Assignee Title
EP0787217A1 (de) * 1994-10-25 1997-08-06 Pechiney Rhenalu VERFAHREN ZUR HERSTELLUNG VON GEGENSTÄDEN AUS AlSiMgCu-LEGIERUNG MIT VERBESSERTEN INTERKRISTALLINKORROSIONSWIEDERSTAND

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US6296941B1 (en) 1999-04-15 2001-10-02 General Electric Company Silicon based substrate with yttrium silicate environmental/thermal barrier layer
US6645649B2 (en) 2000-10-31 2003-11-11 Kyocera Corporation Surface-coated sintered body of silicon nitride

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0787217A1 (de) * 1994-10-25 1997-08-06 Pechiney Rhenalu VERFAHREN ZUR HERSTELLUNG VON GEGENSTÄDEN AUS AlSiMgCu-LEGIERUNG MIT VERBESSERTEN INTERKRISTALLINKORROSIONSWIEDERSTAND

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
R. DIF ET AL.: "6056-T78: A Corrosion Resistant Copper-rich 6XXX Alloy For Aerospace Applications", ALUMINUM ALLOYS, PROCEEDINGS OF ICAA-6, vol. 3, 1998 *

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
US8083871B2 (en) 2005-10-28 2011-12-27 Automotive Casting Technology, Inc. High crashworthiness Al-Si-Mg alloy and methods for producing automotive casting
US8721811B2 (en) 2005-10-28 2014-05-13 Automotive Casting Technology, Inc. Method of creating a cast automotive product having an improved critical fracture strain
US9353430B2 (en) 2005-10-28 2016-05-31 Shipston Aluminum Technologies (Michigan), Inc. Lightweight, crash-sensitive automotive component
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

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FR2807449B1 (fr) 2002-10-18
FR2807449A1 (fr) 2001-10-12
US20020014290A1 (en) 2002-02-07
EP1143027A1 (de) 2001-10-10
DE60134357D1 (de) 2008-07-24

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