US20020014290A1 - Al-si-mg aluminum alloy aircraft structural component production method - Google Patents

Al-si-mg aluminum alloy aircraft structural component production method Download PDF

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Publication number
US20020014290A1
US20020014290A1 US09/826,289 US82628901A US2002014290A1 US 20020014290 A1 US20020014290 A1 US 20020014290A1 US 82628901 A US82628901 A US 82628901A US 2002014290 A1 US2002014290 A1 US 2002014290A1
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mpa
square root
ageing
hours
product
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US09/826,289
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English (en)
Inventor
Ronan Dif
Philippe Lequeu
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Constellium Issoire SAS
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Pechiney Rhenalu SAS
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Assigned to PECHINEY RHENALU reassignment PECHINEY RHENALU ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: DIF, RONAN, LEQUEU, PHILIPPE
Publication of US20020014290A1 publication Critical patent/US20020014290A1/en
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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 products made of series 6000 Al—Si—Mg aluminum alloy according to Aluminum Association references, intended to produce aircraft structural components, particularly fuselage components.
  • Si 0.4-1.2 Mg: 0.5-1.3
  • Cu 0.6-1.1
  • Mn 0.1-1 Fe ⁇ 0.6
  • the patent EP 0 787 217 also filed by the applicant, relates to a specific ageing treatment, resulting in a T78 temper, for a 6056 type alloy, so as to desensitize it to intercrystalline corrosion, and thus enable its use without cladding for aircraft fuselages.
  • This ageing is defined by a total duration, measured in equivalent time at 175° C., between 30 and 300 hours, and preferentially between 70 and 120 hours.
  • This development was the subject of a presentation by R. Dif, D. Béchet, T. Warner and H. Ribes: “6056 T78: A corrosion resistant copper-rich 6xxx alloy for aerospace applications” at the ICAA-6 congress (July 1998) in Toyohashi (Japan) and published in the Congress Proceedings, pages 1991-1996.
  • the parts are preferentially shaped in the T4 temper, wherein the 6056 alloy shows excellent forming properties.
  • the ageing is performed on shaped and possibly welded parts.
  • the use of 6056-T78 results in complete desensitisation to intercrystalline corrosion of the welded join or the base product and in static mechanical characteristics equivalent to those of clad T3 or T351 2024.
  • the invention relates to an aircraft structural component production method using rolled, extruded or forged products made of aluminum alloy comprising:
  • Si 0.7-1.3
  • Mg 0.6-1.1
  • Cu 0.5-1.1
  • Mn 0.3-0.8
  • Zn ⁇ 1 Fe ⁇ 0.30 Zr ⁇ 0.20 Cr ⁇ 0.25 other elements ⁇ 0.05 each and ⁇ 0.15 in total, the remainder being aluminum
  • ageing of the structural component in one or more stages, for which the total equivalent time at 175° C. expressed in hours is between ( ⁇ 160+57 ⁇ ) and ( ⁇ 184+69 ⁇ ), ⁇ being the sum of the Si+2Mg+2Cu contents in % by weight.
  • the invention also relates to an aircraft structural component production method, wherein the composition of the products belongs to a preferential composition range (% by weight):
  • Si 0.7-1.1 Mg: 0.6-0.9
  • Cu 0.5-0.7 Mn: 0.3-0.8
  • Si+2 Mg 2-2.6 other elements ⁇ 0.05 each and ⁇ 0.15 in total, the remainder being aluminum
  • the ageing time is between 40 and 65 hours of total equivalent time at 175° C.
  • FIG. 1 represents, in the form of Wöhler curves, the fatigue service life of T6 and T78 temper samples according to Example 1, before and after prolonged exposure in a marine environment.
  • FIG. 2 represents the results of intercrystalline corrosion tests as a function of the yield strength in the TL direction in the T4 temper for the samples in Examples 6 and 7.
  • the invention is based on the observation that within the composition and ageing range disclosed in the patent EP 0 787 217, there is a restricted range linking the major elements of the composition (Si, Mg and Cu) and the total equivalent ageing time at 175° C., as this parameter is defined in EP 0 787 217; with this range, in relation to the results given in the examples of this European patent, an improvement in the static mechanical characteristics and tolerance to damage is obtained, with no adverse effect on sensitivity to intercrystalline corrosion. It is thus possible to associate with each alloy composition a factor ⁇ equal to the sum of the Si+2Mg+2Cu contents (in % by weight) and with said factor ⁇ a period of equivalent ageing time at 175° C. between (in hours) ( ⁇ 160+57 ⁇ ) and ( ⁇ 184+69 ⁇ ) and preferentially between ( ⁇ 150+57 ⁇ ) and ( ⁇ 184+69 ⁇ ).
  • the inventors revealed that by unloading the alloy in relation to compositions of the examples in the European patent, i.e. by positioning at the lower end of the content ranges for these 3 elements, while ensuring that these elements are put in solution as completely as possible, the alloy became less sensitive to intercrystalline corrosion at given over-ageing and that, as a result, it was possible to desensitize it with a lower level over-ageing.
  • the equivalent ageing time at 175° C. to reach the T78 temper with total desensitization is between 40 and 65 hours, i.e. below the preferential range (70 to 120 hours) indicated in the patent EP 0 787 217.
  • K R ( ⁇ a 40 mm)>115 MPa ⁇ square root ⁇ m
  • the alloy in the preferential composition according to the invention, in the T6 temper.
  • the level of properties obtained in said T6 temper with the preferential composition according to the invention, in terms of static mechanical characteristics, fracture toughness and crack growth rate is as follows:
  • K R ( ⁇ a 40 mm)>120 MPa ⁇ square root ⁇ m
  • the production method according to the invention comprises the casting of a blank made of the composition mentioned, said blank being a plate for rolled products, a slug for extruded products or a forging block for forged products.
  • the blank is scalped and then heated before hot transformation by rolling, extrusion or forging, and possibly undergoes cold transformation.
  • the semi-finished product obtained undergoes a heat treatment at a temperature between 540 and 570° C., quenched, generally in cold water, and finished, the purpose of said final step essentially being to absorb the deformations of the semi-finished product after quenching.
  • the product is most frequently supplied in this T4 temper to shape the structural component and for welding if required.
  • the formed, and if applicable welded, component then undergoes the ageing treatment according to the invention.
  • a homogenization step at a temperature between 540 and 570°.
  • Said homogenization may comprise a single stage, or two stages, the second stage being at a higher temperature than the first. It helps improve the forming properties of the product in the T4 temper and reduce the grain size, leading to a decrease in the roughness of the metal when it undergoes chemical machining. Excessive roughness may induce initial micro-cracking due to fatigue.
  • Said cold-working, of at least 1%, and preferably of at least 2% permanent elongation may be relatively significant, for example up to 10%, or even up to 15% permanent elongation; indeed, it is observed, surprisingly, that significant cold-working, although it accelerates the ageing kinetics, does not reduce the yield strength in the T78 temper with reference to the same non-cold-worked product.
  • the plate was heated at 530° C., scalped, hot and then cold rolled to a thickness of 3.2 mm.
  • Samples of the sheet obtained were subjected to a solution heat treatment at 550° C., quenched in water, finished and subjected to ageing.
  • the ageing lasted 8 hours at 175° C. to obtain the T6 temper, i.e. the temper corresponding to maximum mechanical resistance; in other cases, it lasted 6 hours at 175° C. and then 2 hours at 220° C., or an equivalent time at 175° C. of 95 hours, to obtain the T78 temper, as described in Example 3 of the patent EP 0 787 217.
  • the fracture toughness was also measured using the R curve method, according to the ASTM E 561 standard.
  • the plate was transformed under the same conditions as in Example 1, except in terms of the ageing in the T78 temper.
  • Part of the samples underwent ageing for 6 hours at 175° C. followed by 5 hours at 210° C., or a total equivalent time at 175° C. of 105 hours, according to the preferential disclosure in the patent EP 0787217.
  • Another part underwent ageing for 6 hours at 175° C. followed by 13 hours at 190° C., or a total equivalent time at 175° C. of 55 hours, according to the present invention.
  • the same measurements as in Example 1 were made for the T6 and T78 tempers at 105 hours and 55 hours. The results are given in Tables 4, 5 and 6.
  • TABLE 4 IC Temper R 0.2 (TL) R m (TL) A (TL) sensitivity T6 360 397 7.5 Yes T78 305 337 10.5 No (105 hrs) T78 339 367 9.2 No (55 hrs)
  • a first plate of this alloy was subjected to the production procedure A comprising the following steps: homogenization for 4 hours at 540° C.+24 hours at 565° C., scalping, heating at 530° C., hot rolling of a strip up to 4.5 mm, conversion of strip into sheets, solution heat treatment in a furnace for 40 min at 550° C. in air, water quenching, finishing, T6 ageing for 8 hours at 175° C.
  • the grain size (thickness e and length l) on the surface and mid-thickness of the sheet was measured in the T4 temper (before ageing) by optical microscopy on a ground section, along with the distribution of the Al—Mn—Si dispersoids in electron microscopy in transmission.
  • the parameter LDH Limit Dome Height
  • This parameter is defined in the patent application EP 1045043 filed by the applicant.
  • This plate alloy was subjected to the following production procedure: homogenization for 4 hours at 540° C.+24 hours at 565° C., scalping, heating at 530° C., hot rolling of a strip up to 5 mm, conversion of strip into sheets, solution heat treatment in a furnace for 40 min at 550° C. in air, water quenching, finishing, T78 ageing for 6 hours at 175° C.+13 hours at 190° C. (or 55 hours of equivalent time at 175° C.).

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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)
US09/826,289 2000-04-07 2001-04-05 Al-si-mg aluminum alloy aircraft structural component production method Abandoned US20020014290A1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
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
FR0004456 2000-04-07

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US20020014290A1 true US20020014290A1 (en) 2002-02-07

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US (1) US20020014290A1 (fr)
EP (1) EP1143027B1 (fr)
DE (1) DE60134357D1 (fr)
FR (1) FR2807449B1 (fr)

Cited By (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2398752A (en) * 2003-02-26 2004-09-01 Wuxi Prohandy Tool Co Ltd Roller-typed paintbrush's structural improvement
US20060021415A1 (en) * 2004-07-27 2006-02-02 Boxal France Aerosol can fabrication process
US6994760B2 (en) 2002-06-24 2006-02-07 Corus Aluminium Walzprodukte Gmbh Method of producing a high strength balanced Al-Mg-Si alloy and a weldable product of that alloy
WO2006037647A1 (fr) * 2004-10-05 2006-04-13 Aleris Aluminum Koblenz Gmbh Plaque de moulage d'aluminium de haute durete et procede de production de la plaque
US20070151636A1 (en) * 2005-07-21 2007-07-05 Corus Aluminium Walzprodukte Gmbh Wrought aluminium AA7000-series alloy product and method of producing said product
US20070194603A1 (en) * 2003-06-18 2007-08-23 Myriam Bouet-Griffon Autobody skin piece made of an al-si-mg sheet metal alloy and fixed to a steel structure
US20080173378A1 (en) * 2006-07-07 2008-07-24 Aleris Aluminum Koblenz Gmbh Aa7000-series aluminum alloy products and a method of manufacturing thereof
US8002913B2 (en) 2006-07-07 2011-08-23 Aleris Aluminum Koblenz Gmbh AA7000-series aluminum alloy products and a method of manufacturing thereof
US10472707B2 (en) 2003-04-10 2019-11-12 Aleris Rolled Products Germany Gmbh Al—Zn—Mg—Cu alloy with improved damage tolerance-strength combination properties
CN113265569A (zh) * 2021-05-14 2021-08-17 无锡海特铝业有限公司 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
US11920229B2 (en) 2015-12-18 2024-03-05 Novelis Inc. High strength 6XXX aluminum alloys and methods of making the same

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7666267B2 (en) 2003-04-10 2010-02-23 Aleris Aluminum Koblenz Gmbh Al-Zn-Mg-Cu alloy with improved damage tolerance-strength combination properties
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
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
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

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2726007B1 (fr) * 1994-10-25 1996-12-13 Pechiney Rhenalu Procede de fabrication de produits en alliage alsimgcu a resistance amelioree a la corrosion intercristalline
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

Cited By (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6994760B2 (en) 2002-06-24 2006-02-07 Corus Aluminium Walzprodukte Gmbh Method of producing a 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
GB2398752A (en) * 2003-02-26 2004-09-01 Wuxi Prohandy Tool Co Ltd Roller-typed paintbrush's structural improvement
US10472707B2 (en) 2003-04-10 2019-11-12 Aleris Rolled Products Germany Gmbh Al—Zn—Mg—Cu alloy with improved damage tolerance-strength combination properties
US20070194603A1 (en) * 2003-06-18 2007-08-23 Myriam Bouet-Griffon Autobody skin piece made of an al-si-mg sheet metal alloy and fixed to a steel structure
US7520044B2 (en) * 2004-07-27 2009-04-21 Boxal France Aerosol can fabrication process
US20060021415A1 (en) * 2004-07-27 2006-02-02 Boxal France Aerosol can fabrication process
WO2006037647A1 (fr) * 2004-10-05 2006-04-13 Aleris Aluminum Koblenz Gmbh Plaque de moulage d'aluminium de haute durete et procede de production de la plaque
US20070151636A1 (en) * 2005-07-21 2007-07-05 Corus Aluminium Walzprodukte Gmbh Wrought aluminium AA7000-series alloy product and method of producing said product
US20080173378A1 (en) * 2006-07-07 2008-07-24 Aleris Aluminum Koblenz Gmbh Aa7000-series aluminum alloy products and a method of manufacturing thereof
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
US11920229B2 (en) 2015-12-18 2024-03-05 Novelis Inc. High strength 6XXX aluminum alloys and methods of making the same
US12043887B2 (en) 2015-12-18 2024-07-23 Novelis Inc. High strength 6xxx aluminum alloys and methods of making the same
CN113265569A (zh) * 2021-05-14 2021-08-17 无锡海特铝业有限公司 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

Also Published As

Publication number Publication date
EP1143027A1 (fr) 2001-10-10
FR2807449A1 (fr) 2001-10-12
DE60134357D1 (de) 2008-07-24
EP1143027B1 (fr) 2008-06-11
FR2807449B1 (fr) 2002-10-18

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Owner name: PECHINEY RHENALU, FRANCE

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNORS:DIF, RONAN;LEQUEU, PHILIPPE;REEL/FRAME:011922/0358

Effective date: 20010601

STCB Information on status: application discontinuation

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