EP1026270B1 - Produkt aus AlCuMg-Legierung für ein Zellenbauteil eines Flugzeuges - Google Patents

Produkt aus AlCuMg-Legierung für ein Zellenbauteil eines Flugzeuges Download PDF

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Publication number
EP1026270B1
EP1026270B1 EP00420020A EP00420020A EP1026270B1 EP 1026270 B1 EP1026270 B1 EP 1026270B1 EP 00420020 A EP00420020 A EP 00420020A EP 00420020 A EP00420020 A EP 00420020A EP 1026270 B1 EP1026270 B1 EP 1026270B1
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EP
European Patent Office
Prior art keywords
mpa
measured
thickness
product
quenched
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Expired - Lifetime
Application number
EP00420020A
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English (en)
French (fr)
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EP1026270A1 (de
Inventor
Timothy Warner
Philippe Lassince
Philippe Lequeu
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.)
Constellium Issoire SAS
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Pechiney Rhenalu SAS
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Priority claimed from FR9901468A external-priority patent/FR2789405A1/fr
Application filed by Pechiney Rhenalu SAS filed Critical 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 rolled, spun or forged products made from hardened AlCuMg alloys and tractionned for the manufacture of aircraft structural elements, in particular skin panels and underside stiffeners of wing, and having, for example, compared to the products of the prior art used for the same application, a improved compromise between the properties of mechanical strength, formability, toughness, tolerance to damage and residual stresses.
  • the designation of alloys and metallurgical states corresponds to the nomenclature of Aluminum Association, adopted by European standards EN 515 and EN 573.
  • Large commercial aircraft wings have an upper section (or extrados) consisting of a skin made from thick alloy plates 7150 to the T651 state, or 7055 alloy to the T7751 state or 7449 to the T7951 state, and stiffeners made from profiles of the same alloy, and a lower part (or intrados) consisting of a skin made from thick 2024 alloy state T351 or 2324 in state T39, and stiffeners made from same alloy. Both parts are assembled by longitudinal members and ribs.
  • the alloy 2024 according to the designation of the Aluminum Association or the standard EN 573-3 has the following chemical composition (% by weight): If ⁇ 0.5 Fe ⁇ 0.5 Cu: 3.8 - 4.9 Mg: 1.2 - 1.8 Mn: 0.3 - 0.9 Cr ⁇ 0.10 Zn ⁇ 0.25 Ti ⁇ 0 15
  • Patent Application EP 0731185 of the Applicant relates to an alloy, registered subsequently under No. 2024A, of composition: Si ⁇ 0.25 Fe ⁇ 0.25 Cu: 3.5 - 5 Mg: 1 - 2 Mn ⁇ 0.55 with the relation: 0 ⁇ Mn - 2Fe ⁇ 0.2
  • the thick plates of this alloy have both improved toughness and reduced level of residual stresses, without loss on the other properties.
  • US Pat. No. 5,863,359 and US Pat. No. 5,865,914 to Alcoa relate respectively to an aircraft wing comprising an alloy intrados of composition: Cu: 3.6 - 4 Mg: 1 - 1.6 (pref: 1.15 - 1.5) Mn: 0.3 - 0.7 (pref: 0.5 - 0.6) Zr: 0, 05 - 0.25 and preferably Fe ⁇ 0.07 and Si ⁇ 0.05 having both the following properties: R 0.2 (LT)> 60 ksi (414 MPa) and K 1c (LT)> 38 ksi ⁇ inch (42 MPa ⁇ m), and a method of manufacturing a lower surface element having an R 0.2 (LT)> 60 ksi comprising casting an alloy of the above composition, homogenizing at 471 to 482 ° C, a temperature> 399 ° C., dissolution above 488 ° C., quenching, cold working preferably of more than 9% and traction of at least 1%.
  • the object of the invention is therefore to provide AlCuMg alloy products in the state quenched and cold deformed, intended for the manufacture of the underside of aircraft wings, and having, compared to similar products of the prior art, a compromise more favorable for all the properties of use: mechanical resistance, speed of crack propagation, toughness, fatigue resistance, and stress ratio residual.
  • the subject of the invention is a rolled, spun or forged product made of AlCuMg alloy, treated by homogenization, heat-treated with an outlet temperature greater than 420 ° C., so as to obtain a recrystallization rate at a quarter-thickness less than 20%, dissolving, quenching, cold drawing and aging, intended for the manufacture of aircraft structural elements, composition (% by weight): Fe ⁇ 0.15 If ⁇ 0.15 Cu: 4.0 - 4.3 Mg: 1.0 - 1.5 Mn: 0.5 - 0.8 Zr: 0.08 - 0.15 other elements: ⁇ 0.05 each and ⁇ 0.15 in total, having a ratio R m (L) / R 0.2 (L) of the breaking strength in the L direction at the yield stress in the L direction greater than 1 , 25 (and preferably at 1.30).
  • This sheet also has a level of residual stresses such that the arrow f measured in the L and TL directions after machining at mid-thickness of a bar resting on two supports distant by a length l is such that: f ⁇ (0.14 l 2 ) / ef being measured in microns, the thickness e of the sheet and the length 1 being expressed in mm.
  • the chemical composition of the product differs from that of the usual 2024 by a reduced in iron and silicon, a higher manganese content and an addition of zirconium. Compared to 2034, we have a lower manganese content and a lower slightly reduced copper content. Compared to the composition of the alloys described in US Pat. No. 5,863,359 and US Pat. No. 5,865,914, the copper content is higher; which makes it possible to compensate, for the mechanical strength, cold working less high after quenching. Surprisingly, this narrow domain of composition (notably with regard to manganese), associated with changes in the range of manufacture, leads, compared to the prior art, to an improvement significant compromise between mechanical strength, elongation and tolerance damage to the operating conditions of a large civil aircraft.
  • the manufacturing method comprises the casting of plates, in the case where the product to be manufactured is a rolled sheet, or billets in the case where it is a spun section or a forged part.
  • the plate or the billet is scalped, then homogenized between 450 and 500 ° C.
  • the hot transformation is then carried out by rolling, spinning or forging. This transformation is preferably carried out at a temperature higher than the temperatures usually used, the outlet temperature being greater than 420 ° C. and preferably 440 ° C. so as to obtain a little recrystallized structure on the treated product, with a rate of recrystallization at a quarter thickness less than 20%, and preferably 10%.
  • the laminated, spun or forged half-product is then dissolved between 480 and 505 ° C., so that this dissolution is as complete as possible, that is to say that the maximum of potentially soluble phases, in particular the Al 2 Cu and Al 2 CuMg precipitates are actually in solid solution.
  • the quality of the dissolution can be assessed by differential enthalpy analysis (AED) by measuring the specific energy using the area of the peak on the thermogram. This specific energy must preferably be less than 2 J / g.
  • the products according to the invention have significantly improved static mechanical characteristics compared to the alloy 2024-T351, currently used for aircraft wing-backs, and only slightly lower than those of 2034-T351.
  • the high plastic gap and elongation of the material result in excellent cold forming ability.
  • the tenacity, measured by the critical stress stress factors K c and K oc, is more than 10% greater than that of 2024 and 2034, and the crack propagation rate da / dn is significantly improved by compared to these two alloys, especially for the high values of ⁇ K, and for variable amplitude loadings.
  • the fatigue life times, measured on notched specimens taken at mid-thickness in the L direction, are also improved by more than 20% compared to 2024 and 2034.
  • alloy 2024, 2034 and alloy according to the invention Three plates 1450 mm wide and 446 mm thick were cast in alloy 2024, 2034 and alloy according to the invention respectively.
  • the chemical compositions (% by weight) of the alloys are given in Table 1: alloy Yes Fe Cu mg mn Zr 2024 0.12 0.20 4.06 1.36 0.54 0,002 2034 0.05 0.07 4.30 1.34 0.98 0.104 invention 0.06 0.08 4.14 1.26 0.65 0,102
  • the sheets was then hot rolled to a thickness of 40 mm by successive passes of the order of 20 mm. Another part of the sheets has been rolled hot up to 15 mm.
  • the inlet temperature at hot rolling was 467 ° C
  • Fatigue tests according to the Airbus AITM 1-0011 specification have been carried out on test pieces with a hole length 230 mm, width 50 mm and thickness 7.94 mm, taken at mid-thickness of the L-shaped plate.
  • the diameter of the hole is 7.94 mm.
  • a mean full test stress of 80 MPa with 4 levels was applied of alternating stresses: 85 MPa, 55 MPa, 45 MPa and 35 MPa for the plates of 40 mm, 110, 85, 55 and 45 MPa for 15 mm sheets, with 2 test pieces per level.
  • the arrow f is measured as follows. We take from the thick sheet e two bars, one called bar L sense, length b in the direction of the length sheet metal (L-direction), width 25 mm in the width direction of the sheet (TL direction) and of thickness e according to the full thickness of the sheet (TC direction), the other, called bar TL direction, having 25 mm in the L direction, b in the TL direction and e in the TC direction.
  • Each bar is machined to mid-thickness and the arrow is measured at mid-length of the bar.
  • This arrow is representative of the level of internal stresses of the sheet and its ability not to deform at machining.
  • the distance 1 between the supports was 180 mm and the length b of the bars 200 mm. Machining is a progressive mechanical machining with passes of about 2 mm.
  • the measurement of the arrow at mid-length is carried out using a comparator with a resolution of one micron. Results for arrows and recrystallization rates are given in Table 6.

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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 Steel (AREA)

Claims (10)

  1. Walz-, Press- oder Schmiedeerzeugnis aus AlCuMg-Legierung, behandelt durch Homogenisieren, Warmumformen bei einer Austrittstemperatur oberhalb 420°C, um auf einem Viertel der Dicke einen Rekristallisationsgrad von weniger als 20 % zu erhalten, Lösungsglühen, Abschrecken, Kaltrecken und Auslagern, für die Herstellung von Zellenbauteilen eines Flugzeugs, mit der Zusammensetzung (Gew.-%):
    Fe < 0,15   Si < 0,15   Fe + Si < 0,15 %   Cu: 4,0 - 4,3 Mg: 1 - 1,5   Mn: 0,5 - 0,8   Zr: 0,08 - 0,15
    weitere Elemente jeweils < 0,05 und insgesamt < 0,15, mit einem Rm(L)/R0,2(L)-Verhältnis > 1,25 (vorzugsweise > 1,30).
  2. Walzerzeugnis von 6 bis 60 mm Dicke nach Anspruch 1, das im abgeschreckten und gestreckten Zustand eine Bruchfestigkeit Rm(L) > 475 MPa und eine Dehngrenze R0,2(L) > 370 MPa aufweist.
  3. Walzerzeugnis von 6 bis 60 mm Dicke nach einem der Ansprüche 1 oder 2, das im abgeschreckten und gestreckten Zustand einen Verformungsunterschied zwischen Bruchfestigkeit Rm und Dehngrenze R0,2 in Längs- und Längs-Querrichtung > 100 MPa aufweist.
  4. Walzerzeugnis von 6 bis 60 mm Dicke nach einem der Ansprüche 1 bis 3, das im abgeschreckten und gestreckten Zustand einen kritischen Spannungsintensitätsfaktor (längs/quer) Kc > 170 MPa√m und K co > 120 MPa√m aufweist, gemessen nach der Norm ASTM E 561 an angekerbten, auf einem Viertel der Dicke entnommenen Proben mit den Parametern W = 500 mm, B = 5 mm und 2a0 = 165 mm.
  5. Walzerzeugnis von 6 bis 60 mm Dicke nach einem der Ansprüche 1 bis 4, das im abgeschreckten und gestreckten Zustand eine Rissausbreitungsgeschwindigkeit (längs/quer) aufweist, gemessen nach der Norm ASTM E 647 an angekerbten, auf einem Viertel der Dicke entnommenen Proben mit W = 200 mm und B = 5 mm:
    < 10-4 mm/Zyklus bei ΔK = 10 MPa√m
    < 2,5 10-4 mm/Zyklus bei ΔK = 15 MPa√m
    und < 5 10-4 mm/Zyklus bei ΔK = 20 MPa√m.
  6. Walzerzeugnis nach einem der Ansprüche 1 bis 5, dadurch gekennzeichnet, dass es eine Durchbiegung f, gemessen in Längs- und Längsquerrichtung nach Bearbeitung auf halber Dicke eines auf zwei, um eine Länge I voneinander beabstandeten Stützen aufliegenden Probestabs, von weniger als (0,14 I2)/e aufweist, wobei f in Mikrometern gemessen ist und die Dicke e des Blechs und die Länge I in mm ausgedrückt sind.
  7. Verfahren zur Herstellung eines Erzeugnisses nach einem der Ansprüche 1 bis 6, mit folgenden Schritten:
    Gießen einer Platte mit der genannten Zusammensetzung
    Homogenisieren dieser Platte zwischen 450 und 500°C
    Warm- und eventuell Kaltumformen durch Walzen, Pressen oder Schmieden, bis sich das gewünschte Erzeugnis ergibt
    Lösungsglühen bei einer Temperatur zwischen 480 und 505°C
    Abschrecken mit kaltem Wasser
    Kaltrecken bis auf mehr als 1,5 % bleibende Verformung
    Kaltauslagerung bei Raumtemperatur.
  8. Verfahren nach Anspruch 7, dadurch gekennzeichnet, dass die Warmumformung bei einer Austrittstemperatur oberhalb 440°C erfolgt.
  9. Verwendung von Blechen nach einem der Ansprüche 2 bis 6 zur Herstellung der Außenhaut für die Tragflügelunterseite eines Flugzeugs.
  10. Verwendung von Profilen nach Anspruch 1 zur Herstellung von Versteifungen für die Tragflügelunterseite und den Rumpf eines Flugzeugs.
EP00420020A 1999-02-04 2000-02-01 Produkt aus AlCuMg-Legierung für ein Zellenbauteil eines Flugzeuges Expired - Lifetime EP1026270B1 (de)

Applications Claiming Priority (4)

Application Number Priority Date Filing Date Title
FR9901468 1999-02-04
FR9901468A FR2789405A1 (fr) 1999-02-04 1999-02-04 PRODUIT EN ALLIAGE AlCuMg POUR ELEMENT DE STRUCTURE D'AVION
FR9910682A FR2789406B1 (fr) 1999-02-04 1999-08-18 PRODUIT EN ALLIAGE AlCuMg POUR ELEMENT DE STRUCTURE D'AVION
FR9910682 1999-08-18

Publications (2)

Publication Number Publication Date
EP1026270A1 EP1026270A1 (de) 2000-08-09
EP1026270B1 true EP1026270B1 (de) 2005-04-27

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EP00420020A Expired - Lifetime EP1026270B1 (de) 1999-02-04 2000-02-01 Produkt aus AlCuMg-Legierung für ein Zellenbauteil eines Flugzeuges

Country Status (5)

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US (2) US6602361B2 (de)
EP (1) EP1026270B1 (de)
DE (1) DE60019655T2 (de)
FR (1) FR2789406B1 (de)
GB (1) GB2346381A (de)

Cited By (3)

* 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
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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US6325869B1 (en) * 1999-01-15 2001-12-04 Alcoa Inc. Aluminum alloy extrusions having a substantially unrecrystallized structure
US7323068B2 (en) 2002-08-20 2008-01-29 Aleris Aluminum Koblenz Gmbh High damage tolerant Al-Cu alloy
US7494552B2 (en) 2002-08-20 2009-02-24 Aleris Aluminum Koblenz Gmbh Al-Cu alloy with high toughness
US7604704B2 (en) * 2002-08-20 2009-10-20 Aleris Aluminum Koblenz Gmbh Balanced Al-Cu-Mg-Si alloy product
GB2415202B (en) 2003-04-10 2007-08-29 Corus Aluminium Walzprod Gmbh An Al-Zn-Mg-Cu alloy
US20050034794A1 (en) * 2003-04-10 2005-02-17 Rinze Benedictus High strength Al-Zn alloy and method for producing such an alloy product
US7666267B2 (en) * 2003-04-10 2010-02-23 Aleris Aluminum Koblenz Gmbh Al-Zn-Mg-Cu alloy with improved damage tolerance-strength combination properties
US20060032560A1 (en) * 2003-10-29 2006-02-16 Corus Aluminium Walzprodukte Gmbh Method for producing a high damage tolerant aluminium alloy
US20070151636A1 (en) * 2005-07-21 2007-07-05 Corus Aluminium Walzprodukte Gmbh Wrought aluminium AA7000-series alloy product and method of producing said product
US20070204937A1 (en) * 2005-07-21 2007-09-06 Aleris Koblenz Aluminum Gmbh Wrought aluminium aa7000-series alloy product and method of producing said product
WO2010085678A1 (en) 2009-01-22 2010-07-29 Alcoa Inc. Improved aluminum-copper alloys containing vanadium
JP6057855B2 (ja) * 2013-07-31 2017-01-11 株式会社神戸製鋼所 切削用アルミニウム合金押出材
FR3011252B1 (fr) 2013-09-30 2015-10-09 Constellium France Tole d'intrados a proprietes de tolerance aux dommages ameliorees
EP3622096B1 (de) * 2017-05-11 2021-09-22 Aleris Aluminum Duffel BVBA Verfahren zur herstellung eines walzblechprodukts aus einer al-si-mg-legierung mit ausgezeichneter formbarkeit
US20190233921A1 (en) * 2018-02-01 2019-08-01 Kaiser Aluminum Fabricated Products, Llc Low Cost, Low Density, Substantially Ag-Free and Zn-Free Aluminum-Lithium Plate Alloy for Aerospace Application
CN108704967A (zh) * 2018-04-25 2018-10-26 南京航空航天大学 一种铝合金电脉冲新淬火成形工艺及装置

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FR2731440B1 (fr) * 1995-03-10 1997-04-18 Pechiney Rhenalu Toles en alliage al-cu-mg a faible niveau de contraintes residuelles
JP3053352B2 (ja) * 1995-04-14 2000-06-19 株式会社神戸製鋼所 破壊靭性、疲労特性および成形性の優れた熱処理型Ａｌ合金
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US6325869B1 (en) * 1999-01-15 2001-12-04 Alcoa Inc. Aluminum alloy extrusions having a substantially unrecrystallized structure

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
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

Also Published As

Publication number Publication date
US20020014288A1 (en) 2002-02-07
DE60019655D1 (de) 2005-06-02
EP1026270A1 (de) 2000-08-09
US20030217793A1 (en) 2003-11-27
GB9924277D0 (en) 1999-12-15
DE60019655T2 (de) 2006-02-02
GB2346381A (en) 2000-08-09
FR2789406A1 (fr) 2000-08-11
FR2789406B1 (fr) 2001-03-23
US6602361B2 (en) 2003-08-05

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