EP1945825B1 - Alliages a base d'aluminium, de cuivre et de magnesium (al cu mg) pour les applications aerospatiales - Google Patents

Alliages a base d'aluminium, de cuivre et de magnesium (al cu mg) pour les applications aerospatiales Download PDF

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Publication number
EP1945825B1
EP1945825B1 EP06818278.1A EP06818278A EP1945825B1 EP 1945825 B1 EP1945825 B1 EP 1945825B1 EP 06818278 A EP06818278 A EP 06818278A EP 1945825 B1 EP1945825 B1 EP 1945825B1
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Prior art keywords
aluminium alloy
product
alloy product
alloy
processed
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German (de)
English (en)
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EP1945825A1 (fr
Inventor
Paola Valentina Absala Morra
Martinez Carlos Ernesto Caicedo
Jörgen VAN DE LANGKRUIS
Johan Boezewinkel
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Novelis Koblenz GmbH
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Aleris Rolled Products Germany GmbH
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    • 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 an aluminium wrought alloy, in particular an Al-Cu-Mg type alloy (or AA2000 series aluminium alloy as designated by the Aluminium Association). More specifically, the present invention relates to an aluminium alloy product having high strength, high fracture toughness exhibiting low crack propagation and high resistance to intergranular corrosion. Products made from the aluminium alloy according to the invention are very suitable for aerospace applications but not limited thereto.
  • the alloy can be processed to various product forms such as sheet, thin plate or an extruded product, a forged product, or a welded product.
  • the aluminium alloy product can be uncoated or coated or plated with another aluminium alloy in order to improve desired properties even further.
  • AA2000 series aluminium alloys in aeroplanes is as fuselage or skin plate, for which purpose typically AA2024 in the T351 temper is used or as lower wing plate for which purpose typically AA2024 in the T351 temper and AA2324 in the T39 temper is used.
  • high tensile strength and high toughness are required. It is known that these properties of a AA2000 series aluminium alloy can be improved by higher levels of alloying elements such as Cu, Mg and Ag.
  • Intergranular corrosion of an aluminium alloy not only affects the integrity of the structure for which it is used, in which may corroded grain boundaries may act as a nucleus for cracks which propagate under the influence of the alternating load during operation of the structure. Therefore, the occurrence of intergranular corrosion sets limits to the use of aluminium alloys of the AA2000 series with high levels of the mentioned alloying elements.
  • the most commonly used aluminium alloys form the AA2000 series for aerospace application are AA2024, AA2024HDT ("High Damage Tolerant") and AA2324.
  • the present invention is directed to a AA2000 series aluminium alloy having the capability of achieving a balance of properties in any relevant product made of the alloy that is better than the balance of properties of the variety of commercially available aluminium alloys of the AA2000 series, nowadays used for such a product or of AA2000 series aluminium alloys disclosed so far.
  • One object of the present invention is to provide an aluminium alloy wrought product, in particular suitable for aerospace application within the AA2000 series alloys having an improved balance of high strength and fracture toughness and high resistance to intergranular corrosion.
  • Another object of the present invention is to provide an aluminium alloy wrought product as referred to above which shows a high resistance to exfoliation corrosion and stress corrosion cracking.
  • a further object of the present invention is to provide an aluminium alloy wrought product as referred to above which is tolerant to the usual variation in process parameters during its manufacturing process.
  • Yet another object of the present invention is to provide an aluminium alloy wrought product as referred to above which is weldable and suitable for use in welded constructions.
  • Yet another object of the present invention is to provide an aluminium wrought product as referred to above in a form which is suitable for use in an aerospace structure.
  • a further object of the present invention is to provide a method of manufacturing an aluminium alloy wrought product as mentioned hereinabove.
  • an aluminium alloy wrought product having high strength and high fracture toughness and high resistance to intergranular corrosion, the aluminium alloy comprising in weight %:
  • the present invention provides an aluminium alloy wrought product having high strength and high fracture toughness and high resistance to intergranular corrosion, the aluminium alloy comprising in weight %:
  • composition of the aluminium alloy according to our invention leads to an alloy product having a high resistance to intergranular corrosion while maintaining a higher strength and higher toughness as compared to the conventional AA2024 alloy.
  • the alloy product of the invention also exhibits a high resistance to exfoliation corrosion and stress corrosion cracking.
  • Another embodiment has the range wherein 0.05% ⁇ Cr ⁇ 0.3%, preferably 0.05% ⁇ Cr ⁇ 0.15%. In this embodiment in particular good intergranular corrosion properties are maintained while at the same time the alloy product is less quench sensitive.
  • a further embodiment has the range wherein 0.1 % ⁇ Ti + Cr ⁇ 0.4%. It has been found that within the given range Ti and Cr can be substituted by each other while maintaining good resistance against intergranular corrosion and good mechanical properties.
  • the Cu level is selected in the range wherein 4.4% ⁇ Cu ⁇ 5.5%, more preferably 4.7% ⁇ Cu ⁇ 5.3%.
  • the Mg level is selected in the range wherein 0.3% ⁇ Mg ⁇ 1.2%, more preferably 0.4% ⁇ Mg ⁇ 0.75%.
  • Iron can be present in the range of up to 0.20% and preferably is kept to a maximum of 0.15%, more preferably to a maximum of 0.1%.
  • a typical preferred iron level would be in the range of 0.03% to 0.08%.
  • Silicon can be present in a range of up to 0.20% and preferably is kept to a maximum of 0.15%, more preferably to a maximum of 0.1%.
  • a typical preferred silicon level would be as low as possible and would typically be for practical reasons in a range of 0.02% to 0.07%.
  • Zirconium can be present in the alloy product according to the invention in an amount of up to 0.20%.
  • a suitable Zr level is a range of 0.04% to 0.15%.
  • a more preferred upper limit for the Zr level is 0.13%, and even more preferably not more than 0.11 %.
  • Manganese can be added alone or in combination with other dispersoid formers.
  • a preferred maximum for the Mn level is 0.80% and a preferred minimum level is 0.15%.
  • a preferred range for the Mn level is in the range of wherein 0.2% ⁇ Mn ⁇ 0.5%.
  • the alloy is free of Ag.
  • the alloy is substantially free of Ag. With “substantially free” is meant that no purposeful addition of Ag was made to the chemical composition but that due to impurities and/or leaking from contact with manufacturing equipment, trace quantities of Ag may nevertheless find their way into the aluminium alloy product.
  • the alloy has a composition consisting of, in wt.%:
  • the aluminium alloy product according to the invention is in the T3x, T6x or T8x temper.
  • the appropriate temper is selected to give the alloy product desired properties. Temper designations are according to the Aluminium Association.
  • the product is preferably provided in the form of a sheet, plate, forging or extrusion for use in an aerospace structure.
  • the aluminium alloy product according to the invention shows an excellent balance of properties for application as plate over a wide variety of thickness, preferably in the form of a plate having a thickness in the range of 0.7 to 80 mm. In the plate thickness range of 0.6 to 1.5 mm the aluminium alloy product is also of particular interest as automotive body sheet.
  • the properties of the aluminium alloy product will be excellent for fuselage sheet and preferably the thickness is up to 25 mm.
  • the properties are excellent for wing plates, e.g. lower wing plate, when tensile strength and fatigue properties are of great importance.
  • the aluminium alloy products can also be used for stringers or to form an integral wing panel and stringer for use in an aircraft wing structure.
  • aluminium alloy product according to the invention can also be used as tooling plate or mould plate, e.g. for moulds for manufacturing formed plastic products for example via die-casting or injection moulding.
  • higher Fe and Si levels up to 0.4% for each of these elements are acceptable.
  • the invention is also embodied in a method for the manufacture of an aluminium alloy product having high strength and high fracture toughness and a high resistance to intergranular corrosion comprising the steps of:
  • the method according to the invention yields aluminium alloy product having excellent resistance to intergranular corrosion and having high strength and excellent fatigue properties.
  • the alloy products of the present invention are regularly prepared by melting and alloying an aluminium alloy product and may be direct chill (“D.C.") cast into ingots or other suitable casting techniques. Homogenisation treatment is typically carried out in one or more steps, each step having a temperature preferably in the range of 460°C to 535°C.
  • the pre-heat temperature involves heating the ingot to the hot working temperature which is typically in a temperature range of 400°C to 480°C.
  • Working the alloy product can be done by one or more methods selected from the group consisting of rolling, extruding and forging. For the present alloy product hot rolling is preferred.
  • Solution heat treatment is typically carried out in the same temperature range as used for homogenisation although somewhat shorter soaking times can be selected.
  • artificial ageing preferably comprises an ageing step at a temperature in the range of 135°C to 210°C, preferably for 5 to 20 hours.
  • the natural ageing preferably comprises a step of ageing at room temperature during 1 to 10 days.
  • the aluminium alloy product is aged to a temper selected from the group comprising T3, T351, T39, T6, T651, and T87.
  • the aluminium alloy product is processed to fuselage sheet, preferably to fuselage sheet having a thickness of less then 30 mm.
  • the aluminium alloy product is processed to lower wing plate.
  • the aluminium alloy product is processed to upper wing plate.
  • the aluminium alloy product is processed to an extruded product.
  • the aluminium alloy product is processed to a forged product.
  • the aluminium alloy product is processed to a thin plate having a thickness in the range of 15 to 40 mm.
  • the aluminium alloy product is processed to a thick plate having a thickness up to 300 mm.
  • the point P indicates the Cr and Ti content of a sample of an alloy according to the invention which was used for testing (also referred to as Alloy 3 in the following examples).
  • alloys 1 and 2 indicate the Cr and Ti content of two comparative alloys, also used for testing and also referred to as alloys 1 and 2. Alloys 1 and 2 fall outside the invention.
  • Alloy 2 has, with the exception of the Cr and Ti content, the same chemical composition as Alloy 3 according to the invention.
  • Alloy 1 has a chemical composition typical for a conventional AA2024 alloy.
  • Table 2 shows that a balanced addition of Cr and Ti according to an embodiment of the invention gives rise to outstanding intergranular corrosion free properties in the T3x tempers with a markedly lower pit depth compared with the other alloys.
  • Alloy T3 T351 T39 1 (Ref. AA2024) 188 (ii) 181 (iii) 257 (iii) 2 151 (i) 137 (ii) 311 (iii) 3 101 (i) 90 (i) 56 (i)
  • Figs. 2a, 2b show micrographs of a cross section of a sample of an alloy according to the invention in T3 temper and of a comparative alloy after corrosion testing.
  • Fig. 2a shows a micrograph of a cross section of a sample of comparative alloy 1 (Ref. AA2024) in T3 temper after corrosion testing.
  • the micrograph clearly shows pitting corrosion and intergranular corrosion to a depth of more than 150 ⁇ m.
  • Fig. 2b shows a micrograph of a cross section of a sample of an alloy according to the invention (alloy 3) also in T3 temper after corrosion testing.
  • the samples show only slight pitting, with a maximum depth of 60 ⁇ m and no intergranular corrosion.
  • Figs. 3a, 3b show micrographs of a cross section of sample of an alloy according to the invention in T6 temper and of a comparative alloy after corrosion testing.
  • Fig. 3a shows a micrograph of a cross section of a sample of a comparative alloy 1 (Ref. AA2024) in T6 temper after corrosion testing.
  • the micrograph clearly shows local intergranular corrosion, extending to a depth of about 220 ⁇ m.
  • Fig. 3b shows a micrograph of a cross section of a sample of an alloy according to the invention (alloy 3) also in T6 temper after corrosion testing.
  • the sample exhibits pitting with only slight intergranular corrosion to a depth of less than 160 ⁇ m.

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  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Extrusion Of Metal (AREA)
  • Metal Rolling (AREA)

Claims (23)

  1. Produit forgé en alliage d'aluminium ayant une haute résistance et une haute ténacité à la fracture ainsi qu'une haute résistance à la corrosion inter-granulaire, ledit produit forgé en alliage d'aluminium étant réalisé en un alliage comprenant, en pourcentage en poids :
    Cu 4,1 à 5,5 %
    Mg 0,30 à 1,6 %
    Mn 0,15 à 0,8 %
    Ti 0,03 à 0,4 %
    Cr 0,05 à 0,4 %
    Ag <0,7%
    Zr < 0,2 %
    Fe < 0,20 %, de préférence < 0,15 %
    Si < 0,20 %, de préférence < 0,15 %,
    le reste étant de l'aluminium et d'autres impuretés ou éléments inévitables,
    chacun < 0,05 % et au total < 0,15 %.
  2. Produit en alliage d'aluminium selon la revendication 1, dans lequel 0,03 % < Ti < 0,3 %, de préférence 0,05 % < Ti < 0,2 %.
  3. Produit en alliage d'aluminium selon la revendication 1 ou 2, dans lequel 0,05 % < Cr < 0,3 %, de préférence 0,05 % < Cr < 0,15 %.
  4. Produit en alliage d'aluminium selon l'une ou plusieurs des revendications précédentes, dans lequel 0,1 % < Ti + Cr < 0,4 %.
  5. Produit en alliage d'aluminium selon l'une ou plusieurs des revendications précédentes, dans lequel 0,1 % < Ti + Cr < 0,3 %.
  6. Produit en alliage d'aluminium selon l'une ou plusieurs des revendications précédentes, dans lequel 4,4 % < Cu < 5,5 %, de préférence 4,7 % < Cu < 5,3 %.
  7. Produit en alliage d'aluminium selon l'une ou plusieurs des revendications précédentes, dans lequel 0,3 % < Mg < 1,2 %, de préférence 0,4 % < Mg < 0,75 %.
  8. Produit en alliage d'aluminium selon l'une ou plusieurs des revendications précédentes, dans lequel 0,2 % < Mn < 0,5 %.
  9. Produit en alliage d'aluminium selon l'une ou plusieurs des revendications précédentes, dans lequel Ag est présent au niveau d'une impureté ou d'un élément inévitable.
  10. Produit en alliage d'aluminium selon la revendication 9, qui est sensiblement exempt de Ag.
  11. Produit en alliage d'aluminium selon l'une ou plusieurs des revendications précédentes, dans lequel le produit se présente dans les nuances tempérées T3x, T6x ou T8x.
  12. Produit en alliage d'aluminium selon l'une ou plusieurs des revendications précédentes, dans lequel le produit est sous la forme d'une tôle, d'une plaque, d'une pièce forgée ou d'un produit extrudé à utiliser dans une structure aérospatiale.
  13. Produit en alliage d'aluminium selon l'une ou plusieurs des revendications précédentes, dans lequel le produit est sous la forme d'une plaque ayant une épaisseur dans la plage de 0,7 à 80 mm.
  14. Procédé pour la fabrication d'un produit en alliage d'aluminium ayant une haute résistance et une haute ténacité à la fracture ainsi qu'une haute résistance à la corrosion inter-granulaire, comprenant les étapes consistant à :
    a) couler un lingot ayant une composition de l'alliage selon l'une ou plusieurs des revendications 1 à 10 ;
    b) homogénéiser et/ou préchauffer le lingot après coulée ;
    c) oeuvrer à chaud le lingot en un produit intermédiaire par un ou plusieurs procédés choisis parmi le groupe comprenant laminage, extrusion et forgeage ;
    d) en option réchauffer le produit intermédiaire, et
    e) travailler en outre en option à chaud et/ou à froid pour donner une forme désirée à la pièce à oeuvrer ;
    f) traiter à chaud en solution ladite pièce à oeuvrer mise en forme à une température et pendant un temps suffisant pour mettre sensiblement tous les constituants solubles dans l'alliage sous forme de solution solide ;
    g) tremper la pièce à oeuvrer traitée à chaud en solution par une procédure de trempe par pulvérisation ou de trempe par immersion dans de l'eau ou un autre agent de trempe ;
    h) étirer ou comprimer en option la pièce à oeuvrer trempée ;
    i) vieillir naturellement ou artificiellement la pièce à oeuvrer trempée et en option étirée ou comprimée pour atteindre une nuance de températion désirée.
  15. Procédé selon la revendication 14, dans lequel le produit en alliage d'aluminium est vieilli à une nuance de températion choisie parmi le groupe comprenant T3, T351, T39, T6, T651 et T87.
  16. Procédé de fabrication selon la revendication 14 ou 15, dans lequel le produit en alliage d'aluminium est traité pour former une tôle de fuselage.
  17. Procédé de fabrication selon l'une quelconque des revendications 14 à 16, dans lequel le produit en alliage d'aluminium est traité pour former une tôle de fuselage ayant une épaisseur inférieure à 30 mm.
  18. Procédé de fabrication selon l'une quelconque des revendications de 14 à 16, dans lequel le produit en alliage d'aluminium est traité pour former une plaque d'aile inférieure.
  19. Procédé de fabrication selon l'une quelconque des revendications de 14 à 16, dans lequel le produit en alliage d'aluminium est traité pour former une plaque d'aile supérieure.
  20. Procédé de fabrication selon l'une quelconque des revendications 14 à 16, dans lequel le produit en alliage d'aluminium est traité pour former un produit extrudé.
  21. Procédé de fabrication selon l'une quelconque des revendications 14 à 16, dans lequel le produit en alliage d'aluminium est traité pour former un produit forgé.
  22. Procédé de fabrication selon l'une quelconque des revendications 14 à 16, dans lequel le produit en alliage d'aluminium est traité pour former une plaque mince ayant une épaisseur dans la plage de 15 à 40 mm.
  23. Procédé de fabrication selon l'une quelconque des revendications 14 à 16, dans lequel le produit en alliage d'aluminium est traité pour former une plaque épaisse ayant une épaisseur allant jusqu'à 300 mm.
EP06818278.1A 2005-10-25 2006-10-24 Alliages a base d'aluminium, de cuivre et de magnesium (al cu mg) pour les applications aerospatiales Active EP1945825B1 (fr)

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Application Number Priority Date Filing Date Title
EP06818278.1A EP1945825B1 (fr) 2005-10-25 2006-10-24 Alliages a base d'aluminium, de cuivre et de magnesium (al cu mg) pour les applications aerospatiales

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
EP05077448 2005-10-25
PCT/EP2006/010216 WO2007048565A1 (fr) 2005-10-25 2006-10-24 Alliage al-cu-mg adapte a une application aerospatiale
EP06818278.1A EP1945825B1 (fr) 2005-10-25 2006-10-24 Alliages a base d'aluminium, de cuivre et de magnesium (al cu mg) pour les applications aerospatiales

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EP1945825A1 EP1945825A1 (fr) 2008-07-23
EP1945825B1 true EP1945825B1 (fr) 2014-06-25

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EP (1) EP1945825B1 (fr)
CN (1) CN101297054A (fr)
BR (1) BRPI0617699A2 (fr)
CA (1) CA2627070C (fr)
RU (1) RU2418876C2 (fr)
WO (1) WO2007048565A1 (fr)

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EP2559779B1 (fr) * 2011-08-17 2016-01-13 Otto Fuchs KG Alliage d'Al-Cu-Mg-Ag résistant à la chaleur et procédé de fabrication d'un demi-produit ou d'un produit à partir d'un tel alliage d'aluminium
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CN105908028B (zh) * 2016-06-16 2018-02-27 江苏大学 一种设计高淬透性高强度铝合金主要成分的方法
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CN109136697B (zh) * 2018-08-28 2020-12-22 兰州飞行控制有限责任公司 一种高强度铝铜系铝合金
CN113226585B (zh) * 2018-11-12 2024-07-30 空中客车简化股份公司 由7xxx系列合金制备高能液压成形结构的方法
WO2020200869A1 (fr) * 2019-04-03 2020-10-08 Aleris Rolled Products Germany Gmbh Procédé de production d'une structure hydroformée à haute énergie à partir d'un alliage série 2xxx
CN110724866A (zh) * 2019-11-28 2020-01-24 西南铝业（集团）有限责任公司 一种2014铝合金航空精密轮毂模锻件的无锆毛坯
CN111020321B (zh) * 2019-12-11 2021-09-14 兰州飞行控制有限责任公司 一种适于锻造加工的Al-Cu系铸造合金及其制备方法
CN111101038A (zh) * 2019-12-20 2020-05-05 山东南山铝业股份有限公司 一种多元耐热铝合金及其制备方法
FR3111143B1 (fr) * 2020-06-04 2022-11-18 Constellium Issoire Produits en alliage aluminium cuivre magnésium performants à haute température
CN112281033B (zh) * 2020-09-25 2021-09-28 中南大学 一种同时提高铝铜镁合金油井管耐腐蚀和耐热性的方法
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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
CN115821131B (zh) * 2022-12-05 2024-05-14 山东南山铝业股份有限公司 一种低疲劳裂纹扩展速率2系铝合金型材及其制造方法
CN115927936B (zh) * 2022-12-22 2023-06-09 北京机科国创轻量化科学研究院有限公司 一种高强韧铝合金及其制备方法
CN117660816A (zh) * 2023-11-08 2024-03-08 东北轻合金有限责任公司 一种航空用高强耐腐蚀2024铝合金小壁厚热挤压型材的制造方法

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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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US8043445B2 (en) * 2003-06-06 2011-10-25 Aleris Aluminum Koblenz Gmbh High-damage tolerant alloy product in particular for aerospace applications
FR2858984B1 (fr) * 2003-08-19 2007-01-19 Corus Aluminium Walzprod Gmbh Produit en alliage ai-cu a haute tenacite et son procede de production

Also Published As

Publication number Publication date
BRPI0617699A2 (pt) 2011-08-02
CA2627070A1 (fr) 2007-05-03
EP1945825A1 (fr) 2008-07-23
CN101297054A (zh) 2008-10-29
CA2627070C (fr) 2014-07-29
RU2008115928A (ru) 2009-10-27
RU2418876C2 (ru) 2011-05-20
WO2007048565A1 (fr) 2007-05-03

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