EP3414352B1 - Produit travaillé en alliage al-cu-li-mg-mn-zn - Google Patents

Produit travaillé en alliage al-cu-li-mg-mn-zn Download PDF

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Publication number
EP3414352B1
EP3414352B1 EP17702339.7A EP17702339A EP3414352B1 EP 3414352 B1 EP3414352 B1 EP 3414352B1 EP 17702339 A EP17702339 A EP 17702339A EP 3414352 B1 EP3414352 B1 EP 3414352B1
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Prior art keywords
product
aluminium alloy
range
stock
alloy
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German (de)
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EP3414352A1 (fr
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Sven SCHNITTGER
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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
    • 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
    • C22C21/14—Alloys based on aluminium with copper as the next major constituent with silicon
    • 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
    • C22C21/18—Alloys based on aluminium with copper as the next major constituent with zinc
    • 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 an Al-Cu-Li wrought alloy product, more in particular an Al-Cu-Li-Mg-Mn-Zn type alloy product for structural members. Products made from this aluminium alloy product are very suitable for aerospace applications, but not limited to that.
  • the alloy can be processed to various product forms, e.g. sheet, thin plate, thick plate, extruded or forged products.
  • Aluminium Association alloys such as AA2090 and AA2091 contain about 2.0% lithium, which translates into about a 7% weight savings over alloys containing no lithium. Aluminium alloys AA2094 and AA2095 contain about 1.2% lithium. Another aluminium alloy, AA8090 contains about 2.5% lithium, which translates into an almost 10% weight savings over alloys without lithium.
  • Patent document US-2004/0071586 discloses a broad range for an aluminium alloy comprising, 3 to 5% of Cu, 0.5% to 2% of Mg, and 0.01% to 0.9% of Li. It is disclosed that the Li content should remain at a low level in combination with having controlled amounts of Cu and Mg to provide the desired levels of fracture toughness and strength. Preferably the Cu and Mg are present in the alloy in a total amount below a solubility limit of the alloy.
  • Patent document WO-2004/106570 discloses an Al-Cu-Li-Mg-Ag-Mn-Zr alloy for use as a structural member.
  • the alloy has 2.5% to 5.5% Cu, 0.1% to 2.5% Li, 0.2% to 1% Mg, 0.2% to 0.8% Ag, 0.2% to 0.8% Mn, and up to 0.3% Zr, balance aluminium. It is known in the art that this patent document covers the AA2050 alloy being registered with in Aluminium Association in 2004 and having a registered alloy composition of: Cu 3.2 - 3.9 Li 0.7 - 1.3 Mg 0.20 - 0.6 Ag 0.20 - 0.7 Mn 0.20 - 0.50 Zr 0.06 - 0.14
  • Patent document US-2007/0181229 discloses an aluminium alloy having 2.1% to 2.8% Cu, 1.1% to 1.7% Li, 0.1% to 0.8% Ag, 0.2% to 0.6% Mg, 0.2% to 0.6% Mn, a content of Fe and Si less or equal to 0.1% each, balance impurities and aluminium, and wherein the alloy is substantially zirconium free.
  • the low Zr content is reported to increase the toughness.
  • Patent document WO-2009/036953 discloses an Al-Cu-Li-Mg-Ag-Zn-Mn-Zr alloy for use as an aircraft structural member.
  • the alloy has Cu 3.4% to 5.0%, Li 0.9% to 1.7%, Mg 0.2% to 0.8%, Ag 0.1% to 0.8%, Mn 0.1% to 0.9%, Zn max. 1.5%, one or more elements selected from the group (Zr, Cr, Ti, Sc, Hf).
  • Patent document WO-2009/073794 discloses an Al-Cu-Li-Mg-Ag-Zn-Mn-Zr alloy for use as an aircraft structural member.
  • the alloy has Cu 3.4% to 4.2%, Li 0.9% to 1.4%, Ag 0.3% to 0.7%, Mg 0.1% to 0.6%, Zn 0.2% to 0.8%, Mn 0.1% to 0.6%, and 0.01% to 0.6% of a grain structure control element.
  • Patent document WO2015/082779 discloses an Al-Ci-Li alloy product is the form of an rolled or forged product having a thickness of 14 to 100 mm, and wherein the alloy has 1.8% to 2.6% Cu, 1.3% to 1.8% Li, 0.1% to 0.5% Mg, 0.1% to 0.5% Mn with Zr ⁇ 0.05%, or ⁇ 0.05% Mn with 0.10% to 0.16% Zr, 0 to 0.5% Ag, ⁇ 0.20% Zn, 0.01% to 0.15% Ti, ⁇ 0.1% Fe, ⁇ 0.1% Si.
  • the material is in particular suitable for manufacturing airplane underwing elements.
  • alloy designations and temper designations refer to the Aluminium Association designations in Aluminium Standards and Data and the Registration Records, as published by the Aluminium Association in 2015 and known to the skilled person.
  • the term "about" when used to describe a compositional range or amount of an alloying addition means that the actual amount of the alloying addition may vary from the nominal intended amount due to factors such as standard processing variations as understood by those skilled in the art.
  • up to 0.07% Fe may include an alloy having no Fe.
  • an aluminium alloy wrought product for structural members having a chemical composition consisting of, in wt.%: Cu 3.2% to 4.4%, Li 0.8% to 1.4%, Mg 0.20% to 0.90%, Mn 0.10% to 0.8%, Zn 0.20% to 0.80%, one or more elements selected from the group consisting of: (Zr 0.05% to 0.25%, Cr 0.05% to 0.30%, Ti 0.01% to 0.25%, Sc 0.05% to 0.4%, Hf 0.05% to 0.4%), Ag ⁇ 0.05%, Fe ⁇ 0.15%, Si ⁇ 0.15%, unavoidable impurities and balance aluminium.
  • the alloy wrought product may contain normal and inevitable impurities, typically each ⁇ 0.05% and the total ⁇ 0.15%, and the balance is made by aluminium.
  • this compositional range offers a good balance of strength, fracture toughness and corrosion resistance meeting the requirements for commercial delivery and also offering a very good thermal stability after being long term aged or exposed for 1000 hours at 85°C.
  • Copper is one of the main alloying elements in the alloy product and is added to increase the strength of the alloy product. Care must be taken, however, to not add too much copper since the corrosion resistance can be reduced. Also, copper additions beyond maximum solubility will lead to low fracture toughness and low damage tolerance.
  • the upper-limit for the Cu-content is for that reason 4.4%, and preferably about 4.2%, and more preferably about 4.10%.
  • a preferred lower-limit is about 3.6%, and more preferably about 3.75%, and most preferably about 3.85%.
  • Magnesium is another main alloying element in the alloy product and is added to increase strength and reduce density. Care should be taken, however, to not add too much magnesium in combination with copper since additions beyond maximum solubility will lead to low fracture toughness and low damage tolerance.
  • a more preferred lower-limit for the Mg addition is about 0.35%, more preferably 0.38%.
  • a more preferred upper-limit is about 0.65%, and more preferably 0.55%. It has been found that at a level of above 0.8% the further addition of Mg may result in a decrease in toughness of the alloy product.
  • Lithium is another important alloying element in the wrought product of this invention and added together with the copper and magnesium to obtain an improved combination of fracture toughness and strength.
  • a preferred lower-limit for the Li addition is 0.9%, and more preferably 1.0%.
  • a preferred upper-limit for the Li addition is less than 1.30%.
  • a too high Li content has adverse effect on the damage tolerance properties of the alloy product in particular with the relatively high Cu levels in the alloy product of this invention.
  • the zinc is purposively added to improve strength and the corrosion resistance and in addition it has a small effect on the damage tolerance properties of the alloy product.
  • the zinc is typically present in a range of 0.2% to 0.80%.
  • a preferred lower-limit for the Zn-content is 0.25%.
  • a preferred upper-limit for the Zn-content is about 0.70%, and more preferably about 0.65%.
  • the silver content is less than 0.05%.
  • the silver content is less than about 0.02%, such that the aluminium alloy is substantially free from Ag.
  • substantially free or “essentially free” is meant that no purposeful addition 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 alloy product.
  • less than 0.01% is an example of a trace quantity. That the alloy product has a very low Ag content makes the alloy product more cost effective in comparison to the many Al-Cu-Li alloy known in the art having a purposive addition of Ag, while still offering a good balance of engineering properties in combination with a very good thermal stability.
  • the manganese addition is to control the grain structure by providing a more uniform distribution of the main precipitating phases, a reduced grain size and thereby further increases strength in particular.
  • the Mn addition should not exceed about 0.8% and should be at least about 0.10%.
  • a preferred lower-limit for the manganese addition is at least about 0.20%, and more preferably at least 0.30%.
  • a preferred upper-limit for the Mn addition is about 0.6%, and more preferably about 0.55%.
  • a too high Mn content results in a decrease in both the yield strength and fracture toughness.
  • alloy product of the present invention contains at least one element selected from the defined group of Zr, Cr, Ti, Sc, and Hf.
  • zirconium to the alloy product in a range of 0.05% to 0.25%, and preferably in a range of 0.05% to 0.15%.
  • a too low Zr addition has an adverse on the unit propagation energy of the alloy wrought product.
  • Ti can be added to the alloy product amongst others for grain refiner purposes during casting of the alloy stock, e.g. ingots or billets.
  • the addition of Ti should not exceed 0.25%.
  • a preferred lower limit for the Ti addition is about 0.01%.
  • Ti can be added as a sole element or with either boron or carbon serving as a casting aid, for grain size control.
  • the Si content in the alloy product is present as an impurity element of less than 0.15%, and should be present at the lower-end of this range, e.g. less than about 0.10%, and more preferably less than 0.07%, to maintain fracture toughness properties at desired levels.
  • the Fe content in the alloy product should be less than 0.15%.
  • the lower-end of this range is preferred, e.g. less than about 0.1%, and more preferably less than about 0.07% to maintain in particular the toughness at a sufficiently high level.
  • a higher Fe content can be tolerated.
  • the product is in the form of a rolled, extruded or forged product, and more preferably the product is in the form of a sheet, plate, forging or extrusion as part of an aircraft structural part.
  • the alloy product is provided in the form of an extruded product.
  • the alloy product is provided in the form of a plate product, preferably having a thickness of 12.0 to 175 mm, and preferably of at least 75 mm.
  • the plate product provides a good balance in engineering properties, in particular strength and has shown reduced quench sensitivity.
  • the part When used as part of an aircraft structural part the part can be for example a fuselage sheet, upper wing plate, lower wing plate, thick plate for machined parts, forging or thin sheet for stringers.
  • Resistance to intergranular corrosion of the alloy products of the present invention is generally high, for example, typically only pitting is detected when the metal is submitted to corrosion testing according to MASTMAASIS (ASTM-69 A2-85).
  • the sheet and light gauge plate may also be clad, with preferred cladding thickness of from about 1% to about 8% of the thickness of the sheet or plate.
  • the cladding is typically a low composition aluminium alloy.
  • the aluminium alloy can be provided as an ingot or slab or billet for fabrication into a suitable wrought product by casting techniques regular in the art for cast products, e.g. DC-casting, EMC-casting, EMS-casting.
  • Grain refiners such as those containing titanium and boron, or titanium and carbon, may also be used as is known in the art.
  • the ingot is commonly scalped to remove segregation zones near the cast surface of the ingot.
  • Homogenisation treatment is typically carried out in one or multiple steps, each step having a temperature in the range of about 475°C to 535°C.
  • the pre-heat temperature involves heating the hot working stock to the hot-working entry temperature, which is typically in a temperature range of about 440°C to 490°C.
  • the stock can be hot worked by one or more methods selected from the group consisting of rolling, extrusion, and forging, preferably using regular industry practice.
  • the method of hot rolling is preferred for the present invention.
  • the hot working, and hot rolling in particular, may be performed to a final gauge, e.g. 3 mm or less or alternatively thick gauge products.
  • the hot working step can be performed to provide stock at intermediate gauge, typical sheet or thin plate. Thereafter, this stock at intermediate gauge can be cold worked, e.g. by means of rolling, to a final gauge.
  • an intermediate anneal may be used before or during the cold working operation.
  • Solution heat-treatment is typically carried out within the same temperature range as used for homogenisation, although the soaking times that are chosen can be somewhat shorter.
  • a typical SHT is carried out at a temperature of 480°C to 525°C for 15 min to about 5 hours. Lower SHT temperatures generally favour high fracture toughness.
  • the stock is rapidly cooled or quenched, preferably by one of spray quenching or immersion quenching in water or other quenching media.
  • the SHT and quenched stock may be further cold worked, for example, by stretching in the range of about 0.5% to 15% of its original length to relieve residual stresses therein and to improve the flatness of the product.
  • the stretching is in the range of about 0.5% to 6%, more preferably of about 0.5% to 4%.
  • the stock After cooling the stock is aged, typically at ambient temperatures, and/or alternatively the stock can be artificially aged.
  • the alloy product according to this invention is preferably provided in a slightly under-aged T8 condition, in particular a T84 condition, to provide the best balance in strength and damage tolerance properties.
  • a desired structural shape is then machined from these heat treated plate sections, more often generally after artificial ageing, for example, an integral wing spar.
  • SHT, quench, optional stress relief operations and artificial ageing are also followed in the manufacture of thick sections made by extrusion and/or forged processing steps.
  • the ageing step can be divided into two steps: a pre-ageing step prior to a welding operation, and a final heat treatment to form a welded structural member.
  • the AlCuLi-alloy product according to this invention can be used amongst others as in the thickness range of at most 0.5 inch (12.5 mm) the properties will be excellent for fuselage sheet. In the thin plate thickness range of 0.7 to 3 inch (17.7 to 76 mm) the properties will be excellent for wing plate, e.g. lower wing plate.
  • the thin plate thickness range can be used also for stringers or to form an integral wing panel and stringer for use in an aircraft wing structure. When processed to thicker gauges of more than 3 inch (75 mm) to about 11 inch (280 mm) excellent properties have been obtained for integral part machined from plates, or to form an integral spar for use in an aircraft wing structure, or in the form of a rib for use in an aircraft wing structure.
  • the alloy products according to the invention can also be provided in the form of a stepped extrusion or extruded spar or extruded stiffeners for use in an aircraft structure, or in the form of a forged spar for use in an aircraft
  • the yield strength or proof strength of the product When applied in the form of a sheet product the yield strength or proof strength of the product should be at least 460 MPa in the L-direction, and preferably at least 480 MPa.
  • the yield strength or proof strength of the product When applied in the form of an extruded product, e.g. as a stringer, or in the form of a plate product the yield strength or proof strength of the product should be at least 470 MPa in the L-direction, and more preferably at least 480 MPa.
  • These strength levels can be obtained by a selecting the alloy composition within the claimed ranges, and preferably within the preferred narrower ranges, in combination with the artificial ageing practice to a T8 condition.
  • the Ag-free alloy was aged for 16h@150°C and the Ag containing alloy for 10.5h@150°C.
  • the difference in ageing time to arrive at the T84 temper is due to the difference in silver-content which has an effect on the ageing response.

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  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
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  • Mechanical Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Physics & Mathematics (AREA)
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Claims (19)

  1. Produit corroyé en alliage d'aluminium pour des éléments structurels ayant une composition chimique constituée de, en pourcentage en poids : Cu 3,2 à 4,4 Li 0,8 à 1,4 Mg 0,20 à 0,90 Mn 0,10 à 0,8 Zn 0,20 à 0,80,
    un ou plusieurs éléments sélectionnés parmi le groupe constitué de : Zr 0,05 à 0,25, Cr 0,05 à 0,30, Ti 0,01 à 0,25, Sc 0,05 à 0,4, Hf 0,05 à 0,4,
    Ag < 0,05 Fe < 0,15 Si < 0,15,
    des impuretés inévitables et le reste étant de l'aluminium.
  2. Produit corroyé en alliage d'aluminium selon la revendication 1, dans lequel la teneur en Cu est dans une plage de 3,6 % à 4,4 %, de préférence dans une plage de 3,75 % à 4,20 %.
  3. Produit corroyé en alliage d'aluminium selon la revendication 1 ou 2, dans lequel la teneur en Li est dans une plage de 0,90 % à 1,4 %, et de préférence dans une plage de 1,0 % à 1,30 %.
  4. Produit corroyé en alliage d'aluminium selon l'une quelconque des revendications 1 à 3, dans lequel le produit contient du Zr dans une plage de 0,05 % à 0,15 %.
  5. Produit corroyé en alliage d'aluminium selon l'une quelconque des revendications 1 à 4, dans lequel la teneur en Zn est au maximum 0,70 %, de préférence au maximum 0,65 %.
  6. Produit corroyé en alliage d'aluminium selon l'une quelconque des revendications 1 à 5, dans lequel la teneur en Ag est inférieure à 0,02 % et, de façon plus préférée, le produit en alliage est sensiblement dépourvu de Ag.
  7. Produit corroyé en alliage d'aluminium selon l'une quelconque des revendications 1 à 6, dans lequel le produit contient du Mn dans une plage de 0,20 % à 0,6 %, et de préférence de 0,20 % à 0,55 %.
  8. Produit corroyé en alliage d'aluminium selon l'une quelconque des revendications 1 à 7, dans lequel le produit contient du Mg dans une plage de 0,20 % à 0,8 %, et de préférence de 0,20 % à 0,65 %, et de manière plus préférée de 0,35 % à 0,65 %.
  9. Produit corroyé en alliage d'aluminium selon l'une quelconque des revendications 1 à 8, dans lequel le produit est sous la forme d'un produit laminé, extrudé ou forgé.
  10. Produit corroyé en alliage d'aluminium selon la revendication 9, dans lequel le produit corroyé est sous la forme d'un produit extrudé.
  11. Produit corroyé en alliage d'aluminium selon l'une quelconque des revendications 1 à 9, dans lequel le produit corroyé est sous la forme d'un produit en plaque ayant une épaisseur de 12,0 mm à 175 mm, et de préférence au moins 75 mm.
  12. Produit corroyé en alliage d'aluminium selon l'une quelconque des revendications 1 à 11, dans lequel le produit est dans une condition de vieillissement T8, et de préférence dans une condition T84.
  13. Procédé de fabrication d'un produit corroyé en alliage d'aluminium selon l'une quelconque des revendications 1 à 12, comprenant les étapes comprenant à :
    a) couler en bloc un lingot d'un alliage AlCuLi selon l'une quelconque des revendications 1 à 8,
    b) préchauffer et/ou homogénéiser le bloc coulé ;
    c) œuvrer à chaud le bloc par un ou plusieurs procédés sélectionnés parmi le groupe comprenant le laminage, l'extrusion et le forgeage ;
    d) en option œuvrer à froid le bloc œuvré à chaud ;
    e) effectuer un traitement en solution à chaud (SHT) du bloc œuvré à chaud et/ou en option œuvré à froid, le traitement SHT étant mis en œuvre à une température et pendant un temps suffisant pour mettre en solution solide les constituants solubles dans l'alliage d'aluminium ;
    f) refroidir le bloc traité par SHT ;
    g) en option étirer ou comprimer le bloc SHT refroidi, ou œuvrer à froid d'une autre manière le bloc SHT refroidi pour libérer les contraintes, par exemple en planifiant ou en étirant ou en laminant à froid le bloc SHT refroidi ; et
    h) faire vieillir, de préférence par un vieillissement artificiel, le bloc SHT refroidi et en option étiré ou comprimé ou œuvré à froid d'une autre manière pour atteindre une températion désirée.
  14. Procédé selon la revendication 13, dans lequel l'homogénéisation est effectuée à une température dans une plage de 475° C à 535° C.
  15. Procédé selon la revendication 13 ou 14, dans lequel le travail à chaud est effectué par laminage et la température d'entrée du travail à chaud est à une température dans la plage de 440° C à 490° C.
  16. Procédé selon l'une quelconque des revendications 13 à 15, dans lequel le traitement à chaud en solution est effectué à une température dans une plage de 480° C à 525° C.
  17. Procédé selon l'une quelconque des revendications 13 à 16, dans lequel l'étirage est effectué dans une plage de 0,5 % à 6 %, et de préférence dans une plage de 0,5 % à 4 %.
  18. Procédé selon l'une quelconque des revendications 13 à 17, dans lequel le produit a été vieilli jusqu'à une condition de vieillissement T8.
  19. Procédé selon l'une quelconque des revendications 13 à 18, dans lequel le produit corroyé est laminé pour donner un produit en plaque ayant une épaisseur d'au moins 12,0 mm, et de préférence d'au moins 75 mm.
EP17702339.7A 2016-02-09 2017-01-26 Produit travaillé en alliage al-cu-li-mg-mn-zn Revoked EP3414352B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
EP16154856 2016-02-09
PCT/EP2017/051595 WO2017137260A1 (fr) 2016-02-09 2017-01-26 Produit d'alliage corroyé à base d'al-cu-li-mg-mn-zn

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EP3414352A1 EP3414352A1 (fr) 2018-12-19
EP3414352B1 true EP3414352B1 (fr) 2019-12-04

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US (1) US20210207254A1 (fr)
EP (1) EP3414352B1 (fr)
CN (1) CN109072358A (fr)
BR (1) BR112018015112A2 (fr)
CA (1) CA3013955A1 (fr)
WO (1) WO2017137260A1 (fr)

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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
FR3080861B1 (fr) * 2018-05-02 2021-03-19 Constellium Issoire Procede de fabrication d'un alliage aluminium cuivre lithium a resistance en compression et tenacite ameliorees
CN113039303A (zh) * 2018-11-07 2021-06-25 奥科宁克技术有限责任公司 2xxx铝锂合金
CN113106311B (zh) * 2021-03-15 2022-03-29 丽水学院 一种金属3D打印的Al-Li-Cu-Mg系铝合金丝材的制备方法及其设备
CN113249665A (zh) * 2021-07-02 2021-08-13 中国航发北京航空材料研究院 一种铝合金构件的成形方法
CN115386818A (zh) * 2022-08-25 2022-11-25 中南大学 一种Al-Cu-Li系合金热轧板坯的形变热处理方法

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WO2017137260A1 (fr) 2017-08-17
US20210207254A1 (en) 2021-07-08

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