EP3072984B1 - Alliage d'al-cu-mg-li et produit allié ainsi produit - Google Patents

Alliage d'al-cu-mg-li et produit allié ainsi produit Download PDF

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Publication number
EP3072984B1
EP3072984B1 EP15161219.9A EP15161219A EP3072984B1 EP 3072984 B1 EP3072984 B1 EP 3072984B1 EP 15161219 A EP15161219 A EP 15161219A EP 3072984 B1 EP3072984 B1 EP 3072984B1
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Prior art keywords
alloy
weight
content
strength
product
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German (de)
English (en)
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EP3072984B2 (fr
EP3072984A1 (fr
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Tina Schlingmann
Joachim Becker
Thomas Witulski
Abi D. Dehbozorgi
Mark Timko
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Otto Fuchs KG
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Otto Fuchs KG
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Priority to EP15161219.9A priority Critical patent/EP3072984B2/fr
Priority to ES15161219T priority patent/ES2642118T5/es
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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
    • 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-Mg-Li alloy and an alloy product produced therefrom.
  • High-performance aluminum alloy components are an indispensable component of aircraft design in many cases. Components of such high-performance aluminum alloys are used among other things in the fuselage and in the wing as structural components. These parts are forged, extruded parts. These must meet the necessary combination of static and dynamic strength and have certain requirements in terms of tensile strength, yield strength, elongation at break and crack toughness (K 1C and stress corrosion cracking). In addition, the weight plays a not insignificant role in components used in the aerospace industry. Thus, the specific gravity (density) of the high performance alloy used is also relevant.
  • Al-Cu-Mg-Li alloy meeting these requirements is the aluminum alloy AA 2195.
  • This alloy has a composition of 3.7-4.3% by weight of Cu, 0.25%. 0.8% by weight of Mg, 0.8-1.2% by weight of Li, 0.25-0.6% by weight of Ag, max. 0.25% by weight of Zn, max. 0.25% by weight of Mn, max. 0.12% by weight of Si, max. 0.15 wt.% Fe, max. 0.1% by weight of Ti and 0.08-0.16% by weight of Zr.
  • the components made from this alloy have a density of about 2.7 g / cm 3.
  • the aluminum alloy AA 2050 is an example of such a high-performance alloy, which replaced the alloy 2195, from which often components were previously made in the aviation sector in the meantime.
  • the alloy AA 2050 has a Cu content of 3.2-3.9% by weight, a Li content from 0.7 to 1.3 wt%, an Mn content of 0.2 to 0.8 wt%, and a Mg content of 0.1 to 0.5 wt%.
  • Zn is usually involved in the construction of the alloy with up to 0.25 wt .-%.
  • silver is alloyed in this alloy in amounts of 0.2-0.7% by weight. This measure accounts for the prevailing opinion that silver is a necessary alloying component especially in lithium-containing Al-Cu alloys for achieving high strengths of components made therefrom.
  • An alloy with an even higher Li content similar to the AA 2050 alloy, is the alloy AA 2196 with a Li content of 1.4-2.1% by weight.
  • the Cu content of this alloy is slightly reduced compared to the Cu content in the 2050 alloy. From this alloy, however, only components with a lower strength can be produced compared to components that can be made of the AA 2050 alloy.
  • Previously known Ag-containing high-performance aluminum alloys such as the AA 2050 alloy, contain Mn as a necessary alloying element.
  • the AA 2050 alloy requires a Mn content of 0.2-0.5 wt%.
  • Mn in a recrystallization inhibitor Mainly due to the latter property, Mn is an element necessary for achieving the desired strength properties.
  • This also corresponds to the prevailing opinion that in Ag-containing Al-Cu-Mg-Li alloys at least 0.2 wt .-% Mn, if not significantly more involved in the construction of the alloy must be.
  • care must be taken to ensure that the Mn content is not so high that coarse primary solidification does not form in the microstructure, which in particular adversely affects the fatigue behavior.
  • Such a high-performance aluminum alloy must contain enough Mn to fulfill the desired property as a recrystallization inhibitor. These requirements meet the previously known alloys with Mn contents, such as in the AA 2050 between 0.2 and 0.5 wt .-%.
  • the Mn content information given in the prior art high-performance aluminum alloys containing Ag and Li has a relatively large margin. It depends largely on the participation of others Alloy elements Cu, Li, Mg, Mn, Ti, Zr, Si, Fe and Ag from whether a selected Mn content from the specified range can actually be melted an alloy from which components can be produced that meet the specified strength requirements and fatigue and toughness are sufficient.
  • the invention is based on the above-appreciated prior art, the task of proposing an Ag and Li-containing Al-Cu alloy, which is not only simplified in terms of their construction compared to prior art alloys, but in which is also ensured that within the specified spectrum of the alloying elements components produced therefrom after appropriate heat treatment satisfy the desired combination of mechanical properties.
  • All alloy compositions described in this embodiment may contain unavoidable impurities per element of 0.05% by weight, the total amount of impurities should not exceed 0.15% by weight. However, it is preferable to keep the impurity as low as possible and not to exceed 0.03 wt% per element at a total amount of 0.08 wt%.
  • This Ag and Li-containing high-performance aluminum alloy has a particularly narrow range of its alloying elements. This is especially true for the alloying element Mn, which not only in A very narrow spectrum, but also with surprisingly small proportions in the structure of the alloy is involved and fulfills the functions intended for this element. It should be pointed out in this context that this alloy is Zn-free. It was surprising to find that in this alloy having an Mn content as small as that required in the AA 2050 alloy, it is sufficient to effectively prevent recrystallization. In addition, care is taken within the stated range of 0.01% by weight to ⁇ 0.2% by weight that no or only to a significant extent primary phases are formed which would impair fatigue and toughness.
  • a component has extremely strong properties if the yield strength R p0.2 is at least 600 MPa.
  • a component is said to have high strength properties if the yield strength R p0.2 is at least 500 MPa.
  • the necessary strength does not appear in combination with the other alloying elements. Copper contents above 3.9 wt.% In the alloy are unable to further increase the strength of a component made from the alloy. On the contrary, it is to be expected that at higher Cu contents property-damaging phases form.
  • Lithium is included to reduce the density (specific gravity) in the alloy.
  • the lithium content is adapted to the Cu and Mg contents of the alloy in such a way that as much as possible Lithium is incorporated into the alloy, but only so much that this can be brought into solution and no unwanted Li-containing phases. Therefore, the Li content of the alloy is limited to the narrow range between 0.9 and 1.3 wt%.
  • Magnesium contributes to the desired properties of a component made of the alloy, but is only permitted with one share, so that no undesirable phases (such as an S phase Al 2 CuMg) form. Taking into account the further alloying elements, the Mg content should not exceed 0.45% by weight.
  • Titanium acts as a grain refiner in the cast structure and zirconium as a dispersoid former and thus contributes to the inhibition of recrystallization.
  • an Mn content of between 0.10 and 0.18 wt .-% is sufficient to effectively prevent recrystallization. This is attributed to the specific and targeted selection of the share and the range of Mn as well as the very limited Mn content. This ensures that within these limits can be consistently set the desired combination of mechanical properties in a made of the alloy component. If the Mn content exceeds 0.18% by weight, taking into account the other alloying elements, this may already lead to coarser primary solidifications in the microstructure, which in turn was not to be expected in accordance with prevailing opinion. Finally, in the alloy AA 2050, an Mn content of 0.2-0.8 wt% is proposed.
  • the Mn content of the claimed alloy is limited to a maximum amount of 0.18 wt%. If no primary solidification in the microstructure is to be accepted, the Mn content is limited to a range of 0.10-0.15% by weight at the top. Particularly good results can be achieved if the Mn content is between 0.10 and 0.12 wt .-%.
  • the Ag content is included to increase the strength in this alloy.
  • the Ag content is chosen to be slightly lower or slightly more within the claimed limit of between 0.2 and 0.45 wt%.
  • the Ag content should be more than 0.35 wt .-%.
  • a preferred contribution of the Ag content to the construction of the alloy is from 0.38 to 0.43 wt%.
  • the alloy is preferably Fe-free.
  • dispersion-forming elements have Mn + Fe + Si ⁇ 0.3% by weight.
  • alloys according to the invention were melted as reference alloy on a laboratory scale by casting into random billets.
  • the molten alloys have the following composition, wherein the alloy XL33 is the alloy according to the invention, while the alloy AA 2050 has been melted as a reference alloy: alloy Cu Li mg Mn Ti Zr Si Fe Ag XL33 3.78 0.90 0.35 0.11 0,052 0.112 0.02 0.02 0.404 AA 2050 3.72 0.94 0.31 0.38 0.40 0.092 0.04 0.063 0.491
  • the cast billets were homogenized, extruded and solution annealed as profiles and then stretched longitudinally by about 2-4%.
  • the hot aging was carried out at 153 ° C for 48 hours.
  • studies have been carried out to determine the yield strength R p0,2, the tensile strength R m, the elongation at break A 5 as well as the fracture toughness. The tests were carried out on the specimens in the same places.
  • a component made of this alloy is suitable as a component for use in the aerospace industry, especially for structural components, due to the properties described above.
  • components made of this alloy can also be made and used for other applications, especially if a low density should also play a role.

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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)
  • Conductive Materials (AREA)
  • Powder Metallurgy (AREA)
  • Manufacture Of Metal Powder And Suspensions Thereof (AREA)

Claims (9)

  1. Alliage Al-Cu-Mg-Li comportant
    3,7 à 3,9 % de poids de Cu,
    0,9 à 1,3 % de poids de Li,
    0,30 à 0,45 % de poids de Mg,
    0,10 à < 0,2 % de poids de Mn,
    0,2 à 0,45 % de poids d'Ag,
    0,09 à 0,13 % de poids de Zr,
    au max. 0,07 % de poids de Ti, le Ti étant présent sous forme de TiB2 ou de TiC,
    le reste, de l'Al ainsi que les inévitables impuretés.
  2. Alliage Al-Cu-Mg-Li selon la revendication 1 comportant 3,7 à 3,9 % de poids de Cu,
    0,95 à 1,2 % de poids de Li,
    0,35 à 0,45 % de poids de Mg,
    0,10 à 0,18 % de poids de Mn,
    0,38 à 0,43 % de poids d'Ag,
    0,09 à 0,13 % de poids de Zr,
    au max. 0,07 % de poids de Ti, le Ti étant présent sous forme de TiB2 ou de TiC,
    le reste, de l'Al ainsi que les inévitables impuretés.
  3. Alliage Al-Cu-Mg-Li selon la revendication 1 ou 2, caractérisé en ce que la teneur en Mn est située entre 0,10 et 0,15 % de poids.
  4. Alliage Al-Cu-Mg-Li selon l'une des revendications 1 à 3, caractérisé en ce que le total des éléments à l'origine de la dispersion Mn+Fe+Si représente < 0,3 % de poids.
  5. Alliage Al-Cu-Mg-Li selon l'une des revendications 1 à 4, caractérisé en ce que le rapport entre Cu/Mg est situé entre 8,22 et 12.
  6. Produit d'alliage Al-Cu-Mg-Li constitué d'une composition d'alliage selon l'une des revendications 1 à 5, caractérisé en ce que le produit a subi un vieillissement à chaud de telle manière que le produit d'alliage présente parallèlement à la fibre, une limite d'élasticité Rp0,2 de 0,2 % de plus de 620 MPa et une résistance en rupture à la traction Rm de plus de 630 MPa.
  7. Produit d'alliage Al-Cu-Mg-Li selon la revendication 6, caractérisé en ce que celui-ci présente, parallèlement à la fibre, un allongement à la rupture A5 d'au moins 9 %.
  8. Produit d'alliage Al-Cu-Mg-Li selon la revendication 6 ou 7, caractérisé en ce que la composition de l'alliage est sélectionnée de telle sorte que le produit fabriqué à partir de ce dernier présente une densité d'environ 2,70 g/cm3.
  9. Produit d'alliage Al-Cu-Mg-Li selon l'une des revendications 6 à 8, caractérisé en ce que le produit d'alliage est une pièce structurelle destiné à une application technique aéronautique et/ou aérospatiale.
EP15161219.9A 2015-03-27 2015-03-27 Alliage d'al-cu-mg-li et produit allié ainsi produit Active EP3072984B2 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP15161219.9A EP3072984B2 (fr) 2015-03-27 2015-03-27 Alliage d'al-cu-mg-li et produit allié ainsi produit
ES15161219T ES2642118T5 (es) 2015-03-27 2015-03-27 Aleación de Al-Cu-Mg-Li así como producto de aleación fabricado a partir de la misma

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP15161219.9A EP3072984B2 (fr) 2015-03-27 2015-03-27 Alliage d'al-cu-mg-li et produit allié ainsi produit

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EP3072984A1 EP3072984A1 (fr) 2016-09-28
EP3072984B1 true EP3072984B1 (fr) 2017-07-05
EP3072984B2 EP3072984B2 (fr) 2020-05-06

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Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN115125422B (zh) * 2022-06-09 2023-10-10 烟台南山学院 一种耐蚀高强韧Al-Li-Cu-Zr-Er合金板材及其制备方法

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2009036953A1 (fr) 2007-09-21 2009-03-26 Aleris Aluminum Koblenz Gmbh Produit en alliage ai-cu-li qui convient pour une application aérospatiale
US20090142222A1 (en) 2007-12-04 2009-06-04 Alcoa Inc. Aluminum-copper-lithium alloys
US20090180890A1 (en) 2006-04-29 2009-07-16 Oerlikon Leybold Vacuum Gmbh Rotors or stators of a turbomolecular pump
US20110030856A1 (en) 2009-06-25 2011-02-10 Alcan Rhenalu Casting process for aluminum alloys
US20110247730A1 (en) 2010-04-12 2011-10-13 Alcoa Inc. 2xxx series aluminum lithium alloys having low strength differential

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20090180890A1 (en) 2006-04-29 2009-07-16 Oerlikon Leybold Vacuum Gmbh Rotors or stators of a turbomolecular pump
WO2009036953A1 (fr) 2007-09-21 2009-03-26 Aleris Aluminum Koblenz Gmbh Produit en alliage ai-cu-li qui convient pour une application aérospatiale
US20090142222A1 (en) 2007-12-04 2009-06-04 Alcoa Inc. Aluminum-copper-lithium alloys
US20110030856A1 (en) 2009-06-25 2011-02-10 Alcan Rhenalu Casting process for aluminum alloys
US20110247730A1 (en) 2010-04-12 2011-10-13 Alcoa Inc. 2xxx series aluminum lithium alloys having low strength differential

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
TEAL SHEETS: "International Alloy Designations and Chemical Composition Limits for Wrought Aluminum and Wrought Aluminum Alloys", ALUMINUM ASSOCIATION, 2015, XP055460438

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EP3072984B2 (fr) 2020-05-06
EP3072984A1 (fr) 2016-09-28
ES2642118T5 (es) 2020-12-30
ES2642118T3 (es) 2017-11-15

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