EP3072984B2 - Al-cu-mg-li-legierung sowie daraus hergestelltes legierungsprodukt - Google Patents

Al-cu-mg-li-legierung sowie daraus hergestelltes legierungsprodukt Download PDF

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Publication number
EP3072984B2
EP3072984B2 EP15161219.9A EP15161219A EP3072984B2 EP 3072984 B2 EP3072984 B2 EP 3072984B2 EP 15161219 A EP15161219 A EP 15161219A EP 3072984 B2 EP3072984 B2 EP 3072984B2
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Prior art keywords
alloy
weight
content
strength
product
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German (de)
English (en)
French (fr)
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EP3072984A1 (de
EP3072984B1 (de
Inventor
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/de
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 made therefrom.
  • Components made of high-performance aluminum alloys are in many cases an indispensable component in the construction of aircraft.
  • Components made 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 required combination of static and dynamic strength and have certain requirements with regard to tensile strength, yield strength, elongation at break and crack toughness (K 1C and stress corrosion cracking).
  • K 1C tensile strength
  • yield strength elongation at break and crack toughness
  • stress corrosion cracking the weight of components that are used for the aerospace industry plays a significant role.
  • the specific weight (density) of the high-performance alloy used is also relevant.
  • Al-Cu-Mg-Li alloy that has been launched on the market and meets 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 Mg, 0.8-1.2% by weight Li, 0.25-0.6% by weight Ag, max. 0.25% by weight Zn, max. 0.25% by weight Mn, max. 0.12% by weight Si, max. 0.15% by weight 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 approximately 2.7 g / cm 3 .
  • the aluminum alloy AA 2050 is an example of such a high-performance alloy, which in the meantime replaces the alloy 2195, from which components were often made previously, in the aviation sector.
  • the alloy AA 2050 has a Cu content of 3.2-3.9% by weight, a Li content of 0.7-1.3% by weight, a Mn content of 0.2-0, 8% by weight and a Mg content of 0.1-0.5% by weight.
  • Zn is usually involved in the build-up of the alloy with up to 0.25% by weight.
  • silver is alloyed with this alloy, in a content of 0.2 - 0.7% by weight.
  • This measure takes account of the prevailing opinion that silver, particularly in the case of lithium-containing Al-Cu alloys, is a necessary alloy component in order to achieve high strengths in components made therefrom.
  • An alloy similar to the AA 2050 alloy with an even higher Li content 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 2050 alloy.
  • only lower strength components can be made from this alloy compared to components that can be made from AA 2050 alloy.
  • Previously known Ag-containing high-performance aluminum alloys such as the alloy AA 2050 contain Mn as the necessary alloying element.
  • the alloy AA 2050 requires a Mn content of 0.2-0.5% by weight.
  • Mn in a recrystallization inhibitor Mainly because of the latter property, Mn is an element necessary to achieve the desired strength properties.
  • Mn is an element necessary to achieve the desired strength properties.
  • Mn content is not so high, so that no coarse primary solidifications form in the microstructure, which in particular negatively influence the fatigue behavior. In this respect, a certain maximum may not be exceeded.
  • such a high-performance aluminum alloy must contain enough Mn to fulfill the desired property as a recrystallization inhibitor.
  • the previously known alloys with Mn contents meet these requirements, for example in the AA 2050 between 0.2 and 0.5% by weight.
  • Mn content of the previously known high-performance aluminum alloys containing Ag and Li have a relatively wide range. It depends to a large extent on the participation of the other alloy elements Cu, Li, Mg, Mn, Ti, Zr, Si, Fe and Ag whether an alloy from which components can actually be melted with a selected Mn content from the specified range can be melted be able to meet the requirements of strength, fatigue and toughness.
  • the invention is based on the object of proposing an Ag and Li-containing Al-Cu alloy which is not only simplified in terms of its structure in comparison with previously known alloys, but which also ensures that that components made therefrom within the specified spectrum of the alloying elements, after appropriate heat treatment, meet the desired combination of mechanical properties.
  • All alloy compositions described in the context of this embodiment may contain unavoidable impurities per element of 0.05% by weight, the total amount of impurities not exceeding 0.15% by weight. However, it is preferred to keep the contamination as low as possible and not to exceed 0.03% by weight per element for a total amount of 0.08% by weight.
  • This Ag and Li-containing high-performance aluminum alloy has a particularly narrow range of its alloying elements. This applies in particular to the alloy element Mn, which is involved not only in a very narrow spectrum, but also with astonishingly small proportions in the structure of the alloy and fulfills the functions intended for this element. In this context it should be emphasized that this alloy is Zn-free. It was surprising to find that this alloy with an Mn content that can even be only half as large as that required in the AA 2050 alloy is sufficient to effectively prevent recrystallization. In addition, within the stated range of 0.01 wt.% To ⁇ 0.2 wt. Studies have shown that with this special alloy composition, unwanted, plate-shaped Al 6 Mn phases do not form, or at most only very subordinately.
  • the Cu content is less than 3.7% by weight, the required strength is not achieved in combination with the other alloy elements. Copper contents in excess of 3.9% by weight in the alloy cannot further increase the strength of a component made from the alloy. Rather, it can be expected that at higher Cu contents, property-damaging phases will form.
  • Lithium is contained in the alloy to reduce the density (specific weight).
  • the lithium content is adapted to the Cu and Mg contents of the alloy in such a way that as much lithium as possible is built into the alloy, but only so much that it can be brought into solution and does not contain any unwanted Li Phases arise. Therefore, the Li content of the alloy is limited to the narrow range between 0.9 and 1.3% by weight.
  • Magnesium contributes to the desired properties of a component made from the alloy, but is only permitted to a certain extent so that no undesired phases (such as an S-phase Al 2 CuMg) form. Taking into account the other alloying elements, the Mg content should not exceed 0.45% by weight.
  • Titan acts as a grain refiner in the cast structure and zircon as a dispersoid former and thus helps to inhibit recrystallization.
  • an Mn content between 0.10 and 0.18% by weight is sufficient to effectively prevent recrystallization. This is attributed to the special and targeted selection of the proportion and bandwidth of Mn as well as the very narrowly limited Mn content. This ensures that the desired combination of mechanical properties for a component made from the alloy can be set within these limits. If the Mn content exceeds 0.18% by weight, taking into account the other alloying elements, this can lead to coarser primary solidifications in the microstructure, which in turn was not to be expected according to the prevailing opinion. Finally, a Mn content of 0.2-0.8% by weight is proposed in the alloy AA 2050.
  • the Mn content of the claimed alloy is therefore limited to a maximum proportion of 0.18% by weight. If no primary solidifications in the microstructure are to be accepted, the Mn content is limited to a range of 0.10-0.15% by weight. Particularly good results can be achieved if the Mn content is between 0.10 and 0.12% by weight.
  • the Ag content is included in this alloy to increase strength.
  • the Ag content is selected to be somewhat lower or somewhat more within the claimed limit between 0.2 and 0.45% by weight.
  • the Ag content should be more than 0.35% by weight in order to achieve a component which should meet the requirements for a high-strength component.
  • a preferred contribution of the Ag portion to the structure of the alloy extends from 0.38 to 0.43% by weight.
  • the alloy is preferably Fe-free.
  • the alloy has the dispersion-forming elements Mn + Fe + Si ⁇ 0.3% by weight.
  • alloys according to the invention were melted on a laboratory scale by casting molds into test bars.
  • the molten alloys have the following composition, the alloy XL33 being the alloy according to the invention, while the alloy AA 2050 has been melted as a comparison 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 ingots were homogenized, extruded and solution-annealed as profiles and then stretched lengthways, by about 2-4%.
  • the hot aging was carried out at 153 ° C. for 48 hours.
  • tests were carried out to determine the proof stress R p0.2 , the tensile strength R m , the elongation at break A 5 and the fracture toughness.
  • the examinations were carried out on the sample pieces at the same locations.
  • results are of interest insofar as they demonstrate the insensitivity of the alloy according to the invention and thus the effectiveness of the special Mn content.
  • the results of these tests correspond to the strength values for the alloy according to the invention, which were also determined for the sample, the hot aging of which took place at 153 ° C.
  • a component made from this alloy is suitable due to the properties described above as a component for use in the aerospace industry, especially for structural components. Nevertheless, components made of this alloy can also be manufactured 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)
  • Manufacture Of Metal Powder And Suspensions Thereof (AREA)
  • Powder Metallurgy (AREA)
EP15161219.9A 2015-03-27 2015-03-27 Al-cu-mg-li-legierung sowie daraus hergestelltes legierungsprodukt Active EP3072984B2 (de)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP15161219.9A EP3072984B2 (de) 2015-03-27 2015-03-27 Al-cu-mg-li-legierung sowie daraus hergestelltes legierungsprodukt
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 (de) 2015-03-27 2015-03-27 Al-cu-mg-li-legierung sowie daraus hergestelltes legierungsprodukt

Publications (3)

Publication Number Publication Date
EP3072984A1 EP3072984A1 (de) 2016-09-28
EP3072984B1 EP3072984B1 (de) 2017-07-05
EP3072984B2 true EP3072984B2 (de) 2020-05-06

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EP15161219.9A Active EP3072984B2 (de) 2015-03-27 2015-03-27 Al-cu-mg-li-legierung sowie daraus hergestelltes legierungsprodukt

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EP (1) EP3072984B2 (es)
ES (1) ES2642118T5 (es)

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 (en) † 2007-09-21 2009-03-26 Aleris Aluminum Koblenz Gmbh Al-cu-li alloy product suitable for aerospace application
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 (en) † 2007-09-21 2009-03-26 Aleris Aluminum Koblenz Gmbh Al-cu-li alloy product suitable for aerospace application
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 †

Also Published As

Publication number Publication date
ES2642118T3 (es) 2017-11-15
EP3072984A1 (de) 2016-09-28
EP3072984B1 (de) 2017-07-05
ES2642118T5 (es) 2020-12-30

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