EP3072985B2 - Alliage d' al-cu-mg-li exempt d'ag - Google Patents

Alliage d' al-cu-mg-li exempt d'ag Download PDF

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Publication number
EP3072985B2
EP3072985B2 EP15161222.3A EP15161222A EP3072985B2 EP 3072985 B2 EP3072985 B2 EP 3072985B2 EP 15161222 A EP15161222 A EP 15161222A EP 3072985 B2 EP3072985 B2 EP 3072985B2
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EP
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weight
alloy
max
free
product
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German (de)
English (en)
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EP3072985B1 (fr
EP3072985A1 (fr
Inventor
Joachim Becker
Gregor Terlinde
Thomas Witulski
Tina Schlingmann
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Otto Fuchs KG
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Otto Fuchs KG
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Application filed by Otto Fuchs KG filed Critical Otto Fuchs KG
Priority to ES15161222T priority Critical patent/ES2642730T5/es
Priority to EP15161222.3A priority patent/EP3072985B2/fr
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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 an Ag-free Al-Cu-Mg-Li alloy and an alloy product made therefrom.
  • Components made from high-performance aluminum alloys are in many cases an indispensable part of the construction of aircraft.
  • Components made of such high-performance aluminum alloys are used as structural components in the fuselage and wing, among other things. These parts are extruded and / or forged 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 fracture toughness (K 1C and stress corrosion cracking).
  • K 1C tensile strength
  • fracture toughness K 1C and stress corrosion cracking
  • the weight of components that are used in the aerospace industry plays a not insignificant role.
  • the specific weight (density) of the high-performance alloy used is therefore also relevant.
  • a conventionally used Al-Cu-Zn-Mg alloy that meets these requirements is the aluminum alloy AA 7449.
  • This previously known alloy has a composition of 1.4 - 2.1% by weight Cu, 1.8 - 2.7 wt% Mg, 7.5-8.7 wt% Zn, max. 0.2 wt% Mn, max. 0.12 wt% Si, max. 0.15% by weight Fe and max. 0.25 wt% Ti + Zr.
  • the components made from this alloy have a density of around 2.85 g / cm 3 .
  • Al-Cu-Zn-Mg alloy used that meets these requirements is the aluminum alloy AA 7050.
  • This previously known alloy has a composition of 2.0 - 2.6% by weight Cu, 1.9 - 2.6 wt% Mg, 5.7 - 6.7 wt% Zn, max. 0.10 wt% Mn, max. 0.12% by weight Si, max. 0.15% by weight Fe and max. 0.06 wt% Ti and 0.08-0.15 wt% Zr max. 0.06% by weight Ti.
  • the components made from this alloy have a density of approximately 2.83 g / cm 3 .
  • Al-Cu-Li alloys have been developed in order to meet this requirement, based on the alloy AA 7449 and AA7050, which have strength values comparable to those of the alloy AA 7449 and AA 7050, although the specific weight of components made from them is around 2.7 g / cm 3 .
  • the aluminum alloy AA 2050 is an example of such a high-performance alloy, which often replaces components that were previously made from the alloy AA 7449 in the aerospace 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 and an Mg content of 0.1 - 0, 5% by weight.
  • Zn usually contributes up to 0.25% by weight to the structure of the alloy.
  • silver is added to this alloy in a content of 0.2-0.7% by weight. This measure takes account of the prevailing opinion that silver, especially in lithium-containing Al-Cu alloys, is a necessary alloy component to achieve high strengths in components made from it.
  • 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 alloy 2050.
  • only components with a lower fracture toughness and stress corrosion cracking can be produced from this alloy compared to components that can be produced from the AA 2050 alloy.
  • the invention is based on the object of providing an Al-Cu-aluminum alloy with which high-strength and ultra-high-strength components can be produced, as well as a product made therefrom, particularly suitable for use as a component in an air or For aerospace engineering, to propose that not only meet the strength requirements, but are also more cost-effective in terms of materials compared to the components made from the AA 2050 alloy.
  • All alloy compositions that are described in the context of these explanations can contain unavoidable impurities of 0.05% by weight per element, the total amount of impurities should not exceed 0.15% by weight. However, it is preferred to keep the impurities as low as possible hold, so that these per element do not exceed a proportion of 0.02% by weight and a total amount of 0.08% by weight.
  • Components with extremely high-strength properties can only be produced within the narrow limits of the alloying elements used using an otherwise customary heat treatment process.
  • Artificial aging is preferably carried out so that maximum strengths are set in the component made from the alloy.
  • a conventional artificial aging process is considered to be one in which artificial aging is carried out between 145 ° C. and 170 ° C. with an adapted artificial aging time between 10 h and 90 h.
  • This alloy is characterized by particularly narrow bandwidths in the proportions of alloy elements. Apart from this, the alloy is Ag and Zn-free, even if a certain amount of Zn can be tolerated. It was precisely against the background of the prevailing opinion that the necessary strengths could only be achieved with a Li-containing Al-Cu alloy in the components made from it if silver is added in not inconsiderable proportions, surprisingly to find that one of the Alloy-made component not only meets the strength requirements set by the options of alloy AA 7449, but even has increased strength properties compared to this and also to alloy AA 2050.
  • the targeted narrow bandwidth of the contents of the alloy partners provides an Al-Cu-Mg-Li alloy from which high-strength components can be manufactured.
  • a component has high-strength properties if the yield strength R p0.2 is at least 600 MPa.
  • a component is assigned high-strength properties if the yield strength R p0.2 is at least 500 MPa.
  • the Cu content is below 3.5% by weight, the necessary strength is not achieved in combination with the other alloy elements. Copper contents of more than 4.3% by weight in the alloy are unable to further increase the strength of a component made from the alloy. Rather, it is to be expected that with higher Cu contents. Phases arise that could damage the fracture properties and the fatigue behavior.
  • Lithium is contained in the alloy to reduce the density (the specific weight).
  • the lithium content is adapted to the Cu and Mg contents of the alloy, namely in such a way that as much lithium as possible is incorporated into the alloy, but only enough so that it is brought into solution and no undesired Li-containing phases arise. Therefore, the Li content of the alloy is limited to the narrow range between 0.8 and 1.3 wt%.
  • Magnesium contributes to the desired properties of a component made from the alloy, but is only permitted in part so that no undesired phases (such as the S phases Al 2 CuMg) arise. Taking into account the other alloying elements, the Mg content should not exceed 0.8% by weight.
  • Titanium is added to the alloy to refine the cast structure and zircon to avoid / inhibit undesirable recrystallization during hot forming.
  • Components made from this alloy are cheaper because the alloy is Ag-free.
  • the cost of the material used to create the alloy can be up to 30% and more lower than the corresponding costs of an Ag-containing comparison alloy.
  • the specific weight of a component made from this alloy is approximately 2.7 g / cm 3 for a typical alloy composition and thus corresponds to the specific weight, for B. a component made from the alloy AA 2050.
  • the components made from this alloy have the same weight-reducing advantage as these components that, for. B. made of the alloy AA 2050 is awarded.
  • the strength properties are relatively uniform over the range of the alloyed elements.
  • Fe cannot be completely avoided as an accompanying element.
  • contents between 0.02-0.035% by weight are tolerable.
  • alloys according to the invention and comparative alloys were melted and cast into test bars on a laboratory scale by permanent mold casting.
  • the melted alloys have the following composition, the alloys XL21, XL29 being alloys according to the invention, while the other alloys have been melted as comparison alloys: alloy Cu Li Mg Mn Ti Zr Si Fe Ag Zn XL21 3.87 0.97 0.46 0.17 0.05 0.10 0.02 0.027 ⁇ 0.02 ⁇ 0.02 XL29 4.1 0.95 0.47 0.17 0.04 0.11 0.03 0.03 ⁇ 0.02 ⁇ 0.02 AA 2050 3.72 0.94 0.31 0.38 0.04 0.092 0.04 0.063 0.491 ⁇ 0.02 AA 2196 2.61 1.6 0.37 ⁇ 0.02 0.05 0.11 0.02 0.03 0.3 ⁇ 0.02 AA 7449 1.62 ⁇ 0.02 2.45 0.15 0.02 0.10 0.04 0.09 ⁇ 0.02 7.7 AA 7050 2.24 ⁇ 0.02 2.17 0.08 0.03 0.11 0.06 0.09 ⁇ 0.02 6.4
  • 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. At the same time, 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)
  • Extrusion Of Metal (AREA)
  • Sliding-Contact Bearings (AREA)

Claims (7)

  1. Alliage Al-Cu exempt d'Ag comportant
    3,5 à 4,3 % de poids de Cu,
    0,9 à 1,2 % de poids de Li,
    0,38 à 0,6 % de poids de Mg,
    0,14 à 0,22 % de poids de Mn,
    0,08 à 0,17 % de poids de Zr,
    0,03 à 0,07 % de poids de Ti, le Ti étant présent sous forme de TiB2 ou de TiC,
    max. 0,08 % de poids de Fe,
    max. 0,05 % de poids de Si,
    le reste, de l'Al ainsi que les inévitables impuretés pour un total de 0,15 % de poids maximum.
  2. Alliage Al-Cu exempt d'Ag comportant
    3,7 à 4,0 % de poids de Cu,
    0,9 à 1,2 % de poids de Li,
    0,43 à 0,52 % de poids de Mg,
    0,14 à 0,20 % de poids de Mn,
    0,09 à 0,11 % de poids de Zr,
    0,04 à 0,06 % de poids de Ti,
    max. 0,08 % de poids de Fe,
    max. 0,05 % de poids de Si,
    le reste, de l'Al ainsi que les inévitables impuretés pour un total de 0,15 % de poids maximum.
  3. Alliage Al-Cu exempt d'Ag selon l'une des revendications 1 ou 2, caractérisé en ce que l'alliage contient en plus au maximum 0,03 % de poids de Si et/ou au maximum 0,05 % de poids de Fe.
  4. Alliage Al-Cu exempt d'Ag selon l'une des revendications 1 à 3, caractérisé en ce que le rapport Cu/mg correspond à la formule suivante : 3,85 % de poids - 0,7 % de poids de Mg < Cu < 4,63 % de poids -0,7 % de poids de Mg.
  5. Alliage Al-Cu exempt d'Ag selon l'une des revendications 1 à 4, caractérisé en ce que la composition de l'alliage a été sélectionnée de telle sorte qu'un produit fabriqué à partir de ce dernier présente une densité de moins de 2,73 g/cm3, notamment de moins de 2,71 g/cm3, de préférence d'environ 2,70 g/cm3.
  6. Produit d'alliage Al-Cu-Mg-Li exempt d'Ag constitué d'une composition d'alliage selon l'une des revendications 1 à 4 et de préférence d'une densité selon la revendication 5, caractérisé en ce que le produit a été homogénéisé, moulé à chaud, recuit en solution, étiré, vieilli à chaud et ensuite étiré de telle manière que le produit d'alliage présente une limite d'élasticité Rp0,2 de plus de 600 MPa et une résistance à la traction Rm de plus de 640 MPa et un allongement à la rupture de plus de 7 %.
  7. Produit d'alliage selon la revendication 6, caractérisé en ce que le produit d'alliage est un produit prévu pour une application technique aéronautique et/ou aérospatiale.
EP15161222.3A 2015-03-27 2015-03-27 Alliage d' al-cu-mg-li exempt d'ag Active EP3072985B2 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
ES15161222T ES2642730T5 (es) 2015-03-27 2015-03-27 Aleación de Al-Cu-Mg-Li exenta de Ag
EP15161222.3A EP3072985B2 (fr) 2015-03-27 2015-03-27 Alliage d' al-cu-mg-li exempt d'ag

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP15161222.3A EP3072985B2 (fr) 2015-03-27 2015-03-27 Alliage d' al-cu-mg-li exempt d'ag

Publications (3)

Publication Number Publication Date
EP3072985A1 EP3072985A1 (fr) 2016-09-28
EP3072985B1 EP3072985B1 (fr) 2017-07-05
EP3072985B2 true EP3072985B2 (fr) 2020-08-26

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ID=52780887

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EP15161222.3A Active EP3072985B2 (fr) 2015-03-27 2015-03-27 Alliage d' al-cu-mg-li exempt d'ag

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ES (1) ES2642730T5 (fr)

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US11220729B2 (en) * 2016-05-20 2022-01-11 Ut-Battelle, Llc Aluminum alloy compositions and methods of making and using the same
CN106893911B (zh) * 2017-02-27 2018-05-15 广东省材料与加工研究所 一种高强耐热Al-Cu系铝合金及其制备方法
US11242587B2 (en) 2017-05-12 2022-02-08 Ut-Battelle, Llc Aluminum alloy compositions and methods of making and using the same
US11180839B2 (en) 2017-10-26 2021-11-23 Ut-Battelle, Llc Heat treatments for high temperature cast aluminum alloys

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1998033947A1 (fr) † 1997-01-31 1998-08-06 Reynolds Metals Company Procede servant a ameliorer la tenacite d'alliages d'aluminium et de lithium
US20090142222A1 (en) † 2007-12-04 2009-06-04 Alcoa Inc. Aluminum-copper-lithium alloys
US20100183474A1 (en) † 2009-01-22 2010-07-22 Alcoa Inc. aluminum-copper alloys containing vanadium
US20110030856A1 (en) † 2009-06-25 2011-02-10 Alcan Rhenalu Casting process for aluminum alloys
US20120225271A1 (en) † 2011-02-17 2012-09-06 Alcoa Inc. 2xxx series aluminum lithium alloys
US20140050936A1 (en) † 2012-08-17 2014-02-20 Alcoa Inc. 2xxx series aluminum lithium alloys
WO2014167191A1 (fr) † 2013-04-12 2014-10-16 Constellium France Procédé de transformation de tôles en alliage al-cu-li améliorant la formabilité et la résistance à la corrosion

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1998033947A1 (fr) † 1997-01-31 1998-08-06 Reynolds Metals Company Procede servant a ameliorer la tenacite d'alliages d'aluminium et de lithium
US20090142222A1 (en) † 2007-12-04 2009-06-04 Alcoa Inc. Aluminum-copper-lithium alloys
US20100183474A1 (en) † 2009-01-22 2010-07-22 Alcoa Inc. aluminum-copper alloys containing vanadium
US20110030856A1 (en) † 2009-06-25 2011-02-10 Alcan Rhenalu Casting process for aluminum alloys
US20120225271A1 (en) † 2011-02-17 2012-09-06 Alcoa Inc. 2xxx series aluminum lithium alloys
US20140050936A1 (en) † 2012-08-17 2014-02-20 Alcoa Inc. 2xxx series aluminum lithium alloys
WO2014167191A1 (fr) † 2013-04-12 2014-10-16 Constellium France Procédé de transformation de tôles en alliage al-cu-li améliorant la formabilité et la résistance à la corrosion

Also Published As

Publication number Publication date
ES2642730T3 (es) 2017-11-17
ES2642730T5 (es) 2021-06-09
EP3072985B1 (fr) 2017-07-05
EP3072985A1 (fr) 2016-09-28

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