EP3072984B2 - Al-cu-mg-li alloy and alloy product produced from same - Google Patents

Al-cu-mg-li alloy and alloy product produced from same Download PDF

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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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alloy
weight
content
strength
product
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EP3072984A1 (en
EP3072984B1 (en
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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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    • 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.

Description

Die Erfindung betrifft eine Al-Cu-Mg-Li-Legierung sowie ein daraus hergestelltes Legierungsprodukt.The invention relates to an Al-Cu-Mg-Li alloy and an alloy product made therefrom.

Bauteile aus Hochleistungsaluminiumlegierungen sind in vielen Fällen unverzichtbarer Bestandteil bei der Konstruktion von Flugzeugen. Bauteile aus derartigen Hochleistungsaluminiumlegierungen werden unter anderem im Rumpf und im Flügel als Strukturbauteile eingesetzt. Bei diesen Teilen handelt es sich um geschmiedete, stranggepresste Teile. Diese müssen der notwendigen Kombination aus statischer und dynamischer Festigkeit genügen und bestimmte Anforderungen in Bezug auf Zugfestigkeit, Dehngrenze, Bruchdehnung und Risszähigkeit (K1C und Spannungsrisskorrosion) aufweisen. Zudem spielt das Gewicht bei Bauteilen, die für die Luft- und Raumfahrtindustrie eingesetzt werden, eine nicht unbedeutende Rolle. Somit ist auch das spezifische Gewicht (die Dichte) der verwendeten Hochleistungslegierung von Relevanz.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). In addition, 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.

Eine am Markt eingeführte Al-Cu-Mg-Li-Legierung, die diesen Anforderungen genügt, ist die Aluminium-Legierung AA 2195. Diese Legierung hat eine Zusammensetzung von 3,7 - 4,3 Gew.-% Cu, 0,25 - 0,8 Gew.-% Mg, 0,8 - 1,2 Gew.% Li, 0,25 - 0,6 Gew.% Ag, max. 0,25 Gew.-% Zn, max. 0,25 Gew.-% Mn, max. 0,12 Gew.-% Si, max. 0,15 Gew.-% Fe, max. 0,1 Gew.-% Ti und 0,08 - 0,16 Gew.% Zr. Die aus dieser Legierung hergestellten Bauteile haben eine Dichte von etwa 2,7 g/cm3.An 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 .

Mit zunehmender Größe der Flugzeuge geht das Bestreben einher, in Ergänzung zu einer hohen Festigkeit die Bauteile mit einem besseren damage tolerant Verhalten zu versehen. Entwickelt worden sind, um dieser Anforderung zu genügen, ausgehend von der Legierung AA 2195, Al-Cu-Mg-Li-Legierungen mit verbesserter Zähigkeit und Schwingfestigkeit. Die Aluminiumlegierung AA 2050 ist ein Beispiel für eine solche Hochleistungslegierung, die die Legierung 2195, aus der zuvor oftmals Bauteile gefertigt wurden, im Luftfahrtbereich zwischenzeitlich ersetzt. Die Legierung AA 2050 weist einen Cu-Anteil von 3,2 - 3,9 Gew.-%, einen Li-Gehalt von 0,7 - 1,3 Gew.-%, einen Mn-Gehalt von 0,2 - 0,8 Gew.-% und einen Mg-Gehalt von 0,1 - 0,5 Gew.-% auf. Zn ist üblicherweise am Aufbau der Legierung mit bis zu 0,25 Gew.-% beteiligt. Um die notwendigen Festigkeitseigenschaften zu erzielen, wird bei dieser Legierung Silber zulegiert, und zwar in Gehalten von 0,2 - 0,7 Gew.-%. Durch diese Maßnahme wird der herrschenden Meinung Rechenschaft getragen, dass Silber, gerade bei Lithium-haltigen Al-Cu-Legierungen zum Erzielen hoher Festigkeiten daraus hergestellter Bauteile notwendiger Legierungsbestandteil ist.With the increasing size of the aircraft, there is a desire to provide the components with better damage-tolerant behavior in addition to their high strength. To meet this requirement, we have developed AA 2195, Al-Cu-Mg-Li alloys with improved toughness and vibration resistance. 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. In order to achieve the necessary strength properties, 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.

Eine der Legierung AA 2050 ähnliche Legierung mit einem noch höheren Li-Anteil ist die Legierung AA 2196 mit einem Li-Anteil von 1,4 - 2.1 Gew.-%. Der Cu-Anteil dieser Legierung ist gegenüber dem Cu-Anteil in der Legierung 2050 geringfügig reduziert. Aus dieser Legierung können jedoch nur Bauteile mit einer geringeren Festigkeit hergestellt werden, verglichen mit Bauteilen, die aus der Legierung AA 2050 hergestellt werden können.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. However, only lower strength components can be made from this alloy compared to components that can be made from AA 2050 alloy.

Vorbekannte Ag-haltige Hochleistungsaluminiumlegierungen wie die Legierung AA 2050 beinhalten als notwendiges Legierungselement Mn. Bei der Legierung AA 2050 ist ein Mn-Gehalt von 0,2 - 0,5 Gew.-% erforderlich. Mn in ein Rekristallisationshemmer. Vor allem aufgrund letzterer Eigenschaft ist Mn ein für die Erzielung der gewünschten Festigkeitseigenschaften notwendiges Element. Dieses entspricht auch der herrschenden Meinung, dass bei Ag-haltigen Al-Cu-Mg-Li-Legierungen zumindest 0,2 Gew.-% Mn, wenn nicht deutlich mehr am Aufbau der Legierung beteiligt sein muss. Allerdings ist darauf zu achten, dass der Mn-Gehalt nicht so hoch ist, damit sich keine groben Primärerstarrungen im Mikrogefüge ausbilden, die insbesondere das Ermüdungsverhalten negativ beeinflussen. Insofern darf ein gewisses Maximum nicht überschritten werden. Auf der anderen Seite muss eine solche Hochleistungsaluminiumlegierung genügend Mn enthalten, um die gewünschte Eigenschaft als Rekristallisationshemmer erfüllen zu können. Diesen Anforderungen genügen die vorbekannten Legierungen mit Mn-Gehalten, wie beispielsweise bei der AA 2050 zwischen 0,2 und 0,5 Gew.-%.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. This also corresponds to the prevailing opinion that, in the case of Ag-containing Al-Cu-Mg-Li alloys, at least 0.2% by weight Mn, if not significantly more, must be involved in the structure of the alloy. However, it must be ensured that the 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. On the other hand, 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.

Die zu den vorbekannten Hochleistungsaluminiumlegierungen, die Ag und Li enthalten, gemachten Angaben zu dem Mn-Gehalt weisen eine relativ große Spanne auf. Es hängt maßgeblich von der Beteiligung der anderen Legierungselemente Cu, Li, Mg, Mn, Ti, Zr, Si, Fe und Ag ab, ob mit einem ausgewählten Mn-Gehalt aus dem angegebenen Bereich tatsächlich eine Legierung erschmolzen werden kann, aus der Bauteile hergestellt werden können, die den gestellten Festigkeitsanforderungen sowie der Ermüdung und Zähigkeit genügen.The statements made regarding the 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.

Der Erfindung liegt ausgehend von dem vorstehend gewürdigten Stand der Technik die Aufgabe zugrunde, eine Ag- und Li-haltige Al-Cu-Legierung vorzuschlagen, die nicht nur hinsichtlich ihres Aufbaus im Vergleich zu vorbekannten Legierungen vereinfacht ist, sondern bei der auch gewährleistet ist, dass innerhalb des angegebenen Spektrums der Legierungselemente daraus hergestellte Bauteile nach entsprechender Wärmebehandlung der gewünschten Kombination mechanischer Eigenschaften genügen.On the basis of the prior art acknowledged above, 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.

Gelöst wird diese Aufgabe durch eine Al-Cu-Mg-Li-Legierung mit den Merkmalen des Anspruchs 1.This object is achieved by an Al-Cu-Mg-Li alloy with the features of claim 1.

Bei allen Legierungszusammensetzungen, die im Rahmen dieser Ausführung beschrieben sind, konnen unvermeidbare Verunreinigungen je Element von 0,05 Gew.-% enthalten sein, wobei die Gesamtmenge an Verunreinigungen 0,15 Gew.-% nicht überschreiten sollte. Es ist jedoch bevorzugt, die Verunreinigung möglichst gering zu halten und einen Anteil von 0,03 Gew.-% je Element bei einer Gesamtmenge von 0,08 Gew.-% nicht zu überschreiten.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.

Diese Ag- und Li-haltige Hochleistungsaluminiumlegierung weist eine besonders enge Bandbreite seiner Legierungselemente auf. Dieses gilt in besonderem Maße für das Legierungselement Mn, welches nicht nur in einem sehr engen Spektrum, sondern auch mit erstaunlich geringen Anteilen am Aufbau der Legierung beteiligt ist und den diesem Element zugedachten Funktionen erfüllt. Herauszustellen ist in diesem Zusammenhang, dass diese Legierung Zn-frei ist. Es war überraschend festzustellen, dass bei dieser Legierung mit einem Mn-Gehalt, der sogar nur halb so groß sein kann wie der in der Legierung AA 2050 benötigte, ausreicht, um eine Rekristallisation wirksam zu verhindern. Zudem ist innerhalb der angegebenen Spanne von 0,01 Gew.-% bis < 0,2 Gew.-% Mn Sorge dafür getragen, dass keine oder nur in einem nicht nennenswerten Maße Primärphasen entstehen, die die Ermüdung und Zähigkeit verschlechtem würden. Untersuchungen haben gezeigt, dass sich bei dieser besonderen Legierungszusammensetzung ungewollte, plattenförmige Al6Mn-Phasen nicht oder allenfalls nur sehr untergeordnet bilden. In aller Regel ist Fe als Begleitelement nicht auszuschließen. Die sich mit Fe bildenden Phasen Al7Cu2Fe beeinträchtigen aufgrund ihrerkompakten Morphologie die mechanischen Eigenschaften eines aus dieser Legierung hergestellten Bauteils hingegen deutlich weniger. Insofern war es überraschend festzustellen, dass bei eine Al-Cu-Mg-Li-Legierung mit der vorbeschriebenen Zusammensetzung und ihrem besonders geringen Mn-Gehalt davon auszugehen ist, dass Bauteile mit der gewünschten Kombination aus Eigenschaften, die nicht nur hochfest, sondern auch zäh und ermüdungsbeständig sind, hergestellt werden konnten, die sogar höchstfesten Anforderungen genügen. Zur Definition hochfest und höchstfest: Ein Bauteil weist höchstfeste Eigenschaften auf, wenn die Dehngrenze Rp0,2 zumindest 600 MPa beträgt. Einem Bauteil werden hochfeste Eigenschaften zugesprochen, wenn die Dehngrenze Rp0,2 zumindest 500 MPa beträgt.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. As a rule, Fe cannot be excluded as an accompanying element. The Al 7 Cu 2 Fe phases that form with Fe, on the other hand, affect the mechanical properties of a component made from this alloy significantly less due to their compact morphology. In this respect, it was surprising to find that an Al-Cu-Mg-Li alloy with the above-described composition and its particularly low Mn content can be assumed to have components with the desired combination of properties that are not only high-strength but also tough and are fatigue-resistant, could be produced, which even meet the highest strength requirements. For the definition of high strength and high strength: A component has high strength 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.

Liegt der Cu-Anteil unter 3,7 Gew.-% stellt sich in Kombination mit den anderen Legierungselementen nicht die notwendige Festigkeit ein. Kupfergehalte über 3,9 Gew.-% in der Legierung vermögen die Festigkeit eines aus der Legierung hergestellten Bauteils nicht weiter zu erhöhen. Vielmehr ist damit zu rechnen, dass sich bei höheren Cu-Gehalten eigenschaftsschädigende Phasen bilden.If 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 ist zur Reduzierung der Dichte (des spezifischen Gewichtes) in der Legierung enthalten. Der Lithium-Gehalt ist an die Cu- und Mg-Gehalte der Legierung angepasst, und zwar dergestalt, dass zwar möglichst viel Lithium in die Legierung eingebaut wird, jedoch nur so viel, dass dieses in Lösung gebracht werden kann und keine unerwünschten Li-haltigen Phasen entstehen. Daher ist der Li-Gehalt der Legierung auf den engen Bereich zwischen 0,9 und 1,3 Gew.-% begrenzt.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 trägt zu den gewünschten Eigenschaften eines aus der Legierung hergestellten Bauteils bei, ist jedoch nur mit einem Anteil zugelassen, damit sich keine unerwünschten Phasen (wie z.B. eine S-Phase Al2CuMg) ausbilden. Unter Berücksichtigung der weiteren Legierungselemente soll der Mg-Anteil 0,45 Gew.-% nicht überschreiten.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 wirkt als Kornfeiner im Gussgefüge und Zirkon als Dispersoidbildner und trägt somit zur Hemmung der Rekristallisation bei.Titan acts as a grain refiner in the cast structure and zircon as a dispersoid former and thus helps to inhibit recrystallization.

Überraschend hat sich gezeigt, dass unter Berücksichtigung der anderen Legierungselemente und deren Gehalte ein Mn-Gehalt zwischen 0,10 und 0,18 Gew.-% ausreicht, um wirksam eine Rekristallisation zu verhindern. Zugeschrieben wird dieses der speziellen und gezielten Auswahl des Anteils und der Bandbreite von Mn als auch der sehr eng begrenzte Mn-Gehalt. Dies gewährleistet, dass sich innerhalb dieser Grenzen durchweg die gewünschten Kombination an mechanischen Eigenschaften bei einem aus der Legierung hergestellten Bauteil einstellen lassen. Überschreitet der Mn-Gehalt 0,18 Gew.-% kann dieses unter Berücksichtigung der anderen Legierungselemente bereits zu gröberen Primärerstarrungen im Mikrogefüge führen, was wiederum der herrschenden Meinung entsprechend nicht zu erwarten war. Schließlich wird in der Legierung AA 2050 ein Mn-Gehalt von 0,2 - 0,8 Gew.-% vorgeschlagen. Daher ist der Mn-Gehalt der beanspruchten Legierung auf einen Maximalanteil von 0,18 Gew.-% begrenzt. Sollen keinerlei Primärerstarrungen im Mikrogefüge in Kauf genommen werden, wird der Mn-Gehalt auf eine Spanne von 0,10 - 0,15 Gew.-% nach oben hin begrenzt. Besonders gute Ergebnisse lassen sich erzielen, wenn der Mn-Gehalt zwischen 0,10 und 0,12 Gew.-% liegt.It has surprisingly been found that, taking into account the other alloy elements and their contents, 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.

Ag ist zur Erhöhung der Festigkeit in dieser Legierung enthalten. In Abhängigkeit von der in dem Bauteil einzustellenden gewünschten Festigkeit wird der Ag-Gehalt etwas geringer oder etwas mehr innerhalb der beanspruchten Grenze zwischen 0,2 und 0,45 Gew.-% gewählt. Zur Erzielung eines Bauteiles, welches den Anforderungen an ein höchstfestes Bauteil genügen soll, sollte der Ag-Gehalt mehr als 0,35 Gew.-% betragen. Eine bevorzugte Beteiligung des Ag-Anteils am Aufbau der Legierung erstreckt sich von 0,38 - 0,43 Gew.-%.Ag is included in this alloy to increase strength. Depending on the desired strength to be set in the component, 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.

Bemerkenswert ist auch, dass die Legierung vorzugsweise Fe-frei ist.It is also noteworthy that the alloy is preferably Fe-free.

Erfindungsgemäß weist die Legierung die dispersionsbildenden Elemente Mn+Fe+Si < 0,3 Gew.-% auf.According to the invention, the alloy has the dispersion-forming elements Mn + Fe + Si <0.3% by weight.

Es hat sich gezeigt, dass ein Cu/Mg-Verhältnis zwischen 8,22 und 12 besonders zweckmäßig ist, um die gewünschten Legierungseigenschaften zu erhalten.It has been shown that a Cu / Mg ratio between 8.22 and 12 is particularly expedient in order to obtain the desired alloy properties.

Für Untersuchungen der Legierungszusammensetzung und der sich einstellenden Kombination der gewünschten Eigenschaften von daraus hergestellten Bauteilen wurden erfindungsgemäße Legierungen sowie solche gemäß AA 2050 als Vergleichslegierung erschmolzen im Labormaßstab durch Kokillenguss zu Versuchsbarren gegossen.For investigations of the alloy composition and the combination of the desired properties of components produced therefrom, alloys according to the invention and those in accordance with AA 2050 as a comparison alloy were melted on a laboratory scale by casting molds into test bars.

Die erschmolzenen Legierungen haben folgende Zusammensetzung, wobei die Legierung XL33 die erfindungsgemäße Legierung ist, während die Legierung AA 2050 als Vergleichslegierung erschmolzen worden ist: Legierung 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 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

Die gegossenen Barren wurden homogenisiert, stranggepresst und als Profile lösungsgeglüht und anschließend in Längsrichtung gereckt, und zwar um etwa 2 - 4 %. Die Warmauslagerung wurde für 48 Stunden bei 153 °C durchgeführt. Nachfolgend sind Untersuchungen durchgeführt worden, um die Dehngrenze R p0,2 , die Zugfestigkeit Rm , die Bruchdehnung A 5 sowie die Risszähigkeit zu ermitteln. Die Untersuchungen sind an den Probenstücken an jeweils gleichen Stellen vorgenommen worden. Die Untersuchungen ergaben folgende Ergebnisse: Probe Dichte [g/cm3] Rp0,2 [MPa] Rm [MPa] A5 [%] K1C [MPa√m] XL33 L 2,7 653 668 9,8 L-T 37,3 T-L 25,9 AA 2050 L 2,7 615 638 11,2 L-T 42,1 T-L 31,6 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. In the following, 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. The investigations showed the following results: sample Density [g / cm 3 ] R p0.2 [MPa] Rm [MPa] A 5 [%] K 1 C [MPa√m] XL33 L 2.7 653 668 9.8 LT 37.3 TL 25.9 AA 2050 L 2.7 615 638 11.2 LT 42.1 TL 31.6

Parallel zu den vorbeschriebenen Probenstücken wurden solche hergestellt, deren Warmauslagerung für 48 Stunden bei etwa 160° C durchgeführt worden ist. Die Ergebnisse sind insofern von Interesse, da diese die Unempfindlichkeit der erfindungsgemäßen Legierung und somit die Wirksamkeit des speziellen Mn-Gehaltes belegen. Die Ergebnisse dieser Untersuchungen entsprechen bei der erfindungsgemäßen Legierung den Festigkeitswerten, die auch zu der Probe ermittelt worden sind, deren Warmauslagerung bei 153° C stattgefunden hat. Die Festigkeitswerte der Proben mit einer Warmauslagerung über 48 Stunden bei 160 °C sind nachfolgend wiedergegeben: Probe Dichte [g/cm3] Rp0,2 [MPa] Rm [MPa] A5 [%] K1C [MPa√m] XL33 L 2,7 642 663 9,7 L-T 36,9 T-L 25,2 AA 2050 L 2,7 597 629 9,5 L-T 41,1 T-L 30,5 In parallel to the previously described specimens, those were produced, which were aged for 48 hours at about 160 ° C. The 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. The strength values of the samples with hot aging for 48 hours at 160 ° C are shown below: sample Density [g / cm 3 ] R p0.2 [MPa] R m [MPa] A 5 [%] K 1 C [MPa√m] XL33 L 2.7 642 663 9.7 LT 36.9 TL 25.2 AA 2050 L 2.7 597 629 9.5 LT 41.1 TL 30.5

Die vorstehenden Untersuchungsergebnisse machen deutlich, dass Bauteile, die aus der erfindungsgemäßen Legierung hergestellt sind, sogar höchstfesten Ansprüchen genügen, die auch besser sind als die Festigkeitswerte, die an der Vergleichsprobe aus der Legierung AA 2050 ermittelt wurden. Zugeschrieben wird diese Steigerung in den Festigkeitswerten dem speziellen, gegenüber vorbekannten Legierungen sehr geringen Mn-Anteil. Die Festigkeitswerte zeigen zudem, dass auch bei derart niedrigen Mn-Gehalten in der speziellen Zusammensetzung der beanspruchten Legierung in Bezug auf die übrigen Legierungselemente Rekristallisationen wirksam gehemmt sind.The above test results make it clear that components which are produced from the alloy according to the invention even meet the highest strength requirements, which are also better than the strength values which were determined on the comparative sample from the alloy AA 2050. This increase in strength values is attributed to the special Mn content, which is very low compared to previously known alloys. The strength values also show that recrystallization is effectively inhibited in relation to the other alloy elements even with such low Mn contents in the special composition of the claimed alloy.

Die vorstehenden mechanischen Eigenschaften konnten anhand etlicher Paralleluntersuchungen mit Variationen in der erfindungsgemäßen Legierungszusammensetzung im Rahmen der durch den Anspruch 1 gesetzten Grenzen bestätigt werden.

  • Figur 1 zeigt ein Gefügebild einer Probe aus der erfindungsgemäßen Legierung mit einem Cu-Gehalt von 3,3 Gew.-% und einem Mn-Gehalt von 0,11 Gew.-%. Bei den in Figur 1 erkennbaren Phasen handelt es sich ausschließlich um Al7Cu2Fe-Phasen.
  • Figur 2 zeigt ein Gefügebild einer Vergleichsprobe mit einer Legierungszusammensetzung entsprechend AA 2050 (s. Figur 2). Diese Legierung weist einen Cu-Gehalt von 3,7 Gew.-% und einen Mn-Gehalt von 0,37 Gew.-% auf. Das Gefügebild zeigt deutlich, dass in dieser Legierung neben den Al7Cu2Fe-Phasen die aufgrund ihrer Morphologie unerwünschten Al6Mn-Phasen vorhanden sind. Diese sind, wie in Figur 2 erkennbar, als lagig in der untersuchten Probe angeordnet, welche lagige Anordnung sich in der Al6Mn-Partikel-Zeile zeigt.
The above mechanical properties could be confirmed on the basis of a number of parallel investigations with variations in the alloy composition according to the invention within the limits set by claim 1.
  • Figure 1 shows a micrograph of a sample made of the alloy according to the invention with a Cu content of 3.3% by weight and a Mn content of 0.11% by weight. In the Figure 1 recognizable phases are exclusively Al 7 Cu 2 Fe phases.
  • Figure 2 shows a micrograph of a comparative sample with an alloy composition corresponding to AA 2050 (s. Figure 2 ). This alloy has a Cu content of 3.7% by weight and a Mn content of 0.37% by weight. The microstructure clearly shows that in addition to the Al 7 Cu 2 Fe phases, this alloy also contains the Al 6 Mn phases which are undesirable due to their morphology. These are as in Figure 2 recognizable as arranged in layers in the examined sample, which layer arrangement is shown in the Al 6 Mn particle line.

Ein aus dieser Legierung hergestelltes Bauteil eignet sich aufgrund der vorbeschriebenen Eigenschaften als Bauteil zur Verwendung in der Luft- und Raumfahrtindustrie, vor allem für Strukturbauteile. Gleichwohl können Bauteile aus dieser Legierung auch für andere Anwendungen hergestellt und eingesetzt werden, vor allem dann, wenn auch eine geringe Dichte eine Rolle spielen sollte.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.

Claims (8)

  1. Al-Cu-Mg-Li alloy with
    3.7 - 3.9 % by weight Cu,
    0.9 - 1.3 % by weight Li,
    0.30 - 0.45 % by weight Mg,
    0.10 - < 0.2 by weight Mn,
    0.2 - 0.45 % by weight Ag,
    0.09 - 0.13 % by weight Zr
    Ti is existent in the alloy up to max. 0.07 % by weight Ti, wherein the Ti is present as TiB2 or TiC,
    remainder Al, together with unavoidable impurities,
    whereas sum of the dispersion-forming elements Mn+Fe+Si < 0.3 % by weight.
  2. Al-Cu-Mg-Li alloy according to claim 1, with
    3.7 - 3.9 % by weight Cu,
    0.95 - 1.2 % by weight Li,
    0.35 - 0.45 % by weight Mg,
    0.10 - 0.18 by weight Mn,
    0.38 - 0.43 % by weight Ag,
    0.09 - 0.13 % by weight Zr
    max. 0.07 % by weight Ti, wherein the Ti is present as TiB2 or TiC, remainder Al, together with unavoidable impurities.
  3. Al-Cu-Mg-Li alloy according to claim 1 or 2, characterised in that the Mn content is between 0.10 and 0.15 % by weight.
  4. Al-Cu-Mg-Li alloy according to one of claims 1 to 3, characterised in that the Cu/Mg ratio is between 8.22 and 12.
  5. Al-Cu-Mg-Li alloy product with an alloy composition according to any one of claims 1 to 4, characterised in that the product has been hardened in such a way that the alloy product exhibits parallel to the fibre a 0.2% elongation limit Rp0.2 of more than 620 MPa and a tensile strength Rm of more than 630 MPa.
  6. Al-Cu-Mg-Li alloy product according to claim 5, characterised in that this exhibits parallel to the fibre an elongation after fracture As of at least 9% parallel to the fibre.
  7. Al-Cu-Mg-Li alloy product according to claim 5 or 6, characterised in that the composition of the alloy is selected in such a way that the product resulting from it exhibits a density of some 2.70 g/cm3.
  8. Al-Cu-Mg-Li alloy product according to any one of claims 5 to 7, characterised in that the alloy product is a structural component for an aeronautical and/or aerospace application.
EP15161219.9A 2015-03-27 2015-03-27 Al-cu-mg-li alloy and alloy product produced from same Active EP3072984B2 (en)

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