EP3072985B2 - Ag-free al-cu-mg-li alloy - Google Patents

Ag-free al-cu-mg-li alloy Download PDF

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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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EP3072985A1 (en
EP3072985B1 (en
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Joachim Becker
Gregor Terlinde
Thomas Witulski
Tina Schlingmann
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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
    • 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

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Description

Die Erfindung betrifft eine Ag-freie Al-Cu-Mg-Li-Legierung sowie ein daraus hergestelltes Legierungsprodukt.The invention relates to an Ag-free 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 stranggepresste und/oder geschmiedete Teile. Diese müssen der notwendigen Kombination aus statischer und dynamischer Festigkeit genügen und bestimmte Anforderungen in Bezug auf Zugfestigkeit, Dehngrenze, Bruchdehnung und Risszähigkeit (K 1C 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 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). In addition, 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.

Eine herkömmlich eingesetzte Al-Cu-Zn-Mg-Legierung, die diesen Anforderungen genügt, ist die Aluminium-Legierung AA 7449. Diese vorbekannte Legierung hat eine Zusammensetzung von 1,4 - 2,1 Gew.-% Cu, 1,8 - 2,7 Gew.-% Mg, 7,5 - 8,7 Gew.-% Zn, max. 0,2 Gew.-% Mn, max. 0,12 Gew.-% Si, max. 0,15 Gew.-% Fe sowie max. 0,25 Gew.-% Ti + Zr. Die aus dieser Legierung hergestellten Bauteile haben eine Dichte von etwa 2,85 g/cm3.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 .

Eine weitere eingesetzte Al-Cu-Zn-Mg-Legierung, die diesen Anforderungen genügt, ist die Aluminium-Legierung AA 7050. Diese vorbekannte Legierung hat eine Zusammensetzung von 2,0 - 2,6 Gew.-% Cu, 1,9 - 2,6 Gew.-% Mg, 5,7 - 6,7 Gew.-% Zn, max. 0,10 Gew.-% Mn, max. 0,12 Gew.-% Si, max 0,15 Gew.-% Fe sowie max. 0,06 Gew.-% Ti und 0,08 - 0,15 Gew,% Zr max. 0,06 Gew.-% Ti. Die aus dieser Legierung hergestellten Bauteile haben eine Dichte von etwa 2,83 g/cm3.Another 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 .

Mit zunehmender Größe der Flugzeuge geht das Bestreben einher, das Gewicht der Bauteile möglichst noch weiter zu reduzieren. Entwickelt worden sind, um dieser Anforderung zu genügen, ausgehend von der Legierung AA 7449 und AA7050, Al-Cu-Li-Legierungen, die vergleichbare Festigkeitswerte aufweisen wie die Legierung AA 7449 und AA 7050, wobei jedoch das spezifische Gewicht daraus hergestellter Bauteile bei etwa 2,7 g/cm3 liegt. Die Aluminiumlegierung AA 2050 ist ein Beispiel für eine solche Hochleistungslegierung, die oftmals Bauteile, die zuvor aus der Legierung AA 7449 hergestellt worden sind, 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.-% 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.As the size of the aircraft increases, the aim is to reduce the weight of the components even further. 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. In order to achieve the necessary strength properties, 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.

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 Risszähigkeit und Spannungsrisskorrosion hergestellt werden, verglichen mit Bauteilen, die aus der Legierung AA 2050 hergestellt werden können.An alloy similar to alloy AA 2050 with an even higher Li content is 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. However, 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.

Auch wenn Bauteile aus der Legierung AA 2050 die gewünschten Festigkeitseigenschaften aufweisen, muss hingenommen werden, dass aufgrund des notwendigen Ag-Anteils diese bereits bei der Kalkulation des Materialeinsatzes teurer sind als Bauteile aus der Ag-freien Al-Cu-Mg- Legierung AA 7449 oder AA 7050.Even if components made of the alloy AA 2050 have the desired strength properties, it must be accepted that, due to the necessary Ag content, these are already more expensive than components made of the Ag-free Al-Cu-Mg alloy AA 7449 or when calculating the material used AA 7050.

Ausgehend von diesem diskutierten Stand der Technik liegt der Erfindung die Aufgabe zugrunde, eine Al-Cu-Aluminiumlegierung, mit der sich hoch- und höchstfeste Bauteile herstellen lassen, sowie ein daraus hergestelltes Produkt, insbesondere geeignet für den Einsatz als Bauteil in einer luft- oder raumfahrtechnischen Anwendung, vorzuschlagen, die nicht nur den gestellten Festigkeitsanforderungen genügen, sondern die auch gegenüber den aus der Legierung AA 2050 hergestellten Bauteilen kostengünstiger im Materialeinsatz sind.Starting from this discussed prior art, 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.

Gelöst wird diese Aufgabe erfindungsgemäß durch eine Al-Cu-Legierung mit den Merkmalen der Ansprüche 1 oder 2.This object is achieved according to the invention by an Al-Cu alloy with the features of claims 1 or 2.

Bei allen Legierungszusammensetzungen, die im Rahmen dieser Ausführungen beschrieben sind, können 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 Verunreinigungen möglichst gering zu halten, so dass diese je Element einen Anteil von 0,02 Gew.-% und eine Gesamtmenge von 0,08 Gew.-% nicht überschreiten.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.

Bauteile mit höchstfesten Eigenschaften lassen sich nur in den engen Grenzen der beanspruchten Legierungselemente mit einem ansonsten üblichen Warmbehandlungsverfahren herstellen. Bevorzugt wird das Warmauslagern durchgeführt, damit maximale Festigkeiten in dem aus der Legierung hergestellten Bauteil eingestellt werden. Als übliches Warmauslagerungsverfahren wird ein solches angesehen, bei dem die Warmauslagerung zwischen 145°C und 170°C mit angepasster Warmauslagerungszeit zwischen 10 h und 90 h durchgeführt wird.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.

Diese Legierung zeichnet sich durch besonders enge Bandbreiten in den Anteilen der Legierungselemente aus. Abgesehen hiervon ist die Legierung Ag- und Zn-frei, auch wenn ein gewisser Zn-Anteil geduldet werden kann. Es war gerade vor dem Hintergrund der herrschenden Meinung, die notwendigen Festigkeiten ließen sich bei einer Li-haltigen Al-Cu-Legierung in den daraus hergestellten Bauteilen nur erreichen, wenn Silber mit nicht unerheblichen Anteilen zulegiert ist, überraschend festzustellen, dass ein aus der erfindungsgemäßen Legierung hergestelltes Bauteil nicht nur den durch die Möglichkeiten der Legierung AA 7449 gestellten Festigkeitsanforderungen genügt, sondern gegenüber dieser und auch der Legierung AA 2050 sogar gesteigerte Festigkeitseigenschaften aufweist. Durch die gezielte enge Bandbreite der Gehalte der Legierungspartner ist eine Al-Cu-Mg-Li-Legierung bereitgestellt, aus der höchstfeste Bauteile hergestellt werden können. Zur Definition hochfest und höchstfest: Ein Bauteil weist höchstfeste Eigenschaften auf, wenn die Dehngrenze R p0,2 zumindest 600 MPa beträgt. Einem Bauteil werden hochfeste Eigenschaften zugesprochen, wenn die Dehngrenze R p0,2 zumindest 500 MPa beträgt.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. To define 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 assigned high-strength properties if the yield strength R p0.2 is at least 500 MPa.

Es war nicht zu erwarten, dass man mit einer Ag-freien Al-Cu-Legierung höchstfeste Bauteile herstellen kann. Vor allem gelingt dieses ohne den Aufwand in der Wärmebehandlung des aus der Legierung hergestellten Bauteils aufwendiger gestalten zu müssen.It was not to be expected that high-strength components could be produced with an Ag-free Al-Cu alloy. Above all, this is achieved without the expense of having to make the heat treatment of the component made from the alloy more complex.

Liegt der Cu-Anteil unter 3,5 Gew.-% stellt sich in Kombination mit den anderen Legierungselementen nicht die notwendige Festigkeit ein. Kupfergehalte über 4,3 Gew.-% in der Legierung vermögen die Festigkeit eines aus der Legierung hergestellten Bauteils nicht weiter zu erhöhen. Vielmehr ist damit zu rechnen, dass bei höheren Cu-Gehalten. Phasen entstehen, die die Brucheigenschaften und das Ermüdungsverhalten schädigen könnten.If 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 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 wird und keine unerwünschten Li-haltigen Phasen entstehen. Daher ist der Li-Gehalt der Legierung auf den engen Bereich zwischen 0,8 und 1,3 Gew.-% begrenzt.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 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. die S-Phasen Al2CuMg) einstellen. Unter Berücksichtigung der weiteren Legierungselemente soll der Mg-Anteil 0,8 Gew.-% nicht überschreiten.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.

Titan wird zu Feinung des Gussgefüges zulegiert und Zirkon zur Vermeidung/Hemmung unerwünschter Rekristallisationen bei der Warmumformung.Titanium is added to the alloy to refine the cast structure and zircon to avoid / inhibit undesirable recrystallization during hot forming.

Bauteile aus dieser Legierung sind bereits deswegen kostengünstiger, da die Legierung Ag-frei ist. Die Kosten des Materialeinsatzes zum Erstellen der Legierung können bis zu 30 % und mehr geringer sein als die entsprechenden Kosten einer Ag-haltigen Vergleichslegierung.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.

Das spezifische Gewicht eines aus dieser Legierung hergestellten Bauteils beträgt bei einer typischen Legierungszusammensetzung etwa 2,7 g/cm3 und entspricht damit dem spezifischen Gewicht z. B. eines aus der Legierung AA 2050 hergestellten Bauteils. Somit kommt den aus dieser Legierung hergestellten Bauteilen derselbe gewichtsreduzierende Vorteil zu, wie dieser auch Bauteilen, die z. B. aus der Legierung AA 2050 hergestellt sind, zugesprochen wird.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. Thus, 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.

Die Festigkeitseigenschaften sind über den Bereich der beanspruchten Legierungselemente relativ einheitlich.The strength properties are relatively uniform over the range of the alloyed elements.

Fe kann als Begleitelement in aller Regel nicht völlig vermieden werden. Tolerabel sind diesbezüglich Gehalte zwischen 0,02 - 0,035 Gew.-%.As a rule, Fe cannot be completely avoided as an accompanying element. In this regard, contents between 0.02-0.035% by weight are tolerable.

Für Untersuchungen der Legierungszusammensetzung und der sich einstellenden Festigkeiten von daraus hergestellten Bauteilen wurden erfindungsgemäße Legierungen sowie Vergleichslegierungen erschmolzen und im Labormaßstab durch Kokillenguss zu Versuchsbarren gegossen.For investigations of the alloy composition and the resulting strengths of components made from them, alloys according to the invention and comparative alloys were melted and cast into test bars on a laboratory scale by permanent mold casting.

Die erschmolzenen Legierungen haben folgende Zusammensetzung, wobei die Legierungen XL21, XL29 erfindungsgemäße Legierungen sind, während die übrigen Legierungen als Vergleichslegierungen erschmolzen worden sind: Legierung 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 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

Die jeweils gegossenen Barren wurden homogenisiert und stranggepresst oder geschmiedet und anschließend als Profile lösungsgeglüht, gereckt (2 - 4% in Längsrichtung) und warmausgelagert. Nachfolgend sind Untersuchungen durchgeführt worden, um die Dehngrenze R p0,2 , die Zugfestigkeit R m , die Bruchdehnung A 5 sowie die Risszähigkeit K 1C zu ermitteln. Die Untersuchungen sind an den Probenstücken an Probenstücken aus stranggepressten Stangen an jeweils gleichen Stellen vorgenommen worden. Die Untersuchungen ergaben folgende Ergebnisse: Probe Dichte [g/cm3] Rp0,2 [MPa] Rm [MPa] A5 [%] K1C [MPa√m] XL21 L 2,70 628 653 9,0 L-T 41,2 T-L 28,4 XL29 L 2,70 658 673 10,5 L-T 37,24 T-L 28,10 AA 2050 L 2,70 615 637 9,0 L-T 42,1 T-L 31,6 AA 2196 L 2,63 589 606 8,2 L-T 32,1 T-L 22,2 AA 7449 L 2,85 600 625 7,0 L-T 24,2 T-L 21,3 AA 7050 L 2,83 531 581 12,8 L-T 35,1 T-L 29,1 The bars cast in each case were homogenized and extruded or forged and then solution-annealed as profiles, stretched (2-4% in the longitudinal direction) and artificially aged. Investigations were subsequently carried out to determine the yield strength R p0.2 , the tensile strength R m , the elongation at break A 5 and the fracture toughness K 1C . The tests were carried out on the test pieces on test pieces made of extruded bars at the same points in each case. The investigations produced the following results: sample Density [g / cm 3 ] R p0.2 [MPa] R m [MPa] A 5 [%] K 1 C [MPa√m] XL21 L. 2.70 628 653 9.0 LT 41.2 TL 28.4 XL29 L. 2.70 658 673 10.5 LT 37.24 TL 28.10 AA 2050 L. 2.70 615 637 9.0 LT 42.1 TL 31.6 AA 2196 L. 2.63 589 606 8.2 LT 32.1 TL 22.2 AA 7449 L. 2.85 600 625 7.0 LT 24.2 TL 21.3 AA 7050 L. 2.83 531 581 12.8 LT 35.1 TL 29.1

Die Angaben zu der Vergleichslegierung AA 7449 sind der Literatur entnommen.The information on the comparison alloy AA 7449 is taken from the literature.

Die vorstehenden Festigkeitsergebnisse konnten anhand etlicher Paralleluntersuchungen mit Variationen in der erfindungsgemäßen Legierungszusammensetzung im Rahmen der durch den Anspruch 1 gesetzten Grenzen bestätigt werden.The above strength results could be confirmed on the basis of several parallel investigations with variations in the alloy composition according to the invention within the limits set by claim 1.

Besonders bevorzugt ist ein Cu/Mg-Verhältnis gemäß der Formel:

  • 3,85 Gew. -% - 0,7 · Mg Gew. -% < Cu < 4,63 Gew. -% - 0,7 · Mg Gew. -%.
A Cu / Mg ratio according to the formula is particularly preferred:
  • 3.85 wt% - 0.7 Mg wt% <Cu <4.63 wt% - 0.7 Mg wt%.

Die Beschreibung der beanspruchten Al-Cu-Mg-Li-Legierung macht deutlich, dass trotz seiner Silberfreiheit überraschenderweise daraus hergestellte Bauteile höchstfesten Anforderungen genügen und sogar gegenüber der herkömmlichen Legierung AA 7449 und AA 7050 einen nicht unerheblichen Vorteil in ihrer Dichte aufweisen.The description of the claimed Al-Cu-Mg-Li alloy makes it clear that, despite its freedom from silver, components made from it surprisingly meet the highest strength requirements and even have a not inconsiderable advantage in their density compared to the conventional alloy AA 7449 and AA 7050.

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. 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.

Claims (7)

  1. Ag-free Al-Cu alloy with
    3.5 - 4.3 % by weight Cu,
    0.9 - 1.2 % by weight Li,
    0.38 - 0.6 % by weight Mg,
    0.14 - 0.22 % by weight Mn,
    0.08 - 0.17 % by weight Zr,
    0.03 - 0.07 % by weight Ti, wherein the Ti is present as TiB2 or TiC,
    max. 0.08 % by weight Fe,
    max. 0.05 % by weight Si,
    remainder Al as well as unavoidable impurities of a total maximum of 0.15 % by weight.
  2. Ag-free Al-Cu alloy with
    3.7 - 4.0 % by weight Cu,
    0.9 - 1.2 % by weight Li,
    0.43 - 0.52 % by weight Mg,
    0.14 - 0.20 % by weight Mn,
    0.09 - 0.11 % by weight Zr,
    0.04 - 0.06 % by weight Ti,
    max. 0.08 % by weight Fe,
    max. 0.05 % by weight Si,
    remainder Al as well as unavoidable impurities of a total maximum of 0.15 % by weight.
  3. Ag-free Al-Cu alloy according to any one of claims 1 or 2, characterised in that the alloy additionally contains max. 0.03 % by weight Si and/or max. 0.05 % by weight Fe.
  4. Ag-free Al-Cu alloy according to any one of claims 1 to 3, characterised in that the Cu/Mg ratio corresponds to the following formula: 3.85 % by weight - 0.7 Mg % by weight < Cu < 4.63 % by weight - 0.7 Mg % by weight.
  5. Ag-free Al-Cu alloy according to any one of claims 1 to 4, characterised in that the composition of the alloy is selected in such a way that a product manufactured from it exhibits a density of less than 2.73 g/cm3, in particular of less than 2.71 g/cm3, preferably of some 2.70 g/cm3.
  6. Ag-free Al-Cu alloy product with an alloy composition according to any one of claims 1 to 4 and preferably a density according to claim 5, characterised in that the product is homogenised, heat-formed, solution-annealed, drawn and heat-hardened, and then drawn, in such a way that the alloy product exhibits a 0.2 % elongation limit Rp0.2 of more than 600 MPa, a tensile strength Rm of more than 640 MPa, and an elongation to fracture of more than 7%.
  7. Alloy product according to claim 6, characterised in that the alloy product is a product intended for technical aerospace applications.
EP15161222.3A 2015-03-27 2015-03-27 Ag-free al-cu-mg-li alloy Active EP3072985B2 (en)

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EP15161222.3A EP3072985B2 (en) 2015-03-27 2015-03-27 Ag-free al-cu-mg-li alloy
ES15161222T ES2642730T5 (en) 2015-03-27 2015-03-27 Ag-free Al-Cu-Mg-Li alloy

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US11220729B2 (en) * 2016-05-20 2022-01-11 Ut-Battelle, Llc Aluminum alloy compositions and methods of making and using the same
CN106893911B (en) * 2017-02-27 2018-05-15 广东省材料与加工研究所 A kind of high-strength temperature-resistant Al-Cu line aluminium alloys and preparation method thereof
US11242587B2 (en) 2017-05-12 2022-02-08 Ut-Battelle, Llc Aluminum alloy compositions and methods of making and using the same
WO2019084320A1 (en) 2017-10-26 2019-05-02 Amit Shyam 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 (en) † 1997-01-31 1998-08-06 Reynolds Metals Company Method of improving fracture toughness in aluminum-lithium alloys
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 (en) † 2013-04-12 2014-10-16 Constellium France Method for transforming al-cu-li alloy sheets improving formability and corrosion resistance

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1998033947A1 (en) † 1997-01-31 1998-08-06 Reynolds Metals Company Method of improving fracture toughness in aluminum-lithium alloys
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 (en) † 2013-04-12 2014-10-16 Constellium France Method for transforming al-cu-li alloy sheets improving formability and corrosion resistance

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EP3072985A1 (en) 2016-09-28
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EP3072985B1 (en) 2017-07-05

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