EP3072985B1 - Ag-free al-cu-mg-li alloy - Google Patents

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

Info

Publication number
EP3072985B1
EP3072985B1 EP15161222.3A EP15161222A EP3072985B1 EP 3072985 B1 EP3072985 B1 EP 3072985B1 EP 15161222 A EP15161222 A EP 15161222A EP 3072985 B1 EP3072985 B1 EP 3072985B1
Authority
EP
European Patent Office
Prior art keywords
weight
alloy
free
max
product
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Active
Application number
EP15161222.3A
Other languages
German (de)
French (fr)
Other versions
EP3072985B2 (en
EP3072985A1 (en
Inventor
Joachim Becker
Gregor Terlinde
Thomas Witulski
Tina Schlingmann
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Otto Fuchs KG
Original Assignee
Otto Fuchs KG
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Family has litigation
First worldwide family litigation filed litigation Critical https://patents.darts-ip.com/?family=52780887&utm_source=google_patent&utm_medium=platform_link&utm_campaign=public_patent_search&patent=EP3072985(B1) "Global patent litigation dataset” by Darts-ip is licensed under a Creative Commons Attribution 4.0 International License.
Application filed by Otto Fuchs KG filed Critical Otto Fuchs KG
Priority to EP15161222.3A priority Critical patent/EP3072985B2/en
Priority to ES15161222T priority patent/ES2642730T5/en
Publication of EP3072985A1 publication Critical patent/EP3072985A1/en
Publication of EP3072985B1 publication Critical patent/EP3072985B1/en
Application granted granted Critical
Publication of EP3072985B2 publication Critical patent/EP3072985B2/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

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 produced therefrom.
  • High-performance aluminum alloy components are an indispensable component of aircraft design in many cases. Components of such high-performance aluminum alloys are used among other things in the fuselage and in the wing as structural components. These parts are 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 crack toughness (K 1C and stress corrosion cracking). In addition, the weight plays a not insignificant role in components used in the aerospace industry. Thus, the specific gravity (density) of the high performance alloy used is also relevant.
  • a conventionally used Al-Cu-Zn-Mg alloy which satisfies these requirements is the aluminum alloy AA 7449.
  • This prior art alloy has a composition of 1.4-2.1% by weight of Cu, 1.8. 2.7% by weight Mg, 7.5-8.7% by weight Zn, max. 0.2% by weight of Mn, max. 0.12% by weight of Si, max. 0.15 wt .-% Fe and max. 0.25% by weight of Ti + Zr.
  • the components made from this alloy have a density of about 2.85 g / cm 3 .
  • Al-Cu-Zn-Mg alloy that meets these requirements is the aluminum alloy AA 7050.
  • This prior art alloy has a composition of 2.0-2.6 wt.% Cu, 1.9. 2.6% by weight Mg, 5.7-6.7% by weight Zn, max. 0.10% by weight of Mn, max. 0.12 wt .-% Si, max 0.15 wt .-% Fe and max. 0.06 wt% Ti and 0.08-0.15 wt% Zr max. 0.06 wt.% Ti.
  • the components made from this alloy have a density of about 2.83 g / cm 3 .
  • Al-Cu-Li alloys which have comparable strength values as the alloy AA 7449 and AA 7050, but the specific weight of components made from them is approximately 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 produced from the AA 7449 alloy in the aerospace industry.
  • 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 a Mg content of 0.1-0, 5 wt .-% on.
  • Zn is usually involved in the construction of the alloy with up to 0.25 wt .-%.
  • silver is alloyed in this alloy in amounts of 0.2-0.7% by weight. This measure accounts for the prevailing opinion that silver is a necessary alloying component especially in lithium-containing Al-Cu alloys for achieving high strengths of components made therefrom.
  • An alloy with an even higher Li content similar to the AA 2050 alloy, is the alloy AA 2196 with a Li content of 1.4-2.1% by weight.
  • the Cu content of this alloy is slightly reduced compared to the Cu content in the 2050 alloy. From this alloy, however, only components with lower fracture toughness and stress corrosion cracking can be made compared to components that can be made from the AA 2050 alloy.
  • the present invention seeks to provide an Al-Cu-aluminum alloy, with which high and very high strength components can be produced, and a product made therefrom, in particular suitable for use as a component in an air or space technology application, which not only meet the set strength requirements, but also the opposite made of the AA 2050 alloy components are more cost-effective in the use of materials.
  • unavoidable impurities may be contained per element of 0.05% by weight, the total amount of impurities should not exceed 0.15% by weight. However, it is preferred to keep the impurities as low as possible, so that they do not exceed a proportion of 0.02 wt .-% and a total amount of 0.08 wt .-% per element.
  • Components with very high-strength properties can only be produced within the narrow limits of the claimed alloying elements using an otherwise customary heat treatment method.
  • the aging is carried out to set maximum strengths in the component made of the alloy.
  • the usual method of thermal aging is considered to be one in which the thermal aging is carried out between 145 ° C and 170 ° C with an adapted hot aging time between 10 h and 90 h.
  • This alloy is characterized by particularly narrow bandwidths in the proportions of the alloying elements. Apart from this, the alloy is Ag and Zn-free, although a certain Zn content can be tolerated. It was just against the background of the prevailing opinion that the necessary strength could only be achieved with a Li-containing Al-Cu alloy in the components produced from it, if silver was not insignificant proportions is added surprisingly, that a manufactured from the alloy according to the invention component not only meets the requirements of the possibilities of the alloy AA 7449 strength requirements, but even against this and the alloy AA 2050 has increased strength properties.
  • the targeted narrow range of contents of the alloying partners provides an Al-Cu-Mg-Li alloy from which ultra-high-strength components can be produced.
  • a component has extremely strong properties if the yield strength R p0.2 is at least 600 MPa.
  • a component is said to have high strength properties if the yield strength R p0.2 is at least 500 MPa.
  • the Cu content is less than 3.5% by weight, the necessary strength does not arise in combination with the other alloying elements. Copper contents above 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 at higher Cu contents. Phases develop that could damage the fracture properties and fatigue behavior.
  • Lithium is included to reduce the density (specific gravity) in the alloy.
  • the lithium content is adapted to the Cu and Mg contents of the alloy in such a way that as much lithium as possible is incorporated into the alloy, but only so much that it is brought into solution and no unwanted 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 of the alloy, but is only allowed in one part, so that no unwanted phases (such as the S phases Al 2 CuMg) are established. Taking into account the other alloying elements should the Mg content not exceed 0.8 wt .-%.
  • Titanium is alloyed to fine-tune the cast and zircon to prevent / inhibit unwanted recrystallization during hot working.
  • Components made of this alloy are already cheaper because the alloy is Ag-free.
  • the cost of using the material to make the alloy can be up to 30% and more less than the corresponding cost of a comparative alloy containing Ag.
  • the specific gravity of a component made from this alloy is about 2.7 g / cm 3 for a typical alloy composition and thus corresponds to the specific gravity z.
  • a made of the alloy AA 2050 component As a made of the alloy AA 2050 component.
  • the components produced from this alloy the same weight-reducing advantage, as this also components that z. B. made of the alloy AA 2050, is awarded.
  • Fe can not be completely avoided as a companion element.
  • contents between 0.02-0.035% by weight are tolerable.
  • alloys according to the invention and comparative alloys were melted and cast on a laboratory scale into random billets by chill casting.
  • the molten alloys have the following composition, wherein the alloys XL21, XL29 alloys according to the invention, while the other alloys have been melted as comparative 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
  • the cast ingots were homogenized and extruded or forged and then solution annealed as profiles, stretched (2 - 4% in the longitudinal direction) and warmed up.
  • 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 specimens on specimens of extruded rods in the same places.
  • a manufactured from this alloy component is due to the above-described properties as a component for use in the aerospace industry, especially for structural components. However, components made of this alloy can also be made and used for other applications, especially if a low density should also play a role.

Landscapes

  • 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)

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 produced 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.High-performance aluminum alloy components are an indispensable component of aircraft design in many cases. Components of such high-performance aluminum alloys are used among other things in the fuselage and in the wing as structural components. These parts are 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 crack toughness (K 1C and stress corrosion cracking). In addition, the weight plays a not insignificant role in components used in the aerospace industry. Thus, the specific gravity (density) of the high performance alloy used is also relevant.

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 which satisfies these requirements is the aluminum alloy AA 7449. This prior art alloy has a composition of 1.4-2.1% by weight of Cu, 1.8. 2.7% by weight Mg, 7.5-8.7% by weight Zn, max. 0.2% by weight of Mn, max. 0.12% by weight of Si, max. 0.15 wt .-% Fe and max. 0.25% by weight of Ti + Zr. The components made from this alloy have a density of about 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 that meets these requirements is the aluminum alloy AA 7050. This prior art alloy has a composition of 2.0-2.6 wt.% Cu, 1.9. 2.6% by weight Mg, 5.7-6.7% by weight Zn, max. 0.10% by weight of Mn, max. 0.12 wt .-% Si, max 0.15 wt .-% Fe and max. 0.06 wt% Ti and 0.08-0.15 wt% Zr max. 0.06 wt.% Ti. The components made from this alloy have a density of about 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, efforts are made to further reduce the weight of the components as much as possible. Developed to meet this requirement, based on the alloy AA 7449 and AA7050, Al-Cu-Li alloys which have comparable strength values as the alloy AA 7449 and AA 7050, but the specific weight of components made from them is approximately 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 produced from the AA 7449 alloy in the aerospace industry. 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 a Mg content of 0.1-0, 5 wt .-% on. Zn is usually involved in the construction of the alloy with up to 0.25 wt .-%. In order to obtain the necessary strength properties, silver is alloyed in this alloy in amounts of 0.2-0.7% by weight. This measure accounts for the prevailing opinion that silver is a necessary alloying component especially in lithium-containing Al-Cu alloys for achieving high strengths of components made therefrom.

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 with an even higher Li content, similar to the AA 2050 alloy, is the alloy AA 2196 with a Li content of 1.4-2.1% by weight. The Cu content of this alloy is slightly reduced compared to the Cu content in the 2050 alloy. From this alloy, however, only components with lower fracture toughness and stress corrosion cracking can be made compared to components that can be made 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 AA 2050 alloy have the desired strength properties, it must be accepted that due to the necessary Ag content, these are already more expensive when calculating the material input than components made from the Ag-free Al-Cu-Mg alloy AA 7449 or 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.Based on this discussed prior art, the present invention seeks to provide an Al-Cu-aluminum alloy, with which high and very high strength components can be produced, and a product made therefrom, in particular suitable for use as a component in an air or space technology application, which not only meet the set strength requirements, but also the opposite made of the AA 2050 alloy components are more cost-effective in the use of materials.

Gelöst wird diese Aufgabe erfindungsgemäß durch eine Al-Cu-Legierung, die Ag-frei ist und folgende Zusammensetzung aufweist:

  • 3,5 - 4,5 Gew.-% Cu,
  • 0,8 - 1,3 Gew.-% Li,
  • 0,2 - 0,8 Gew.-% Mg,
  • 0,1 - 0,4 Gew.-% Mn,
  • 0,05 - 0,2 Gew.-% Zr,
  • bis zu 0,1 Gew.-% Ti, wobei das Ti als TiB2 oder TiC vorliegt,
  • Rest Al nebst unvermeidbaren Verunreinigungen.
This object is achieved according to the invention by an Al-Cu alloy which is Ag-free and has the following composition:
  • 3.5-4.5% by weight of Cu,
  • 0.8-1.3% by weight of Li,
  • 0.2-0.8% by weight Mg,
  • 0.1-0.4% by weight of Mn,
  • 0.05-0.2% by weight Zr,
  • up to 0.1% by weight of Ti, the Ti being present as TiB 2 or TiC,
  • Rest Al plus unavoidable impurities.

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.For all alloying compositions described in these statements, unavoidable impurities may be contained per element of 0.05% by weight, the total amount of impurities should not exceed 0.15% by weight. However, it is preferred to keep the impurities as low as possible, so that they do not exceed a proportion of 0.02 wt .-% and a total amount of 0.08 wt .-% per element.

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 very high-strength properties can only be produced within the narrow limits of the claimed alloying elements using an otherwise customary heat treatment method. Preferably, the aging is carried out to set maximum strengths in the component made of the alloy. The usual method of thermal aging is considered to be one in which the thermal aging is carried out between 145 ° C and 170 ° C with an adapted hot 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 the alloying elements. Apart from this, the alloy is Ag and Zn-free, although a certain Zn content can be tolerated. It was just against the background of the prevailing opinion that the necessary strength could only be achieved with a Li-containing Al-Cu alloy in the components produced from it, if silver was not insignificant proportions is added surprisingly, that a manufactured from the alloy according to the invention component not only meets the requirements of the possibilities of the alloy AA 7449 strength requirements, but even against this and the alloy AA 2050 has increased strength properties. The targeted narrow range of contents of the alloying partners provides an Al-Cu-Mg-Li alloy from which ultra-high-strength components can be produced. For the definition of high-strength and highest-strength: A component has extremely strong properties if the yield strength R p0.2 is at least 600 MPa. A component is said to have high strength properties if the yield strength R p0.2 is at least 500 MPa.

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 succeeds without the effort in the heat treatment of the component made of the alloy to make more expensive.

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 less than 3.5% by weight, the necessary strength does not arise in combination with the other alloying elements. Copper contents above 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 at higher Cu contents. Phases develop that could damage the fracture properties and 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 included to reduce the density (specific gravity) in the alloy. The lithium content is adapted to the Cu and Mg contents of the alloy in such a way that as much lithium as possible is incorporated into the alloy, but only so much that it is brought into solution and no unwanted 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 of the alloy, but is only allowed in one part, so that no unwanted phases (such as the S phases Al 2 CuMg) are established. Taking into account the other alloying elements should the Mg content not exceed 0.8 wt .-%.

Titan wird zu Feinung des Gussgefüges zulegiert und Zirkon zur Vermeidung/Hemmung unerwünschter Rekristallisationen bei der Warmumformung.Titanium is alloyed to fine-tune the cast and zircon to prevent / inhibit unwanted recrystallization during hot working.

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 of this alloy are already cheaper because the alloy is Ag-free. The cost of using the material to make the alloy can be up to 30% and more less than the corresponding cost of a comparative alloy containing Ag.

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 gravity of a component made from this alloy is about 2.7 g / cm 3 for a typical alloy composition and thus corresponds to the specific gravity z. As a made of the alloy AA 2050 component. Thus, the components produced from this alloy the same weight-reducing advantage, as this also components that z. B. made of the alloy AA 2050, is awarded.

Die Festigkeitseigenschaften sind über den Bereich der beanspruchten Legierungselemente relativ einheitlich. Eine gewisse Steigerung der Festigkeitswerte lässt sich mit folgender Zusammensetzung erzielen, bei der die zugelassene Bandbreite der Legierungselemente weiter eingeschränkt ist:

  • 3,5 - 4,3 Gew.-% Cu,
  • 0,9 - 1,2 Gew.-% Li,
  • 0,38 - 0,6 Gew.-% Mg,
  • 0,14 - 0,22 Gew.-% Mn,
  • 0,08 - 0,17 Gew.-% Zr,
  • 0,03 - 0,07 Gew.-% Ti,
  • Rest Al nebst unvermeidbaren Verunreinigungen.
The strength properties are relatively uniform over the range of claimed alloying elements. A certain increase in strength values can be achieved with the following composition, in which the permitted range of alloying elements is further restricted:
  • 3.5-4.3% by weight of Cu,
  • 0.9-1.2% by weight of Li,
  • 0.38-0.6 wt.% Mg,
  • 0.14-0.22% by weight of Mn,
  • 0.08 - 0.17 wt.% Zr,
  • 0.03-0.07 wt% Ti,
  • Rest Al plus unavoidable impurities.

Besonders bevorzugt ist die Ag-freie Al-Cu-Legierung mit folgender Zusammensetzung:

  • 3,7 4,0 Gew.-% Cu,
  • 0,9 - 1,2 Gew.-% Li,
  • 0,43 - 0,52 Gew.-% Mg,
  • 0,14 - 0,20 Gew.-% Mn,
  • 0,09 - 0,11 Gew.-% Zr,
  • 0,04 - 0,06 Gew.-% Ti,
  • Rest Al nebst unvermeidbaren Verunreinigungen.
Particularly preferred is the Ag-free Al-Cu alloy having the following composition:
  • 3.7 4.0% by weight of Cu,
  • 0.9-1.2% by weight of Li,
  • 0.43-0.52 wt% Mg,
  • 0.14-0.20% by weight of Mn,
  • 0.09 - 0.11 wt.% Zr,
  • 0.04-0.06 wt% Ti,
  • Rest Al plus unavoidable impurities.

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 can not be completely avoided as a companion 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 properties of components produced therefrom, alloys according to the invention and comparative alloys were melted and cast on a laboratory scale into random billets by chill 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 molten alloys have the following composition, wherein the alloys XL21, XL29 alloys according to the invention, while the other alloys have been melted as comparative 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 cast ingots were homogenized and extruded or forged and then solution annealed as profiles, stretched (2 - 4% in the longitudinal direction) and warmed up. In the following investigations were 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 specimens on specimens of extruded rods in the same places. The investigations gave 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 details of the comparative alloy AA 7449 are 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 by 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. -%.
Particularly preferred is a Cu / Mg ratio according to the formula:
  • 3.85% by weight - 0.7 × Mg% by weight <Cu <4.63% by weight - 0.7 × Mg by weight.

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, in spite of its freedom from silver, surprisingly components made from it satisfy the highest requirements and even have a considerable advantage over the conventional alloy AA 7449 and AA 7050 in their density.

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 manufactured from this alloy component is due to the above-described properties as a component for use in the aerospace industry, especially for structural components. However, components made of this alloy can also be made and used for other applications, especially if a low density should also play a role.

Claims (8)

  1. Ag-free Al-Cu-Mg-Li alloy with
    3.5 - 4.5 % by weight Cu,
    0.8 - 1.3 % by weight Li,
    0.2 - 0.8 % by weight Mg,
    0.1 - 0.4 % by weight Mn,
    0.05 - 0.2 % by weight Zr
    up to 0.1 % by weight Ti, wherein the Ti is present as TiB2 or TiC, remainder Al as well as unavoidable impurities of a total maximum of 0.15 % by weight.
  2. Ag-free Al-Cu alloy according to claim 1 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,
    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 claim 1 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.
  4. Ag-free Al-Cu alloy according to any one of claims 1 to 3, characterised in that the alloy additionally contains max. 0.03 % by weight Si and/or max. 0.05 % by weight Fe.
  5. Ag-free Al-Cu alloy according to any one of claims 1 to 4, 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.
  6. Ag-free Al-Cu alloy according to any one of claims 1 to 5, 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.
  7. Ag-free Al-Cu alloy product with an alloy composition according to any one of claims 1 to 5 and preferably a density according to claim 6, 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%.
  8. Alloy product according to claim 7, 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)

Priority Applications (2)

Application Number Priority Date Filing Date Title
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

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP15161222.3A EP3072985B2 (en) 2015-03-27 2015-03-27 Ag-free al-cu-mg-li alloy

Publications (3)

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

Family

ID=52780887

Family Applications (1)

Application Number Title Priority Date Filing Date
EP15161222.3A Active EP3072985B2 (en) 2015-03-27 2015-03-27 Ag-free al-cu-mg-li alloy

Country Status (2)

Country Link
EP (1) EP3072985B2 (en)
ES (1) ES2642730T5 (en)

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 (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
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 (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

Also Published As

Publication number Publication date
ES2642730T5 (en) 2021-06-09
ES2642730T3 (en) 2017-11-17
EP3072985B2 (en) 2020-08-26
EP3072985A1 (en) 2016-09-28

Similar Documents

Publication Publication Date Title
AT502311B1 (en) HIGHLY DAMAGED ALUMINUM ALLOY PRODUCT IN PARTICULAR FOR AIR AND SPACE APPLICATIONS
EP1683882B1 (en) Aluminium alloy with low quench sensitivity and process for the manufacture of a semi-finished product of this alloy
EP2954081B1 (en) Aluminium casting alloy
DE69912850T2 (en) METHOD OF PRODUCING AN ALUMINUM-MAGNESIUM-LITHIUM ALLOY PRODUCT
DE60007882T3 (en) ALUMINUM MAGNESIUM SCANDIUM ALLOYS WITH ZINC AND COPPER
EP2653579B1 (en) Aluminium alloy
DE60021619T3 (en) brazing
DE60004398T2 (en) ALUMINIUMLOTLEGIERUNG
DE102016219711B4 (en) Aluminum alloy for die casting and process for its heat treatment
DE112008003052T5 (en) Product of Al-Mg-Zn wrought alloy and manufacturing method therefor
EP3176275B2 (en) Aluminium-silicon die casting alloy method for producing a die casting component made of the alloy, and a body component with a die casting component
DE102005045341A1 (en) High strength, high strength Al-Zn alloy product and method of making such a product
EP2735621A1 (en) Aluminium die casting alloy
DE10393072T5 (en) Al-Cu alloy with high toughness
DE102017114162A1 (en) HIGH STRENGTH AND HIGH CRYAN RESISTANT ALUMINUM ALLOY ALLOYS AND HPDC MOTOR BLOCKS
EP3072985B1 (en) Ag-free al-cu-mg-li alloy
DE112018005321T5 (en) DIE CAST ALUMINUM ALLOY AND FUNCTIONAL COMPONENT USING THIS
EP3775309B1 (en) Aluminum die casting alloy
EP2888382A1 (en) Intergranular corrosion-resistant aluminum alloy strip, and method for the production thereof
WO2004003244A1 (en) Al/cu/mg/ag alloy with si, semi-finished product made from such an alloy and method for production of such a semi-finished product
DE102013107810A1 (en) High-temperature cast aluminum alloy and casting for internal combustion engines cast from such an alloy
EP1917372A2 (en) Aluminium casting alloy
DE102012108590A1 (en) casting
DE202017100517U1 (en) Al-Cu-Li-Mg-Mn-Zn wrought alloy product
EP3818187B1 (en) Aluminum alloy and overaged aluminum alloy product made of such an alloy

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

AX Request for extension of the european patent

Extension state: BA ME

17P Request for examination filed

Effective date: 20161011

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

INTG Intention to grant announced

Effective date: 20170308

RBV Designated contracting states (corrected)

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

REG Reference to a national code

Ref country code: GB

Ref legal event code: FG4D

Free format text: NOT ENGLISH

REG Reference to a national code

Ref country code: CH

Ref legal event code: EP

REG Reference to a national code

Ref country code: AT

Ref legal event code: REF

Ref document number: 906662

Country of ref document: AT

Kind code of ref document: T

Effective date: 20170715

REG Reference to a national code

Ref country code: IE

Ref legal event code: FG4D

Free format text: LANGUAGE OF EP DOCUMENT: GERMAN

REG Reference to a national code

Ref country code: DE

Ref legal event code: R096

Ref document number: 502015001366

Country of ref document: DE

REG Reference to a national code

Ref country code: CH

Ref legal event code: NV

Representative=s name: ALDO ROEMPLER PATENTANWALT, CH

REG Reference to a national code

Ref country code: NL

Ref legal event code: MP

Effective date: 20170705

REG Reference to a national code

Ref country code: ES

Ref legal event code: FG2A

Ref document number: 2642730

Country of ref document: ES

Kind code of ref document: T3

Effective date: 20171117

REG Reference to a national code

Ref country code: LT

Ref legal event code: MG4D

REG Reference to a national code

Ref country code: NO

Ref legal event code: T2

Effective date: 20170705

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20170705

Ref country code: SE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20170705

Ref country code: NL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20170705

Ref country code: FI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20170705

Ref country code: HR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20170705

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: GR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20171006

Ref country code: IS

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20171105

Ref country code: RS

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20170705

Ref country code: BG

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20171005

Ref country code: PL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20170705

Ref country code: LV

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20170705

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 4

REG Reference to a national code

Ref country code: DE

Ref legal event code: R026

Ref document number: 502015001366

Country of ref document: DE

PLBI Opposition filed

Free format text: ORIGINAL CODE: 0009260

PLAX Notice of opposition and request to file observation + time limit sent

Free format text: ORIGINAL CODE: EPIDOSNOBS2

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: CZ

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20170705

Ref country code: RO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20170705

Ref country code: DK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20170705

26 Opposition filed

Opponent name: ARCONIC INC.

Effective date: 20180403

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SM

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20170705

Ref country code: EE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20170705

Ref country code: SK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20170705

PLBB Reply of patent proprietor to notice(s) of opposition received

Free format text: ORIGINAL CODE: EPIDOSNOBS3

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20170705

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: MT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20170705

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: MC

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20170705

REG Reference to a national code

Ref country code: BE

Ref legal event code: MM

Effective date: 20180331

REG Reference to a national code

Ref country code: IE

Ref legal event code: MM4A

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LU

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20180327

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: IE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20180327

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: BE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20180331

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: TR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20170705

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: PT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20170705

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: CY

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20170705

Ref country code: HU

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT; INVALID AB INITIO

Effective date: 20150327

Ref country code: MK

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20170705

PUAH Patent maintained in amended form

Free format text: ORIGINAL CODE: 0009272

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: PATENT MAINTAINED AS AMENDED

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: AL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20170705

REG Reference to a national code

Ref country code: CH

Ref legal event code: AELC

27A Patent maintained in amended form

Effective date: 20200826

AK Designated contracting states

Kind code of ref document: B2

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

REG Reference to a national code

Ref country code: DE

Ref legal event code: R102

Ref document number: 502015001366

Country of ref document: DE

REG Reference to a national code

Ref country code: NO

Ref legal event code: TB2

REG Reference to a national code

Ref country code: ES

Ref legal event code: DC2A

Ref document number: 2642730

Country of ref document: ES

Kind code of ref document: T5

Effective date: 20210609

REG Reference to a national code

Ref country code: DE

Ref legal event code: R082

Ref document number: 502015001366

Country of ref document: DE

Representative=s name: HAVERKAMP PATENTANWAELTE PARTG MBB, DE

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: GB

Payment date: 20220324

Year of fee payment: 8

Ref country code: CH

Payment date: 20220324

Year of fee payment: 8

Ref country code: AT

Payment date: 20220214

Year of fee payment: 8

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: NO

Payment date: 20220322

Year of fee payment: 8

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: IT

Payment date: 20220331

Year of fee payment: 8

Ref country code: ES

Payment date: 20220420

Year of fee payment: 8

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: FR

Payment date: 20230320

Year of fee payment: 9

P01 Opt-out of the competence of the unified patent court (upc) registered

Effective date: 20230529

REG Reference to a national code

Ref country code: NO

Ref legal event code: MMEP

REG Reference to a national code

Ref country code: CH

Ref legal event code: PL

REG Reference to a national code

Ref country code: AT

Ref legal event code: MM01

Ref document number: 906662

Country of ref document: AT

Kind code of ref document: T

Effective date: 20230327

GBPC Gb: european patent ceased through non-payment of renewal fee

Effective date: 20230327

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: GB

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20230327

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: NO

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20230331

Ref country code: LI

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20230331

Ref country code: GB

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20230327

Ref country code: CH

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20230331

Ref country code: AT

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20230327

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: IT

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20230327

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: DE

Payment date: 20240205

Year of fee payment: 10

REG Reference to a national code

Ref country code: ES

Ref legal event code: FD2A

Effective date: 20240528