EP3072985A1 - Ag-free al-cu-mg-li alloy - Google Patents
Ag-free al-cu-mg-li alloy Download PDFInfo
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- EP3072985A1 EP3072985A1 EP15161222.3A EP15161222A EP3072985A1 EP 3072985 A1 EP3072985 A1 EP 3072985A1 EP 15161222 A EP15161222 A EP 15161222A EP 3072985 A1 EP3072985 A1 EP 3072985A1
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- 239000001989 lithium alloy Substances 0.000 title claims abstract description 8
- 229910000733 Li alloy Inorganic materials 0.000 title abstract 2
- 239000012535 impurity Substances 0.000 claims abstract description 10
- 229910045601 alloy Inorganic materials 0.000 claims description 76
- 239000000956 alloy Substances 0.000 claims description 76
- 239000000203 mixture Substances 0.000 claims description 12
- 229910018182 Al—Cu Inorganic materials 0.000 claims description 10
- 229910052749 magnesium Inorganic materials 0.000 claims description 9
- 229910052802 copper Inorganic materials 0.000 claims description 8
- 229910052726 zirconium Inorganic materials 0.000 claims description 8
- 229910019400 Mg—Li Inorganic materials 0.000 claims description 5
- 229910052742 iron Inorganic materials 0.000 claims description 2
- 239000010949 copper Substances 0.000 description 17
- 239000011777 magnesium Substances 0.000 description 15
- 239000010936 titanium Substances 0.000 description 12
- 238000005275 alloying Methods 0.000 description 9
- 229910052719 titanium Inorganic materials 0.000 description 8
- 229910052744 lithium Inorganic materials 0.000 description 7
- 229910000838 Al alloy Inorganic materials 0.000 description 6
- 229910052709 silver Inorganic materials 0.000 description 5
- WHXSMMKQMYFTQS-UHFFFAOYSA-N Lithium Chemical compound [Li] WHXSMMKQMYFTQS-UHFFFAOYSA-N 0.000 description 4
- 230000000052 comparative effect Effects 0.000 description 4
- 230000005484 gravity Effects 0.000 description 4
- 238000011835 investigation Methods 0.000 description 4
- 239000004332 silver Substances 0.000 description 4
- 229910052748 manganese Inorganic materials 0.000 description 3
- 239000000463 material Substances 0.000 description 3
- 229910009369 Zn Mg Inorganic materials 0.000 description 2
- 229910007573 Zn-Mg Inorganic materials 0.000 description 2
- 230000032683 aging Effects 0.000 description 2
- 230000007797 corrosion Effects 0.000 description 2
- 238000005260 corrosion Methods 0.000 description 2
- 238000005336 cracking Methods 0.000 description 2
- 238000010438 heat treatment Methods 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 230000035882 stress Effects 0.000 description 2
- 229910000601 superalloy Inorganic materials 0.000 description 2
- 238000003878 thermal aging Methods 0.000 description 2
- QYEXBYZXHDUPRC-UHFFFAOYSA-N B#[Ti]#B Chemical compound B#[Ti]#B QYEXBYZXHDUPRC-UHFFFAOYSA-N 0.000 description 1
- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical compound [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 description 1
- 229910017539 Cu-Li Inorganic materials 0.000 description 1
- 229910017818 Cu—Mg Inorganic materials 0.000 description 1
- FYYHWMGAXLPEAU-UHFFFAOYSA-N Magnesium Chemical compound [Mg] FYYHWMGAXLPEAU-UHFFFAOYSA-N 0.000 description 1
- 230000018199 S phase Effects 0.000 description 1
- 229910033181 TiB2 Inorganic materials 0.000 description 1
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 description 1
- 238000005266 casting Methods 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000001953 recrystallisation Methods 0.000 description 1
- 230000003068 static effect Effects 0.000 description 1
- 229910052845 zircon Inorganic materials 0.000 description 1
- GFQYVLUOOAAOGM-UHFFFAOYSA-N zirconium(iv) silicate Chemical compound [Zr+4].[O-][Si]([O-])([O-])[O-] GFQYVLUOOAAOGM-UHFFFAOYSA-N 0.000 description 1
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% by weight of Si, max. 0.15% by weight of 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 similar to the alloy AA 2050 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 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 given strength requirements, but even against these and also 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 as possible lithium 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 poured on a laboratory scale into random billets by means of 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 Cu / Mg ratio according to the formula: 3 . 85 weight , - % - 0 . 7 ⁇ Mg wt , - % ⁇ Cu ⁇ 4 . 63 weight , - % - 0 . 7 ⁇ Mg wt , - % ,
- 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.
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- Organic Chemistry (AREA)
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Abstract
Beschrieben ist eine Ag-freie Al-CuMg-Li-Legierung mit 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 TiB 2 oder TiC vorliegt, Rest Al nebst unvermeidbaren Verunreinigungen von gesamt max. 0,15 Gew.-%.Described is an Ag-free Al-CuMg-Li alloy with 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 of a total of max. 0.15% by weight.
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 (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.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% by weight of Si, max. 0.15% by weight of 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 similar to the alloy AA 2050 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 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.
- 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 given strength requirements, but even against these and also 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 as possible lithium 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.
- 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.
- 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 poured on a laboratory scale into random billets by means of 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:
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:
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:
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 Luftund 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.
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US11180839B2 (en) | 2017-10-26 | 2021-11-23 | Ut-Battelle, Llc | Heat treatments for high temperature cast aluminum alloys |
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