WO2014159324A1 - Improved aluminum-magnesium-lithium alloys, and methods for producing the same - Google Patents

Improved aluminum-magnesium-lithium alloys, and methods for producing the same Download PDF

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Publication number
WO2014159324A1
WO2014159324A1 PCT/US2014/023032 US2014023032W WO2014159324A1 WO 2014159324 A1 WO2014159324 A1 WO 2014159324A1 US 2014023032 W US2014023032 W US 2014023032W WO 2014159324 A1 WO2014159324 A1 WO 2014159324A1
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Prior art keywords
aluminum alloy
alloys
new
another embodiment
aluminum
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PCT/US2014/023032
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English (en)
French (fr)
Inventor
Francine BOVARD
Roberto J. Rioja
Ralph R. Sawtell
Dirk C. Mooy
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Alcoa Inc.
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Application filed by Alcoa Inc. filed Critical Alcoa Inc.
Priority to RU2015143481A priority Critical patent/RU2665655C2/ru
Priority to EP14775660.5A priority patent/EP2971213B1/en
Priority to CN201480014854.3A priority patent/CN105143492B/zh
Priority to CA2901879A priority patent/CA2901879C/en
Publication of WO2014159324A1 publication Critical patent/WO2014159324A1/en
Priority to IL240665A priority patent/IL240665A0/en

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    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22F—CHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS AND NON-FERROUS ALLOYS
    • C22F1/00—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
    • C22F1/04—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon
    • C22F1/047—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 magnesium 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
    • C22C21/06—Alloys based on aluminium with magnesium as the next major constituent
    • 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
    • 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
    • C22F1/053—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 zinc as the next major constituent

Definitions

  • Aluminum alloys are useful in a variety of applications. However, improving one property of an aluminum alloy without degrading another property is elusive, For example, it is difficult to increase the strength of an alloy without decreasing the toughness of an alloy. Other properties of interest for aluminum alloys include corrosion resistance and fatigue resistance, to name two.
  • the present patent application relates to new aluminum-magnesium- lithium alloys, and methods for producing the same.
  • the alloys generally contain 2.0 - 3.9 wt. % Mg, 0.1 - 1.8 wt. % Li, up to 1.5 wt. % Cu, up to 2.0 wt. % Zn, up to 1.0 wt. % Ag, up to 1.5 wt. % Mn, up to 0.5 wt. % Si, up to 0.35 wt. % Fe, 0.05 to 0.50 wt. % of a grain structure control element (defined below), up to 0.10 wt. % Ti, and up to 0.10 wt. % of any other element, with the total of these other elements not exceeding 0.35 wt. %, the balance being aluminum.
  • a grain structure control element defined below
  • the new aluminum-magnesium-lithium generally contain 2,0 to 3.9 wt. % Mg. Magnesium may help improve strength, but too much magnesium may degrade corrosion resistance.
  • the new alloys include at least 2,25 wt. % Mg. In another embodiment, the new alloys contain at least 2.5 wt. % Mg. in yet another embodiment, the new alloys include at least 2.75 wt. % Mg. In one embodiment, the new alloys include not greater than 3.75 wt. % Mg. In another embodiment, the new alloys include not greater than 3.5 wt. % Mg. In yet another embodiment, the new alloys include not greater than 3.25 wt. % Mg.
  • the new aluminum-magnesium-lithium generally contain 0.1 to 1.8 wt. % Li. Lithium helps reduce density and may help improve strength, but too much lithium may reduce ductility.
  • the new alloys include at least 0.4 wt. % Li. In another embodiment, the new alloys include at least 0.6 wt. % Li. In yet another embodiment, the new alloys include at least 0,8 wt. % Li. In another embodiment, the new alloys include at least 1 ,0 wt. % Li. In yet another embodiment, the new alloys include at least 1.05 wt. % Li. In another embodiment, the new alloys include at least 1.10 wt. % Li.
  • the new alloys include at least 1 ,20 wt. % Li. In one embodiment, the new alloys include not greater than 1.5 wt. % Li. In another embodiment, the ne alloys include not greater than 1.45 wt, % Li. In yet another embodiment, the new alloys include not greater than 1.4 wt. % Li.
  • the new alloys may contain up to about 1.5 wt. % Cu. Copper may improve strength but increases density. In one embodiment, the new alloys contain not greater than 1.0 wt. % Cu. In another embodiment, the new alloys contain not greater than 0,9 wt. % Cu, In yet another embodiment, the new alloys contain not greater than 0.6 wt. % Cu. in another embodiment, the new alloys contain not greater tha 0.5 wt. % Cu. In embodiments where copper is used, the new alloys generally contain at least 0.05 wt. % Cu. In one embodiment, the new alloys include at least 0.10 wt. % Cu. In embodiments where copper is not used, the new alloys include less than 0.05 wt. % Cu.
  • the new alloys may contain up to about 2.0 wt. % Zn. Zinc may improve strength, but increases density. In one embodiment, the new alloys contain not greater than 1.5 wt. % Zn, In another embodiment, the new alloys contain not greater than 1.0 wt. % Zn. In embodiments where zinc is used, the new alloys generally contain at least 0.20 wt. % Zn. In one embodiment, the new alloys contain at least 0.4 wt. % Zn. In another embodiment, the new alloys contain at least 0,5 wt. % Zn. In embodiments where zinc is not used, the new alloys include less than 0.20 wt. % Zn.
  • the new alloys may contain up to 1.5 wt. % Mn. Manganese may improve strength, but increases density. In one embodiment, the new alloys contain not greater than 1.0 wt. % Mn. In another embodiment, the new alloys contain not greater than 0.9 wt. % Mn. In yet another embodiment, the new alloys contain not greater than 0,7 wt, % Mn. In embodiments where manganese is used, the new alloys generally contain at least 0.05 wt. % Mn. In one embodiment, the new alloys include at least 0.20 wt. % Mn. In embodiments where manganese is not used, the new alloys include not greater than 0.04 wt. % Mn.
  • the new alloys may contain up to 1.0 wt, % Ag. Silver may improve strength, but silver decreases density and is expensive. In one embodiment, the new alloys contain not greater than 0.9 wt. % Ag. In another embodiment, the new alloys contain not greater than 0.6 wt. % Ag. In embodiments where silver is used, the new alloys generally contain at least 0.05 wt, % Ag. In one embodiment, the new alloys include at least 0.20 wt. % Ag. In embodiments where silver is not used, the new alloys include not greater than 0.04 wt. % Ag.
  • the new alloys may contain up to 0.5 wt. % Si, Silicon may improve corrosion resistance, but may decrease fracture toughness. In one embodiment, the new alloys contain not greater than 0.35 wt. % Si. In another embodiment, the new alloys contain not greater than 0.25 wt. % Si. In embodiments where silicon is used, the new alloys generally contain at least 0.10 wt. % Si. In embodiments where silicon is not used, the new alloys include not greater than 0.09 wt. % Si.
  • the new alloys may optionally include at least one secondary element selected from the group consisting of Zr, Sc, Cr, Hf, V, Ti, and rare earth elements. Such elements may be used, for instance, to facilitate the appropriate grain structure in the resultant aluminum alloy product.
  • the secondary elements may optionally be present as follows: up to 0.20 wt. % Zr, up to 0.30 wt. % Sc, up to 0.50 wt. % of Cr, up to 0.25 wt. % each of any of Hf, V, and rare earth elements, and up to 0.10 wt. % Ti.
  • Zirconium (Zr) and/or scandium are preferred for grain structure control.
  • the new aluminum alloys When zirconium is used, it is generally included in the new aluminum alloys at 0.05 to 0.20 wt. % Zr. In one embodiment, the new aluminum alloys include 0.07 to 0.16 wt. % Zr. Scandium (Sc) may be used in addition to, or as a substitute for zirconium, and, when present, is generally included in the new aluminum alloys at 0.05 to 0.30 wt. % Sc. In one embodiment, the new aluminum alloys include 0.07 to 0.25 wt. % Sc. Chromium (Cr) may also be used in addition to, or as a substitute for zirconium, and/or scandium, and when present is generally included in the new alloys at 0.05 to 0.50 wt. % Cr.
  • the new aluminum alloys include 0.05 to 0.35 wt. % Cr. In another embodiment, the new aluminum alloys include 0.05 to 0.25 wt. % Cr. In other embodiments, any of zirconium, scandium, and/or chromium may be included in the alloy as an impurity, and in these embodiments such elements would be included in the alloy at less than 0.05 wt. %.
  • Hf, V and rare earth elements may be included an in an amount of up to 0.25 wt. % each of any of Hf, V, and rare earth elements (0.25 wt. % each of any rare earth element may be included).
  • the new aluminum alloys include not greater than 0,05 wt. % each of Hf, V, and rare earth elements ( ⁇ 0.05 wt. % each of any rare earth element).
  • Titanium is preferred for grain refining during casting, and, when present is generally included in the new aluminum alloys at 0.005 to 0,10 wt. % Ti.
  • the new aluminum alloys include 0.01 to 0.05 wt. % Ti.
  • the aluminum alloys include 0.01 to 0.03 wt. % Ti.
  • the new alloys may include up to 0.35 wt. % Fe.
  • the iron content of the new aluminum alloys is not greater than about 0.25 wt. % Fe, or not greater than about 0,15 wt. % Fe, or not greater than about 0.10 wt, % Fe, or not greater than about 0,08 wt, % Fe, or not greater than 0.05 wt. % Fe, or less.
  • the balance (remainder) of the new aluminum alloys is generally aluminum and other elements, where the new aluminum alloys include not greater than 0.15 wt. % each of these other elements, and where the total of these other elements does not exceed 0,35 wt. %.
  • other elements includes any elements of the periodic table other than the above-identified elements, i.e., any elements other than Ah Mg, Li, Cu, Zn, Mn, Si, Fe, Zr, Sc. Cr, Ti, Hf, V, and rare earth elements.
  • the new aluminum alloys include not greater than 0.10 wt. % each of other elements, and with the total of these other elements not exceeding 0.25 wt.
  • the new aluminum alloys include not greater than 0.05 wt, % each of other elements, and with the total of these other elements not exceeding 0.15 wt. %. In yet another embodiment, the new aluminum alloys include not- greater than 0,03 wt. % each of other elements, and with the total of these other elements not exceeding 0.10 wt. %.
  • an aluminum alloy includes zinc, and includes 2.0 - 3.9 wt. % Mg, 0.1 - 1.8 wt. % Li, 0.4 to 2.0 wt. % Zn, up to 1.5 wt. % Cu, up to 1.0 wt. % Ag, up to 1.5 wt. % Mn, up to 0.5 wt. % Si, up to 0.35 wt. % Fe, optionally at least one secondary element, as described above, up to 0.10 wt. % of any other element, with the total of these other elements not exceeding 0.35 wt. %, the balance being aluminum.
  • This alloy may be modified to any of the above-described Mg, Li, Zn, Cu, Ag, Mn, Si, Fe, secondary elements and other elements amounts, described above,
  • the aluminum alloy is a high-lithium alloy, and includes 2,5 - 3.9 wt. % Mg, 1.05 - 1.8 wt. % Li, up to 2.0 wt. % Zn, up to 1.5 wt. % Cu, up to 1.0 wt. % Ag, up to 1.5 wt. % Mn, up to 0,5 wt, % Si, up to 0,35 wt, % Fe, optionally at least one secondary element, as described above, up to 0.10 wt. % of any other element, with the total of these other elements not exceeding 0.35 wt, %, the balance being aluminum.
  • This alloy may be modified to any of the above-described Mg, Li, Zn, Cu, Ag, Mn, Si, Fe, secondary elements and other elements amounts, described above.
  • the total amount of magnesium, lithium, copper, zinc, silicon, iron, the secondary elements and the other elements should be chosen so that the aluminum alloy can be appropriately solutionized (e.g., to promote hardening while restricting the amount of constituent particles).
  • the aluminum alloy includes an amount of alloying elements that leaves the aluminum alloy free of, or substantially free of, soluble constituent particles after solutionizing.
  • the aluminum alloy includes an amount of alloying elements that leaves the aluminum alloy with low amounts of (e.g., restricted / minimized) insoluble constituent particles after solutionizing. In other embodiments, the aluminum alloy may benefit from controlled amounts of insoluble constituent particles.
  • the new aluminum alloys may be processed into a variety of wrought forms, such as in rolled form (sheet, plate), as an extrusion, or as a forging, and in a variety of tempers.
  • new aluminum alloys may be cast (e.g.. direct chill cast or continuously cast), and then worked (hot and/or cold worked) into the appropriate product form (sheet, plate, extrusion, or forging).
  • the new aluminum alloys may be processed into one of an H temper, T temper or a W temper, as defined by the Aluminum Association.
  • the aluminum alloy may be hot worked, such as by rolling, extruding and/or forging.
  • the hot working temperature is maintained below the recrystallization temperature of the alloy.
  • the hot working exit temperature is not greater than 600°F. In another embodiment, the hot working exit temperature is not greater than 55()°F. In yet another embodiment, the hot working exit temperature is not greater than 500°F. In another embodiment, the hot working exit temperature is not greater than 450°F. In yet another embodiment, the hot working exit temperature is not greater than 400°F,
  • the new alloy is processed to an H temper.
  • the processing may include casting the new aluminum alloy, including any version of the aluminum alloy described above, after which the aluminum alloy is hot rolled to an intermediate gauge or final gauge.
  • the alloy will then be cold rolled to final gauge (e.g., cold rolled 2-25%), and then optionally stretched (e.g., 1 -10%), for instance, for flatness and/or for stress relief.
  • the alloy may be stretched (e.g., 1-10%), for instance, for flatness and/or for stress relief.
  • the aluminum alloy may be cooled to a temperature of not greater than 400°F prior to the cold rolling and/or the stretching. In one embodiment, the aluminum alloy is cooled to a temperature of not greater than 250°F prior to the cold rolling and/or the stretching. In another embodiment, the aluminum alloy is cooled to a temperature of not greater than 20G°F prior to the cold rolling and/or the stretching. In yet another embodiment, the aluminum alloy is cooled to a temperature of not greater than 150°F prior to the cold rolling and/or the stretching. In yet another embodiment, the aluminum alloy is cooled to ambient temperature prior to the cold rolling and/or the stretching.
  • the process includes maintaining the aluminum alloy at a temperature below 400°F between the hot rolling step and any cold rolling and/or stretching step.
  • the process includes maintaining the aluminum alloy at a temperature of net 250°F between the hot rolling step and/or any cold rolling and/or stretching step.
  • the process includes maintaining the aluminum alloy at a temperature of net 200°F between the hot rolling step and/or any cold rolling and/or stretching step.
  • the process includes maintaining the aluminum alloy at a temperature of net 150°F between the hot rolling step and/or any cold roiling and/or stretching step. In another H-temper embodiment, the process includes maintaining the aluminum alloy at ambient temperature between the hot rolling step and/or any cold rolling and/or stretching step.
  • an H-temper processing method is absent of any thermal treatments after any cold rolling step and/or any stretching step.
  • one or more anneal steps could be used, such as before or after hot and/or cold rolling.
  • the cold rolling when cold rolling is used as a pail of H-temper processing, the cold rolling may be restricted to so as to facilitate good strength, ductility and/or corrosion resistance.
  • the cold rolling comprises cold rolling the intermediate gauge product by 1 -25%, i.e., the thickness of the intermediate gauge product is reduced by 1-25% by cold rolling.
  • the cold roiling is 2-22%, i.e., the thickness of the intermediate gauge product is reduced by 2-22% by cold rolling.
  • the cold rolling is 3-20%, i.e., the thickness of the intermediate gauge product is reduced by 3-20% by cold rolling.
  • the new aluminum alloy is processed to a "T temper" (thermally treated).
  • the new aluminum alloys may be processed to any of a Tl , T2, T3, T4, T5, T6, T7, T8 or T.9 temper, as defined by the Aluminum Association.
  • the new aluminum alloys are processed to one of a T4, T6 or T7 temper, where the new aluminum alloys are solution heat treated, and then quenched, and then either naturally aged (T4) or artificially aged (T6 or T7).
  • the new aluminum alloys are processed to one of a T3 or T8 temper, where the new aluminum alloys are solution heat treated, and then quenched, and then cold worked, and then either naturally aged (T3) or artificially aged (T8).
  • the new aluminum alloy is processed to an "W temper” (solution heat treated), as defined by the Aluminum Association.
  • no solution heat treatment is applied after the hot working, and thus the new aluminum alloy may be processed to an "F temper" (as fabricated), as defined by the Aluminum Association.
  • the alloys may also be processed with high cold work after the solution heat treatment and quench, e.g., 25% or more cold work, as described in commonly-owned U.S. Patent Publication No. 2012/0055590.
  • the new aluminum alloys may achieve an improved combination of properties.
  • the new aluminum alloys may achieve an improved combination of strength, corrosion resistance and/or ductility, among others.
  • the new aluminum alloys are in an H-temper, are hot rolled, and then stretched 1-10%, (no cold rolling step) and realize a tensile yield strength (L) of at least 35 ksi (tested via ASTM E8 and B557).
  • the new aluminum alloys realize a tensile yield strength (L) of at least 36 ksi.
  • the new aluminum alloys realize a tensile yield strength (L) of at least 38 ksi.
  • the new aluminum alloys realize a tensile yield strength (L) of at least 40 ksi.
  • the new aluminum alloys realize a tensile yield strength (L) of at least 42 ksi. In yet another embodiment, the new aluminum alloys realize a tensile yield strength (L) of at least 44 ksi. In another embodiment, the new aluminum alloys realize a tensile yield strength (L) of at least 46 ksi. In yet another embodiment, the new aluminum alloys realize a tensile yield strength (L) of at least 48 ksi. In another embodiment, the new aluminum alloys realize a tensile yield strength (L) of at least 50 ksi.
  • the new aluminum alloys realize a tensile yield strength (L) of at least 51 ksi, or more, in these H-temper and stretching embodiments, the new aluminum alloys may realize an elongation (L) of at least 10% (tested via ASTM E8 and B557), In one embodiment, the new aluminum alloys realize an elongation (L) of at least 12%. in another embodiment, the new aluminum alloys realize an elongation (L) of at least 14%. In yet another embodiment, the new aluminum alloys realize an elongation (L) of at least 16%. In another embodiment, the new aluminum alloys realize an elongation (L) of at least 1 8%, or more.
  • the new aluminum alloys may realize a mass loss of not greater than 25 mg/cm (tested in accordance with ASMT G67, and with 1 week of exposure to 100°C). In one embodiment, the new aluminum alloys realize a mass loss of not greater than 15 rag/cm . in these H-temper and stretching embodiments, the new aluminum alloys may realize an EXCO rating of at least EB (at T/10 and/or at surface, and as tested in accordance with ASMT G66, and with 1 week of exposure to 100°C). In one embodiment, the new aluminum alloys realize an EXCO rating of at least EA. In another embodiment, the new aluminum alloys realize an EXCO rating of at least PC. In yet another embodiment, the new aluminum alloys realize an EXCO rating of at least PB. In another embodiment, the new aluminum alloys realize an EXCO rating of at least PA.
  • the new aluminum alloys are in an H-temper, are hot rolled, and then cold rolled 1-25% and realize a tensile yield strength (L) of at least 40 ksi (tested via ASTM E8 and B557).
  • the new aluminum alloys realize a tensile yield strength (L) of at least 42 ksi.
  • the new aluminum alloys realize a tensile yield strength (L) of at least 44 ksi.
  • the new aluminum alloys realize a tensile yield strength (L) of at least 46 ksi.
  • the new aluminum alloys realize a tensile yield strength (L) of at least 48 ksi.
  • the new aluminum alloys realize a tensile yield strength (L) of at least 50 ksi. In another embodiment, the new aluminum alloys realize a tensile yield strength (L) of at least 52 ksi. In yet another embodiment, the new aluminum alloys realize a tensile yield strength (L) of at least 54 ksi. In another embodiment, the new aluminum alloys realize a tensile yield strength (L) of at least 56 ksi. in yet another embodiment, the new aluminum alloys realize a tensile yield strength (L) of at least 58 ksi, or more.
  • the new aluminum alloys may realize an elongation (L) of at least 6% (tested via ASTM E8 and B557), In one embodiment, the new aluminum alloys realize an elongation (L) of at least 8%, In ano ther embodiment, the new aluminum alloys realize an elongation (L) of at least 10%. in yet another embodiment, the new aluminum alloys realize an elongation (L) of at least 12%. In another embodiment, the new aluminum alloys realize an elongation (L) of at least 14%, or more.
  • the new aluminum alloys may realize a mass loss of not greater than 25 mg/cm (tested in accordance with ASMT G67, and with I week of exposure to 100°C). In these H-temper and cold rolling embodiments, the new aluminum alloys may realize a mass loss of not greater than 35 mg/cm 2 . In these H-temper and cold rolling embodiments, the new aluminum alloys may realize an EXCX) rating of at least EB (at T/10 and/or at surface, and as tested in accordance with ASMT G66, and with 1 week of exposure to 100°C). In one embodiment, the new aluminum alloys realize an EXCO rating of at least EA. In another embodiment, the new aluminum alloys realize an EXCO rating of at least PC. In yet another embodiment, the new aluminum alloys realize an EXCO rating of at least PB. In another embodiment, the new aluminum alloys realize an EXCO rating of at least PA.
  • the new aluminum alloys are in an T-temper, and realize a tensile yield strength (L) of at least 45 ksi (tested via ASTM E8 and B557). in one embodiment, the new aluminum alloys realize a tensile yield strength (L) of at least 46 ksi. In another embodiment, the new aluminum alloys realize a tensile yield strength (L) of at least 48 ksi. In yet another embodiment, the new aluminum alloys realize a tensile yield strength (L) of at least 50 ksi. In another embodiment, the new aluminum alloys realize a tensile yield strength (L) of at least 52 ksi.
  • the new aluminum alloys realize a tensile yield strength (L) of at least 54 ksi. In another embodiment, the new aluminum alloys realize a tensile yield strength (L) of at least 56 ksi. In yet another embodiment, the new aluminum alloys realize a tensile yield strength (L) of at least 58 ksi. In another embodiment, the new aluminum alloys realize a tensile yield strength (L) of at least 60 ksi. In yet another embodiment, the new aluminum alloys realize a tensile yield strength (L) of at least 62 ksi, or more.
  • new aluminum alloys may realize an elongation (L) of at least 6% (tested via ASTM E8 and B557). In one embodiment, the new aluminum alloys realize an elongation (L) of at least 8%. In another embodiment, the new aluminum alloys realize an elongation (L) of at least 10%. In yet another embodiment, the new aluminum alloys realize an elongation (L) of at least 12%. In another embodiment, the new aluminum alloys realize an elongation (L) of at least 14%, or more. In these T-temper embodiments, the new aluminum alloys may realize a mass loss of not greater than 25 mg/cm 2 (tested in accordance with ASMT G67, and with 1 week of exposure to 100°C).
  • the new aluminum alloys realize mass loss of not greater than 15 mg/cm , In these T-temper embodiments, the new aluminum alloys may realize an EXCO rating of at least EB (at T/10 and/or at surface, and as tested in accordance with ASM i G66, and with 1 week of exposure to 100°C). In one embodiment, the new aluminum alloys realize an EXCO rating of at least EA. In another embodiment, the new aluminum alloys realize an EXCO rating of at least PC. In yet another embodiment, the new aluminum alloys realize an EXCO rating of at least PB. In another embodiment, the new aluminum alloys realize an EXCO rating of at least PA.
  • the new aluminum alloys described herein may be used in a variety of applications, such as in automotive and/or aerospace applications, among others.
  • the new aluminum alloys are used in an aerospace application, such as wing skins (upper and lower) or stringers / stiffeners, fuselage skin or stringers, ribs, frames, spars, bulkheads, circumferential frames, empennage (such as horizontal and vertical stabilizers), floor beams, seat tracks, doors, and control surface components (e.g., rudders, ailerons) among others
  • the new aluminum alloys are used in an automotive application, such as closure panels (e.g., hoods, fenders, doors, roofs, and trunk lids, among others), wheels, and critical strength applications, such as in body-in-white (e.g., pillars, reinforcements) applications, among others.
  • the new aluminum alloys are used in a marine application, such as for ships and boats (e.g., hulls, decks, masts, and superstructures, among others).
  • the new aluminum alloys are used in a munitions / ballistics / military application, such as in ammunition cartridges and armor, among others.
  • Ammunition cartridges may include those used in small aims and cannons or for artillery or tank rounds.
  • Other possible ammunition components would include sabots and fins.
  • Artillery, fuse components are another possible application as are fins and control surfaces for precision guided bombs and missiles, Armor components could include armor plates or structural components for military vehicles.
  • FIGS. 1-12 are graphs illustrating results of Example 1.
  • FIGS. 13 is a graph illustrating results of Example 2.
  • FIGS. 14-21 are graphs illustrating results of Example 3.
  • Example 1 Twelve book mold ingots were produced, the compositions of which are provided in Table 1 , below (all values in weight percent).
  • all alloys contained the listed elements, from about 0.10 to 0.13 wt. % Zr, about 0.60 wt. % Mn, not more than about 0,04 wt. % Fe, not more than 0.03 wt. % Si, about 0.02 wt. % Ti, the balance being aluminum and other elements, where the other elements did not exceed more than 0.05 wt. % each, and not more than 0.15 wt. % total of the other elements.
  • the alloys were cast as approximately 2.875 inch (ST) x 4.75 inch (LT) x 17 inch (L) ingots that were scalped (machined) to about 2 inches thick. Alloys 10-12 were then homogenized. Each ingot was then hot rolled to a gauge of about 0.25 inch. The finish hot rolling temperature varied as shown below (the starting hot rolling temperature was about 850°F). Part of these hot rolled pieces were then cold rolled to a gauge of about 0.1875 inch (about a 25% reduction in thickness). For Alloys 1-5, other parts of the hot rolled pieces were stretched about 2% for flatness.
  • the HR only alloys and the HR + 25% CR alloys were also tested for corrosion resistance in accordance with ASTM G66 (exfoliation resistance) and G67 (mass loss). Specifically, the alloys were tested for corrosion resistance before and after exposure to a temperature of about 100°C for about 1 week. Alloys 1 -5 that were hot rolled and then stretched 2% were also tested for corrosion resistance in accordance with ASTM G67 (mass loss). The corrosion resistance results are shown in Tables 5-7, below.
  • FIG. 10 illustrates mass loss as a function of lithium for high magnesium alloys. As shown above, the higher magnesium alloys also realize worse exfoliation resistance.
  • alloys contained the listed elements, from about 0.10 to 0.012 wt. % Zr, not more than about 0.03 wt. % Fe, not more than 0.04 wt. % Si, about 0.02 wt. % Mn, about 0.02 wt. % Ti, the balance being aluminum and other elements, where the other elements did not exceed more than 0.05 wt. % each, and not more than 0.15 wt. % total of the other elements. Alloy 25 contained about 0.24 wt. % Si. Alloy 26 contained about 0.87 wt. % Si.
  • the alloys were cast as approximately 2.875 inch (ST) x 4.75 inch (LT) x 17 inch (L) ingots that were scalped to about 2 inches thick, and then homogenized. After homogenization, each ingot was hot rolled to a gauge of about 0,25 inch, and then coid rolled about 25% (reduced in thickness by 25%) to a final gauge of about 0.1875 inch.
  • Tensile yield strength and corrosion resistance properties were then tested, the results of which are provided in Tables 9a- 9b, below. Tensile yield strength properties were measured in accordance with ASTM E8 and B557 ⁇ all test values relative to the longitudinal. (L) direction, unless otherwise indicated. Corrosion resistance was tested in accordance with ASTM G66 (exfoliation resistance) and G67 (mass loss) — the alloys were tested for corrosion resistance before and after exposure to a temperature of about 100°C for about 1 week.
  • the strongest alloy contained about 1.0 wi. % Zn, 0.35 wt. % Cu and 0.65 wt. % Ag.
  • low silver alloys ⁇ 0.25 wt. % Ag
  • increasing copper from about 0.35 to 0,95 wt. % and/or increasing zinc did appear to benefit strength.
  • medium silver alloys ⁇ 0.45 wt. % Ag
  • increasing copper from about 0.65 to 1.85 wt. % decreased strength
  • increasing zinc from about 1.45 to 2.82 wt. % had little effect on strength.
  • moderately-high silver alloys ⁇ 0.65 wt. % Ag
  • increasing copper fro about 0.35 to about 0.90 wt. % decreased strength, and increasing zinc also decreased strength.
  • ail alloys contained the listed elements, from about 0.10 to 0, 14 wt. % Zr, not more than about 0.04 wt. % Fe, not more than 0,08 wt. % Si, the balance being aluminum and other elements, where the other elements did not exceed more than 0.05 wt. % each, and not more than 0, 15 wt. % total of the other elements.
  • Alloy 46 contained about 0.09 wt. % Zr, about 0.10 wt. % Fe and about 0.14 wt. % Si,
  • the alloys were cast as 2.875 inch (ST) x 4,75 inch (LT) x 17 inch (L) ingots that were scalped to 2 inches thick and then homogenized. After homogenization, each ingot was hot rolled to a gauge of about 0,25 inch (Alloy 36 could not be rolled due to too much manganese). Part of these hot rolled pieces were then cold rolled to a gauge of about 0.1875 inch (about 25% reduction in thickness). Other parts of the hot rolled pieces were stretched about 2% for flatness. The mechanical properties and corrosion resistance properties of the hot rolled and cold rolled materials were then tested, the results of which are provided in Tables 1 1-14, below.

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CN104532071A (zh) * 2014-12-23 2015-04-22 合肥派成铝业有限公司 一种不易黄变的门窗用铝合金
CN109913711A (zh) * 2019-04-23 2019-06-21 中国兵器工业第五九研究所 铸造铝合金成型装置及成型方法
WO2020169014A1 (zh) * 2019-02-22 2020-08-27 北京工业大学 Yb微合金化的AI-Li合金

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CN110042285B (zh) * 2019-05-23 2020-03-24 江苏亨通电力特种导线有限公司 铆钉用高强度铝镁合金丝及其制备方法
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CN112646994B (zh) * 2020-12-16 2022-03-04 中南大学 一种高比强高比模铝合金及其制备方法

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WO2020169014A1 (zh) * 2019-02-22 2020-08-27 北京工业大学 Yb微合金化的AI-Li合金
CN109913711A (zh) * 2019-04-23 2019-06-21 中国兵器工业第五九研究所 铸造铝合金成型装置及成型方法

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