WO2023028070A1 - Procédés de production d'alliages d'aluminium 2xxx - Google Patents

Procédés de production d'alliages d'aluminium 2xxx Download PDF

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Publication number
WO2023028070A1
WO2023028070A1 PCT/US2022/041247 US2022041247W WO2023028070A1 WO 2023028070 A1 WO2023028070 A1 WO 2023028070A1 US 2022041247 W US2022041247 W US 2022041247W WO 2023028070 A1 WO2023028070 A1 WO 2023028070A1
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Prior art keywords
aluminum alloy
hours
2xxx aluminum
mpa
temperature
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PCT/US2022/041247
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English (en)
Inventor
Daniel J. SAUZA
Julien Boselli
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Arconic Technologies Llc
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Application filed by Arconic Technologies Llc filed Critical Arconic Technologies Llc
Priority to EP22861993.8A priority Critical patent/EP4392591A1/fr
Priority to CN202280054819.9A priority patent/CN117881809A/zh
Priority to CA3227929A priority patent/CA3227929A1/fr
Publication of WO2023028070A1 publication Critical patent/WO2023028070A1/fr
Priority to US18/435,464 priority patent/US20240175114A1/en

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    • CCHEMISTRY; METALLURGY
    • C22METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22CALLOYS
    • C22C21/00Alloys based on aluminium
    • C22C21/12Alloys based on aluminium with copper as the next major constituent
    • CCHEMISTRY; METALLURGY
    • C22METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22CALLOYS
    • C22C21/00Alloys based on aluminium
    • C22C21/12Alloys based on aluminium with copper as the next major constituent
    • C22C21/14Alloys based on aluminium with copper as the next major constituent with silicon
    • CCHEMISTRY; METALLURGY
    • C22METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22CALLOYS
    • C22C21/00Alloys based on aluminium
    • C22C21/12Alloys based on aluminium with copper as the next major constituent
    • C22C21/16Alloys based on aluminium with copper as the next major constituent with magnesium
    • CCHEMISTRY; METALLURGY
    • C22METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22CALLOYS
    • C22C21/00Alloys based on aluminium
    • C22C21/12Alloys based on aluminium with copper as the next major constituent
    • C22C21/18Alloys based on aluminium with copper as the next major constituent with zinc
    • CCHEMISTRY; METALLURGY
    • C22METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22FCHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS AND NON-FERROUS ALLOYS
    • C22F1/00Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
    • C22F1/04Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon
    • C22F1/057Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon of alloys with copper as the next major constituent

Definitions

  • Aluminum alloys are useful in a variety of applications. However, improving one property of an aluminum alloy without degrading another property often proves 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 crack growth rate resistance, to name two.
  • a method comprises artificially aging a 2xxx aluminum alloy in at least two-steps (“two-step artificial aging”).
  • the artificial aging comprises (a) first aging a 2xxx aluminum alloy at a first temperature of from 300°F to 450°F and for a first aging time of from 4 to 120 hours, and (b) second aging the 2xxx aluminum alloy at a second temperature for a second aging time of from 30 minutes to 120 hours, wherein the second temperature is from 20°F to 150°F lower than the first temperature.
  • the new two-step artificial aging step may facilitate an improved combination of properties, such as an improved combination of two or more of strength, ductility, fracture toughness, and corrosion resistance.
  • the 2xxx aluminum alloy is (i) LT stress corrosion cracking resistant (defined below), (ii) ST stress corrosion cracking resistant (defined below), or (iii) both LT stress corrosion cracking resistant and ST stress corrosion cracking resistant. Additional details are provided in the sections that follow. i. Composition
  • a 2xxx aluminum alloy comprises (and in some instances consists essentially of, or consists of) from 0.08 to 0.20 wt. % Ti, from 4.5 to 5.5 wt. % Cu, from 0.20 to 0.6 wt. % Mn, from 0.20 to 0.8 wt. % Mg, from 0.05 to 0.60 wt. % Ag, up to 1.0 wt.
  • the 2xxx aluminum alloy is a 2039 alloy (as defined by the Aluminum Association Teal Sheets document, described below) modified to include 0.08 to 0.20 wt. % Ti, such as any of the titanium limits/ranges described below.
  • the 2xxx aluminum alloy is a 2039 alloy modified to include 0.08 to 0.20 wt. % Ti and from 0 to 0.10 wt. % Zr.
  • the teachings of this paragraph also apply to other 2x39 alloys, such as 2139.
  • the 2xxx aluminum alloys described herein may realize an improved combination of at least two of strength, ductility, fracture toughness, and corrosion resistance (e.g., stress corrosion cracking resistance), among others.
  • the 2xxx aluminum alloys generally include 0.08 to 0.20 wt. % Ti.
  • the use of titanium in combination with other elements of the 2xxx aluminum alloys may result in 2xxx aluminum alloys products having an improved combination of properties, such as an improved combination of two or more of strength, ductility (elongation), fracture toughness and corrosion resistance (e.g., stress corrosion cracking resistance), among others.
  • the amount of titanium present in the 2xxx aluminum alloys should be limited such that large primary particles do not form in the alloy.
  • a 2xxx aluminum alloy includes at least 0.09 wt. % Ti.
  • a 2xxx aluminum alloy includes at least 0.10 wt. % Ti.
  • a 2xxx aluminum alloy includes at least 0.11 wt. % Ti. In one embodiment, a 2xxx aluminum alloy includes not greater than 0.18 wt. % Ti. In another embodiment, a 2xxx aluminum alloy includes not greater than 0.16 wt. % Ti. In yet another embodiment, a 2xxx aluminum alloy includes not greater than 0.15 wt. % Ti. In another embodiment, a 2xxx aluminum alloy includes not greater than 0.14 wt. % Ti. In yet another embodiment, a 2xxx aluminum alloy includes not greater than 0.13 wt. % Ti. The titanium may facilitate improved stress corrosion cracking resistance properties while also facilitating, for instance, grain refining, among other things.
  • Titanium may be added as a separate element and/or as part of a grain refining compound.
  • grain refiners include Ti combined with B (e.g., TiB 2 ) or carbon (TiC), although other grain refiners, such as Al-Ti master alloys may be utilized.
  • Grain refiners in combination with elemental titanium may be used in the 2xxx aluminum alloys in any appropriate amount, and generally depending on the desired as-cast grain size.
  • a 2xxx aluminum alloy may include from 4.5 to 5.5 wt. % Cu.
  • a 2xxx aluminum alloy includes at least 4.6 wt. % Cu.
  • a 2xxx aluminum alloy includes at least 4.7 wt. % Cu.
  • a 2xxx aluminum alloy includes at least 4.8 wt. % Cu.
  • a 2xxx aluminum alloy includes not greater than 5.4 wt. % Cu.
  • a 2xxx aluminum alloy includes not greater than 5.3 wt. % Cu.
  • a 2xxx aluminum alloy includes not greater than 5.2 wt. % Cu.
  • a 2xxx aluminum alloy includes not greater than 5.1 wt. % Cu.
  • a 2xxx aluminum alloy includes not greater than 5.0 wt. % Cu.
  • a 2xxx aluminum alloy may include from 0.20 to 0.6 wt. % Mn.
  • a 2xxx aluminum alloy includes at least 0.25 wt. % Mn.
  • a 2xxx aluminum alloy includes at least 0.30 wt. % Mn.
  • a 2xxx aluminum alloy includes not greater than 0.55 wt. % Mn.
  • a 2xxx aluminum alloy includes not greater than 0.50 wt. % Mn.
  • a 2xxx aluminum alloy includes not greater than 0.45 wt. % Mn.
  • a 2xxx aluminum alloy includes not greater than 0.40 wt. % Mn.
  • a 2xxx aluminum alloy may include from 0.20 to 0.6 wt. % Mg. In one embodiment, a 2xxx aluminum alloy includes at least 0.25 wt. % Mg. In another embodiment, a 2xxx aluminum alloy includes at least 0.30 wt. % Mg. In one embodiment, a 2xxx aluminum alloy includes not greater than 0.55 wt. % Mg. In another embodiment, a 2xxx aluminum alloy includes not greater than 0,50 wt. % Mg.
  • a 2xxx aluminum alloy may include from 0.05 to 0.6 wt. % Ag.
  • a 2xxx aluminum alloy includes at least 0.10 wt. % Ag.
  • a 2xxx aluminum alloy includes at least 0.15 wt. % Ag.
  • a 2xxx aluminum alloy includes at least 0.20 wt. % Ag.
  • a 2xxx aluminum alloy includes at least 0.25 wt. % Ag.
  • a 2xxx aluminum alloy includes at least 0.30 wt. % Ag.
  • a 2xxx aluminum alloy includes not greater than 0.55 wt. % Ag.
  • a 2xxx aluminum alloy includes not greater than 0.50 wt. % Ag. In yet another embodiment, a 2xxx aluminum alloy includes not greater than 0.45 wt. % Ag. In another embodiment, a 2xxx aluminum alloy includes not greater than 0.40 wt. % Ag. [0011] As noted above, a 2xxx aluminum alloy may include up to 1.0 wt. % Zn. In one embodiment, a 2xxx aluminum alloy includes at least 0.10 wt. % Zn. In another embodiment, a 2xxx aluminum alloy includes at least 0.20 wt. % Zn. In yet another embodiment, a 2xxx aluminum alloy includes at least 0.30 wt. % Zn.
  • a 2xxx aluminum alloy includes at least 0.40 wt. % Zn. In yet another embodiment, a 2xxx aluminum alloy includes at least 0.50 wt. % Zn. In one embodiment, a 2xxx aluminum alloy includes not greater than 0.90 wt. % Zn. In another embodiment, a 2xxx aluminum alloy includes not greater than 0.80 wt. % Zn. In yet another embodiment, a 2xxx aluminum alloy includes not greater than 0.70 wt. % Zn. In another embodiment, a 2xxx aluminum alloy includes not greater than 0.60 wt. % Zn.
  • a 2xxx aluminum alloy may include up to 0.25 wt. % Zr.
  • the combination of both (a) elevated levels of titanium, and (b) use of zirconium may facilitate the realization of improved 2xxx aluminum alloy products having an improved combination of at least two of strength, elongation, fracture toughness and corrosion resistance (e.g., stress corrosion cracking resistance), among others.
  • a 2xxx aluminum alloy includes at least 0.05 wt. % Zr.
  • a 2xxx aluminum alloy includes at least 0.06 wt. % Zr.
  • a 2xxx aluminum alloy includes at least 0.07 wt. % Zr.
  • a 2xxx aluminum alloy includes at least 0.08 wt. % Zr. In one embodiment, a 2xxx aluminum alloy includes not greater than 0.18 wt. % Zr. In another embodiment, a 2xxx aluminum alloy includes not greater than 0.16 wt. % Zr. In yet another embodiment, a 2xxx aluminum alloy includes not greater than 0.15 wt. % Zr. In another embodiment, a 2xxx aluminum alloy includes not greater than 0.14 wt. % Zr. In yet another embodiment, a 2xxx aluminum alloy includes not greater than 0.13 wt. % Zr. In another embodiment, a 2xxx aluminum alloy includes not greater than 0.12 wt. % Zr.
  • a 2xxx aluminum alloy includes not greater than 0.11 wt. % Zr. In another embodiment, a 2xxx aluminum alloy includes not greater than 0.10 wt. % Zr. In yet another embodiment, a 2xxx aluminum alloy includes not greater than 0.09 wt. % Zr. In another embodiment, a 2xxx aluminum alloy includes not greater than 0.08 wt. % Zr.
  • a 2xxx aluminum alloy may include up to 0.30 wt. % Fe.
  • a 2xxx aluminum alloy includes at least 0.01 wt. % Fe.
  • a 2xxx aluminum alloy includes at least 0.02 wt. % Fe.
  • a 2xxx aluminum alloy includes not greater than 0.25 wt. % Fe.
  • a 2xxx aluminum alloy includes not greater than 0.20 wt. % Fe.
  • a 2xxx aluminum alloy includes not greater than 0.15 wt. % Fe.
  • a 2xxx aluminum alloy includes not greater than 0.10 wt. % Fe.
  • a 2xxx aluminum alloy includes not greater than 0.08 wt. % Fe. In another embodiment, a 2xxx aluminum alloy includes not greater than 0.06 wt. % Fe. In yet another embodiment, a 2xxx aluminum alloy includes not greater than 0.04 wt. % Fe.
  • a 2xxx aluminum alloy may include up to 0.20 wt. % Si.
  • a 2xxx aluminum alloy includes at least 0.01 wt. % Si.
  • a 2xxx aluminum alloy includes at least 0.02 wt. % Si.
  • a 2xxx aluminum alloy includes not greater than 0.15 wt. % Si.
  • a 2xxx aluminum alloy includes not greater than 0.10 wt. % Si.
  • a 2xxx aluminum alloy includes not greater than 0.07 wt. % Si.
  • a 2xxx aluminum alloy includes not greater than 0.05 wt. % Si.
  • a 2xxx aluminum alloy includes not greater than 0.03 wt. % Si.
  • a 2xxx aluminum alloy may include up to 0.25 wt. % Cr.
  • a 2xxx aluminum alloy includes not greater than 0.20 wt. % Cr.
  • a 2xxx aluminum alloy includes not greater than 0.15 wt. % Cr.
  • a 2xxx aluminum alloy includes not greater than 0.10 wt. % Cr.
  • a 2xxx aluminum alloy includes not greater than 0.05 wt. % Cr.
  • a 2xxx aluminum alloy includes not greater than 0.03 wt. % Cr.
  • a 2xxx aluminum alloy includes not greater than 0.01 wt. % Cr.
  • a 2xxx aluminum alloy may include up to 0.25 wt. % V.
  • a 2xxx aluminum alloy includes not greater than 0.20 wt. % V.
  • a 2xxx aluminum alloy includes not greater than 0.15 wt. % V.
  • a 2xxx aluminum alloy includes not greater than 0.10 wt. % V.
  • a 2xxx aluminum alloy includes not greater than 0.05 wt. % V.
  • a 2xxx aluminum alloy includes not greater than 0.03 wt. % V.
  • a 2xxx aluminum alloy includes not greater than 0.01 wt. % V.
  • the 2xxx aluminum alloy is a 2039 aluminum alloy modified to include 0.08 to 0.20 wt. % Ti, such as any of the titanium limits/ranges described above.
  • a 2039 aluminum alloy comprises 4.5 to 5.5 wt. % Cu, 0.20 to 0.50 wt. % Mn, 0.40 to 0.8 wt. % Mg, 0.05 to 0.50 wt. % Ag, 0.10 to 0.25 wt. % Zr, up to 0.20 wt. % Si, up to 0.30 wt. % Fe, up to 0.15 wt.
  • the 2xxx aluminum alloy is a 2139 aluminum alloy modified to include 0.08 to 0.20 wt. % Ti, such as any of the titanium limits/ranges described above.
  • a 2139 aluminum alloy comprises 4.5 to 5.5 wt. % Cu, 0.20 to 0.6 wt. % Mn, 0.20 to 0.8 wt. % Mg, 0.15 to 0.60 wt. % Ag, up to 0.10 wt. % Si, up to 0.15 wt. % Fe, up to 0.05 wt. % Cr, up to 0.25 wt. % Zn, up to 0.15 wt.
  • a 2039 aluminum alloy or 2139 aluminum alloy is modified to include from 0.08 to 0.20 wt. % Ti, such as any of the titanium limits/ranges described above (“a modified 2039/2139 aluminum alloy”), and is further modified to include zinc (Zn).
  • a modified 2039/2139 aluminum alloy includes from 0.08 to 0.20 wt. % Ti and includes from 0.10 to 1.0 wt. % Zn.
  • a modified 2039/2139 aluminum alloy includes at least 0.20 wt. % Zn.
  • a modified 2039/2139 aluminum alloy includes at least 0.30 wt. % Zn.
  • a modified 2039/2139 aluminum alloy includes at least 0.40 wt.
  • a modified 2039/2139 aluminum alloy includes at least 0.50 wt. % Zn. In one embodiment, a modified 2039/2139 aluminum alloy includes not greater than 0.90 wt. % Zn. In another embodiment, a modified 2039/2139 aluminum alloy includes not greater than 0.80 wt. % Zn. In another embodiment, a modified 2039/2139 aluminum alloy includes not greater than 0.70 wt. % Zn. In another embodiment, a modified 2039/2139 aluminum alloy includes not greater than 0.60 wt. % Zn.
  • a 2039/2139 aluminum alloy is modified to include from 0.08 to 0.20 wt. % Ti, such as any of the titanium limits/ranges described above (“a modified 2139 aluminum alloy”), and is further modified to include appropriate amounts of zirconium. (2039, as specified by the Aluminum Association Teal Sheets, includes 0.10 - 0.25 wt.
  • % Zr, and 2139 as specified by the Aluminum Association Teal Sheets, includes zirconium as an impurity only.
  • the combination of both (a) elevated levels of titanium, and (b) use of zirconium may facilitate the realization of improved 2039/2139 aluminum alloy products having an improved combination of at least two of strength, elongation, fracture toughness and corrosion resistance (e.g., stress corrosion cracking resistance), among others.
  • a modified 2039/2139 aluminum alloy includes from 0.05 to 0.20 wt. % Zr.
  • a modified 2039/2139 aluminum alloy includes at least 0.06 wt. % Zr.
  • a modified 2039/2139 aluminum alloy includes at least 0.07 wt. % Zr.
  • a modified 2039/2139 aluminum alloy includes at least 0.08 wt. % Zr. In one embodiment, a modified 2039/2139 aluminum alloy includes not greater than 0.18 wt. % Zr. In another embodiment, a modified 2039/2139 aluminum alloy includes not greater than 0.16 wt. % Zr. In another embodiment, a modified 2039/2139 aluminum alloy includes not greater than 0.15 wt. % Zr. In yet another embodiment, a modified 2039/2139 aluminum alloy includes not greater than 0.14 wt. % Zr. In another embodiment, a modified 2039/2139 aluminum alloy includes not greater than 0.13 wt. % Zr. In another embodiment, a modified 2039/2139 aluminum alloy includes not greater than 0.12 wt.
  • a modified 2039/2139 aluminum alloy includes not greater than 0.11 wt. % Zr. In yet another embodiment, a modified 2039/2139 aluminum alloy includes not greater than 0.10 wt. % Zr. In another embodiment, a modified 2039/2139 aluminum alloy includes not greater than 0.09 wt. % Zr. In another embodiment, a modified 2039/2139 aluminum alloy includes not greater than 0.08 wt. % Zr. In one embodiment, a modified 2039/2139 aluminum alloy includes from 0.05 wt. % to 0.15 wt. % Zr. In another embodiment, a modified 2039/2139 aluminum alloy includes from 0.07 wt. % to 0.14 wt. % Zr.
  • a modified 2039/2139 aluminum alloy includes from 0.08 wt. % to 0.13 wt. % Zr.
  • the amount of zirconium present in the 2xxx aluminum alloys should be limited such that large primary particles do not form in the alloy.
  • a 2139 aluminum alloy is modified to include from 0.08 to 0.20 wt. % Ti, such as any of the titanium limits/ranges described above (“a modified 2139 aluminum alloy”), and is further modified to include zirconium, such as any of the zirconium limits/ranges described above, and is further modified to include zinc, such as any of the zinc limits/ranges described above.
  • the alloys generally include the stated alloying ingredients, the balance being aluminum, optional incidental elements, and impurities.
  • incidental elements means those elements or materials, other than the above listed elements, that may optionally be added to the alloy to assist in the production of the alloy.
  • incidental elements include casting aids, such as grain refiners and deoxidizers.
  • Optional incidental elements may be included in the alloy in a cumulative amount of up to 1.0 wt. %.
  • one or more incidental elements may be added to the alloy during casting to reduce or restrict (and in some instances eliminate) ingot cracking due to, for example, oxide fold, pit and oxide patches.
  • deoxidizers These types of incidental elements are generally referred to herein as deoxidizers.
  • deoxidizers include Ca, Sr, and Be.
  • Ca calcium
  • Sr calcium
  • Be Be
  • Ca calcium
  • Ca is included in the alloy in an amount of 0.001-0.03 wt. % or 0.05 wt. %, such as 0.001-0.008 wt. % (or 10 to 80 ppm).
  • Strontium (Sr) may be included in the alloy as a substitute for Ca (in whole or in part), and thus may be included in the alloy in the same or similar amounts as Ca.
  • Be beryllium
  • some embodiments of the alloy are substantially Be-free.
  • Be is included in the alloy, it is generally present in an amount of up to 20 ppm.
  • Incidental elements may be present in minor amounts, or may be present in significant amounts, and may add desirable or other characteristics on their own without departing from the alloy described herein, so long as the alloy retains the desirable characteristics described herein. It is to be understood, however, that the scope of this disclosure should not/cannot be avoided through the mere addition of an element or elements in quantities that would not otherwise impact on the combinations of properties desired and attained herein.
  • the 2xxx aluminum alloys generally contain low amounts of impurities.
  • a 2xxx aluminum alloy includes not greater than 0.15 wt. %, in total, of the impurities, and wherein the 2xxx aluminum alloy includes not greater than 0.05 wt. % of each of the impurities.
  • a 2xxx aluminum alloy includes not greater than 0.10 wt. %, in total, of the impurities, and wherein the 2xxx aluminum alloy includes not greater than 0.03 wt. % of each of the impurities.
  • the new alloys may be useful in a variety of product forms, including ingot or billet, wrought product forms (plate, forgings and extrusions), shape castings, additively manufactured products, and powder metallurgy products, for instance.
  • a new 2xxx aluminum alloy is in the form of a thick wrought product.
  • Thick wrought aluminum alloy products are those wrought products having a cross- sectional thickness of at least 12.7 mm.
  • the wrought products may be rolled products, forged products or extruded products.
  • a thick wrought aluminum alloy product has a thickness of at least 25 mm.
  • a thick wrought aluminum alloy product has a thickness of at least 38 mm.
  • a thick wrought aluminum alloy product has a thickness of at least 50 mm.
  • a thick wrought aluminum alloy product has a thickness of at least 76 mm.
  • a thick wrought aluminum alloy product has a thickness of at least 102 mm, or higher.
  • a thick wrought aluminum alloy product has a thickness of not greater than 254 mm.
  • a thick wrought aluminum alloy product has a thickness of not greater than 203 mm.
  • a thick wrought aluminum alloy product has a thickness of not greater than 178 mm.
  • a thick wrought aluminum alloy product has a thickness of not greater than 152 mm.
  • thickness refers to the minimum thickness of the product, realizing that some portions of the product may realize slightly larger thicknesses than the minimum stated.
  • a new 2xxx aluminum alloy is a thin wrought product having a thickness of less than 12.7 mm.
  • Thin wrought products have a thickness of less than 12.7 mm.
  • a thin wrought product has a thickness of from 0.5 mm to 12.6 mm.
  • a thin wrought product has a thickness of from 1.0 mm to 12.6 mm.
  • a thin wrought product has a thickness of from 2.0 mm to 12.6 mm.
  • a thin wrought product has a thickness of from 3.0 mm to 12.6 mm.
  • a thin wrought product has a thickness of from 4.0 mm to 12.6 mm.
  • a thin wrought product has a thickness of from 5.0 mm to 12.6 mm. In yet another embodiment, a thin wrought product has a thickness of from 6.0 mm to 12.6 mm. In another embodiment, a thin wrought product has a thickness of from 7.0 mm to 12.6 mm. In yet another embodiment, a thin wrought product has a thickness of from 8.0 mm to 12.6 mm.
  • a method comprises artificially aging a 2xxx aluminum alloy in at least two-steps (“two-step artificial aging”).
  • two-step artificial aging As shown below, 2xxx aluminum alloys aged using a first step aging practice of 350°F for 24 hours and a second step aging practice of 270°F for 24 hours realized an unexpected combination of at least two of strength, ductility, fracture toughness, and corrosion resistance.
  • aging temperatures and/or times may be adjusted based on well-known aluminum alloy aging principles and/or formulas.
  • some embodiments disclosed herein are directed to first artificially aging at 350°F for 24 hours, or a substantially equivalent artificial aging temperature and duration, and second artificially aging at 270°F for 24 hours, or a substantially equivalent artificial aging temperature and duration.
  • the amount of artificial aging practices that could achieve the same result as this specific practice is numerous, and therefore all such substitute aging practices are not listed herein, even though they are within the scope of the present invention.
  • the use of the phrase “or a substantially equivalent artificial aging temperature and duration” or the phrase “or a substantially equivalent practice” is used to capture all such substitute aging practices.
  • these substitute artificial aging steps can occur in one or multiple steps, and at one or multiple temperatures. That is, multiple sub-steps may be used to accomplish the first aging step and/or the second aging step, which sub-steps may include age integration.
  • the artificial aging practice consists only of two-steps, i.e., no additional artificial aging steps are completed after the second artificial aging step.
  • an artificial aging practice comprises (a) first aging a 2xxx aluminum alloy at a first temperature of from 300°F to 450°F and for a first aging time of from 4 to 120 hours, and (b) second aging the 2xxx aluminum alloy at a second temperature for a second aging time of from 30 minutes to 120 hours, wherein the second temperature is from 20°F to 150°F lower than the first temperature.
  • the 2xxx aluminum alloy is (i) LT stress corrosion cracking resistant (defined below), (ii) ST stress corrosion cracking resistant (defined below), or (iii) both LT stress corrosion cracking resistant and ST stress corrosion cracking resistant.
  • the first step of the artificial aging process generally comprises aging the 2xxx aluminum alloy at a first temperature for a first period of time, such as from 300°F to 450°F and for a first aging time of from 4 to 120 hours.
  • the first temperature is at least 310°F.
  • the first temperature is at least 320°F.
  • the first temperature is at least 330°F.
  • the first temperature is at least 340°F.
  • the first temperature is at least 350°F.
  • the first temperature is not greater than 440°F.
  • the first temperature is not greater than 430°F.
  • the first temperature is not greater than 420°F.
  • the first temperature is not greater than 410°F. In yet another embodiment, the first temperature is not greater than 400°F. In another embodiment, the first temperature is not greater than 390°F. In yet another embodiment, the first temperature is not greater than 380°F. In another embodiment, the first temperature is not greater than 370°F.
  • the first period of time of the first artificial aging step i.e., the first aging time
  • the first aging time is at least 12 hours.
  • the first aging time is at least 16 hours. In another embodiment, the first aging time is at least 20 hours. In yet another embodiment, the first aging time is at least 24 hours.
  • the first aging time is not greater than 96 hours. In another embodiment, the first aging time is not greater than 72 hours. In yet another embodiment, the first aging time is not greater than 48 hours. In another embodiment, the first aging time is not greater than 40 hours. In yet another embodiment, the first aging time is not greater than 36 hours. In another embodiment, the first aging time is not greater than 32 hours. In yet another embodiment, the first aging time is not greater than 28 hours.
  • the first temperature is from 330°F to 370°F and the first aging time is from 12 to 36 hours.
  • the amount of time of the first step is determined according to an equivalent time at 350°F.
  • the first step time (t1 actual ) is in accordance with the below formula: wherein (a) is the actual temperature of the first step in Fahrenheit, wherein from 300 to 450°F, (b) t1 actual is the actual amount of time at the first temperature, wherein t1 actual is from 10 to 120 hours, and (c) t1 350°F eq . is the equivalent amount of time at a first step temperature of 350°F.
  • t1 350°F eq. is from 20 to 30 hours. In one embodiment, t1 350°F eq. is at least 20.5 hours. In another embodiment, t1 350°F eq. is at least 21 hours. In yet another embodiment, least 21.5 hours. In another embodiment, t1 350°F eq. is at least 22 hours. In yet another embodiment, t1 350°F eq. is at least 22.5 hours. In another embodiment, t1 350°F eq. is at least 23 hours. In yet another embodiment, t1 350°F eq. is at least 23.5 hours. In another embodiment, t1 350°F eq. is at least 24 hours.
  • t1 350°F eq. is not greater than 29 hours. In another embodiment, t1 350°F eq. is not greater than 28 hours. In yet another embodiment, t1 350°F eq. is not greater than 27 hours. In another embodiment, t1 350°F eq. is not greater than 26 hours. In yet another embodiment, t1 350°F eq. is not greater than 25 hours. In another embodiment, t1 350°F eq. is not greater than 24.5 hours. In yet another embodiment, t1 350°F eq. is not greater than 24 hours. In one embodiment, t1 350°F eq. is from 20.5 to 24 hours. In another embodiment, t1 350°F eq.
  • the second step of the artificial aging process generally comprises aging the 2xxx aluminum alloy at a second temperature for a second period of time, such as at a temperature that is at least 20°F lower than, but not more than 150°F lower than, the first aging temperature and for a period of time of from 30 minutes to 120 hours.
  • the second aging temperature would be no higher than 330°F (i.e., 20°F lower than the first temperature), but the second aging temperature would be at least 200°F (i.e., not more than 150°F lower than the first aging temperature).
  • the second temperature is at least at least 30°F lower than the first temperature In another embodiment, the second temperature is at least 40°F lower than the first temperature. In yet another embodiment, the second temperature is at least 50°F lower than the first temperature. In another embodiment, the second temperature is at least 60°F lower than the first temperature. In yet another embodiment, the second temperature is at least 70°F lower than the first temperature. In another embodiment, the second temperature is at least 80°F lower than the first temperature. In one embodiment, the second temperature is not greater than 140°F lower than the first temperature. In another embodiment, the second temperature is not greater than 130°F lower than the first temperature. In yet another embodiment, the second temperature is not greater than 120°F lower than the first temperature. In another embodiment, the second temperature is not greater than 110°F lower than the first temperature. In yet another embodiment, the second temperature is not greater than 100°F lower than the first temperature.
  • the second period of time of the second artificial aging step (i.e., the second aging time) is at least 8 hours. In another embodiment, the second aging time is at least 12 hours. In yet another embodiment, the second aging time is at least 16 hours. In another embodiment, the second aging time is at least 20 hours. In yet another embodiment, the second aging time is at least 24 hours. In one embodiment, the second aging time is not greater than 96 hours. In another embodiment, the second aging time is not greater than 72 hours. In yet another embodiment, the second aging time is not greater than 48 hours. In another embodiment, the second aging time is not greater than 40 hours. In yet another embodiment, the second aging time is not greater than 36 hours. In another embodiment, the second aging time is not greater than 32 hours. In yet another embodiment, the second aging time is not greater than 28 hours.
  • the second aging temperature is from 250° to 290°F and the second aging time is from 12 to 36 hours.
  • the two-step aging practices described herein may be conducted in a conventional fashion, such as by the use of temperature controlled furnaces.
  • the 2xxx aluminum alloy is allowed to cool to room temperature (e.g., by turning off the furnace and/or removing the material from the furnace, after which the material is allowed to cool to room temperature.)
  • the material may then be reheated from room temperature to complete the second aging step, e.g., reheated to the second temperature of the second aging step.
  • the material is cooled from the first temperature to the second temperature.
  • the furnace set-point may be changed and/or the furnace may be turned off and allowed to cool to the second temperature, after which the second aging step is initiated (e.g., due to achievement of the second temperature). In this embodiment, cooling below the second step is not completed.
  • a method comprises preparing a 2xxx aluminum alloy for artificial aging.
  • the preparing step may include, for instance, casting a 2xxx aluminum alloy into an ingot or billet (e.g., via direct chill (DC) casting).
  • DC direct chill
  • the ingots/billets may be further processed by hot working the product.
  • the product may then be optionally cold worked, solution heat treated, quenched, and final cold worked (e.g., by stretching or compression of from 0.5% to 15%).
  • final cold working step the product may be artificially aged, as provided above.
  • the products may be produced in a T3 or T8 temper.
  • other T tempers may be used (e.g., any of a T1, T2, T4, T5, T6, T7 or T9 temper).
  • T tempers are defined in ANSI H35.1 (2009).
  • forming operations may be completed concomitant to artificial aging, for instance, by forming the alloy into a predetermined shaped product before artificial aging, during artificial aging, after artificial aging, and combinations thereof.
  • the accumulated amount of cold work completed after solution heat treatment may be higher, such as from 10-15% cold work, or more.
  • the wrought product may be solution heat treated and then optionally cold worked, such as by stretching.
  • a wrought product is processed to a T temper and part of that processing includes stretching by from 0.5 to 10% after solution heat treatment.
  • a wrought product is stretched at least 1% after solution heat treatment. In another embodiment, a wrought product is stretched at least 1.5% after solution heat treatment. In yet another embodiment, a wrought product is stretched at least 2% after solution heat treatment. In one embodiment, a wrought product is stretched not greater than 9% after solution heat treatment. In another embodiment, a wrought product is stretched not greater than 8% after solution heat treatment.
  • the new 2xxx aluminum alloys generally realize an improved combination of at least two of strength, elongation, fracture toughness, and corrosion resistance (e g., stress corrosion cracking resistance).
  • T8 temper is per ANSI H35.1(2009), and includes all artificial aging conditions, including underaged, peak or near peak aged, and overaged aging conditions.
  • a new 2xxx aluminum alloy has a thickness of at least 12.7 mm and realizes a tensile yield strength (L) of at least 390 MPa in the T8 temper.
  • a new 2xxx aluminum alloy has a thickness of at least 12.7 mm and realizes a tensile yield strength (L) of at least 400 MPa in the T8 temper.
  • a new 2xxx aluminum alloy has a thickness of at least 12.7 mm and realizes a tensile yield strength (L) of at least 410 MPa in the T8 temper.
  • a new 2xxx aluminum alloy has a thickness of at least 12.7 mm and realizes a tensile yield strength (L) of at least 420 MPa in the T8 temper.
  • a new 2xxx aluminum alloy has a thickness of at least 12.7 mm and realizes a tensile yield strength (L) of at least 430 MPa in the T8 temper.
  • a new 2xxx aluminum alloy has a thickness of at least 12.7 mm and realizes a tensile yield strength (L) of at least 440 MPa in the T8 temper.
  • a new 2xxx aluminum alloy has a thickness of at least 12.7 mm and realizes a tensile yield strength (L) of at least 450 MPa in the T8 temper.
  • a new 2xxx aluminum alloy has a thickness of at least 12.7 mm and realizes a tensile yield strength (L) of at least 460 MPa, or more, in the T8 temper.
  • the above strength properties may be realized in products having a thickness of at least 25 mm, or at least 38 mm, or at least 50 mm, or at least 76 mm, or at least 108 mm, or higher.
  • the above strength properties may be realized in thin wrought products having a thickness of 0.5 to 12.6 mm.
  • a new 2xxx aluminum alloy has a thickness of at least 12.7 mm and realizes a plane-strain (K IC ) fracture toughness (L-T) of at least 30 MPa-sqrt-m in the T8 temper.
  • a new 2xxx aluminum alloy has a thickness of at least 12.7 mm and realizes a plane-strain (K IC ) fracture toughness (L-T) of at least 31 MPa-sqrt-m in the T8 temper.
  • a new 2xxx aluminum alloy has a thickness of at least 12.7 mm and realizes a plane-strain (K IC ) fracture toughness (L-T) of at least 32 MPa-sqrt-m in the T8 temper.
  • a new 2xxx aluminum alloy has a thickness of at least 12.7 mm and realizes a plane-strain (K IC ) fracture toughness (L-T) of at least 33 MPa-sqrt-m in the T8 temper.
  • a new 2xxx aluminum alloy has a thickness of at least 12.7 mm and realizes a plane-strain (K IC ) fracture toughness (L-T) of at least 34 MPa-sqrt-m in the T8 temper.
  • a new 2xxx aluminum alloy has a thickness of at least 12.7 mm and realizes a plane-strain (K IC ) fracture toughness (L-T) of at least 35 MPa-sqrt-m in the T8 temper.
  • a new 2xxx aluminum alloy has a thickness of at least 12.7 mm and realizes a plane-strain (K IC ) fracture toughness (L-T) of at least 36 MPa-sqrt-m in the T8 temper.
  • a new 2xxx aluminum alloy has a thickness of at least 12.7 mm and realizes a plane-strain (K IC ) fracture toughness (L-T) of at least 37 MPa-sqrt-m in the T8 temper.
  • a new 2xxx aluminum alloy has a thickness of at least 12.7 mm and realizes a plane-strain (K IC ) fracture toughness (L-T) of at least 38 MPa-sqrt-m in the T8 temper.
  • a new 2xxx aluminum alloy has a thickness of at least 12.7 mm and realizes a plane-strain (K IC ) fracture toughness (L-T) of at least 39 MPa-sqrt-m in the T8 temper.
  • a new 2xxx aluminum alloy has a thickness of at least 12.7 mm and realizes a plane-strain (K IC ) fracture toughness (L-T) of at least 40 MPa-sqrt-m in the T8 temper.
  • a new 2xxx aluminum alloy has a thickness of at least 12.7 mm and realizes a plane-strain (K IC ) fracture toughness (L-T) of at least 41 MPa-sqrt-m in the T8 temper.
  • a new 2xxx aluminum alloy has a thickness of at least 12.7 mm and realizes a plane-strain (K IC ) fracture toughness (L-T) of at least 42 MPa-sqrt-m in the T8 temper.
  • a new 2xxx aluminum alloy has a thickness of at least 12.7 mm and realizes a plane-strain (K IC ) fracture toughness (L-T) of at least 43 MPa-sqrt-m in the T8 temper.
  • a new 2xxx aluminum alloy has a thickness of at least 12.7 mm and realizes a plane-strain (K IC ) fracture toughness (L-T) of at least 44 MPa-sqrt-m in the T8 temper.
  • a new 2xxx aluminum alloy has a thickness of at least 12.7 mm and realizes a plane-strain (K IC ) fracture toughness (L-T) of at least 45 MPa-sqrt-m in the T8 temper.
  • a new 2xxx aluminum alloy has a thickness of at least 12.7 mm and realizes a plane-strain (K IC ) fracture toughness (L-T) of at least 46 MPa-sqrt-m in the T8 temper.
  • a new 2xxx aluminum alloy has a thickness of at least 12.7 mm and realizes a plane-strain (K IC ) fracture toughness (L-T) of at least 47 MPa-sqrt-m in the T8 temper.
  • a new 2xxx aluminum alloy has a thickness of at least 12.7 mm and realizes a plane-strain (K IC ) fracture toughness (L-T) of at least 48 MPa-sqrt-m in the T8 temper.
  • a new 2xxx aluminum alloy has a thickness of at least 12.7 mm and realizes a plane-strain (K IC ) fracture toughness (L-T) of at least 49 MPa-sqrt-m in the T8 temper.
  • a new 2xxx aluminum alloy has a thickness of at least 12.7 mm and realizes a plane-strain (K IC ) fracture toughness (L-T) of at least 50 MPa-sqrt-m, or more, in the T8 temper.
  • K IC plane-strain
  • L-T fracture toughness
  • the above fracture toughness properties may be realized in products having a thickness of at least 25 mm, or at least 38 mm, or at least 50 mm, or at least 76 mm, or at least 108 mm, or higher.
  • the above fracture toughness properties may be realized in thin wrought products having a thickness of 0.5 to 12.6 mm.
  • a new 2xxx aluminum alloy has a thickness of at least 12.7 mm and realizes an elongation (L) of at least 6.0% in the T8 temper. In another embodiment, a new 2xxx aluminum alloy has a thickness of at least 12.7 mm and realizes an elongation (L) of at least 8.0% in the T8 temper. In yet another embodiment, a new 2xxx aluminum alloy has a thickness of at least 12.7 mm and realizes an elongation (L) of at least 10.0% in the T8 temper. In another embodiment, a new 2xxx aluminum alloy has a thickness of at least 12.7 mm and realizes an elongation (L) of at least 12.0% in the T8 temper.
  • a new 2xxx aluminum alloy has a thickness of at least 12.7 mm and realizes an elongation (L) of at least 14.0% in the T8 temper.
  • a new 2xxx aluminum alloy has a thickness of at least 12.7 mm and realizes an elongation (L) of at least 16.0%, or more, in the T8 temper.
  • the above elongation properties may be realized in products having a thickness of at least 25 mm, or at least 38 mm, or at least 50 mm, or at least 76 mm, or at least 108 mm, or higher.
  • the above elongation properties may be realized in thin wrought products having a thickness of 0.5 to 12.6 mm.
  • a new 2xxx aluminum alloy has a thickness of at least 12.7 mm and realizes a tensile yield strength (LT) of at least 390 MPa in the T8 temper.
  • a new 2xxx aluminum alloy has a thickness of at least 12.7 mm and realizes a tensile yield strength (LT) of at least 400 MPa in the T8 temper.
  • a new 2xxx aluminum alloy has a thickness of at least 12.7 mm and realizes a tensile yield strength (LT) of at least 410 MPa in the T8 temper.
  • a new 2xxx aluminum alloy has a thickness of at least 12.7 mm and realizes a tensile yield strength (LT) of at least 420 MPa in the T8 temper.
  • a new 2xxx aluminum alloy has a thickness of at least 12.7 mm and realizes a tensile yield strength (LT) of at least 430 MPa in the T8 temper.
  • a new 2xxx aluminum alloy has a thickness of at least 12.7 mm and realizes a tensile yield strength (LT) of at least 440 MPa in the T8 temper.
  • a new 2xxx aluminum alloy has a thickness of at least 12.7 mm and realizes a tensile yield strength (LT) of at least 450 MPa in the T8 temper.
  • a new 2xxx aluminum alloy has a thickness of at least 12.7 mm and realizes a tensile yield strength (LT) of at least 460 MPa, or more, in the T8 temper.
  • the above strength properties may be realized in products having a thickness of at least 25 mm, or at least 38 mm, or at least 50 mm, or at least 76 mm, or at least 108 mm, or higher.
  • the above strength properties may be realized in thin wrought products having a thickness of 0.5 to 12.6 mm.
  • a new 2xxx aluminum alloy has a thickness of at least 12.7 mm and realizes a plane-strain (K IC ) fracture toughness (T-L) of at least 30 MPa-sqrt-m in the T8 temper.
  • a new 2xxx aluminum alloy has a thickness of at least 12.7 mm and realizes a plane-strain (K IC ) fracture toughness (T-L) of at least 31 MPa-sqrt-m in the T8 temper.
  • a new 2xxx aluminum alloy has a thickness of at least 12.7 mm and realizes a plane-strain (K IC ) fracture toughness (T-L) of at least 32 MPa-sqrt-m in the T8 temper.
  • a new 2xxx aluminum alloy has a thickness of at least 12.7 mm and realizes a plane-strain (K IC ) fracture toughness (T-L) of at least 33 MPa-sqrt-m in the T8 temper.
  • a new 2xxx aluminum alloy has a thickness of at least 12.7 mm and realizes a plane-strain (K IC ) fracture toughness (T-L) of at least 34 MPa-sqrt-m in the T8 temper.
  • a new 2xxx aluminum alloy has a thickness of at least 12.7 mm and realizes a plane-strain (K IC ) fracture toughness (T-L) of at least 35 MPa-sqrt-m in the T8 temper.
  • a new 2xxx aluminum alloy has a thickness of at least 12.7 mm and realizes a plane-strain (K IC ) fracture toughness (T-L) of at least 36 MPa-sqrt-m in the T8 temper.
  • a new 2xxx aluminum alloy has a thickness of at least 12.7 mm and realizes a plane-strain (K IC ) fracture toughness (T-L) of at least 37 MPa-sqrt-m in the T8 temper.
  • a new 2xxx aluminum alloy has a thickness of at least 12.7 mm and realizes a plane-strain (K IC ) fracture toughness (T-L) of at least 38 MPa-sqrt-m in the T8 temper.
  • a new 2xxx aluminum alloy has a thickness of at least 12.7 mm and realizes a plane-strain (K IC ) fracture toughness (T-L) of at least 39 MPa-sqrt-m in the T8 temper.
  • a new 2xxx aluminum alloy has a thickness of at least 12.7 mm and realizes a plane-strain (K IC ) fracture toughness (T-L) of at least 40 MPa-sqrt-m in the T8 temper.
  • a new 2xxx aluminum alloy has a thickness of at least 12.7 mm and realizes a plane-strain (K IC ) fracture toughness (T-L) of at least 41 MPa-sqrt-m in the T8 temper.
  • a new 2xxx aluminum alloy has a thickness of at least 12.7 mm and realizes a plane-strain (K IC ) fracture toughness (T-L) of at least 42 MPa-sqrt-m in the T8 temper.
  • a new 2xxx aluminum alloy has a thickness of at least 12.7 mm and realizes a plane-strain (K IC ) fracture toughness (T-L) of at least 43 MPa-sqrt-m in the T8 temper.
  • a new 2xxx aluminum alloy has a thickness of at least 12.7 mm and realizes a plane-strain (K IC ) fracture toughness (T-L) of at least 44 MPa-sqrt-m in the T8 temper.
  • a new 2xxx aluminum alloy has a thickness of at least 12.7 mm and realizes a plane-strain (K IC ) fracture toughness (T-L) of at least 45 MPa-sqrt-m in the T8 temper.
  • a new 2xxx aluminum alloy has a thickness of at least 12.7 mm and realizes a plane-strain (K IC ) fracture toughness (T-L) of at least 46 MPa-sqrt-m in the T8 temper.
  • a new 2xxx aluminum alloy has a thickness of at least 12.7 mm and realizes a plane-strain (K IC ) fracture toughness (T-L) of at least 47 MPa-sqrt-m in the T8 temper.
  • a new 2xxx aluminum alloy has a thickness of at least 12.7 mm and realizes a plane-strain (K IC ) fracture toughness (T-L) of at least 48 MPa-sqrt-m in the T8 temper.
  • a new 2xxx aluminum alloy has a thickness of at least 12.7 mm and realizes a plane-strain (K IC ) fracture toughness (T-L) of at least 49 MPa-sqrt-m in the T8 temper.
  • a new 2xxx aluminum alloy has a thickness of at least 12.7 mm and realizes a plane-strain (K IC ) fracture toughness (T-L) of at least 50 MPa-sqrt-m, or more, in the T8 temper.
  • K IC plane-strain
  • T-L fracture toughness
  • the above fracture toughness properties may be realized in products having a thickness of at least 25 mm, or at least 38 mm, or at least 50 mm, or at least 76 mm, or at least 108 mm, or higher.
  • the above fracture toughness properties may be realized in thin wrought products having a thickness of 0.5 to 12.6 mm.
  • a new 2xxx aluminum alloy has a thickness of at least 12.7 mm and realizes an elongation (LT) of at least 6.0% in the T8 temper.
  • a new 2xxx aluminum alloy has a thickness of at least 12.7 mm and realizes an elongation (LT) of at least 8.0% in the T8 temper.
  • a new 2xxx aluminum alloy has a thickness of at least 12.7 mm and realizes an elongation (LT) of at least 10.0% in the T8 temper.
  • a new 2xxx aluminum alloy has a thickness of at least 12.7 mm and realizes an elongation (LT) of at least 12.0% in the T8 temper.
  • a new 2xxx aluminum alloy has a thickness of at least 12.7 mm and realizes an elongation (LT) of at least 14.0% in the T8 temper.
  • a new 2xxx aluminum alloy has a thickness of at least 12.7 mm and realizes an elongation (LT) of at least 16.0%, or more, in the T8 temper.
  • the above elongation properties may be realized in products having a thickness of at least 25 mm, or at least 38 mm, or at least 50 mm, or at least 76 mm, or at least 108 mm, or higher.
  • the above elongation properties may be realized in thin wrought products having a thickness of 0.5 to 12.6 mm.
  • a new 2xxx aluminum alloy has a thickness of at least 12.7 mm and realizes a tensile yield strength (ST) of at least 350 MPa in the T8 temper.
  • a new 2xxx aluminum alloy has a thickness of at least 12.7 mm and realizes a tensile yield strength (ST) of at least 360 MPa in the T8 temper.
  • a new 2xxx aluminum alloy has a thickness of at least 12.7 mm and realizes a tensile yield strength (ST) of at least 370 MPa in the T8 temper.
  • a new 2xxx aluminum alloy has a thickness of at least 12.7 mm and realizes a tensile yield strength (ST) of at least 380 MPa in the T8 temper.
  • a new 2xxx aluminum alloy has a thickness of at least 12.7 mm and realizes a tensile yield strength (ST) of at least 390 MPa in the T8 temper.
  • a new 2xxx aluminum alloy has a thickness of at least 12.7 mm and realizes a tensile yield strength (ST) of at least 400 MPa in the T8 temper.
  • a new 2xxx aluminum alloy has a thickness of at least 12.7 mm and realizes a tensile yield strength (ST) of at least 410 MPa in the T8 temper.
  • a new 2xxx aluminum alloy has a thickness of at least 12.7 mm and realizes a tensile yield strength (ST) of at least 420 MPa, or more, in the T8 temper.
  • the above strength properties may be realized in products having a thickness of at least 25 mm, or at least 38 mm, or at least 50 mm, or at least 76 mm, or at least 108 mm, or higher.
  • the above strength properties may be realized in thin wrought products having a thickness of 7.0 to 12.6 mm.
  • a new 2xxx aluminum alloy has a thickness of at least 12.7 mm and realizes a plane-strain (K IC ) fracture toughness (S-L) of at least 30 MPa-sqrt-m in the T8 temper.
  • a new 2xxx aluminum alloy has a thickness of at least 12.7 mm and realizes a plane-strain (K IC ) fracture toughness (S-L) of at least 31 MPa-sqrt-m in the T8 temper.
  • a new 2xxx aluminum alloy has a thickness of at least 12.7 mm and realizes a plane-strain (K IC ) fracture toughness (S-L) of at least 32 MPa-sqrt-m in the T8 temper.
  • a new 2xxx aluminum alloy has a thickness of at least 12.7 mm and realizes a plane-strain (K IC ) fracture toughness (S-L) of at least 33 MPa-sqrt-m in the T8 temper.
  • a new 2xxx aluminum alloy has a thickness of at least 12.7 mm and realizes a plane-strain (K IC ) fracture toughness (S-L) of at least 34 MPa-sqrt-m in the T8 temper.
  • a new 2xxx aluminum alloy has a thickness of at least 12.7 mm and realizes a plane-strain (K IC ) fracture toughness (S-L) of at least 35 MPa-sqrt-m in the T8 temper.
  • a new 2xxx aluminum alloy has a thickness of at least 12.7 mm and realizes a plane-strain (K IC ) fracture toughness (S-L) of at least 36 MPa-sqrt-m in the T8 temper.
  • a new 2xxx aluminum alloy has a thickness of at least 12.7 mm and realizes a plane-strain (K IC ) fracture toughness (S-L) of at least 37 MPa-sqrt-m in the T8 temper.
  • a new 2xxx aluminum alloy has a thickness of at least 12.7 mm and realizes a plane-strain (K IC ) fracture toughness (S-L) of at least 38 MPa-sqrt-m in the T8 temper.
  • a new 2xxx aluminum alloy has a thickness of at least 12.7 mm and realizes a plane-strain (K IC ) fracture toughness (S-L) of at least 39 MPa-sqrt-m in the T8 temper.
  • a new 2xxx aluminum alloy has a thickness of at least 12.7 mm and realizes a plane-strain (K IC ) fracture toughness (S-L) of at least 40 MPa-sqrt-m in the T8 temper.
  • a new 2xxx aluminum alloy has a thickness of at least 12.7 mm and realizes a plane-strain (K IC ) fracture toughness (S-L) of at least 41 MPa-sqrt-m in the T8 temper.
  • a new 2xxx aluminum alloy has a thickness of at least 12.7 mm and realizes a plane-strain (K IC ) fracture toughness (S-L) of at least 42 MPa-sqrt-m in the T8 temper.
  • a new 2xxx aluminum alloy has a thickness of at least 12.7 mm and realizes a plane-strain (K IC ) fracture toughness (S-L) of at least 43 MPa-sqrt-m in the T8 temper.
  • a new 2xxx aluminum alloy has a thickness of at least 12.7 mm and realizes a plane-strain (K IC ) fracture toughness (S-L) of at least 44 MPa-sqrt-m in the T8 temper.
  • a new 2xxx aluminum alloy has a thickness of at least 12.7 mm and realizes a plane-strain (K IC ) fracture toughness (S-L) of at least 45 MPa-sqrt-m in the T8 temper.
  • a new 2xxx aluminum alloy has a thickness of at least 12.7 mm and realizes a plane-strain (K IC ) fracture toughness (S-L) of at least 46 MPa-sqrt-m in the T8 temper.
  • a new 2xxx aluminum alloy has a thickness of at least 12.7 mm and realizes a plane-strain (K IC ) fracture toughness (S-L) of at least 47 MPa-sqrt-m in the T8 temper.
  • a new 2xxx aluminum alloy has a thickness of at least 12.7 mm and realizes a plane-strain (K IC ) fracture toughness (S-L) of at least 48 MPa-sqrt-m in the T8 temper.
  • a new 2xxx aluminum alloy has a thickness of at least 12.7 mm and realizes a plane-strain (K IC ) fracture toughness (S-L) of at least 49 MPa-sqrt-m in the T8 temper.
  • a new 2xxx aluminum alloy has a thickness of at least 12.7 mm and realizes a plane-strain (K IC ) fracture toughness (S-L) of at least 50 MPa-sqrt-m, or more, in the T8 temper.
  • K IC plane-strain
  • S-L fracture toughness
  • the above fracture toughness properties may be realized in products having a thickness of at least 25 mm, or at least 38 mm, or at least 50 mm, or at least 76 mm, or at least 108 mm, or higher.
  • the above fracture toughness properties may be realized in thin wrought products having a thickness of 7.0 to 12.6 mm.
  • a new 2xxx aluminum alloy has a thickness of at least 12.7 mm and realizes an elongation (ST) of at least 3.0% in the T8 temper. In another embodiment, a new 2xxx aluminum alloy has a thickness of at least 12.7 mm and realizes an elongation (ST) of at least 4.0% in the T8 temper. In yet another embodiment, a new 2xxx aluminum alloy has a thickness of at least 12.7 mm and realizes an elongation (ST) of at least 5.0% in the T8 temper. In another embodiment, a new 2xxx aluminum alloy has a thickness of at least 12.7 mm and realizes an elongation (ST) of at least 6.0% in the T8 temper.
  • a new 2xxx aluminum alloy has a thickness of at least 12.7 mm and realizes an elongation (ST) of at least 7.0% in the T8 temper.
  • ST elongation
  • the above elongation properties may be realized in products having a thickness of at least 25 mm, or at least 38 mm, or at least 50 mm, or at least 76 mm, or at least 108 mm, or higher.
  • the above elongation properties may be realized in thin wrought products having a thickness of 7.0 to 12.6 mm.
  • a new 2xxx aluminum alloy has a thickness of at least 12.7 mm and is LT stress corrosion cracking resistant (defined below) in the T8 temper.
  • the LT stress corrosion cracking resistance properties may be realized in products having a thickness of at least 25 mm, or at least 38 mm, or at least 50 mm, or at least 76 mm, or at least 108 mm, or higher.
  • the LT stress corrosion cracking resistance properties may be realized in thin wrought products having a thickness of 0.5 to 12.6 mm.
  • a new 2xxx aluminum alloy has a thickness of at least 12.7 mm and is ST stress corrosion cracking resistant (defined below) in the T8 temper.
  • the ST stress corrosion cracking resistance properties may be realized in products having a thickness of at least 25 mm, or at least 38 mm, or at least 50 mm, or at least 76 mm, or at least 108 mm, or higher.
  • the ST stress corrosion cracking resistance properties may be realized in thin wrought products having a thickness of 7.0 to 12.6 mm.
  • a new 2xxx aluminum alloy has a thickness of at least 12.7 mm and is both LT stress corrosion cracking resistant and ST stress corrosion cracking resistant in the T8 temper.
  • 2xxx aluminum alloys are aluminum alloys compositions having copper as the maj or alloying element as per the Aluminum Association definition provided in "International Alloy Designations and Chemical Composition Limits for Wrought Aluminum and Wrought Aluminum Alloys,” a.k.a. the “Teal Sheets” (2015).
  • 2xxx aluminum alloy compositions may be used in non-wrought products, such as in shape castings, ingot/billet, and additively manufactured products, among others.
  • the 2xxx aluminum alloys of the present patent application are generally lithium-free, having less than 0,05 wt. % Li, and generally less than 0.03 wt. % Li, or less than 0.01 wt. % Li.
  • “Wrought aluminum alloy product” means an aluminum alloy product that is hot worked after casting, and includes rolled products (sheet or plate), forged products, and extruded products.
  • Formged aluminum alloy product means a wrought aluminum alloy product that is either die forged or hand forged.
  • Solution heat treating means exposure of an aluminum alloy to elevated temperature for the purpose of placing solute(s) into solid solution.
  • Hot working such as by hot rolling means working the aluminum alloy product at elevated temperature. Strain-hardening is restricted I avoided during hot working, which generally differentiates hot working from cold working.
  • Cold working such as by cold rolling means working the aluminum alloy product at temperatures that are not considered hot working temperatures.
  • Temper definitions are per ANSI H35.1 (2009), entitled “American National Standard Alloy and Temper Designation Systems for Aluminum,” published by The Aluminum Association.
  • LT Stress corrosion cracking resistant means that at least two-out-of-three specimens of a 2xxx aluminum alloy product do not fail after 60 days of alternate immersion testing at a net stress of 300 MPa in the LT direction and in accordance with ASTM G47 using constant-strain type stressing frame fixtures according to Figure 4 of ASTM G49, and with three replicate specimens being required for testing. In one embodiment, all three specimens do not fail after 60 days of alternate immersion testing at a net stress of 300 MPa in the LT direction and in accordance with ASTM G47. In another embodiment, all three specimens do not fail after 90 days of alternate immersion testing at a net stress of 300 MPa in the LT direction and in accordance with ASTM G47.
  • all three specimens do not fail after 60 days of alternate immersion testing at a net stress of 350 MPa in the LT direction and in accordance with ASTM G47. In another embodiment, all three specimens do not fail after 90 days of alternate immersion testing at a net stress of 350 MPa in the LT direction and in accordance with ASTM G47.
  • ST Stress corrosion cracking resistant means that at least two-out-of-three specimens of a 2xxx aluminum alloy product do not fail after 60 days of alternate immersion testing at a net stress of 250 MPa in the ST direction and in accordance with ASTM G47 and using fixtures according to G49, and with at least 3 specimens being required for testing. In one embodiment, all three specimens do not fail after 60 days of alternate immersion testing at a net stress of 250 MPa in the ST direction and in accordance with ASTM G47. In another embodiment, all three specimens do not fail after 90 days of alternate immersion testing at a net stress of 250 MPa in the ST direction and in accordance with ASTM G47.
  • all three specimens do not fail after 60 days of alternate immersion testing at a net stress of 300 MPa in the ST direction and in accordance with ASTM G47. In another embodiment, all three specimens do not fail after 90 days of alternate immersion testing at a net stress of 300 MPa in the ST direction and in accordance with ASTM G47. vi. Miscellaneous
  • the term “or” is an inclusive “or” operator, and is equivalent to the term “and/or,” unless the context clearly dictates otherwise.
  • the term “based on” is not exclusive and allows for being based on additional factors not described, unless the context clearly dictates otherwise.
  • the meaning of “a,” “an,” and “the” include plural references, unless the context clearly dictates otherwise.
  • the meaning of “in” includes “in” and “on”, unless the context clearly dictates otherwise.
  • FIG. 1 is a graph illustrating TYS(L) versus K IC (L-T) for the Example 1 alloys.
  • FIG. 2 is a graph illustrating TYS(LT) versus K IC (T-L) for the Example 1 alloys.
  • FIG. 3 is a graph illustrating TYS(ST) versus K IC (S-L) for the Example 1 alloys.
  • the multistep practice demonstrates higher yield strength than the 350°F/24h aged condition. Also, the difference in properties is lower between the 2% and 8%- stretch for both strength and toughness, indicating the two-step aged materials may be suited for hydroforming applications (e.g., where a single hydroformed component may contain regions of variable strain and therefore variation in properties as a function of location within the plate).
  • the SCC (stress corrosion cracking) properties of the alloys in the ST direction were also measured as per the “ST Stress corrosion cracking resistance” definition provided above.
  • the SCC results are shown in Table 4, below.
  • the specimen type was T-bar and the location was T/2 for all tests.
  • the multi-step aged alloys did not realize any failures over the 90-day test period at both the 210 MPa and the 250 MPa net-stress levels.
  • the single-step aged alloys realized multiple failures.
  • the SCC resistance of the alloys in the ST direction were also tested at the seacoast to test the alloys against corrosion in natural saltwater conditions.
  • the specimens for the seacoast environment SCC testing are tested in constant strain fixtures (e.g., similar to those use in accelerated laboratory SCC testing).
  • the seacoast SCC testing conditions include continuously exposing the samples via racks to a seacoast environment, where the samples are ⁇ 1.5 meters from the ground, the samples are oriented 45° from the horizontal, and a face of the sample face the prevailing winds. The samples are located 100 meters from the coastline.
  • the coastline is of a rocky nature, with the prevailing winds oriented toward the samples so as to provide an aggressive salt-mist exposure (e.g., a location similar to the seacoast exposure station, Pt. Judith, Rhode Island, USA of Arconic Corp.).
  • the test results are shown in Table 5, below.
  • the specimen type was T-bar and the location was T/2 for all tests.
  • the multi-step aged alloys did not realize any failures after 596 days in test at the 210 MPa and 250 MPa net-stress levels.
  • the single-step aged alloys realized multiple failures.
  • the single-step aged alloys realized multiple failures, most occurring in 60 days or less.

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Abstract

Des procédés de fabrication de nouveaux produits en feuilles d'alliage d'aluminium 2xxx sont divulgués. Selon une approche, un procédé consiste à vieillir artificiellement un alliage d'aluminium 2xxx en au moins deux étapes. Selon un mode de réalisation, la première étape de vieillissement comprend un premier vieillissement d'un alliage d'aluminium 2xxx à une première température comprise entre 300 °F et 450 °F et pendant un premier temps de vieillissement compris entre 4 et 120 heures, et un second vieillissement de l'alliage d'aluminium 2xxx à une seconde température pendant un second temps de vieillissement compris entre 30 minutes et 120 heures, la seconde température étant entre 20 °F et 150 °F inférieure à la première température. La nouvelle étape de vieillissement artificiel en deux étapes peut faciliter une combinaison améliorée de propriétés, telle qu'une combinaison améliorée d'au moins deux propriétés parmi la résistance mécanique, la ductilité, la ténacité à la rupture et la résistance à la corrosion.
PCT/US2022/041247 2021-08-24 2022-08-23 Procédés de production d'alliages d'aluminium 2xxx WO2023028070A1 (fr)

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CN202280054819.9A CN117881809A (zh) 2021-08-24 2022-08-23 生产2xxx铝合金的方法
CA3227929A CA3227929A1 (fr) 2021-08-24 2022-08-23 Procedes de production d'alliages d'aluminium 2xxx
US18/435,464 US20240175114A1 (en) 2021-08-24 2024-02-07 Methods of producing 2xxx aluminum alloys

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Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2004041468A2 (fr) * 2002-09-21 2004-05-21 Universal Alloy Corporation Structure constituee d'alliages d'aluminium soudes
US20070151637A1 (en) * 2005-10-28 2007-07-05 Aleris Aluminum Koblenz Gmbh Al-Cu-Mg ALLOY SUITABLE FOR AEROSPACE APPLICATION
KR20120045624A (ko) * 2010-10-29 2012-05-09 국방과학연구소 인듐을 첨가한 2090 알루미늄 합금의 다단 열처리 방법
CN112011709A (zh) * 2020-07-10 2020-12-01 中南大学 一种Al-Cu-Mg-Si系合金及其制备方法和应用
CN112030085A (zh) * 2020-08-06 2020-12-04 中南大学 一种Al-Cu-Mg-Si系合金形变热处理工艺

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2004041468A2 (fr) * 2002-09-21 2004-05-21 Universal Alloy Corporation Structure constituee d'alliages d'aluminium soudes
US20070151637A1 (en) * 2005-10-28 2007-07-05 Aleris Aluminum Koblenz Gmbh Al-Cu-Mg ALLOY SUITABLE FOR AEROSPACE APPLICATION
KR20120045624A (ko) * 2010-10-29 2012-05-09 국방과학연구소 인듐을 첨가한 2090 알루미늄 합금의 다단 열처리 방법
CN112011709A (zh) * 2020-07-10 2020-12-01 中南大学 一种Al-Cu-Mg-Si系合金及其制备方法和应用
CN112030085A (zh) * 2020-08-06 2020-12-04 中南大学 一种Al-Cu-Mg-Si系合金形变热处理工艺

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