WO2020263864A1 - Alliages d'aluminium 7xxx corroyés épais perfectionnés et leurs procédés de production - Google Patents

Alliages d'aluminium 7xxx corroyés épais perfectionnés et leurs procédés de production Download PDF

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WO2020263864A1
WO2020263864A1 PCT/US2020/039196 US2020039196W WO2020263864A1 WO 2020263864 A1 WO2020263864 A1 WO 2020263864A1 US 2020039196 W US2020039196 W US 2020039196W WO 2020263864 A1 WO2020263864 A1 WO 2020263864A1
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ksi
aluminum alloy
7xxx aluminum
sqrt
alloy product
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PCT/US2020/039196
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English (en)
Inventor
Severine CAMBIER
Julien Boselli
Wei Wang
Cagatay Yanar
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Arconic Technologies Llc
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Priority to CN202080044888.2A priority Critical patent/CN114008229A/zh
Priority to CA3143806A priority patent/CA3143806A1/fr
Priority to EP20831122.5A priority patent/EP3987072A4/fr
Priority to BR112021026189A priority patent/BR112021026189A2/pt
Publication of WO2020263864A1 publication Critical patent/WO2020263864A1/fr
Priority to US17/550,994 priority patent/US20220106672A1/en

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    • 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
    • C22C21/10—Alloys based on aluminium with zinc 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
    • C22F1/002—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working by rapid cooling or quenching; cooling agents used therefor
    • 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

  • the present patent application relates to improved thick wrought 7xxx aluminum alloy products and methods for producing the same.
  • 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 a wrought aluminum alloy without affecting other properties such as fracture toughness or corrosion resistance. 7xxx (Al-Zn-Mg based) are prone to corrosion. See, e.g., Bonn, W. Grubl,“ The stress corrosion behaviour of high strength AIZnMg alloysf Paper held at the International Meeting of Associazione Italiana di Metallurgie,“Aluminum Alloys in Aircraft Industries,” Turin, October 1976.
  • Patent Owner has described some 7xxx aluminum alloy products in, inter alia , U. S. Patent Nos. 6,972,110, and 8,673,209, and International Patent Application Publication Nos. W02016/183030 and WO2018/237196.
  • the present patent application relates to improved thick wrought 7xxx aluminum alloy products, and methods for producing the same.
  • the new thick wrought 7xxx aluminum alloy products (“the new 7xxx aluminum alloy products”) may realize an improved combination of environmentally assisted crack (EAC) resistance and at least one of strength, elongation, and fracture toughness, among other properties.
  • EAC environmentally assisted crack
  • the new 7xxx aluminum alloy products generally include (and in some instances consist of, or consist essentially of) 5.5-6.5 wt. % Zn, 1.7-2.3 wt. % Cu, and 1.3-1.7 wt. % Mg.
  • the new wrought 7xxx aluminum alloy products are generally at least 2.5 inches thick, and may be up to 12 inches thick, and realize resistance to environmentally assisted cracking in the short transverse (ST) direction, which resistance is important for aerospace and other applications, especially those with structural loading in the short transverse (ST) direction.
  • Such thick, wrought 7xxx aluminum alloy product generally also realize good strength, elongation, fracture toughness and/or crack-deviation resistance properties.
  • the new wrought 7xxx aluminum alloy products may realize an improved combination of environmentally assisted cracking resistance and at least one of strength, elongation, fracture toughness and crack-deviation resistance.
  • the new 7xxx aluminum alloy products may include normal grain structure control materials, grain refiners, and impurities.
  • the new 7xxx aluminum alloy products may include one or more of Zr, Cr, Sc, and Hf as grain structure control materials (e.g., from 0.05-0.25 wt. % each of one or more of Zr, Cr, Sc, and Hf), limiting the total amounts of these elements such that large primary particles do not form in the alloy.
  • new 7xxx aluminum alloy products may include less than 0.15 wt.
  • the new 7xxx aluminum alloy products may include up to 0.15 wt. % Ti as a grain refiner, optionally with some of the titanium in the form of TiB2 and/or TiC.
  • the new 7xxx aluminum alloy products may include up to 0.20 wt. % Fe and up to 0.15 wt. % Si as impurities. Lower amounts of iron and silicon may be used.
  • the balance of the new 7xxx aluminum alloy products is generally aluminum and other unavoidable impurities (other than iron and silicon).
  • the new 7xxx aluminum alloy products generally include tailored amounts of zinc, magnesium and copper to facilitate realization of EAC resistance in combination with good strength and/or fracture toughness properties, among others.
  • the new 7xxx aluminum alloy products generally include from 5.5 to 6.5 wt. % Zn.
  • a new alloy includes not greater than 6.4 wt. % Zn.
  • a new alloy includes not greater than 6.3 wt. % Zn.
  • a new alloy includes not greater than 6.2 wt. % Zn.
  • a new alloy includes at least 5.6 wt. % Zn.
  • a new alloy includes at least 5.7 wt. % Zn.
  • a new alloy includes at least 5.8 wt. % Zn.
  • a new alloy includes at least 5.9 wt. % Zn.
  • the new 7xxx aluminum alloy products generally include from 1.7 to 2.3 wt. % Cu.
  • a new alloy includes not greater than 2.25 wt. % Cu.
  • a new alloy includes not greater than 2.20 wt. % Cu.
  • a new alloy includes at least 1.75 wt. % Cu.
  • a new alloy includes at least 1.80 wt. % Cu.
  • a new alloy includes at least 1.85 wt. % Cu.
  • a new alloy includes at least 1.90 wt. % Cu.
  • a new alloy includes at least 1.95 wt. % Cu.
  • a new alloy includes at least 2.00 wt. % Cu.
  • the new 7xxx aluminum alloy products generally include from 1.3 to 1.7 wt. % Mg.
  • a new alloy includes at least 1.35 wt. % Mg.
  • a new alloy includes at least 1.40 wt. % Mg.
  • a new alloy includes not greater than 1.65 wt. % Mg.
  • a new alloy includes not greater than 1.60 wt. % Mg.
  • a new alloy includes not greater than 1.55 wt. % Mg.
  • a new alloy includes not greater than 1.50 wt. % Mg.
  • a new alloy includes not greater than 1.45 wt. % Mg.
  • the amounts of zinc, magnesium and copper within the 7xxx aluminum alloy product satisfy the relationship: 2.569 ⁇ Mg+0.500*Cu+0.067*Zn ⁇ 3.269.
  • the amounts of zinc, magnesium and copper within the 7xxx aluminum alloy product satisfy the relationship: 2.709 ⁇ Mg+0.500*Cu+0.067*Zn ⁇ 3.119.
  • the amounts of zinc, magnesium and copper within the 7xxx aluminum alloy product satisfy the relationship: 2.869 ⁇ Mg+0.500*Cu+0.067*Zn ⁇ 3.269.
  • the amounts of zinc, magnesium and copper within the 7xxx aluminum alloy product satisfy the relationship: 2.869 ⁇ Mg+0.500*Cu+0.067*Zn ⁇ 3.119. Any of the zinc, magnesium, and copper amounts described in the preceding paragraphs may be used in combination with the above-shown empirical relationships.
  • the amounts of zinc and magnesium within the 7xxx aluminum alloy product are such that the weight ratio of zinc-to-magnesium is not greater than 4.75: 1 (i.e., (wt. % Zn / wt. % Mg) ⁇ 4.75 : 1).
  • a weight ratio of zinc-to-magnesium is not greater than 4.60: 1 (i.e., (wt. % Zn / wt. % Mg) ⁇ 4.60: 1).
  • a weight ratio of zinc-to-magnesium is not greater than 4.50: 1 (i.e., (wt. % Zn / wt. % Mg) ⁇ 4.50: 1).
  • a weight ratio of zinc-to-magnesium is not greater than 4.40: 1 (i.e., (wt. % Zn / wt. % Mg) ⁇ 4.40: 1). In another embodiment, a weight ratio of zinc- to-magnesium is not greater than 4.35: 1 (i.e., (wt. % Zn / wt. % Mg) ⁇ 4.35 : 1). In yet another embodiment, a weight ratio of zinc-to-magnesium is not greater than 4.30: 1 (i.e., (wt. % Zn / wt. % Mg) ⁇ 4.30: 1).
  • a weight ratio of zinc-to-magnesium is not greater than 4.25 : 1 (i.e., (wt. % Zn / wt. % Mg) ⁇ 4.25 : 1). In yet another embodiment, a weight ratio of zinc-to-magnesium is not greater than 4.20: 1 (i.e., (wt. % Zn / wt. % Mg) ⁇ 4.20: 1). In another embodiment, a weight ratio of zinc-to-magnesium is not greater than 4.15: 1 (i.e., (wt. % Zn / wt. % Mg) ⁇ 4.15: 1).
  • a weight ratio of zinc-to-magnesium is not greater than 4.10: 1 (i.e., (wt. % Zn / wt. % Mg) ⁇ 4.10: 1). In another embodiment, a weight ratio of zinc-to-magnesium is not greater than 4.00: 1 (i.e., (wt. % Zn / wt. % Mg) ⁇ 4.00: 1). In yet another embodiment, a weight ratio of zinc-to-magnesium is not greater than 3.95: 1 (i.e., (wt. % Zn / wt. % Mg) ⁇ 3.95: 1). In another embodiment, a weight ratio of zinc- to-magnesium is not greater than 3.90: 1 (i.e., (wt. % Zn / wt. % Mg) ⁇ 3.90: 1).
  • the amounts of zinc and magnesium within the 7xxx aluminum alloy product are such that the weight ratio of zinc-to-magnesium is at least 3.25: 1 (i.e., (wt. % Zn / wt. % Mg) > 3.25: 1). In one embodiment, the amounts of zinc and magnesium within the 7xxx aluminum alloy product are such that the weight ratio of zinc-to-magnesium is at least 3.33 : 1 (i.e., (wt. % Zn / wt. % Mg) > 3.33 : 1).
  • the amounts of zinc and magnesium within the 7xxx aluminum alloy product are such that the weight ratio of zinc-to- magnesium is at least 3.45: 1 (i.e., (wt. % Zn / wt. % Mg) > 3.45: 1). In another embodiment, the amounts of zinc and magnesium within the 7xxx aluminum alloy product are such that the weight ratio of zinc-to-magnesium is at least 3.55: 1 (i.e., (wt. % Zn / wt. % Mg) > 3.55: 1). In yet another embodiment, the amounts of zinc and magnesium within the 7xxx aluminum alloy product are such that the weight ratio of zinc-to-magnesium is at least 3.60: 1 (i.e., (wt. % Zn / wt. % Mg) > 3.60: 1).
  • the new 7xxx aluminum alloy product may include one or more of Zr, Cr, Sc, and Hf as grain structure control materials (e.g., from 0.05-0.25 wt. % each of one or more of Zr, Cr, Sc, and Hf), limiting the total amounts of these elements such that large primary particles do not form in the alloy.
  • Grain structure control materials may, for instance, facilitate an appropriate grain structure (e.g., an unrecrystallized grain structure).
  • a new 7xxx aluminum alloy product generally includes at least 0.05 wt. % of the grain structure control materials. In one embodiment, a new 7xxx aluminum alloy product includes at least 0.07 wt. % of the grain structure control materials.
  • a new 7xxx aluminum alloy product includes at least 0.09 wt. % of the grain structure control materials.
  • a new 7xxx aluminum alloy product generally includes not greater than 1.0 wt. % of the grain structure control materials.
  • a new 7xxx aluminum alloy product includes not greater than 0.75 wt. % of the grain structure control materials.
  • a new 7xxx aluminum alloy product includes not greater than 0.50 wt. % of the grain structure control materials.
  • the grain structure control materials are selected from the group consisting of Zr, Cr, Sc, and Hf.
  • the grain structure control materials are selected from the group consisting of Zr and Cr.
  • the grain structure control material is Zr.
  • the grain structure control material is Cr.
  • the grain structure control materials comprise both Zr and Cr, and a new 7xxx aluminum alloy product includes at least 0.07 wt. % Zr and at least 0.07 wt. % Cr, wherein the wt. % Zr plus the wt. % Cr is not greater than 0.40 wt. % (i.e., wt. % Zr + wt. % Cr ⁇ 0.40 wt. %).
  • the grain structure control materials comprise both Zr and Cr, and a new 7xxx aluminum alloy product includes at least 0.07 wt. % Zr and at least 0.07 wt. % Cr, wherein the wt. % Zr plus the wt.
  • the grain structure control materials comprise both Zr and Cr, and a new 7xxx aluminum alloy product includes at least 0.07 wt. % Zr and at least 0.07 wt. % Cr, wherein the wt. % Zr plus the wt. % Cr is not greater than 0.30 wt. % (i.e., wt. % Zr + wt. % Cr ⁇ 0.30 wt. %).
  • the grain structure control materials comprise both Zr and Cr, and a new 7xxx aluminum alloy product includes at least 0.07 wt. % Zr and at least 0.07 wt. % Cr, wherein the wt. % Zr plus the wt. % Cr is not greater than 0.25 wt. % (i.e., wt. % Zr + wt. % Cr ⁇ 0.25 wt. %).
  • the grain structure control materials comprise both Zr and Cr, and a new 7xxx aluminum alloy product includes at least 0.07 wt. % Zr and at least 0.07 wt. % Cr, wherein the wt. % Zr plus the wt.
  • % Cr is not greater than 0.20 wt. % (i.e., wt. % Zr + wt. % Cr ⁇ 0.20 wt. %).
  • a new 7xxx aluminum alloy product may include at least 0.09 wt. % of at least one of Zr and Cr.
  • a new 7xxx aluminum alloy product may include at least 0.09 wt. % of both Zr and Cr.
  • the grain structure control material is Zr, and a new 7xxx aluminum alloy product includes from 0.07 to 0.18 wt. % Zr. In another embodiment, the grain structure control material is Zr, and a new 7xxx aluminum alloy product includes from 0.07 to 0.16 wt. % Zr. In yet another embodiment, the grain structure control material is Zr, and a new 7xxx aluminum alloy product includes from 0.08 to 0.15 wt. % Zr. In another embodiment, the grain structure control material is Zr, and a new 7xxx aluminum alloy product includes from 0.09 to 0.14 wt. % Zr.
  • a new 7xxx aluminum alloy product generally contains low amounts of the Cr, Sc, and Hf (e.g., ⁇ 0.04 wt. % each of Cr, Sc, and Hf. ). In one embodiment, a new 7xxx aluminum alloy product contains not greater than 0.03 wt. % each of Cr, Sc, and Hf. In another embodiment, a new 7xxx aluminum alloy product contains not greater than 0.02 wt. % each of Cr, Sc, and Hf. In another embodiment, a new 7xxx aluminum alloy product contains not greater than 0.01 wt. % each of Cr, Sc, and Hf. In another embodiment, a new 7xxx aluminum alloy product contains not greater than 0.005 wt. % each of Cr, Sc, and Hf.
  • the grain structure control material is Cr, and a new 7xxx aluminum alloy product includes from 0.07 to 0.25 wt. % Cr.
  • the grain structure control material is Cr, and a new 7xxx aluminum alloy product includes from 0.07 to 0.20 wt. % Cr.
  • the grain structure control material is Cr, and a new 7xxx aluminum alloy product includes from 0.08 to 0.15 wt. % Cr.
  • the grain structure control material is Cr, and a new 7xxx aluminum alloy product includes from 0.10 to 0.15 wt. % Cr.
  • a new 7xxx aluminum alloy product contains low amounts of Cr (e.g., ⁇ 0.04 wt.
  • a new 7xxx aluminum alloy product contains not greater than 0.03 wt. % Cr. In another embodiment, a new 7xxx aluminum alloy product contains not greater than 0.02 wt. % Cr. In yet another embodiment, a new 7xxx aluminum alloy product contains not greater than 0.01 wt. % Cr. In another embodiment, a new 7xxx aluminum alloy product contains not greater than 0.005 wt. % Cr.
  • a new 7xxx aluminum alloy includes low amounts of zirconium (e.g., ⁇ 0.04 wt. % Zr). In one embodiment, a new 7xxx aluminum alloy product contains not greater than 0.03 wt. % Zr. In another embodiment, a new 7xxx aluminum alloy product contains not greater than 0.02 wt. % Zr. In yet another embodiment, a new 7xxx aluminum alloy product contains not greater than 0.01 wt. % Zr. In another embodiment, a new 7xxx aluminum alloy product contains not greater than 0.005 wt. % Zr.
  • the new 7xxx aluminum alloy product generally includes less than 0.15 wt. % Mn.
  • a new 7xxx aluminum alloy product includes not greater than 0.12 wt. % Mn.
  • a new 7xxx aluminum alloy product includes not greater than 0.10 wt. % Mn.
  • a new 7xxx aluminum alloy product includes not greater than 0.08 wt. % Mn.
  • a new 7xxx aluminum alloy product includes not greater than 0.05 wt. % Mn.
  • a new 7xxx aluminum alloy product includes not greater than 0.04 wt. % Mn.
  • a new 7xxx aluminum alloy product includes not greater than 0.03 wt. % Mn. In yet another embodiment, a new 7xxx aluminum alloy product includes not greater than 0.02 wt. % Mn. In another embodiment, a new 7xxx aluminum alloy product includes not greater than 0.01 wt. % Mn.
  • the new 7xxx aluminum alloy product may include up to 0.15 wt. % Ti. Titanium may be used to facilitate grain refining during casting, such as by using T1B2 or TiC. Elemental titanium may also or alternatively be used. In one embodiment, the new 7xxx aluminum alloy product includes from 0.005 to 0.025 wt. % Ti.
  • the new 7xxx aluminum alloy product may include up to 0.15 wt. % Si and up to 0.20 wt. % Fe as impurities.
  • the amount of silicon and iron may be limited so as to avoid detrimentally impacting the combination of strength, fracture toughness and crack deviation resistance.
  • the new 7xxx aluminum alloy product may include up to 0.12 wt. % Si and up to 0.15 wt. % Fe as impurities.
  • the new 7xxx aluminum alloy product may include up to 0.10 wt. % Si and up to 0.12 wt. % Fe as impurities.
  • the new 7xxx aluminum alloy product may include up to 0.08 wt.
  • the new 7xxx aluminum alloy product may include up to 0.06 wt. % Si and up to 0.08 wt. % Fe as impurities.
  • the new 7xxx aluminum alloy product may include up to 0.04 wt. % Si and up to 0.06 wt. % Fe as impurities.
  • the new 7xxx aluminum alloy product may include up to 0.03 wt. % Si and up to 0.05 wt. % Fe as impurities.
  • the new 7xxx aluminum alloy product has a thickness of from 2.5 to 12.0 inches. Thickness refers to the cross sectional thickness of the product at its thickest point. In one embodiment, a new 7xxx aluminum alloy product has a thickness of at least 3.0 inches. In another embodiment, a new 7xxx aluminum alloy product has a thickness of at least 3.5 inches. In yet another embodiment, a new 7xxx aluminum alloy product has a thickness of at least 4.0 inches. In another embodiment, a new 7xxx aluminum alloy product has a thickness of at least 4.5 inches. In yet another embodiment, a new 7xxx aluminum alloy product has a thickness of at least 5.0 inches.
  • a new 7xxx aluminum alloy product has a thickness of not greater than 10.0 inches. In another embodiment, a new 7xxx aluminum alloy product has a thickness of not greater than 9.0 inches. In yet another embodiment, a new 7xxx aluminum alloy product has a thickness of not greater than 8.0 inches.
  • a new 7xxx aluminum alloy product is a rolled product (e.g., a plate product).
  • a new 7xxx aluminum alloy product is an extruded product.
  • a new 7xxx aluminum alloy product is a forged product (e.g., a hand forged product, a die forged product).
  • the new 7xxx aluminum alloy products may realize an improved combination of properties.
  • a new 7xxx aluminum alloy product realizes a typical tensile yield strength (L) of at least 63 ksi as per ASTM E8 and B557.
  • a new 7xxx aluminum alloy product realizes a typical tensile yield strength (L) of at least 64 ksi.
  • a new 7xxx aluminum alloy product realizes a typical tensile yield strength (L) of at least 65 ksi.
  • a 7xxx aluminum alloy product may realize a typical tensile yield strength (L) of at least 66 ksi.
  • a 7xxx aluminum alloy product may realize a typical tensile yield strength (L) of at least 67 ksi. In another embodiment, a 7xxx aluminum alloy product may realize a typical tensile yield strength (L) of at least 68 ksi. In yet another embodiment, a 7xxx aluminum alloy product may realize a typical tensile yield strength (L) of at least 69 ksi. In another embodiment, a 7xxx aluminum alloy product may realize a typical tensile yield strength (L) of at least 70 ksi. In yet another embodiment, a 7xxx aluminum alloy product may realize a typical tensile yield strength (L) of at least 71 ksi.
  • a 7xxx aluminum alloy product may realize a typical tensile yield strength (L) of at least 72 ksi. In yet another embodiment, a 7xxx aluminum alloy product may realize a typical tensile yield strength (L) of at least 73 ksi.
  • a new 7xxx aluminum alloy product realizes a typical tensile yield strength (ST) of at least 57 ksi as per ASTM E8 and B557.
  • a 7xxx aluminum alloy product may realize a typical tensile yield strength (ST) of at least 58 ksi.
  • a 7xxx aluminum alloy product may realize a typical tensile yield strength (ST) of at least 59 ksi.
  • a 7xxx aluminum alloy product may realize a typical tensile yield strength (ST) of at least 60 ksi.
  • a 7xxx aluminum alloy product may realize a typical tensile yield strength (ST) of at least 61 ksi. In another embodiment, a 7xxx aluminum alloy product may realize a typical tensile yield strength (ST) of at least 62 ksi. In yet another embodiment, a 7xxx aluminum alloy product may realize a typical tensile yield strength (ST) of at least 63 ksi. In another embodiment, a 7xxx aluminum alloy product may realize a typical tensile yield strength (ST) of at least 64 ksi. In yet another embodiment, a 7xxx aluminum alloy product may realize a typical tensile yield strength (ST) of at least 65 ksi. In another embodiment, a 7xxx aluminum alloy product may realize a typical tensile yield strength (ST) of at least 66 ksi.
  • a new 7xxx aluminum alloy product realizes a typical Kic plane-strain fracture toughness (L-T) of at least 25 ksi-sqrt-inch as per ASTM E8 and E399- 12.
  • a new 7xxx aluminum alloy product realizes a typical Kic plane-stain fracture toughness (L-T) of at least 27 ksi-sqrt-inch.
  • a new 7xxx aluminum alloy product realizes a typical Kic plane-stain fracture toughness (L-T) of at least 28 ksi-sqrt-inch.
  • a new 7xxx aluminum alloy product realizes a typical Kic plane-stain fracture toughness (L-T) of at least 29 ksi-sqrt-inch. In another embodiment, a new 7xxx aluminum alloy product realizes a typical Kic plane-stain fracture toughness (L-T) of at least 30 ksi-sqrt-inch. In yet another embodiment, a new 7xxx aluminum alloy product realizes a typical Kic plane-stain fracture toughness (L-T) of at least 31 ksi-sqrt- inch.
  • a new 7xxx aluminum alloy product realizes a typical Kic plane- stain fracture toughness (L-T) of at least 32 ksi-sqrt-inch. In yet another embodiment, a new 7xxx aluminum alloy product realizes a typical Kic plane-stain fracture toughness (L-T) of at least 33 ksi-sqrt-inch. In another embodiment, a new 7xxx aluminum alloy product realizes a typical Kic plane-stain fracture toughness (L-T) of at least 34 ksi-sqrt-inch.
  • a new 7xxx aluminum alloy product realizes a typical Kic plane-stain fracture toughness (L-T) of at least 35 ksi-sqrt-inch. In another embodiment, a new 7xxx aluminum alloy product realizes a typical Kic plane-stain fracture toughness (L-T) of at least 36 ksi-sqrt- inch. In yet another embodiment, a new 7xxx aluminum alloy product realizes a typical Kic plane-stain fracture toughness (L-T) of at least 37 ksi-sqrt-inch.
  • a new 7xxx aluminum alloy product realizes a typical Kic plane-stain fracture toughness (L-T) of at least 38 ksi-sqrt-inch. In yet another embodiment, a new 7xxx aluminum alloy product realizes a typical Kic plane-stain fracture toughness (L-T) of at least 39 ksi-sqrt-inch. In another embodiment, a new 7xxx aluminum alloy product realizes a typical Kic plane-stain fracture toughness (L-T) of at least 40 ksi-sqrt-inch.
  • a new 7xxx aluminum alloy product realizes a typical Kic plane-stain fracture toughness (L-T) of at least 41 ksi-sqrt- inch. In another embodiment, a new 7xxx aluminum alloy product realizes a typical Kic plane- stain fracture toughness (L-T) of at least 42 ksi-sqrt-inch. In yet another embodiment, a new 7xxx aluminum alloy product realizes a typical Kic plane-stain fracture toughness (L-T) of at least 43 ksi-sqrt-inch.
  • a new 7xxx aluminum alloy product realizes a typical Kic plane-stain fracture toughness (L-T) of at least 44 ksi-sqrt-inch. In yet another embodiment, a new 7xxx aluminum alloy product realizes a typical Kic plane-stain fracture toughness (L-T) of at least 45 ksi-sqrt-inch.
  • a new 7xxx aluminum alloy product realizes a typical Kic plane-strain fracture toughness (S-L) of at least 20 ksi-sqrt-inch as per ASTM E8 and E399- 12. In another embodiment, a new 7xxx aluminum alloy product realizes a typical Kic plane- strain fracture toughness (S-L) of at least 22 ksi-sqrt-inch. In another embodiment, a new 7xxx aluminum alloy product realizes a typical Kic plane-strain fracture toughness (S-L) of at least 24 ksi-sqrt-inch.
  • a new 7xxx aluminum alloy product realizes a typical Kic plane-strain fracture toughness (S-L) of at least 26 ksi-sqrt-inch. In another embodiment, a new 7xxx aluminum alloy product realizes a typical Kic plane-strain fracture toughness (S- L) of at least 28 ksi-sqrt-inch. In another embodiment, a new 7xxx aluminum alloy product realizes a typical Kic plane-strain fracture toughness (S-L) of at least 30 ksi-sqrt-inch. In another embodiment, a new 7xxx aluminum alloy product realizes a typical Kic plane-strain fracture toughness (S-L) of at least 32 ksi-sqrt-inch.
  • a new 7xxx aluminum alloy product realizes a typical Kic plane-strain fracture toughness (S-L) of at least 34 ksi-sqrt-inch. In another embodiment, a new 7xxx aluminum alloy product realizes a typical Kic plane-strain fracture toughness (S-L) of at least 36 ksi-sqrt-inch. In another embodiment, a new 7xxx aluminum alloy product realizes a typical Kic plane-strain fracture toughness (S-L) of at least 38 ksi-sqrt-inch. In another embodiment, a new 7xxx aluminum alloy product realizes a typical Kic plane-strain fracture toughness (S-L) of at least 40 ksi-sqrt-inch.
  • a new 7xxx aluminum alloy product realizes a typical elongation (L) of at least 6% as per ASTM E8 and B557. In another embodiment, a new 7xxx aluminum alloy product realizes a typical elongation (L) of at least 7%. In yet another embodiment, a new 7xxx aluminum alloy product realizes a typical elongation (L) of at least 8%. In another embodiment, a new 7xxx aluminum alloy product realizes a typical elongation (L) of at least 9%. In yet another embodiment, a new 7xxx aluminum alloy product realizes a typical elongation (L) of at least 10%.
  • a new 7xxx aluminum alloy product realizes a typical elongation (L) of at least 11%. In yet another embodiment, a new 7xxx aluminum alloy product realizes a typical elongation (L) of at least 12%. In another embodiment, a new 7xxx aluminum alloy product realizes a typical elongation (L) of at least 13%. In yet another embodiment, a new 7xxx aluminum alloy product realizes a typical elongation (L) of at least 14%. In another embodiment, a new 7xxx aluminum alloy product realizes a typical elongation (L) of at least 15%. In yet another embodiment, a new 7xxx aluminum alloy product realizes a typical elongation (L) of at least 16%.
  • a new 7xxx aluminum alloy product realizes a typical elongation (ST) of at least 3% as per ASTM E8 and B557. In another embodiment, a new 7xxx aluminum alloy product realizes a typical elongation (ST) of at least 4%. In yet another embodiment, a new 7xxx aluminum alloy product realizes a typical elongation (ST) of at least 5%. In another embodiment, a new 7xxx aluminum alloy product realizes a typical elongation (ST) of at least 6%. In yet another embodiment, a new 7xxx aluminum alloy product realizes a typical elongation (ST) of at least 7%.
  • a new 7xxx aluminum alloy product realizes a typical elongation (ST) of at least 8%. In yet another embodiment, a new 7xxx aluminum alloy product realizes a typical elongation (ST) of at least 9%. In another embodiment, a new 7xxx aluminum alloy product realizes a typical elongation (ST) of at least 10%.
  • a new 7xxx aluminum alloy product realizes a typical L-S crack deviation resistance (K ma x-dev) of at least 25 ksi-sqrt-in.
  • a new 7xxx aluminum alloy product realizes a typical L-S crack deviation resistance (Kmax-dev) of at least 27 ksi-sqrt-in.
  • a new 7xxx aluminum alloy product realizes a typical L-S crack deviation resistance (Kmax-dev) of at least 29 ksi-sqrt-in.
  • a new 7xxx aluminum alloy product realizes a typical L-S crack deviation resistance (Kmax-dev) of at least 3 1 ksi-sqrt-in.
  • a new 7xxx aluminum alloy product realizes a typical L-S crack deviation resistance (Kmax-dev) of at least 33 ksi-sqrt-in.
  • a new 7xxx aluminum alloy product realizes a typical L-S crack deviation resistance (K ma x-dev) of at least 35 ksi-sqrt-in.
  • a new 7xxx aluminum alloy product realizes a typical L-S crack deviation resistance (Kmax-dev) of at least 37 ksi-sqrt-in.
  • a new 7xxx aluminum alloy product realizes a typical L-S crack deviation resistance (Kmax-dev) of at least 39 ksi-sqrt-in.
  • a new 7xxx aluminum alloy product realizes a typical L-S crack deviation resistance (Kmax-dev) of at least 41 ksi-sqrt-in. In another embodiment, a new 7xxx aluminum alloy product realizes a typical L-S crack deviation resistance (Kmax-dev) of at least 43 ksi-sqrt- in. In yet another embodiment, a new 7xxx aluminum alloy product realizes a typical L-S crack deviation resistance (Kmax-dev) of at least 45 ksi-sqrt-in. In another embodiment, a new 7xxx aluminum alloy product realizes a typical L-S crack deviation resistance (Kmax-dev) of at least 47 ksi-sqrt-in.
  • a new 7xxx aluminum alloy product realizes a typical L-S crack deviation resistance (Kmax-dev) of at least 49 ksi-sqrt-in. In another embodiment, a new 7xxx aluminum alloy product realizes a typical L-S crack deviation resistance (Kmax-dev) of at least 50 ksi-sqrt-in.
  • the new 7xxx aluminum alloys may be EAC resistant, which EAC resistance may be determined by Hot and Humid SCC testing.
  • a new 7xxx aluminum alloy product has a thickness of at least 63.5 mm and passes Hot and Humid SCC (stress corrosion cracking) testing using standard stress-corrosion tension test specimens conforming to ASTM G49, as defined below (“HHSCC-G49”).
  • HHSCC-G49 standard stress-corrosion tension test specimens conforming to ASTM G49, as defined below
  • ST short transverse
  • the extracted specimens are then machined into tensile specimens with a diameter as defined in ASTM G47-20 and dimensions proportional to the standard specimen as defined in ASTM E8/8M-16ael . If the final product thickness is at least 2.25 inches (57.15 mm), then the length of the tensile specimen is 2.00 inches (50.8 mm), as shown in FIG. 2. If the final product thickness is from 1.50 inches (38.1 mm) to less than 2.25 inches ( ⁇ 50.8 mm), the length of the specimen must be at least 1.25 inches (31.75 mm) and should be as close to 2.00 inches (50.8 mm) as possible. Prior to testing the tensile specimens are to be cleaned / degreased by washing in acetone.
  • the tensile specimens are then strained in the short-transverse direction at 85% of their ST tensile yield strength at T/2.
  • the alloy s ST tensile yield strength is measured at room temperature and in accordance with ASTM E8 and B557 prior to the HHSCC-G49 testing.
  • the stressing frame used is a constant strain type per ASTM G49, section 7.2.2 (see, e.g., FIG. 4a of ASTM G49).
  • the strained specimens are then placed into a controlled cabinet having air at 85% relative humidity (without additions to the air, such as chlorides) and a temperature of 70°C or 90°C. At least three specimens must be tested.
  • an alloy passes HHSCC-G49 testing at 70°C when all specimens survive at least 100 days.
  • an alloy passes HHSCC-G49 testing at 90°C when all specimens survive at least 10 days.
  • a failure is when the specimen breaks into two halves, either along the gauge length or at one of the specimen shoulders adjoining the gauge length. Shoulder failures are statistically equivalent to gauge length failures. Thread failures are only included when they are statistically equivalent to the gauge length failures when determining whether an alloy passes HHSCC-G49.
  • a thread failure is when a crack occurs in a threaded end of a specimen as opposed to in the gauge length. In some instance, thread failures may not be detectable until the specimen is removed from the stressing frame.
  • the HHSCC-G49 testing is conducted at 70°C and a new 7xxx aluminum alloy product passes 120 days of HHSCC-G49 testing at 70°C, wherein all samples survive 120 days of the HHSCC-G49 test defined above.
  • a new 7xxx aluminum alloy product passes 140 days of HHSCC-G49 testing at 70°C, wherein all samples survive 140 days of the HHSCC-G49 test defined above.
  • a new 7xxx aluminum alloy product passes 150 days of HHSCC-G49 testing at 70°C, wherein all samples survive 150 days of the HHSCC-G49 test defined above.
  • a new 7xxx aluminum alloy product passes 160 days of HHSCC-G49 testing at 70°C, wherein all samples survive 160 days of the HHSCC-G49 test defined above.
  • a new 7xxx aluminum alloy product passes 180 days of HHSCC-G49 testing at 70°C, wherein all samples survive 180 days of the HHSCC-G49 test defined above.
  • a new 7xxx aluminum alloy product passes 200 days of HHSCC-G49 testing at 70°C, wherein all samples survive 200 days of the HHSCC-G49 test defined above.
  • a new 7xxx aluminum alloy product passes 220 days of HHSCC-G49 testing at 70°C, wherein all samples survive 220 days of the HHSCC-G49 test defined above.
  • a new 7xxx aluminum alloy product passes 240 days of HHSCC-G49 testing at 70°C, wherein all samples survive 240 days of the HHSCC-G49 test defined above.
  • a new 7xxx aluminum alloy product passes 260 days of HHSCC- G49 testing at 70°C, wherein all samples survive 260 days of the HHSCC-G49 test defined above.
  • a new 7xxx aluminum alloy product passes 280 days of HHSCC-G49 testing at 70°C, wherein all samples survive 280 days of the HHSCC-G49 test defined above.
  • a new 7xxx aluminum alloy product passes 300 days of HHSCC-G49 testing at 70°C, wherein all samples survive 300 days of the HHSCC- G49 test defined above.
  • the above stress corrosion cracking resistance properties may be realized in products having a thickness of at least 80 mm, or at least 100 mm, at least 120 mm, or at least 140 mm, or higher.
  • the HHSCC-G49 testing is conducted at 90°C and a new 7xxx aluminum alloy product passes 15 days of HHSCC-G49 testing at 90°C, wherein all samples survive 15 days of the HHSCC-G49 test defined above.
  • a new 7xxx aluminum alloy product passes 20 days of HHSCC-G49 testing at 90°C, wherein all samples survive 20 days of the HHSCC-G49 test defined above.
  • a new 7xxx aluminum alloy product passes 25 days of HHSCC-G49 testing at 90°C, wherein all samples survive 25 days of the HHSCC-G49 test defined above.
  • the above stress corrosion cracking resistance properties may be realized in products having a thickness of at least 80 mm, or at least 100 mm, at least 120 mm, or at least 140 mm, or higher.
  • a new 7xxx aluminum alloy product has a thickness of at least 63.5 mm and passes stress corrosion cracking, per ASTM G47 using standard stress-corrosion tension test specimens conforming to ASTM G49 under alternate immersion exposure conditions per ASTM G44 (“SCC alternate immersion testing”).
  • SCC alternate immersion testing For purposes of this patent application, a new 7xxx aluminum alloy passes SCC alternate immersion testing when all samples survive 20 days of the SCC alternate immersion testing at a net stress of 172 MPa in the ST direction, where the test environment is 3.5% NaCl, and with a minimum of five (5) samples required to be tested.
  • a new 7xxx aluminum alloy passes 30 days of SCC alternate immersion testing, as defined above.
  • a new 7xxx aluminum alloy passes 20 days of SCC alternate immersion testing, as defined above, but at a net stress of 241 MPa. In yet another embodiment, a new 7xxx aluminum alloy passes 30 days of SCC alternate immersion testing, as defined above, but at a net stress of 241 MPa.
  • the above stress corrosion cracking resistance properties may be realized in products having a thickness of at least 80 mm, or at least 100 mm, at least 120 mm, or at least 140 mm, or higher.
  • a new 7xxx aluminum alloy product has a thickness of at least 63.5 mm and passes Hot and Humid SCC (stress corrosion cracking) testing under ASTM G168, as defined below (“HHSCC-G168”).
  • HHSCC-G168 Hot and Humid SCC (stress corrosion cracking) testing under ASTM G168, as defined below.
  • a new 7xxx aluminum alloy passes HHSCC-G168 testing when (a) the stress intensity factor gives a crack growth rate of not greater than 10 7 mm/s, and (b) the realized K value is at least 13 MPa-sqrt- m (MPaVm).
  • the HHSCC-G168 testing is to be conducted at 70°C and 85% relative humidity, at T/2 and with S-L specimens.
  • the realized K value is at least 14 MPa- sqrt-m at a crack growth rate of not greater than 10 7 mm/s. In another embodiment, the realized K value is at least 15 MPa-sqrt-m at a crack growth rate of not greater than 10 7 mm/s. In yet another embodiment, the realized K value is at least 16 MPa-sqrt-m at a crack growth rate of not greater than 10 7 mm/s. In another embodiment, the realized K value is at least 17 MPa- sqrt-m at a crack growth rate of not greater than 10 7 mm/s.
  • the realized K value is at least 18 MPa-sqrt-m, or higher, at a crack growth rate of not greater than 10 7 mm/s.
  • the above stress corrosion cracking resistance properties may be realized in products having a thickness of at least 80 mm, or at least 100 mm, at least 120 mm, or at least 140 mm, or higher.
  • a new 7xxx aluminum alloy product passes at least two of the above-defined SCC tests (i.e., at least two of: (a) the HHSCC-G49 test, as defined above, (b) the SCC alternate immersion test, as defined above, and (c) the HHSCC-G168 test, as defined above). In another embodiment, a new 7xxx aluminum alloy passes all of the above-defined SCC tests.
  • L and ST properties generally relate to thick plate products, similar properties may also be realized in thick forged product and thick extruded products. Further, many of the above properties may be realized in combination, as shown by the below examples.
  • the new thick 7xxx aluminum alloy products may be suitable for parts in various aerospace applications.
  • the alloy product is an aerospace structural component.
  • the aircraft structural component may be any of an upper wing panel (skin), an upper wing stringer, an upper wing cover with integral stringers, a spar, a spar cap, a spar web, a rib, rib feet or a rib web, stiffening elements, frames, a landing gear component (e.g., a cylinders, beams), drag braces, bulkheads, flap track assemblies, fuselage and windshield frames, gear ribs, side stays, fittings, a fuselage component (e.g., a fuselage skin), and space components (e.g., for rockets and other vehicles that may exit the earth).
  • a fuselage component e.g., a fuselage skin
  • space components e.g., for rockets and other vehicles that may exit the earth.
  • the alloy product is an armor component (e.g., of a motorized vehicle). In one embodiment, the alloy product is used in the oil and gas industry (e.g., as pipes, structural components). In one embodiment, the alloy product is a thick mold block / mold plate product (e.g., for injection molding). In one embodiment, the alloy product is an automotive product.
  • the new thick 7xxx aluminum alloy products may be made into wrought products by casting an aluminum alloy having any of the aforementioned compositions into an ingot or billet, followed by homogenizing of the ingot or billet.
  • the homogenized ingot or billet may be worked by rolling, extruding, or forging to final gauge, generally by hot working, optionally with some cold working.
  • the final gauge product may be solution heat treated, and then quenched, and then stress relieved (e.g., by stretching or compression) and then artificially aged.
  • the new 7xxx aluminum alloys may be made into shape castings or by additive manufacturing into additively manufactured products.
  • the additively manufactured products may be used as-is, or may be subsequently processed, e.g., processed via mechanical, thermal, or thermomechanical treatment.
  • “typical longitudinal (L) tensile yield strength” or TYS(L) is determined in accordance with ASTM B557-10 and by measuring the tensile yield strength (TYS) in the longitudinal direction (L) at the T/4 location from at least three different lots of material, and with at least duplicate specimens being tested for each lot, for a total of at least 6 different measured specimen values, with the typical TYS(L) being the average of the at least 6 different measured specimen values.
  • Typical elongation (L) is measured during longitudinal tensile testing.
  • TYS(ST) typically longitudinal (ST) tensile yield strength” or TYS(ST) is determined in accordance with ASTM B557-10 and by measuring the tensile yield strength (TYS) in the short transverse direction (ST) from at least three different lots of material, and with at least duplicate specimens being tested for each lot, for a total of at least 6 different measured specimen values, with the typical TYS(ST) being the average of the at least 6 different measured specimen values.
  • Short transverse tensile specimens are taken so that the midpoint of the gage section coincides with the plate mid-thickness plane.
  • Typical elongation (ST) is measured during short transverse tensile testing.
  • “typical plane strain fracture toughness (Kic) (L-T)” is determined in accordance with ASTM E399-12, by measuring the plane strain fracture toughness in the L- T direction at the T/4 location from at least three different lots of material using a C(T) specimen, where“W” is 4.0 inches, and where“B” is 2.0 inches for products having a thickness of at least 2.0 inches and where“B” is 1.5 inches for products having a thickness less than 2.0 inches, with at least duplicate specimens being tested for each lot, for a total of at least 6 different measured specimen values, and with the typical plane strain fracture toughness (Kic) (L-T) being the average of the at least 6 different valid Kic measured specimen values.
  • “typical plane strain fracture toughness (Kic) (S-L)” is determined in accordance with ASTM E399-12, by measuring the plane strain fracture toughness in the S- L direction at the T/2 location from at least three different lots of material using a C(T) specimen, where“W” and“B” are per the below table, with at least duplicate specimens being tested for each lot, for a total of at least 6 different measured specimen values, and with the typical plane strain fracture toughness (Kic) (S-L) being the average of the at least 6 different valid Kic measured specimen values.
  • the typical L-S crack deviation resistance properties are to be determined per the procedure described in commonly-owned U. S. Patent Application Publication No. 2017/0088920, paragraph 0058, which procedure is incorporated herein by reference, except.
  • the“W” dimension of the specimen shall be 2.0 inches (5.08 cm)
  • the specimen shall be centered at T/2 (as opposed to the notch tip)
  • the test specimens may be tested in lab air as opposed to high humidity air.
  • 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 the strength versus Kic fracture toughness properties for the Example 1 alloys.
  • FIG. 2 is a graph illustrating the strength versus EAC resistance for the Example 1 alloys.
  • the ingots were then conventionally prepared for homogenization (e.g. by sawing and scalping).
  • the first ingot was then processed to its final temper as per Japanese Patent No. H03-41540 (1991), Example 1, Alloy 4. 1
  • the second ingot was processed according to the inventive processes disclosed herein.
  • Alloy 1 was homogenized at 842°F (450°C) as per JPH03-41540. The alloy was then hot rolled to a final gauge of 1.75 inches (44.45 mm). Alloy 1 was then solution heat treated at 842°F (450°C) for 1 hour as per JPH03-41540, then quenched in 190°F water (87.8°C), and then stretched 1.5%. After stretching, Alloy 1 was artificially aged by first aging at 248°F (120°C) for 24 hours, heating to 302°F and then aging at 302°F (150°C) for 24 hours as per JPH034-41540.
  • Alloy 2 was homogenized at 895°F (479°C) and then hot rolled to a final gauge of 1.75 inches (44.45 mm). Alloy 2 was then solution heat treated at 895°F (479°C) for 2 hours, quenched in 190°F water (87.8°C), and then stretched 2.25%. After stretching, some Alloy 2 was subjected to two different artificially aging practices:
  • the 190°F quench temperature simulates the quench rate of the middle of a thick ingot (e.g., an eight-inch (203.2 mm) thick ingot).
  • Alloys 1-2 were metallographically examined and were found to be unrecrystallized, i.e., contained not greater than 45% recrystallized grains as determined using standard metallographic analysis procedures.
  • a new wrought 7xxx aluminum alloy product contains not greater than 35% recrystallized grains.
  • a new wrought 7xxx aluminum alloy product contains not greater than 25% recrystallized grains.
  • a new wrought 7xxx aluminum alloy product contains not greater than 15% recrystallized grains.
  • a new wrought 7xxx aluminum alloy product contains not greater than 5% recrystallized grains.
  • the alloys were also subjected to EAC (environmentally assisted crack) resistance testing as per the HHSCC-G49 procedure provided above. Plant produced 7050-T7651 (3.9 inches thick) having a strength level similar to that of Alloys 1-2 was also tested.
  • the HHSCC- G49 results are provided in Table 3, below.
  • Alloy 2 realizes an improved combination of properties over Alloy 1. As shown in FIG. 1, Alloy 2 realizes a much higher combination of strength and toughness over Alloy 1 and the conventional 7050 alloy. As shown in FIG. 2, Alloy 2 also realizes a much better combination of strength and EAC resistance over Alloy 1. Further, as shown in Table 2, the ST ductility of Alloy 2 is significantly higher than that of Alloy 1.
  • the Cu, the Mg, and the Zn are the weight percent amounts of copper, magnesium and zinc, respectively, in the wrought 7xxx aluminum alloy.
  • the below table shows the calculation for Alloys 1 and 2.
  • the homogenization temperature is higher than T(homog.) In one embodiment, the homogenization temperature is at least 5°F higher than T(homog.), i.e., is > 5°F+T(homog.). In another embodiment, the homogenization temperature is at least 10°F higher than T(homog.), i.e., is > 10°F+T(homog.). In yet another embodiment, the homogenization temperature is at least 15°F higher than T(homog.), i.e., is > 15°F+T(homog.).
  • the homogenization temperature is at least 20°F higher than T(homog.), i.e., is > 20°F+T(homog.). In yet another embodiment, the homogenization temperature is at least 25°F higher than T(homog.), i.e., is > 25°F+T(homog.). In another embodiment, the homogenization temperature is at least 30°F higher than T(homog.), i.e., is > 30°F+T(homog.). In yet another embodiment, the homogenization temperature is at least 35°F higher than T(homog.), i.e., is > 35°F+T(homog.).
  • the homogenization temperature is at least 40°F higher than T(homog.), i.e., is > 40°F+T(homog.). In yet another embodiment, the homogenization temperature is at least 45°F higher than T(homog.), i.e., is > 45°F+T(homog.). In another embodiment, the homogenization temperature is at least 50°F higher than T(homog.), i.e., is > 50°F+T(homog.). However, the homogenization temperature should be below the incipient melting temperature of the aluminum alloy. Preferably, the homogenization temperature is at least 10°F below the incipient melting temperature of the aluminum alloy.
  • the solution heat treatment temperature may be the same as T(homog.) and preferably is from 10-50°F higher than T(homog.), as per above, but below the incipient melting temperature of the aluminum alloy, and preferably at least 10°F below the incipient melting temperature of the aluminum alloy.
  • the alloy should be quenched in an appropriate medium, such as water or air.
  • the water is room temperature.
  • T is the instantaneous temperature in Kelvin (K) during the artificial aging
  • Tref is a reference temperature selected at 160°C (433.15K).
  • the t(eq.) for Alloys 1-2 are shown in the below table.
  • t(eq.) is from 7 to 19 hours. In another embodiment, t(eq.) is from 7 to 18 hours. In yet another embodiment, t(eq.) is from 7 to 17 hours. In another embodiment, t(eq.) is from 7 to 16 hours. In yet another embodiment, t(eq.) is from 7 to 15 hours. In another embodiment, t(eq.) is from 7 to 14 hours. In yet another embodiment, t(eq.) is from 7 to 13.5 hours.
  • t(eq.) is from 7 to 13 hours. In yet another embodiment, t(eq.) is from 7 to 12.5 hours. In another embodiment, t(eq.) is from 7 to 12 hours. In yet another embodiment, t(eq.) is from 7 to 11.5 hours. In another embodiment, t(eq.) is from 7 to 11 hours.
  • the artificial aging comprises first aging at a first aging temperature of from 200-300°F followed by second aging at a second aging temperature of from 250-350°F, wherein the second aging temperature is at least 10°F higher than the first aging temperature.
  • the second aging temperature is at least 20°F higher than the first aging temperature.
  • the second aging temperature is at least 30°F higher than the first aging temperature.
  • the second aging temperature is at least 40°F higher than the first aging temperature.
  • the second aging temperature is at least 50°F higher than the first aging temperature. In yet another embodiment, the second aging temperature is at least 60°F higher than the first aging temperature. In another embodiment, the second aging temperature is at least 70°F higher than the first aging temperature.
  • the first aging temperature is not greater than 280°F. In another embodiment, the first aging temperature is not greater than 270°F. In yet another embodiment, the first aging temperature is not greater than 260°F. In another embodiment, the first aging temperature is not greater than 250°F. Multiple aging temperatures may be used within the first aging temperature range provided t(eq) is achieved.
  • the second aging temperature is at least 305°F. In another embodiment, the second aging temperature is at least 310°F. In yet another embodiment, the second aging temperature is at least 315°F. In another embodiment, the second aging temperature is at least 320°F. Multiple aging temperatures may be used within the second aging temperature range provided t(eq) is achieved. After the second aging step, the product may be cooled to room temperature.
  • the third aging step is similar or the same as the first aging step, such as by using an aging temperature of from 200-300°F. Multiple aging temperatures may be used within the third aging temperature range provided t(eq) is achieved.
  • the third aging temperature is at least 10°F lower than second aging temperature.
  • the third aging temperature is at least 20°F lower than second aging temperature.
  • the third aging temperature is at least 30°F lower than second aging temperature.
  • the third aging temperature is at least 40°F lower than second aging temperature.
  • the third aging temperature is at least 50°F lower than second aging temperature. In another embodiment, the third aging temperature is at least 60°F lower than second aging temperature. In yet another embodiment, the third aging temperature is at least 70°F lower than second aging temperature.
  • the third aging temperature is not greater than 280°F. In another embodiment, the third aging temperature is not greater than 270°F. In yet another embodiment, the third aging temperature is not greater than 260°F. In another embodiment, the third aging temperature is not greater than 250°F. Multiple aging temperatures may be used within the third aging temperature range provided t(eq) is achieved.

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Abstract

L'invention concerne des produits d'alliage d'aluminium 7xxx corroyés épais perfectionnés et leurs procédés de production. Les nouveaux produits d'alliage d'aluminium 7xxx peuvent présenter une combinaison améliorée de propriétés, telle qu'une combinaison améliorée d'au moins deux propriétés parmi, entre autres, la résistance aux fissures, la solidité, l'étirement et la résistance aux fractures, assistées par l'environnement. Les nouveaux produits en alliage d'aluminium 7xxx peuvent comprendre de 5,5 à 6,5 % en poids de Zn, de 1,3 à 1,7 % en poids de Mg et de 1,7 à 2,3 % en poids de Cu.
PCT/US2020/039196 2019-06-24 2020-06-23 Alliages d'aluminium 7xxx corroyés épais perfectionnés et leurs procédés de production WO2020263864A1 (fr)

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BR112021026189A BR112021026189A2 (pt) 2019-06-24 2020-06-23 Ligas de alumínio forjado da série 7xxx espessas melhoradas e métodos para fazer as mesmas
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WO2024086117A1 (fr) * 2022-10-17 2024-04-25 MELD Manufacturing Corporation Produits en alliage d'aluminium de série 6000 produits par fabrication à l'état solide
WO2024086118A1 (fr) * 2022-10-17 2024-04-25 MELD Manufacturing Corporation Produits en alliage d'aluminium de série 5000 produits à l'aide d'une fabrication à l'état solide
CN116144993A (zh) * 2022-10-31 2023-05-23 沈阳航空航天大学 电弧增材制造用7系铝合金丝材及其制备方法和应用

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US20220106672A1 (en) 2022-04-07
CA3143806A1 (fr) 2020-12-30
EP3987072A1 (fr) 2022-04-27

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