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EP3294917B2 - Alliages d'aluminium de série 7xxx corroyés épais améliorés et procédés de production correspondants - Google Patents

Alliages d'aluminium de série 7xxx corroyés épais améliorés et procédés de production correspondants

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Publication number
EP3294917B2
EP3294917B2 EP16793338.1A EP16793338A EP3294917B2 EP 3294917 B2 EP3294917 B2 EP 3294917B2 EP 16793338 A EP16793338 A EP 16793338A EP 3294917 B2 EP3294917 B2 EP 3294917B2
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EP
European Patent Office
Prior art keywords
aluminum alloy
7xxx aluminum
max
alloy product
dev
Prior art date
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Application number
EP16793338.1A
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German (de)
English (en)
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EP3294917A1 (fr
EP3294917B1 (fr
EP3294917A4 (fr
Inventor
Julien Boselli
Jen C. Lin
Mark A. James
Gary H. Bray
John R. Brockenbrough
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Arconic Technologies LLC
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Arconic Technologies LLC
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Priority to EP22158417.0A priority Critical patent/EP4074851A1/fr
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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22D—CASTING OF METALS; CASTING OF OTHER SUBSTANCES BY THE SAME PROCESSES OR DEVICES
    • B22D7/00—Casting ingots, e.g. from ferrous metals
    • B22D7/005—Casting ingots, e.g. from ferrous metals from non-ferrous metals
    • 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
    • C22F1/04—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
    • 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
    • C22F1/10—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of nickel or cobalt or alloys based thereon

Definitions

  • Aluminum alloys are useful in a variety of applications. However, improving one property of an aluminum alloy without degrading another property is elusive. For example, it is difficult to increase the strength of a wrought aluminum alloy without affecting other properties such as fracture toughness or corrosion resistance.
  • Another property of interest is "crack deviation", where a crack abruptly changes direction from the intended or expected fracture plane under fatigue loading (e.g., Mode I loading). Crack deviation can be a problem for aircraft manufacturers in some applications because it is difficult to take into account during design.
  • FIG. 13 shows crack deviation of a constant load amplitude fatigue crack growth test specimen.
  • CN 103233148 discloses: an aluminum alloy product comprising, by weight, 5.5-10.0 % Zn, 1.5-2.8 % Mg, 1.5-2.5 % Cu, 0.01-0.50 % Cr, 0.05-0.50 % Mn, and 0.01-0.20 % Zr; and a method of preparing said aluminum alloy product.
  • the present patent application relates to improved thick wrought 7xxx aluminum alloy products.
  • the new thick wrought 7xxx aluminum alloy products may realize an improved combination of crack deviation resistance and at least one of strength, elongation, fracture toughness, and corrosion resistance, among other properties.
  • the new thick wrought 7xxx aluminum alloy products comprise 0.080 - 0.250 wt. % Cr and have a nominal thickness of from 10.16-30.48 cm (4.0 to 12.0 inches).
  • the new thick wrought 7xxx aluminum alloys also contain 6.0 - 10.0 wt. % Zn, 1.3 - 2.3 wt. % Mg, and 1.2 - 2.6 wt. % Cu.
  • the new thick wrought 7xxx aluminum alloys contain 0.15 to 0.50 wt. % Mn.
  • the new thick wrought 7xxx aluminum alloys may contain up to 0.15 wt. % Zr, up to 0.15 wt. % Ti, up to 0.15 wt. % Si, and up to 0.15 wt.
  • a new wrought 7xxx aluminum alloy product includes 0.080 - 0.250 wt. % Cr, 0.15 - 0.50 wt. % Mn, and 0.07 - 0.15 wt. % Zr.
  • the new thick wrought 7xxx aluminum alloy products generally contain a sufficient amount of chromium to obtain improved crack deviation resistance properties as compared to an equivalent 7xxx aluminum alloy product having not greater than 0.01 wt. % Cr and not greater than 0.02 wt. % Mn.
  • an "equivalent 7xxx aluminum alloy product" is of an equivalent composition, form, thickness and temper as the new thick wrought 7xxx aluminum alloy product, but contains not greater than 0.01 wt. % Cr and not greater than 0.02 wt. % Mn.
  • an improved new thick wrought 7xxx aluminum alloy according to the invention would have an equivalent composition to the conventional 7085 aluminum alloy plate product, but would also include 0.080 - 0.250 wt. % Cr and 0.15-0.50 wt. % Mn optionally with 0.07 - 0.15 wt. % Zr, as provided below.
  • Such an improved new thick wrought 7xxx aluminum alloy accordingly would also be a plate product, would have a nominal thickness of 12.7 cm (5.00 inches), and would also be artificially aged to achieve a typical tensile yield strength (L) of about 483 MPa (70 ksi).
  • L tensile yield strength
  • the improved new thick wrought 7xxx aluminum alloy, however, would achieve at least 5% better (higher) typical L-S crack deviation resistance K max-dev at a strength of 483 MPa (70 ksi) as compared to the conventional 7085 aluminum alloy plate product, and at least partially due to the use of chromium and manganese optionally with zirconium.
  • Mn can partially substitute for Cr in E phase but will also likely form separate dispersoid phases (e.g., Al 6 Mn, Al 12 (Mn,Fe) 3 Si). Such dispersoids are believed to help keep the fatigue crack stay in plane through void initiation and growth ahead of the crack-tip. Zirconium forms Al 3 Zr, which, in combination with the E phase and/or Mn-containing dispersoids, may further facilitate improved crack deviation resistance.
  • a new thick wrought 7xxx aluminum alloy product realizes at least a 10% improvement in typical L-S crack deviation resistance K max-dev as compared to an equivalent 7xxx aluminum alloy product having not greater than 0.01 wt. % Cr and not greater than 0.02 wt. % Mn, at equivalent strength.
  • a new thick wrought 7xxx aluminum alloy product realizes at least a 12% improvement in typical L-S crack deviation resistance K max-dev as compared to an equivalent 7xxx aluminum alloy product having not greater than 0.01 wt. % Cr and not greater than 0.02 wt. % Mn, at equivalent strength.
  • a new thick wrought 7xxx aluminum alloy product realizes at least a 14% improvement in typical L-S crack deviation resistance K max-dev as compared to an equivalent 7xxx aluminum alloy product having not greater than 0.01 wt. % Cr and not greater than 0.02 wt. % Mn, at equivalent strength.
  • a new thick wrought 7xxx aluminum alloy product realizes at least a 16% improvement in typical L-S crack deviation resistance K max-dev as compared to an equivalent 7xxx aluminum alloy product having not greater than 0.01 wt. % Cr and not greater than 0.02 wt. % Mn, at equivalent strength.
  • a new thick wrought 7xxx aluminum alloy product realizes at least a 18% improvement in typical L-S crack deviation resistance K max-dev as compared to an equivalent 7xxx aluminum alloy product having not greater than 0.01 wt. % Cr and not greater than 0.02 wt. % Mn, at equivalent strength.
  • a new thick wrought 7xxx aluminum alloy product realizes at least a 20% improvement in typical L-S crack deviation resistance K max-dev as compared to an equivalent 7xxx aluminum alloy product having not greater than 0.01 wt. % Cr and not greater than 0.02 wt. % Mn, at equivalent strength.
  • a new thick wrought 7xxx aluminum alloy product realizes at least a 22% improvement in typical L-S crack deviation resistance K max-dev as compared to an equivalent 7xxx aluminum alloy product having not greater than 0.01 wt. % Cr and not greater than 0.02 wt. % Mn, at equivalent strength.
  • a new thick wrought 7xxx aluminum alloy product realizes at least a 24% improvement in typical L-S crack deviation resistance K max-dev as compared to an equivalent 7xxx aluminum alloy product having not greater than 0.01 wt. % Cr and not greater than 0.02 wt. % Mn, at equivalent strength.
  • a new thick wrought 7xxx aluminum alloy product realizes at least a 26% improvement in typical L-S crack deviation resistance K max-dev as compared to an equivalent 7xxx aluminum alloy product having not greater than 0.01 wt. % Cr and not greater than 0.02 wt. % Mn, at equivalent strength.
  • a new thick wrought 7xxx aluminum alloy product realizes at least a 28% improvement in typical L-S crack deviation resistance K max-dev as compared to an equivalent 7xxx aluminum alloy product having not greater than 0.01 wt. % Cr and not greater than 0.02 wt. % Mn, at equivalent strength.
  • a new thick wrought 7xxx aluminum alloy product realizes at least a 30% improvement in typical L-S crack deviation resistance K max-dev as compared to an equivalent 7xxx aluminum alloy product having not greater than 0.01 wt. % Cr and not greater than 0.02 wt. % Mn, at equivalent strength.
  • a new thick wrought 7xxx aluminum alloy product may realize at least equivalent L-T plane strain fracture toughness to the equivalent 7xxx aluminum alloy product having not greater than 0.01 wt. % Cr and not greater than 0.02 wt. % Mn, at equivalent strength.
  • a new thick wrought 7xxx aluminum alloy product may realize at least equivalent corrosion resistance (e.g., stress corrosion cracking resistance, exfoliation corrosion resistance) to the equivalent 7xxx aluminum alloy product having not greater than 0.01 wt. % Cr and not greater than 0.02 wt. % Mn, at equivalent strength.
  • equivalent corrosion resistance e.g., stress corrosion cracking resistance, exfoliation corrosion resistance
  • chromium may facilitate improved crack deviation resistance properties.
  • too much chromium may result in unnecessary degradation of strength and/or fracture toughness.
  • the amount of chromium in the new thick wrought 7xxx aluminum alloy products may be limited to facilitate achievement of the improved combination of properties described herein.
  • the amount of chromium required to achieve the improved combination of properties may vary over the different types of 7xxx alloys described herein (e.g., due to magnesium content), but the amount of chromium required generally falls within the range of 0.080 to 0.250 wt. % Cr, keeping in mind to limit the amount of chromium so as to avoid coarse chromium particles.
  • the wrought 7xxx aluminum alloy product may include up to 0.15 wt. % Zr (e.g., 0.07 - 0.15 wt. % Zr).
  • a new thick wrought 7xxx aluminum alloy product includes from 0.09 to 0.13 wt. % Zr.
  • a new thick wrought 7xxx aluminum alloy product includes from 0.09 to 0.11 wt. % Zr.
  • a new thick wrought 7xxx aluminum alloy product includes from 0.10 to 0.12 wt. % Zr.
  • a new thick wrought 7xxx aluminum alloy product includes from 0.07 to 0.09 wt. % Zr.
  • a new thick wrought 7xxx aluminum alloy product includes from 0.11 to 0.13 wt. % Zr.
  • the new thick wrought 7xxx aluminum alloy products are essentially free of zirconium, containing not greater than 0.03 wt. % Zr, or not greater than 0.01 wt. % Zr, or not greater than 0.005 wt. % Zr, or not greater than 0.001 wt. % Zr.
  • the new thick wrought 7xxx aluminum alloy product includes 0.15 to 0.50 wt. % Mn.
  • the amount of Mn should be limited so as to avoid detrimentally impacting the combination of strength, fracture toughness and crack deviation resistance.
  • some manganese is included in the new thick wrought 7xxx aluminum alloy product.
  • a new thick wrought 7xxx aluminum alloy product includes from 0.20 to 0.50 wt. % Mn.
  • a new thick wrought 7xxx aluminum alloy product includes from 0.25 to 0.45 wt. % Mn.
  • the new thick wrought 7xxx aluminum alloy products generally contain an amount of chromium sufficient to obtain a typical L-S crack deviation resistance K max-dev of at least 37 MPa ⁇ m (34 ksi ⁇ in.) as measured on a rolled 12.7 cm (5.00 inch) version of the wrought 7xxx aluminum alloy product in the T7451 or T7651 temper, and at least equivalent strength to that of an equivalent 7xxx aluminum alloy product having not greater than 0.01 wt. % Cr and not greater than 0.02 wt. % Mn.
  • the new thick wrought 7xxx aluminum alloy products contain an amount of the chromium sufficient to obtain a typical L-S crack deviation resistance K max-dev of at least 38 MPa ⁇ m (35 ksi ⁇ in.) as measured on a rolled 12.7 cm (5.00 inch) version of the wrought 7xxx aluminum alloy product in the T7451 or T7651 temper, and at least equivalent strength to that of an equivalent 7xxx aluminum alloy product having not greater than 0.01 wt. % Cr and not greater than 0.02 wt. % Mn.
  • the new thick wrought 7xxx aluminum alloy products contain an amount of the chromium sufficient to obtain a typical L-S crack deviation resistance K max-dev of at least 40 MPa ⁇ m (36 ksi ⁇ in.) as measured on a rolled 12.7 cm (5.00 inch) version of the wrought 7xxx aluminum alloy product in the T7451 or T7651 temper, and at least equivalent strength to that of an equivalent 7xxx aluminum alloy product having not greater than 0.01 wt. % Cr and not greater than 0.02 wt. % Mn.
  • the new thick wrought 7xxx aluminum alloy products contain an amount of the chromium sufficient to obtain a typical L-S crack deviation resistance K max-dev of at least 41 MPa ⁇ m (37 ksi ⁇ in.) as measured on a rolled 12.7 cm (5.00 inch) version of the wrought 7xxx aluminum alloy product in the T7451 or T7651 temper, and at least equivalent strength to that of an equivalent 7xxx aluminum alloy product having not greater than 0.01 wt. % Cr and not greater than 0.02 wt. % Mn.
  • the new thick wrought 7xxx aluminum alloy products contain an amount of the chromium sufficient to obtain a typical L-S crack deviation resistance K max-dev of at least 42 MPa ⁇ m (38 ksi ⁇ in.) as measured on a rolled 12.7 cm (5.00 inch) version of the wrought 7xxx aluminum alloy product in the T7451 or T7651 temper, and at least equivalent strength to that of an equivalent 7xxx aluminum alloy product having not greater than 0.01 wt. % Cr and not greater than 0.02 wt. % Mn.
  • the new thick wrought 7xxx aluminum alloy products contain an amount of the chromium sufficient to obtain a typical L-S crack deviation resistance K max-dev of at least 43 MPa ⁇ m (39 ksi ⁇ in.) as measured on a rolled 12.7 cm (5.00 inch) version of the wrought 7xxx aluminum alloy product in the T7451 or T7651 temper, and at least equivalent strength to that of an equivalent 7xxx aluminum alloy product having not greater than 0.01 wt. % Cr and not greater than 0.02 wt. % Mn.
  • the new thick wrought 7xxx aluminum alloy products contain an amount of the chromium sufficient to obtain a typical L-S crack deviation resistance K max-dev of at least 44MPa ⁇ m (40 ksi ⁇ in.) as measured on a rolled 12.7 cm (5.00 inch) version of the wrought 7xxx aluminum alloy product in the T7451 or T7651 temper, and at least equivalent strength to that of an equivalent 7xxx aluminum alloy product having not greater than 0.01 wt. % Cr and not greater than 0.02 wt. % Mn.
  • the new thick wrought 7xxx aluminum alloy products contain an amount of the chromium sufficient to obtain a typical L-S crack deviation resistance K max-dev of at least 45 MPa ⁇ m (41 ksi ⁇ in.) as measured on a rolled 12.7 cm (5.00 inch) version of the wrought 7xxx aluminum alloy product in the T7451 or T7651 temper, and at least equivalent strength to that of an equivalent 7xxx aluminum alloy product having not greater than 0.01 wt. % Cr and not greater than 0.02 wt. % Mn.
  • the new thick wrought 7xxx aluminum alloy products contain an amount of the chromium sufficient to obtain a typical L-S crack deviation resistance K max-dev of at least 46 MPa ⁇ m (42 ksi ⁇ in.) as measured on a rolled 12.7 cm (5.00 inch) version of the wrought 7xxx aluminum alloy product in the T7451 or T7651 temper, and at least equivalent strength to that of an equivalent 7xxx aluminum alloy product having not greater than 0.01 wt. % Cr and not greater than 0.02 wt. % Mn.
  • a new thick wrought 7xxx aluminum alloy product contains an amount of the chromium sufficient to obtain a typical L-S crack deviation resistance K max-dev of at least 47 MPa ⁇ m (43 ksi ⁇ in.) as measured on a rolled 12.7 cm (5.00 inch) version of the wrought 7xxx aluminum alloy product in the T7451 or T7651 temper, and at least equivalent strength to that of an equivalent 7xxx aluminum alloy product having not greater than 0.01 wt. % Cr and not greater than 0.02 wt. % Mn.
  • a new thick wrought 7xxx aluminum alloy product contains an amount of the chromium sufficient to obtain a typical L-S crack deviation resistance K max-dev of at least 48 MPa ⁇ m (44 ksi ⁇ in.) as measured on a rolled 12.7 cm (5.00 inch) version of the wrought 7xxx aluminum alloy product in the T7451 or T7651 temper, and at least equivalent strength to that of an equivalent 7xxx aluminum alloy product having not greater than 0.01 wt. % Cr and not greater than 0.02 wt. % Mn.
  • a new thick wrought 7xxx aluminum alloy product contains an amount of the chromium sufficient to obtain a typical L-S crack deviation resistance K max-dev of at least 49 MPa ⁇ m (45 ksi ⁇ in.) as measured on a rolled 12.7 cm (5.00 inch) version of the wrought 7xxx aluminum alloy product in the T7451 or T7651 temper, and at least equivalent strength to that of an equivalent 7xxx aluminum alloy product having not greater than 0.01 wt. % Cr and not greater than 0.02 wt. % Mn.
  • the new thick wrought 7xxx aluminum alloy product contains an amount of the Zn, Mg, Cu and Cr sufficient to realize all of (a) a typical L-S crack deviation resistance K max-dev of at least 37 MPa ⁇ m (34 ksi ⁇ in.), (b) a typical L tensile yield strength of at least 434 MPa (63 ksi), and (c) a typical L-T plane strain K IC fracture toughness of at least 23 MPa ⁇ m (21 ksi ⁇ in.) relative to (as measured on) a rolled 12.7 cm (5.00 inch) version of the wrought 7xxx aluminum alloy product in the T7451 or T7651 temper.
  • this new thick wrought 7xxx aluminum alloy product contains an amount of the Zn, Mg, Cu and Cr sufficient to realize the above strength and crack deviation properties and such that the realized L-S K max-dev and TYS(L) satisfy the expression y ⁇ -0.8184x + 92.61, where x is the TYS(L) and y is the L-S K max-dev .
  • this new thick wrought 7xxx aluminum alloy product contains an amount of the Zn, Mg, Cu and Cr sufficient to realize the above strength and crack deviation properties and such that the realized L-S K max-dev and TYS(L) satisfy the expression y ⁇ -0.8184x + 93.11, where x is the TYS(L) and y is the L-S K max-dev .
  • this new thick wrought 7xxx aluminum alloy product contains an amount of the Zn, Mg, Cu and Cr sufficient to realize the above strength and crack deviation properties and such that the realized L-S K max-dev and TYS(L) satisfy the expression y ⁇ -0.8184x + 93.61, where x is the TYS(L) and y is the L-S K max-dev .
  • this new thick wrought 7xxx aluminum alloy product contains an amount of the Zn, Mg, Cu and Cr sufficient to realize the above strength and crack deviation properties and such that the realized L-S K max-dev and TYS(L) satisfy the expression y ⁇ -0.8184x + 94.11, where x is the TYS(L) and y is the L-S K max-dev .
  • this new thick wrought 7xxx aluminum alloy product contains an amount of the Zn, Mg, Cu and Cr sufficient to realize the above strength and crack deviation properties and such that the realized L-S K max-dev and TYS(L) satisfy the expression y ⁇ -0.8184x + 94.61, where x is the TYS(L) and y is the L-S K max-dev .
  • this new thick wrought 7xxx aluminum alloy product contains an amount of the Zn, Mg, Cu and Cr sufficient to realize the above strength and crack deviation properties and such that the realized L-S K max-dev and TYS(L) satisfy the expression y ⁇ -0.8184x + 95.11, where x is the TYS(L) and y is the L-S K max-dev .
  • this new thick wrought 7xxx aluminum alloy product contains an amount of the Zn, Mg, Cu and Cr sufficient to realize the above strength and crack deviation properties and such that the realized L-S K max-dev and TYS(L) satisfy the expression y ⁇ -0.8184x + 95.61, where x is the TYS(L) and y is the L-S K max-dev .
  • this new thick wrought 7xxx aluminum alloy product contains an amount of the Zn, Mg, Cu and Cr sufficient to realize the above strength and crack deviation properties and such that the realized L-S K max-dev and TYS(L) satisfy the expression y ⁇ -0.8184x + 96.11, where x is the TYS(L) and y is the L-S K max-dev .
  • this new thick wrought 7xxx aluminum alloy product contains an amount of the Zn, Mg, Cu and Cr sufficient to realize the above strength and crack deviation properties and such that the realized L-S K max-dev and TYS(L) satisfy the expression y ⁇ - 0.8184x + 96.61, where x is the TYS(L) and y is the L-S K max-dev .
  • this new thick wrought 7xxx aluminum alloy product contains an amount of the Zn, Mg, Cu and Cr sufficient to realize the above strength and crack deviation properties and such that the realized L-S K max-dev and TYS(L) satisfy the expression y ⁇ -0.8184x + 97.11, where x is the TYS(L) and y is the L-S K max-dev .
  • this new thick wrought 7xxx aluminum alloy product contains an amount of the Zn, Mg, Cu and Cr sufficient to realize the above strength and crack deviation properties and such that the realized L-S K max-dev and TYS(L) satisfy the expression y ⁇ -0.8184x + 97.61, where x is the TYS(L) and y is the L-S K max-dev .
  • this new thick wrought 7xxx aluminum alloy product contains an amount of the Zn, Mg, Cu and Cr sufficient to realize the above strength and crack deviation properties and such that the realized L-S K max-dev and TYS(L) satisfy the expression y ⁇ -0.8184x + 98.11, where x is the TYS(L) and y is the L-S K max-dev .
  • this new thick wrought 7xxx aluminum alloy product contains an amount of the Zn, Mg, Cu and Cr sufficient to realize the above strength and crack deviation properties and such that the realized L-S K max-dev and TYS(L) satisfy the expression y ⁇ - 0.8184x + 98.61, where x is the TYS(L) and y is the L-S K max-dev .
  • this new thick wrought 7xxx aluminum alloy product contains an amount of the Zn, Mg, Cu and Cr sufficient to realize the above strength and crack deviation properties and such that the realized L-S K max-dev and TYS(L) satisfy the expression y ⁇ -0.8184x + 99.11, where x is the TYS(L) and y is the L-S K max-dev .
  • this new thick wrought 7xxx aluminum alloy product contains an amount of the Zn, Mg, Cu and Cr sufficient to realize the above strength and crack deviation properties and such that the realized L-S K max-dev and TYS(L) satisfy the expression y ⁇ -0.8184x + 99.61, where x is the TYS(L) and y is the L-S K max-dev .
  • x is in units of ksi and y is in units of ksi ⁇ in.
  • Equation (5) is: Mg ⁇ A 5 ⁇ Cu + B 5 ⁇ Zn + C 5 ⁇ Cu ⁇ 1.9 ⁇ Zn ⁇ 8 + D 5 ⁇ Cu ⁇ 1.9 2 + E 5 ⁇ Zn ⁇ 8 2 + F 5 G 5 ⁇ Cu + H 5 ⁇ Zn + I 5 ⁇ Cu ⁇ 1.9 ⁇ Zn ⁇ 8 + J 5 ⁇ Cu ⁇ 1.9 2 + K 5 ⁇ Zn ⁇ 8 2 + 1
  • the new thick wrought 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 TiB 2 or TiC. Elemental titanium may also or alternatively be used. In one embodiment, the new thick wrought 7xxx aluminum alloy product includes from 0.005 to 0.025 wt. % Ti.
  • the new thick wrought 7xxx aluminum alloy product may include up to 0.15 wt. % Si and up to 0.15 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 thick wrought 7xxx aluminum alloy product may include up to 0.10 wt. % Si and up to 0.12 wt. % Fe as impurities.
  • the new thick wrought 7xxx aluminum alloy product may include up to 0.08 wt. % Si and up to 0.10 wt. % Fe as impurities.
  • the new thick wrought 7xxx aluminum alloy product may include up to 0.06 wt.
  • the new thick wrought 7xxx aluminum alloy product may include up to 0.04 wt. % Si and up to 0.06 wt. % Fe as impurities. In another embodiment, the new thick wrought 7xxx aluminum alloy product may include up to 0.03 wt. % Si and up to 0.05 wt. % Fe as impurities.
  • the new thick wrought 7xxx aluminum alloy product has a thickness of from 10.16 - 30.48 cm (4.0 to 12.0 inches). In one embodiment, the new thick wrought 7xxx aluminum alloy product has a thickness of from 10.16 - 25.4 cm (4.0 to 10.0 inches). In another embodiment, the new thick wrought 7xxx aluminum alloy product has a thickness of from 10.16 - 20.3 cm (4.0 to 8.0 inches). In yet another embodiment, the new thick wrought 7xxx aluminum alloy product has a thickness of from 10.16-15.24 cm (4.0 to 6.0 inches). In another embodiment, the new thick wrought 7xxx aluminum alloy product has a thickness of from 10.16-12.7 cm (4.0 to 5.0 inches).
  • the new thick wrought 7xxx aluminum alloy product has a thickness of from 12.7 - 30.48 cm (5.0 to 12.0 inches). In one embodiment, the new thick wrought 7xxx aluminum alloy product has a thickness of from 12.7 - 25.4 cm (5.0 to 10.0 inches). In another embodiment, the new thick wrought 7xxx aluminum alloy product has a thickness of from 12.7 - 20.3 cm (5.0 to 8.0 inches). In yet another embodiment, the new thick wrought 7xxx aluminum alloy product has a thickness of from 12.7 - 15.24 cm (5.0 to 6.0 inches).
  • the wrought 7xxx aluminum alloy product is in the form of a rolled product, an extruded product, or a forged product.
  • a new thick wrought 7xxx aluminum alloy product is a rolled product.
  • a new thick wrought 7xxx aluminum alloy product is an extruded product.
  • a new thick wrought 7xxx aluminum alloy product is a forged product (e.g., a hand forged product, a die forged product).
  • TYS(L) typically longitudinal (L) tensile yield strength
  • 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 L-S crack deviation resistance K max-dev is determined by preparing at least triplicate C(T) specimens in accordance with ASTM E647-13e01, entitled “Standard Test Method for Measurement of Fatigue Crack Growth Rates” (“ASTM E647”).
  • the at least triplicate C(T) specimens are taken in the L-S direction from between width/3 and 2width/3 of the material, where the "B” dimension of the specimen is 6.35 mm (0.25 inch) and the "W” dimension of the specimen is 7.62 cm (3.0 inches), and with the notch tip at T/2.
  • the pre-crack must meet all validity requirements of ASTM E647, and the pre-cracking must be performed at the same loading conditions as the test.
  • the test is started using a K max > 11.1 MPa ⁇ m (10 ksi ⁇ in.), and the starting force must be large enough that crack deviation occurs before the ASTM E647 C(T) specimen validity requirement ((W-a) ⁇ (4/ ⁇ )*(K max-dev /TYS) 2 ) is no longer met for the test.
  • the test must be valid per ASTM E647 up to the point of crack deviation.
  • a crack "deviates" when the crack of the C(T) specimen substantially deviates from the intended fracture plane (e.g., by 70-110°) in any direction, and the deviation leads to specimen separation along an unintended fracture plane.
  • the typical TYS(L), the typical L-T K IC , and/or the typical L-S K max-dev are generally required to be determined on a rolled 12.7 cm (5.00 inch) version of the 7xxx aluminum alloy product in the T7451 and the T7651 tempers.
  • a "rolled 12.7 cm (5.00 inch) version of the 7xxx aluminum alloy product” means a 7xxx aluminum alloy product, having a composition within the scope of the Zn, Mg and Cu limits described herein, that has been conventionally rolled to a nominal thickness of 12.7 cm (5.00 inches), within thickness tolerance limits per ANSI H35.2-2001, table 7.7b.
  • T76 temper means the T76 temper described in ANSI H35.1-2009, and further requiring SCC resistance (stress corrosion cracking resistance), wherein the SCC resistance is tested in accordance with ASTM G47(2011) using three specimens, wherein all three specimens survive the alternate immersion test for a period of 20 days at a net stress of 172 MPa (25 ksi) in the short-transverse (ST) direction.
  • T7651 temper means the T76 temper where the plate is stress-relieved 1.5 - 3.0% by stretching prior to artificial aging.
  • T74 temper means the T74 temper described in ANSI H35.1-2009, and further requiring SCC resistance (stress corrosion cracking resistance), wherein the SCC resistance is tested in accordance with ASTM G47(2011) using three specimens, wherein all three specimens survive the alternate immersion test for a period of 20 days at a net stress of 241 MPa (35 ksi) in the short-transverse (ST) direction.
  • T7451 temper means the T74 temper where the plate is stress-relieved 1.5 - 3.0% by stretching prior to artificial aging.
  • Example alloys 8, 9 and 30 are alloys according to the invention as defined by the claims.
  • Alloy 1 is a conventional aluminum alloy, registered with the Aluminum Association as aluminum alloy 7085.
  • the registered version of the 7085 alloy requires, among other things, 0.08 - 0.15 wt. % Zr, not greater than 0.04 wt. % Mn and not greater than 0.04 wt. % Cr, as shown by the document " International Alloy Designations and Chemical Composition Limits for Wrought Aluminum and Wrought Aluminum Alloys", The Aluminum Association (2009), page 12 .
  • 6,972,110 also relates to the 7085 alloy.
  • Alloys 2-3 are new variants of the 7085 alloy having manganese (Mn) and/or low or no zirconium (Zr).
  • Table 1 Composition of Example 1 Alloys (wt. %) - Lab Scale Materials Alloy Si Fe Cu Mn Mg Cr Zn Ti Zr 1 0.02 0.05 1.65 0.04 1.44 0 7.35 0.03 0.11 2 0.02 0.05 1.68 0.25 1.46 0 7.52 0.02 0.07 3 0.02 0.06 1.70 0.50 1.42 0 7.47 0.04 0
  • each alloy was aluminum and unavoidable impurities ( ⁇ 0.03 wt. % each, ⁇ 0.10 wt. % total).
  • the ingots were stress-relieved, sawed into multiple sections, scalped, homogenized, and then hot rolled to plate having a final gauge of about 4.445 cm (1.75 inches).
  • the alloy plates were then solution heat treated and then hot water quenched in 87.8 °C (190°F) water to simulate cooling conditions at T/2 (mid-thickness) for 12.7 cm (5 inch) plate relative to cold water (ambient) quenching.
  • the plates were then stretched about 2.25% and then artificially aged in accordance with a standard T7651-type aging practice ( see, ANSI H35.1 and AMS 4329A).
  • Tables 2-3 The test results are shown in Tables 2-3, below.
  • Table 2 provides the measured values in standard metric units, and Table 3 provides the measured values in English units.
  • the shown strength and elongation values are averages of duplicate specimens.
  • the fracture toughness values are taken from a single specimen.
  • the crack deviation values are averages of triplicate specimens.
  • Table 4 Composition of Example 1 Alloys (wt. %) - Plant Materials Alloy Si Fe Cu Mn Mg Cr Zn Ti Zr 4 0.024 0.032 1.63 0 1.52 0 7.44 0.018 0.11 5 0.020 0.036 1.643 0 1.51 0 7.28 0.020 0.10
  • Alloy 4 is a conventional 7085-style plate product rolled to a final gauge of 137.2 mm (5.4 inches).
  • Alloy 5 is a conventional 7085-style plate product rolled to a final gauge of 132.1 mm (5.2 inches). Alloy 4 was aged to a T7651-style temper.
  • Alloy 5 was aged to two different aging conditions, (a) a T7451-style temper ( see, ANSI H35.1 and AMS 4470A) and (b) an aging condition overaged relative to the T7451-style temper.
  • a T7451-style temper see, ANSI H35.1 and AMS 4470A
  • an aging condition overaged relative to the T7451-style temper After artificial aging, the mechanical properties of Alloys 4-5 were tested as per the testing of the lab-scale materials, except the strength and elongation properties were measured at T/4, the L-S K max-dev C(T) specimen "W" dimension was 7.62 cm (3.0 inches), and the tests were started using a K max of approximately 11 MPa ⁇ m (10 ksi ⁇ in.) The test results are shown in Tables 5-6, below. Table 5 provides the measured values in standard metric units, and Table 6 provides the measured values in English units.
  • FIGS. 1-3 are graphs illustrating the properties of the alloys based on the above data.
  • the plant and lab-scale 7085 T7651-style materials have generally similar properties, indicating that the slow quench conditions for the lab-scale materials appropriately model the behavior of the plant produced thick gauge products.
  • the addition of manganese in alloys 2-3 appears to have a limited impact on improving the combination of crack deviation resistance and tensile yield strength.
  • Table 7 Composition of Example 2 Alloys (wt. %) - Plant Materials Alloy Si Fe Cu Mn Mg Cr Zn Ti Zr 6 0.02 0.03 1.65 0 1.52 0 7.48 0.02 0.10 7 0.03 0.04 1.75 0 1.53 0.14 7.54 0.02 0.07 8 0.03 0.05 1.65 0.26 1.50 0.15 7.48 0.02 0.07 9 0.03 0.05 1.65 0.26 1.50 0.15 7.48 0.02 0.07 0.07
  • each alloy was aluminum and unavoidable impurities ( ⁇ 0.03 wt. % each, ⁇ 0.10 wt. % total).
  • the plant-scale ingots were scalped, homogenized, and then hot rolled to final gauge.
  • the alloy plates were then solution heat treated and then cold water quenched.
  • the plates were then stretched about 2.25% and then artificially aged in accordance with a T7651-type aging practice ( see, ANSI H35.1 and AMS 4329A).
  • Alloy 6 is a conventional 7085-style plate product rolled to a final gauge of 165.1 mm (6.5 inches).
  • Alloys 7-9 are new variants of the 7085 alloy having manganese (Mn), chromium (Cr), and/or low zirconium (Zr). Alloys 7-8 were rolled to a final gauge of 137.2 mm (5.4 inches). Alloy 9 was rolled to a final gauge of 165.1 mm (6.5 inches).
  • K max-dev The typical L-S crack deviation resistance properties (K max-dev ) were determined per the test procedure described above, except the "W" dimension of the specimen was 5.08 cm (2.0 inches). The test is started using a K max of approximately 16.5 MPa ⁇ m (15 ksi ⁇ in.) The test results are shown in Tables 8-9, below. Table 8 provides the measured values in standard metric units, and Table 9 provides the measured values in English units.
  • FIGS. 5-8 are graphs illustrating the properties of the plant based materials. As shown, the new materials having chromium, manganese, and zirconium realize a large improvement in crack deviation resistance relative to the conventional material. The new materials also realize a similar or improved strength-toughness trade-off.
  • FIG. 4 illustrates one embodiment of a property requirement boundary for the new thick wrought 7xxx alloys based on data herein.
  • Table 10 Composition of Example 3 Alloys (wt. %) - Lab-Scale Alloy Si Fe Cu Mn Mg Cr Zn Ti Zr 10 0.02 0.04 1.67 0 1.51 0 7.64 0.02 0.11 11 0.03 0.03 1.65 0 1.57 0.15 7.46 0.02 0 12 0.02 0.04 1.63 0.45 1.49 0.15 7.47 0.02 0 13 0.02 0.05 1.74 0.46 1.40 0.16 7.48 0.02 0.12 14 0.02 0.04 1.65 0 2.11 0 7.65 0.02 0.11 15 0.03 0.03 1.64 0 2.05 0.14 7.40 0.02 0 16 0.03 0.03 1.69 0 2.03 0.15 7.57 0.02 0 17 0.03 0.03 1.67 0 2.02 0.17 7.56 0.02 0 18 0.02 0.04 1.66 0 1.47 0 6.32 0.02 0.11 19 0.03 0.02 1.63 0 1.48 0.15 6.39 0.02
  • Alloy 10 is a conventional 7085-style alloy. Alloys 11-26 are new alloys having varying amounts of zinc (Zn), magnesium (Mg), copper (Cu), manganese (Mn), chromium (Cr), and/or zirconium (Zr).
  • the lab-scale ingot were stress-relieved, sawed into multiple sections, scalped, homogenized, and then hot rolled to plate having a final gauge of about 4.445 cm (1.75 inches).
  • the alloy plates were then solution heat treated and then hot water quenched in 82.2°C (180°F) water to simulate cooling conditions at T/2 (mid-thickness) for 7.62 cm (3 inch) plate relative to cold water (ambient) quenching.
  • the plates were then stretched about 2.25% and then artificially aged in accordance with a standard T7X51-type aging practice, expected to fall between T7651 and T7451.
  • FIG. 10 shows that a similar trade-off between fracture toughness and tensile yield strength is achieved for a 7085-type alloy containing Cr, Mn and Zr (alloy 13) over the conventional 7085 material (alloy 10).
  • alloys with increased Mg, reduced or increased Zn content with additions of Cr realize similar or improved trade-offs between fracture toughness and tensile yield strength over their Cr-free and Zr-containing base alloys.
  • Table 14 provides the measured values in standard metric units, and Table 15 provides the measured values in English units.
  • FIGS. 11-12 are graphs illustrating properties of the Example 4 alloys. As shown, the addition of manganese in alloys 27 & 28 appears to have a limited impact on improving the trade-off between crack deviation resistance and tensile yield strength. Furthermore, the addition of only low levels of Cr (0.12-0.13) in alloys 29 & 30 appears to be insufficient to provide a significant impact on K max-dev relative to conventional 7085 materials (alloys 31 & 32).

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Claims (4)

  1. Produit d'alliage d'aluminium corroyé 7xxx comprenant :
    0,080 à 0,250 % en poids de Cr ;
    6,0 à 10,0 % en poids de Zn ;
    1,3 à 2,3 % en poids de Mg ;
    1,2 à 2,6 % en poids de Cu ;
    0,15 à 0,50 % en poids de Mn ;
    jusqu'à 0,15 % en poids de Zr ;
    jusqu'à 0,15 % en poids de Ti ;
    jusqu'à 0,15 % en poids de Si ; et
    jusqu'à 0,15 % en poids de Fe,
    le reste étant de l'aluminium et des impuretés, dans lequel le produit d'alliage d'aluminium corroyé 7xxx ne comporte pas plus de 0,05 % en poids de l'une quelconque des impuretés, et dans lequel le produit d'alliage d'aluminium corroyé 7xxx ne comporte pas plus de 0,15 % en poids total des impuretés ;
    dans lequel Cr(min) ≤ Cr ≤ Cr(max), dans lequel :
    Cr(min) = 0,251 - 0,082 (Mg), dans lequel Cr(min) ≥ 0,080 ; et
    Cr(max) = 0,351 - 0,082 (Mg), dans lequel Cr(max) ≤ 0,25 ;
    dans lequel Mg ≥ A 5 ∗ Cu + B 5 ∗ Zn + C 5 ∗ Cu − 1.9 ∗ Zn − 8 + D 5 ∗ Cu − 1.9 2 + E 5 ∗ Zn − 8 2 + F 5 G 5 ∗ Cu + H 5 ∗ Zn + I 5 ∗ Cu − 1.9 ∗ Zn − 8 + J 5 ∗ Cu − 1.9 2 + K 5 ∗ Zn − 8 2 + 1
    dans lequel Mg ≤ A 6 + B 6 * Zn + C 6 * Zn − 8 2 + D 6 * Zn − 8 3 + E 6 * Zn − 8 4 + F 6 * Cu + G 6 * Cu * Zn + H 6 * Cu * Zn − 8 2 + I 6 * Cu * Zn − 8 3 + J 6 * Cu * Zn − 8 4
    dans lequel A5 = -2,676 ; B5 = 0,014 ; C5 = -0,2327 ;
    D5 = 3,2411 ; E5 = 0,1016 ; F5 = 5,9836 ; G5 = -0,2805 ;
    H5 = 0,2631 ; I5 = -0,017 ; J5 = -0,5005 ; K5 = -0,0148 ;
    et A6 = 2,0238 ; B6 = 0,0905 ; C6 = -0,0072 ;
    D6 = 0,0058 ; E6 = -0,0021 ; F6 = 0,5835 ; G6 = -0,121 ;
    H6 = 0,0029 ; I6 = -0,0023 ; J6 = 0,0008 ;
    dans lequel le produit d'alliage d'aluminium corroyé 7xxx est sous la forme d'un produit laminé, d'un produit extrudé ou d'un produit forgé ; et
    dans lequel une épaisseur nominale du produit laminé, du produit extrudé ou du produit forgé est de 101,6 à 304,8 mm (4,0 à 12,0 pouces).
  2. Produit d'alliage d'aluminium corroyé 7xxx selon la revendication 1, comprenant 0,07 à 0,15 % en poids de Zr.
  3. Produit d'alliage d'aluminium corroyé 7xxx selon la revendication 1, dans lequel le produit d'alliage d'aluminium corroyé est essentiellement exempt de zirconium n'ayant pas plus de 0,03 % en poids de Zr.
  4. Produits d'alliage d'aluminium 7xxx corroyés selon la revendication 1, dans lesquels le produit d'alliage d'aluminium corroyé a une épaisseur nominale d'au moins 127 mm (5,0 pouces).
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ES2293813B2 (es) 2003-04-10 2011-06-29 Corus Aluminium Walzprodukte Gmbh Una aleacion de al-zn-mg-cu.
RU2745433C1 (ru) * 2017-06-21 2021-03-25 Арконик Текнолоджиз ЭлЭлСи Улучшенные плотные ковкие сплавы на основе алюминия серии 7xxx и способы их получения
FR3068370B1 (fr) * 2017-07-03 2019-08-02 Constellium Issoire Alliages al- zn-cu-mg et procede de fabrication
WO2019089736A1 (fr) 2017-10-31 2019-05-09 Arconic Inc. Alliages d'aluminium améliorés et leurs procédés de production
JP7621248B2 (ja) 2018-11-07 2025-01-24 アーコニック テクノロジーズ エルエルシー ２ｘｘｘアルミニウムリチウム合金
CN113015816A (zh) * 2018-11-14 2021-06-22 奥科宁克技术有限责任公司 改进的7xxx铝合金
WO2020172046A1 (fr) 2019-02-20 2020-08-27 Howmet Aerospace Inc. Alliages d'aluminium-magnésium-zinc améliorés
CN120174241A (zh) * 2019-06-24 2025-06-20 奥科宁克技术有限责任公司 改进的厚锻造7xxx铝合金及其制造方法
US12221677B2 (en) * 2021-09-27 2025-02-11 Kaiser Aluminum Fabricated Products, Llc Dispersoids 7XXX alloy products with enhanced environmentally assisted cracking and fatigue crack growth deviation resistance
IL322078A (en) * 2023-01-20 2025-09-01 Novelis Koblenz Gmbh Methods for manufacturing mine blast resistant armor from 7xxx series aluminum alloy

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