US20210292875A1 - 6xxx aluminum alloys - Google Patents

6xxx aluminum alloys Download PDF

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US20210292875A1
US20210292875A1 US17/336,859 US202117336859A US2021292875A1 US 20210292875 A1 US20210292875 A1 US 20210292875A1 US 202117336859 A US202117336859 A US 202117336859A US 2021292875 A1 US2021292875 A1 US 2021292875A1
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aluminum alloy
6xxx aluminum
new 6xxx
product
alloys
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Timothy A. Hosch
Cyril F. Bell
Dirk C. Mooy
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Arconic Technologies LLC
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    • C—CHEMISTRY; METALLURGY
    • C21—METALLURGY OF IRON
    • C21D—MODIFYING THE PHYSICAL STRUCTURE OF FERROUS METALS; GENERAL DEVICES FOR HEAT TREATMENT OF FERROUS OR NON-FERROUS METALS OR ALLOYS; MAKING METAL MALLEABLE, e.g. BY DECARBURISATION OR TEMPERING
    • C21D8/00—Modifying the physical properties by deformation combined with, or followed by, heat treatment
    • C21D8/02—Modifying the physical properties by deformation combined with, or followed by, heat treatment during manufacturing of plates or strips
    • C21D8/0221—Modifying the physical properties by deformation combined with, or followed by, heat treatment during manufacturing of plates or strips characterised by the working steps
    • C21D8/0226—Hot rolling
    • C—CHEMISTRY; METALLURGY
    • C21—METALLURGY OF IRON
    • C21D—MODIFYING THE PHYSICAL STRUCTURE OF FERROUS METALS; GENERAL DEVICES FOR HEAT TREATMENT OF FERROUS OR NON-FERROUS METALS OR ALLOYS; MAKING METAL MALLEABLE, e.g. BY DECARBURISATION OR TEMPERING
    • C21D8/00—Modifying the physical properties by deformation combined with, or followed by, heat treatment
    • C21D8/02—Modifying the physical properties by deformation combined with, or followed by, heat treatment during manufacturing of plates or strips
    • C21D8/0221—Modifying the physical properties by deformation combined with, or followed by, heat treatment during manufacturing of plates or strips characterised by the working steps
    • C21D8/0236—Cold rolling
    • C—CHEMISTRY; METALLURGY
    • C21—METALLURGY OF IRON
    • C21D—MODIFYING THE PHYSICAL STRUCTURE OF FERROUS METALS; GENERAL DEVICES FOR HEAT TREATMENT OF FERROUS OR NON-FERROUS METALS OR ALLOYS; MAKING METAL MALLEABLE, e.g. BY DECARBURISATION OR TEMPERING
    • C21D8/00—Modifying the physical properties by deformation combined with, or followed by, heat treatment
    • C21D8/02—Modifying the physical properties by deformation combined with, or followed by, heat treatment during manufacturing of plates or strips
    • C21D8/0247—Modifying the physical properties by deformation combined with, or followed by, heat treatment during manufacturing of plates or strips characterised by the heat treatment
    • C21D8/0273—Final recrystallisation annealing
    • C—CHEMISTRY; METALLURGY
    • C21—METALLURGY OF IRON
    • C21D—MODIFYING THE PHYSICAL STRUCTURE OF FERROUS METALS; GENERAL DEVICES FOR HEAT TREATMENT OF FERROUS OR NON-FERROUS METALS OR ALLOYS; MAKING METAL MALLEABLE, e.g. BY DECARBURISATION OR TEMPERING
    • C21D9/00—Heat treatment, e.g. annealing, hardening, quenching or tempering, adapted for particular articles; Furnaces therefor
    • C21D9/46—Heat treatment, e.g. annealing, hardening, quenching or tempering, adapted for particular articles; Furnaces therefor for sheet 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
    • C22C21/02—Alloys based on aluminium with silicon as the next major constituent
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C21/00—Alloys based on aluminium
    • C22C21/02—Alloys based on aluminium with silicon as the next major constituent
    • C22C21/04—Modified aluminium-silicon alloys
    • 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
    • C22F1/043—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 silicon as the next major constituent

Definitions

  • Aluminum alloys are useful in a variety of applications. However, improving one property of an aluminum alloy without degrading another property often proves elusive. For example, it is difficult to increase the strength of an alloy without decreasing its corrosion resistance. Other properties of interest for aluminum alloys include formability and critical fracture strain, to name two.
  • the present disclosure relates to new 6xxx aluminum alloys having an improved combination of properties, such as an improved combination of strength, formability, bending, and/or corrosion resistance, among others.
  • the new 6xxx aluminum alloys comprise (and in some instances consist essentially of or consist of) from 0.65 to 0.85 wt. % Si, from 0.40 to 0.59 wt. % Mg wherein the ratio of wt. % Mg to wt. % Si is from 0.47:1 to 0.90:1 (Mg:Si), from 0.05 to 0.35 wt. % Fe, from 0.04 to 0.13 wt. % Mn, from 0 to 0.20 wt. % Cu, from 0 to 0.15 wt. % Cr, from 0 to 0.15 wt. % Zr, from 0 to 0.10 wt. % Ti, from 0 to 0.05 wt. % V, from 0 to 0.05 wt. % Zn, the balance being aluminum and impurities.
  • the amount of magnesium (Mg) and silicon (Si) in the new 6xxx aluminum alloys may relate to the improved combination of properties (e.g., strength, formability).
  • the new 6xxx aluminum alloy includes from 0.40 to 0.59 wt. % Mg.
  • a new 6xxx aluminum alloy includes at least 0.425 wt. % Mg.
  • a new 6xxx aluminum alloy includes at least 0.45 wt. % Mg.
  • a new 6xxx aluminum alloy includes at least 0.475 wt. % Mg.
  • a new 6xxx aluminum alloy includes at least 0.50 wt. % Mg.
  • a new 6xxx aluminum alloy includes not greater than 0.57 wt. % Mg.
  • a new 6xxx aluminum alloy includes from 0.49 to 0.59 wt. % Mg.
  • the new 6xxx aluminum alloy includes from 0.65 to 0.85 wt. % Si. In one embodiment, a new 6xxx aluminum alloy includes at least 0.675 wt. % Si. In another embodiment, a new 6xxx aluminum alloy includes at least 0.70 wt. % Si. In one embodiment, a new 6xxx aluminum alloy includes not greater than 0.825 wt. % Si. In another embodiment, a new 6xxx aluminum alloy includes not greater than 0.80 wt. % Si. In one embodiment, a new 6xxx aluminum alloy includes from 0.70 to 0.80 wt. % Si.
  • the new 6xxx aluminum alloy includes silicon and magnesium such that the weight ratio of magnesium-to-silicon of from 0.47:1 to 0.90:1, i.e., the ratio of wt. % Mg to wt. % Si is from 0.47:1 to 0.90:1 (Mg:Si).
  • the ratio of wt. % Mg to wt. % Si is at least 0.50:1(Mg:Si).
  • the ratio of wt. % Mg to wt. % Si is at least 0.52:1(Mg:Si).
  • the ratio of wt. % Mg to wt. % Si is at least 0.54:1(Mg:Si).
  • the ratio of wt. % Mg to wt. % Si is at least 0.56:1(Mg:Si). In yet another embodiment, the ratio of wt. % Mg to wt. % Si is at least 0.58:1(Mg:Si). In another embodiment, the ratio of wt. % Mg to wt. % Si is at least 0.60:1(Mg:Si). In one embodiment, the ratio of wt. % Mg to wt. % Si is not greater than 0.88:1(Mg:Si). In another embodiment, the ratio of wt. % Mg to wt. % Si is not greater than 0.86:1(Mg:Si).
  • the ratio of wt. % Mg to wt. % Si is not greater than 0.84:1(Mg:Si). In another embodiment, the ratio of wt. % Mg to wt. % Si is not greater than 0.82:1(Mg:Si). In one embodiment, the ratio of wt. % Mg to wt. % Si is from 0.61:1 to 0.84:1 (Mg:Si).
  • a new 6xxx aluminum alloy includes at least 0.08 wt. % Fe. In another one embodiment, a new 6xxx aluminum alloy includes at least 0.10 wt. % Fe. In yet another embodiment, a new 6xxx aluminum alloy includes at least 0.12 wt. % Fe. In another embodiment, a new 6xxx aluminum alloy includes at least 0.15 wt. %. In one embodiment, a new 6xxx aluminum alloy includes not greater than 0.32 wt. % Fe. In another embodiment, a new 6xxx aluminum alloy includes not greater than 0.30 wt. % Fe. In yet another embodiment, a new 6xxx aluminum alloy includes not greater than 0.28 wt. % Fe. In one embodiment, a new 6xxx aluminum alloy includes from 0.09 to 0.26 wt. % Fe.
  • the amount of manganese (Mn) in the new 6xxx aluminum alloys may relate to the improved combination of properties (e.g., formability).
  • the new 6xxx aluminum alloy includes from 0.04 to 0.13 wt. % Mn.
  • a new 6xxx aluminum alloy includes at least 0.05 wt. % Mn.
  • a new 6xxx aluminum alloy includes at least 0.06 wt. % Mn.
  • a new 6xxx aluminum alloy includes not greater than 0.12 wt. % Mn.
  • a new 6xxx aluminum alloy includes not greater than 0.11 wt. % Mn.
  • a new 6xxx aluminum alloy includes not greater than 0.10 wt. % Mn.
  • a new 6xxx aluminum alloy includes from 0.06 to 0.10 wt. % Mn.
  • the new 6xxx aluminum alloy may optionally include copper (Cu) and in an amount of up to 0.20 wt. % Cu (e.g., for strengthening purposes).
  • a new 6xxx aluminum alloy includes at least 0.02 wt. % Cu.
  • a new 6xxx aluminum alloy includes at least 0.04 wt. % Cu.
  • a new 6xxx aluminum alloy includes at least 0.06 wt. % Cu.
  • a new 6xxx aluminum alloy includes at least 0.07 wt. % Cu.
  • a new 6xxx aluminum alloy includes at least 0.08 wt. % Cu.
  • a new 6xxx aluminum alloy includes at least 0.09 wt.
  • a new 6xxx aluminum alloy includes not greater than 0.19 wt. % Cu. In another embodiment, a new 6xxx aluminum alloy includes not greater than 0.18 wt. % Cu. In yet another embodiment, a new 6xxx aluminum alloy includes not greater than 0.17 wt. % Cu. In one embodiment, a new 6xxx aluminum alloy includes from 0.09 to 0.17 wt. % Cu.
  • the new 6xxx aluminum alloy may optionally include chromium (Cr) and in an amount of up to 0.15 wt. % Cr (e.g., for grain structure control).
  • a new 6xxx aluminum alloy includes at least 0.01 wt. % Cr.
  • a new 6xxx aluminum alloy includes at least 0.02 wt. % Cr.
  • a new 6xxx aluminum alloy incudes not greater than 0.10 wt. % Cr.
  • a new a new 6xxx aluminum alloy incudes not greater than 0.08 wt. % Cr.
  • a new a new 6xxx aluminum alloy incudes not greater than 0.06 wt. % Cr.
  • a new a new 6xxx aluminum alloy incudes not greater than 0.05 wt. % Cr.
  • a new 6xxx aluminum alloy includes from 0.01 to 0.05 wt. % Cr.
  • the new 6xxx aluminum alloy may optionally include zirconium (Zr) and in an amount of up to 0.15 wt. % Zr (e.g., for grain structure control).
  • Zr zirconium
  • a new 6xxx aluminum alloy incudes not greater than 0.10 wt. % Zr.
  • a new a new 6xxx aluminum alloy incudes not greater than 0.05 wt. % Zr.
  • a new a new 6xxx aluminum alloy incudes not greater than 0.03 wt. % Zr.
  • a new a new 6xxx aluminum alloy incudes not greater than 0.01 wt. % Zr.
  • the new 6xxx aluminum alloy may include up to 0.15 wt. % Ti. Titanium (Ti) may optionally be present in the new 6xxx aluminum alloy, such as for grain refining purposes.
  • a new 6xxx aluminum alloy includes at least 0.005 wt. % Ti.
  • a new 6xxx aluminum alloy includes at least 0.010 wt. % Ti.
  • a new 6xxx aluminum alloy includes at least 0.0125 wt. % Ti.
  • a new 6xxx aluminum alloy includes not greater than 0.10 wt. % Ti.
  • a new 6xxx aluminum alloy includes not greater than 0.08 wt. % Ti.
  • a new 6xxx aluminum alloy includes not greater than 0.05 wt. % Ti. In one embodiment, a target amount of titanium in a new 6xxx aluminum alloy is 0.03 wt. % Ti. In one embodiment, a new 6xxx aluminum alloy includes from 0.01 to 0.05 wt. % Ti.
  • Zinc (Zn) may optionally be present in the new 6xxx aluminum alloy, and in an amount up to 0.10 wt. % Zn.
  • a new alloy includes not greater than 0.05 wt. % Zn.
  • a new alloy includes not greater than 0.03 wt. % Zn.
  • a new alloy includes not greater than 0.01 wt. % Zn.
  • Vanadium (V) may optionally be present in the new 6xxx aluminum alloy, and in an amount of up to 0.05 wt. % V.
  • a new 6xxx aluminum alloy includes not greater than 0.03 wt. % V.
  • a new 6xxx aluminum alloy includes not greater than 0.01 wt. % V.
  • a new 6xxx aluminum alloy includes not greater than 0.15 wt. %, in total, of the impurities, and wherein the 6xxx aluminum alloy includes not greater than 0.05 wt. % of each of the impurities.
  • a new 6xxx aluminum alloy includes not greater than 0.10 wt. %, in total, of the impurities, and wherein the 6xxx aluminum alloy includes not greater than 0.03 wt. % of each of the impurities.
  • the new 6xxx alloys may be useful in a variety of product forms, including ingot or billet, wrought product forms (sheet, plate, forgings and extrusions), shape castings, additively manufactured products, and powder metallurgy products.
  • a new 6xxx aluminum alloy is a rolled product.
  • the new 6xxx aluminum alloys may be produced in sheet form.
  • a sheet made from the new 6xxx aluminum alloy has a thickness of from 1.5 mm to 4.0 mm.
  • the new 6xxx aluminum alloys are produced using ingot casting and hot rolling.
  • a method includes the steps of casting an ingot of the new 6xxx aluminum alloy, homogenizing the ingot, rolling the ingot into a rolled product having a final gauge (via hot rolling and/or cold rolling), solution heat treating the rolled product, wherein the solution heat treating comprises heating the rolled product to a temperature and for a time such that some or substantially all of Mg 2 Si of the rolled product is dissolved into solid solution, and after the solution heat treating, quenching the rolled product (e.g., water or air quenching). After the quenching, the rolled product may be artificially aged.
  • one or more anneal steps may be completed before or after a rolling step (e.g., hot rolling to a first gauge, annealing, cold rolling to the final gauge).
  • the artificially aged product can be painted (e.g., for an automobile part), and may thus be subjected to a paint-bake cycle.
  • the rolled aluminum alloy products produced from the new alloy may be incorporated in an automobile.
  • the new 6xxx aluminum alloys products are cast via continuous casting. Downstream of the continuous casting, the product can be (a) rolled (hot and/or cold), (b) optionally annealed (e.g., after hot rolling and prior to any cold rolling steps), (c) solution heat treated and quenched, (d) optionally cold worked (post-solution heat treatment), and (e) artificially aged, and all steps (a)-(e) may occur in-line or off-line relative to the continuous casting step.
  • Some methods for producing the new 6xxx aluminum alloys products using continuous casting and associated downstream steps are described in, for example, U.S. Pat. No. 7,182,825, U.S. Patent Application Publication No. 2014/0000768, and U.S. Patent Application Publication No. 2014/036998, each of which is incorporated herein by reference in its entirety.
  • the artificially aged product can be painted (e.g., for an automobile part), and may thus be subjected to a paint-bake cycle.
  • the hot rolling comprises hot rolling to an intermediate gauge product, wherein the intermediate gauge product exits the hot rolling apparatus at a temperature of not greater than 290° C.
  • an optional anneal may be completed.
  • the intermediate gauge product may be cold rolled to final gauge.
  • the hot rolling comprises rolling to an intermediate gauge product, wherein the intermediate gauge product exits the hot rolling apparatus at a temperature of from 400-480° C.
  • the intermediate gauge product may then be cold rolled to final gauge, i.e., no anneal is required after the hot rolling and prior to cold rolling in this embodiment.
  • the cold rolling When cold rolling is completed, the cold rolling generally comprises reducing the thickness of the intermediate gauge thickness to the final gauge thickness. In one embodiment, the cold rolling comprises cold rolling by at least 50%. In another embodiment, the cold rolling comprises cold rolling by at least 60%. In yet another embodiment, the cold rolling comprises cold rolling by at least 65%. In one embodiment, the cold rolling is not greater than 85%.
  • XX CR % is the amount of thickness reduction achieved when the aluminum alloy body is reduced from a first thickness of T 1 to a second thickness of T 2 , where T 1 is the intermediate gauge thickness and wherein T 2 is the thickness.
  • XX CR % is equal to:
  • XX CR % is 80%.
  • the peak metal temperature during solution heat treatment is in the range of from 504° C. to 593° C.
  • the peak metal temperature is the highest temperature realized by an alloy product during solution heat treatment.
  • the new 6xxx aluminum alloy products are processed to a T4 temper as defined by ANSI H35.1 (2009), i.e., the new 6xxx are solution heat treated and then quenched and then naturally aged to a substantially stable condition.
  • the natural aging amount is 30 days and the T4 properties of the new 6xxx aluminum alloy are measured at 30 days of natural aging.
  • the new 6xxx aluminum alloys are processed to a T6 temper as defined by ANSI H35.1 (2009), i.e., the new 6xxx are solution heat treated and then quenched and then artificially aged.
  • the artificial aging comprises paint baking.
  • the artificial aging consist of paint baking.
  • paint baking comprises heating the new 6xxx aluminum alloy product to 180° C. and then holding for 20 minutes.
  • the new 6xxx aluminum alloys are processed to a T8 temper as defined by ANSI H35.1 (2009), i.e., the new 6xxx are solution heat treated and then quenched and then cold worked (e.g., stretched), and then artificially aged.
  • the artificial aging comprises paint baking.
  • the artificial aging consist of paint baking.
  • paint baking comprises heating the new 6xxx aluminum alloy product to 180° C. and then holding for 20 minutes.
  • the processing of the new 6xxx aluminum alloy steps may be accomplished such that a new aluminum alloy body product realizes a predominately recrystallized microstructure.
  • a predominately recrystallized microstructure means that the aluminum alloy body contains at least 51% recrystallized grains (by volume fraction).
  • the degree of recrystallization of a new 6xxx aluminum alloy product may be determined using appropriate metallographic samples of the material analyzed with EBSD by an appropriate SEM and computer software to determine intergranular misorientation.
  • a new 6xxx aluminum alloy product is at least 60% recrystallized.
  • a new 6xxx aluminum alloy product is at least 70% recrystallized.
  • a new 6xxx aluminum alloy product is at least 80% recrystallized.
  • a new 6xxx aluminum alloy product is at least 90% recrystallized. In yet another embodiment, a new 6xxx aluminum alloy product is at least 95% recrystallized. In another embodiment, a new 6xxx aluminum alloy product is at least 98% recrystallized, or more.
  • a new 6xxx aluminum alloy product may realize a fine grain size.
  • a new 6xxx aluminum alloy product realizes an area weighted average grain size of not greater than 45 micrometers.
  • a new 6xxx aluminum alloy product realizes an area weighted average grain size of not greater than 40 micrometers.
  • a new 6xxx aluminum alloy product realizes an area weighted average grain size of at least 20 micrometers.
  • a new 6xxx aluminum alloy product realizes an area weighted average grain size of at least 25 micrometers.
  • a new 6xxx aluminum alloy product realizes an area weighted average grain size of at least 30 micrometers.
  • a new 6xxx aluminum alloy product may realize a unique texture.
  • Texture means a preferred orientation of at least some of the grains of a crystalline structure.
  • matchsticks as an analogy, consider a material composed of matchsticks. That material has a random texture if the matchsticks are included within the material in a completely random manner. However, if the heads of at least some of those matchsticks are aligned in that they point the same direction, like a compass pointing north, then the material would have at least some texture due to the aligned matchsticks.
  • the same principles apply with grains of a crystalline material.
  • Texture components resulting from production of aluminum alloy products may include one or more of copper, S texture, brass, cube, and Goss texture, to name a few. Each of these texture components is defined in Table 1, below.
  • grain size and texture are to be measured and normalized as follows:
  • the EBSD acquisition is to be performed using EDAX TSL EBSD Data Collection (OIM)TM software, version 7, or equivalent.
  • OFM EDAX TSL EBSD Data Collection
  • Ai is the area of each individual grain as measured per above.
  • “vi” is the calculated individual grain size assuming the grain is a circle.
  • the number average grain size, v-bar_n, is the arithmetic mean of vi.
  • the new 6xxx aluminum alloys disclosed herein may realize an improved combination of properties.
  • a new 6xxx aluminum alloy realizes a T4 tensile yield strength in the LT (long transverse) direction of from 90 to 110 MPa.
  • a new 6xxx aluminum alloy realizes a T4 uniform elongation in the LT (long transverse) direction of at least 21%.
  • a new 6xxx aluminum alloy realizes a T4 n value (10-20%) in the LT (long transverse) direction of at least 0.245.
  • T4 properties are to be measured after 30 days of natural aging.
  • tensile yield strength and uniform elongation are to be measured in accordance with ASTM E8 and B557.
  • n value (10-20%) is to be measured in accordance with ASTM E646 using 10-20% strain.
  • a new 6xxx aluminum alloy realizes a T6 (0% pre-strain/stretch) tensile yield strength of at least 160 MPa when artificially aged by paint baking at 180° C. for 20 minutes.
  • a new 6xxx aluminum alloy realizes a T6, (0% pre-strain/stretch) tensile yield strength of at least 170 MPa when artificially aged by paint baking at 180° C. for 20 minutes.
  • a new 6xxx aluminum alloy realizes a T6 (0% pre-strain/stretch) tensile yield strength of at least 180 MPa when artificially aged by paint baking at 180° C. for 20 minutes.
  • a new 6xxx aluminum alloy realizes a T8 tensile yield strength of at least 215 MPa when post-SHT stretched 1-3% and then artificially aged by paint baking at 180° C. for 20 minutes.
  • a new 6xxx aluminum alloy realizes a Hem rating of 2 or better. Hem rating is defined in the below Examples. In another embodiment, a new 6xxx aluminum alloy realizes a Hem rating of 1.
  • a new 6xxx aluminum alloy realizes a VDA bend angle of at least 125°.
  • VDA testing is to be tested by natural aging the product for 30 days, and then stretching the product 10% in the L (longitudinal) direction, and then conducting the VDA bend test in accordance with the VDA 238-100 bend test specification. (https://www.vda.de/en/services/Publications/vda-238-100-plate-bending-test-for-metallic-materials.html).
  • a new 6xxx aluminum alloy realizes a VDA bend angle of at least 130°.
  • a new 6xxx aluminum alloy realizes a VDA bend angle of at least 135°.
  • a new 6xxx aluminum alloy realizes a VDA bend angle of at least 140°.
  • a new 6xxx aluminum alloy realizes a VDA bend angle of at least 143°.
  • a new 6xxx aluminum alloy is absent of Ludering.
  • Ludering is to be tested by naturally aging the product for 8 days, and then stretching the product 10% in the L (longitudinal) direction. If Luder lines are visible to the naked eye, the product is not absent of Ludering. If Luder lines are invisible to the naked eye, the product is absent of Ludering.
  • a new 6xxx aluminum alloy realizes a combination of properties shown in the “Preferred Property Box” of FIG. 1 .
  • a new 6xxx aluminum alloy realizes a VDA bend angle of at least 140°. Others of the above-identified properties may also be realized.
  • a new 6xxx aluminum alloy realizes a combination of properties shown in the “Preferred Property Box” of FIG. 2 .
  • a new 6xxx aluminum alloy realizes a VDA bend angle of at least 140°. Others of the above-identified properties may also be realized.
  • a new 6xxx aluminum alloy realizes a combination of properties shown in the “Preferred Property Box” of FIG. 3 .
  • a new 6xxx aluminum alloy realizes a VDA bend angle of at least 140°. Others of the above-identified properties may also be realized.
  • a new 6xxx aluminum alloy realizes a combination of properties shown in the “Preferred Property Box” of FIG. 4 .
  • a new 6xxx aluminum alloy realizes a VDA bend angle of at least 140°. Others of the above-identified properties may also be realized.
  • 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 an image of the grain structure of alloy A1-1.
  • FIG. 2 is an image of the grain structure of alloy A1-10.
  • FIG. 3 is an image of the grain structure of alloy A1-19.
  • FIG. 4 is an image of the grain structure of alloy A1-22.
  • FIG. 5 is a graph illustrating the tensile yield strength (after paint bake, no pre-strain, i.e., T6) versus n value (10-20%) in the as is (T4) temper for various example alloys.
  • FIG. 6 is a graph illustrating the tensile yield strength (after paint bake, no pre-strain, i.e., T6) versus uniform elongation in the as is (T4) temper for various example alloys.
  • FIG. 7 is a graph illustrating the tensile yield strength (after paint bake, 2% pre-strain, i.e., T8) versus n value (10-20%) in the as is (T4) temper for various example alloys.
  • FIG. 8 is a graph illustrating the tensile yield strength (after paint bake, 2% pre-strain, i.e., T8) versus uniform elongation in the as is (T4) temper for various example alloys.
  • Example 1 Compositions of Example 1 Alloys (wt. %) Sample Si Fe Cu Mn Mg Cr Ti Zn Bal. Alloy 0.74 0.18 0.13 0.07 0.52 0.03 0.03 0.005 A1 + A1 Imp. (inv.) Alloy 0.76 0.14 0.13 0.07 0.54 0.03 0.03 0.007 A1 + A2 Imp. (inv.) Alloy 0.63 0.21 0.13 0.07 0.60 0.03 0.02 0.004 A1 + B1 Imp. (non- inv.)
  • the ingots were then homogenized and then hot rolled to an intermediate gauge with an exit temperature of not greater than 290° C.
  • the alloys were then cold rolled to a final gauge of 0.95 or 1.2 mm.
  • the cold rolling amounts (reduction from the intermediate gauge to the final gauge) are provided in Table 2, below.
  • the final gauge products were then solution heat treated by heating to various peak metal temperatures (shown in Table 2), after which the alloys were immediately air quenched. After quenching, some alloys were then stretched while others were not, as shown in Table 2. All alloys were then naturally aged for 30 days, after which some alloys were then stretched, and after which some alloys (both stretched and non-stretched) were artificially aged by heating to 180° C. and then holding at this temperature for 20 minutes, and then cooling to room temperature. The 2% stretching (pre-strain) was completed in the lab and simulates a typical forming operation.
  • the invention alloys achieved higher tensile yield strengths (TYS) and ultimate yield strengths (UTS) than non-invention alloys. Further, the invention alloys showed less strength loss at lower peak metal temperatures. The invention alloys also generally had higher elongation and higher n values over non-invention alloys at most processing conditions, indicating improved formability.
  • Example 1 alloys were tested for hemming performance by stretching them 15% in the L direction after which a flat hem test was performed. The stretching was completed on alloys that had been naturally aged for 30 days and without subsequent artificial aging, i.e., the alloys were in a T4 temper prior to the 15% stretching. Four hems were completed for each processing condition. The hem ratings were then evaluated per the below scale.
  • Table 4 shows the achieved hem ratings for A1 and A2 alloys.
  • A1 alloys have more iron than A2 alloys. Those in industry have associated higher iron content to poorer hemming performance. However, the A1 alloys demonstrated better hemming performance than the A2 alloys. Further, higher iron content improved hemming performance in samples with lower levels of cold working (e.g. alloys A1-22, A1-23 and A1-24 had 65% cold work and demonstrated the same hemming performance as alloys A1-10, A1-11 and A1-12, which were the same gauge but only 81% cold work).
  • Example 1 alloys were naturally aged 8 days and then stretched 10% in the LT direction, after which a coating of paint was applied. After painting, the alloys were examined to determine if Luder bands were present. Table 6, below, shows the tensile yield strength and Luder band results for select Example 2 alloys.
  • Grain size and texture measurements of select A1 samples from Example 2 were obtained via electron backscattering detection in a scanning electron microscope. The results of the grain size and texture measurements are shown in Table 7, below. Further, grain structure images obtained via SEM are shown in FIGS. 1-4 .
  • FIGS. 1-4 show the grain structure images obtained via SEM for alloys A1-1, A1-10, A1-19, and A1-22.
  • the weighted average grain sizes obtained from these images for alloys A1-1, A1-10, A1-19, and A1-22 were 32 ⁇ m, 32 ⁇ m, 34 ⁇ m, and 41 ⁇ m, respectively.
  • the A1 alloy have finer (smaller) grain structure.
  • alloy A1-1 had a coarser grain structure than alloy B1-1.
  • the new alloys disclosed herein may have grain size area weighted average of from 20 micrometers to 45 micrometers. In one embodiment, the new alloys have a grain size of from 30 to 40 micrometers.
  • the new alloys disclosed herein may be in sheet form and have the following texture characteristics:

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Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20190153577A1 (en) * 2016-07-14 2019-05-23 Constellium Neuf-Brisach Method of making 6xxx aluminium sheets

Family Cites Families (20)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS59685B2 (ja) 1974-11-13 1984-01-07 トヨタ自動車株式会社 ナイネンキカンノ ノウコンゴウキキヨウキユウソウチ
JP3590685B2 (ja) * 1994-12-27 2004-11-17 本田技研工業株式会社 自動車外板用アルミニウム合金板の製造方法
JP2004027253A (ja) 2002-06-21 2004-01-29 Furukawa Sky Kk 成形加工用アルミニウム合金板およびその製造方法
US6811625B2 (en) * 2002-10-17 2004-11-02 General Motors Corporation Method for processing of continuously cast aluminum sheet
US7182825B2 (en) 2004-02-19 2007-02-27 Alcoa Inc. In-line method of making heat-treated and annealed aluminum alloy sheet
FR2902442B1 (fr) * 2006-06-16 2010-09-03 Aleris Aluminum Koblenz Gmbh Alliage de la serie aa6xxx, a grande tolerance aux dommages pour l'industrie aerospatiale
JP5059423B2 (ja) * 2007-01-18 2012-10-24 株式会社神戸製鋼所 アルミニウム合金板
JP2009041045A (ja) * 2007-08-06 2009-02-26 Nippon Steel Corp 塗装焼付け硬化性に優れたアルミニウム合金板及びその製造方法
CN100554486C (zh) * 2007-11-16 2009-10-28 苏州有色金属研究院有限公司 改善低Cu含量铝合金汽车板材烘烤硬化性能的方法
JP5758676B2 (ja) * 2011-03-31 2015-08-05 株式会社神戸製鋼所 成形加工用アルミニウム合金板およびその製造方法
US9856552B2 (en) 2012-06-15 2018-01-02 Arconic Inc. Aluminum alloys and methods for producing the same
JP5949315B2 (ja) 2012-08-20 2016-07-06 Ｊｆｅスチール株式会社 連続鋳造鋳片の製造方法
EP2964800B2 (fr) * 2013-03-07 2022-06-15 Aleris Aluminum Duffel BVBA Procédé de fabrication d'un produit en feuille laminé en alliage al-mg-si ayant une excellente formabilité
JP6752146B2 (ja) * 2014-01-21 2020-09-09 アーコニック テクノロジーズ エルエルシーＡｒｃｏｎｉｃ Ｔｅｃｈｎｏｌｏｇｉｅｓ Ｌｌｃ ６０００系アルミニウム合金
EP2993244B1 (fr) * 2014-09-05 2020-05-27 Constellium Valais SA (AG, Ltd) Procédé de fabrication d'un produit extrudé en aluminium alliage 6xxx avec d'excellentes performances de l'accident
JP6785772B2 (ja) * 2015-01-12 2020-11-18 ノベリス・インコーポレイテッドＮｏｖｅｌｉｓ Ｉｎｃ． 表面ローピングが低減されたまたは全くない高度に成形可能な自動車用アルミニウムシート及びその製造方法
JP6506678B2 (ja) 2015-11-02 2019-04-24 株式会社神戸製鋼所 自動車構造部材用アルミニウム合金板およびその製造方法
US10538834B2 (en) * 2015-12-18 2020-01-21 Novelis Inc. High-strength 6XXX aluminum alloys and methods of making the same
CN105441740A (zh) * 2016-01-12 2016-03-30 苏州有色金属研究院有限公司 汽车车身用高卷边性能6xxx系合金板材及其制造方法
JP2017179468A (ja) * 2016-03-30 2017-10-05 株式会社神戸製鋼所 高成形性アルミニウム合金板

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20190153577A1 (en) * 2016-07-14 2019-05-23 Constellium Neuf-Brisach Method of making 6xxx aluminium sheets

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