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    • 专利摘要:
    ENHANCED 6XXX ALUMINUM ALLOYS AND METHODS FOR THE PRODUCTION OF THE SAME. The present invention relates to new 6xxx aluminum alloys. The new 6xxx aluminum alloys may include 1.05 to 1.50 by weight of Mg, 0.60 to 0.95% by weight of Si, in which (% by weight of Mg) / (% by weight of Mg) Si) is 1.30 to 1.90, 0.275 to 0.50% by weight of Cu, and 0.05 to 1.0% by weight of at least one secondary element, in which the secondary element is selected from the group consisting of V, Fe, Cr, Mn, Zr, Ti and combinations thereof.
    公开号:BR112015000878B1
    申请号:R112015000878-0
    申请日:2013-07-15
    公开日:2020-10-27
    发明作者:Jen C. Lin；Anton J. Rovito；Timothy P. Doyle；Shawn P. Sullivan；Gabriele F. Ciccola；Christopher J. Tan
    申请人:Arconic Inc.；
    IPC主号:
    专利说明:

    BACKGROUND
    [0001] Aluminum alloys are useful in a variety of applications. However, improving an aluminum alloy property without degrading another property is inaccurate. For example, it is difficult to make an alloy stronger without decreasing the hardness of an alloy. Other properties of interest for aluminum alloys include corrosion resistance and fatigue resistance, to name two. DESCRIPTION SUMMARY
    [0002] In general, the present patent application refers to the new aluminum alloys 6XXX and the methods for producing them. In general, products of the new aluminum alloy 6XXX achieve an improved combination of properties due, for example, to the amount of alloying elements, as described in further details below. For example, the new 6XXX aluminum alloys can achieve an enhanced combination of two or more properties including strength, toughness, fatigue strength and corrosion resistance, among others, as shown by the examples below. The new 6XXX aluminum alloys can be produced in the worked form, as in a laminated form (for example, as a sheet or plate), as an extrusion, or as a forging, among others. In one embodiment, the new 6XXX aluminum alloy is in the form of a forged wheel product. In one embodiment, the 6XXX forged wheel product is a matrix forged wheel product.
    [0003] The new 6XXX aluminum alloys in general comprise (and some examples essentially consist of, or consist of) magnesium (Mg), silicon (Si), and copper (Cu) as primary alloy elements and at least one secondary element selected from the group consisting of vanadium (V), manganese (Mn), iron (Fe), chromium (Cr), zirconium (Zr) and titanium (Ti), the remainder being aluminum and other impurities, as defined below.
    [0004] Regarding magnesium, the new aluminum alloys 6XXX, in general, include from 1.05% by weight to 1.50% by weight of Mg. In one embodiment, the new 6XXX aluminum alloys include at least 1.10% by weight of Mg. In another embodiment, the new 6XXX aluminum alloys include at least 1.15% by weight of Mg. In yet another embodiment, the new 6XXX aluminum alloys include at least 1.20% by weight of Mg. In one embodiment, the new 6XXX aluminum alloys include no more than 1.45% by weight of Mg. In another embodiment, the new 6XXX aluminum alloys include no more than 1.40% by weight of Mg. In yet another embodiment, the new 6XXX aluminum alloys include no more than 1.35% by weight of Mg.
    [0005] The new 6XXX aluminum alloys in general include silicon and in the range of 0.60% by weight to 0.95% by weight of Si. In one embodiment, the new 6XXX aluminum alloys include at least 0.65% by weight of Si. In another embodiment, the new 6XXX aluminum alloys include at least 0.70% by weight of Si. In one embodiment, the new 6XXX aluminum alloys include no more than 0.85% by weight of Si In yet another embodiment, the new 6XXX aluminum alloys include no more than 0.85% by weight of Si. In yet another embodiment, the new 6XXX aluminum alloys include no more than 0.80% by weight of Si .
    [0006] The new 6XXX aluminum alloys, in general, include magnesium and silicon in a ratio of 1.30 to 1.90 (Mg / Si). In one embodiment, the new 6XXX aluminum alloys have an Mg / Si ratio of at least 1.35. In another embodiment, the new 6XXX aluminum alloys have an Mg / Si ratio of at least 1.40. In yet another modality, the new 6XXX aluminum alloys have an Mg / Si ratio of at least 1.45. In one embodiment, the new 6XXX aluminum alloys have an Mg / Si ratio of no more than 1.85. In another embodiment, the new 6XXX aluminum alloys have an Mg / Si ratio of no more than 1.80. In yet another modality, the new 6XXX aluminum alloys have an Mg / Si ratio of no more than 1.75. In another embodiment, the new 6XXX aluminum alloys have an Mg / Si ratio of no more than 1.70. In yet another embodiment, the new 6XXX aluminum alloys have an Mg / Si ratio of no more than 1.65. In some embodiments, the new 6XXX aluminum alloys have an Mg / Si ratio of 1.35 to 1.85. In yet other modalities, the new 6XXX aluminum alloys have an Mg / Si ratio of 1.35 to 1.80. In yet other modalities, the new 6XXX aluminum alloys have an Mg / Si ratio of 1.40 to 1.75. In other embodiments, the new 6XXX aluminum alloys have an Mg / Si ratio of 1.40 to 1.70. In yet other modalities, the new 6XXX aluminum alloys have an Mg / Si ratio of 1.45 to 1.65. Other combinations of the limits described above can be used. The use of the amounts described above of Mg and Si can facilitate, among other things, the improvement of strength and / or fatigue resistance properties.
    [0007] The new aluminum alloys 6XXX, in general, include copper and in the range of 0.275% by weight to 0.50% by weight of Cu. In one embodiment, the new 6XXX aluminum alloys include at least 0.30% Cu by weight. In another embodiment, the new 6XXX aluminum alloys include at least 0.325% Cu by weight. In yet another embodiment, the new 6XXX aluminum alloys include at least 0.35% Cu by weight. In one embodiment, the new 6XXX aluminum alloys include no more than 0.45% by weight of Cu. In another embodiment, the new 6XXX aluminum alloys include no more than 0.425 wt% Cu. In yet another embodiment, the new 6XXX aluminum alloys include no more than 0.40% Cu by weight. The use of the amounts described above of Cu can facilitate the improvement of strength and with good resistance to corrosion. As described in further detail below, when the new 6XXX aluminum alloy is substantially free of vanadium (that is, it includes less than 0.05% by weight of V), the new 6XXX aluminum alloy must include at least 035% in Cu weight.
    [0008] The new 6XXX aluminum alloys include 0.05 to 1.0% by weight of the secondary elements, the secondary elements being selected from the group consisting of vanadium, manganese, chromium, iron, zirconium, titanium and combinations thereof. In one embodiment, the new 6XXX aluminum alloys include 0.10 to 0.80% by weight of the secondary elements. In another embodiment, the new 6XXX aluminum alloys include 0.15 to 0.60% by weight of the secondary elements. In another embodiment, the new 6XXX aluminum alloys include 0.20 to 0.45% by weight of the secondary elements.
    [0009] In one embodiment, the secondary elements include at least vanadium, and in those embodiments, the new aluminum alloy 6XXX includes at least 0.05% by weight of V. In another embodiment, the secondary elements include at least vanadium and iron. . In yet another embodiment, the secondary elements include at least vanadium, iron and titanium. In another embodiment, the secondary elements include at least vanadium, iron, titanium and chromium. In another embodiment, the secondary elements include at least vanadium, iron, titanium and manganese. In yet another modality, the secondary elements include all of vanadium, iron, titanium, manganese and chromium.
    [0010] In other embodiments, the secondary elements are substantially free of vanadium (that is, they include less than 0.05% by weight of V), and in these modalities, the secondary elements are selected from the group consisting of vanadium, manganese, chromium, iron, zirconium, titanium and combinations thereof, and in which at least one of magnesium, chromium and zirconium is present. In one embodiment, at least chromium is present. In one embodiment, at least chromium and zirconium are present. In one embodiment, at least chromium and manganese are present. In one embodiment, at least zirconium is present. In one embodiment, at least zirconium and magnesium are present. In one embodiment, at least manganese is present.
    [0011] As shown by the data below, vanadium is a useful secondary element, but its inclusion in the new 6XXX aluminum alloys is not required. In modalities where vanadium is included, the new 6XXX aluminum alloys include 0.05 to 0.25% by weight of V. In one embodiment, the new 6XXX aluminum alloys include no more than 0.20% in weight of V. In another embodiment, the new 6XXX aluminum alloys include no more than 0.18% by weight of V. In yet another embodiment, the new 6XXX aluminum alloys include no more than 0.16% by weight of V. In another embodiment, the new 6XXX aluminum alloys include no more than 0.14% by weight of V. In yet another embodiment, the new 6XXX aluminum alloys include no more than 0.13% by weight of V. V. In one embodiment, the new 6XXX aluminum alloys include at least 0.06% by weight of V. In another embodiment, the new 6XXX aluminum alloys include at least 0.07% by weight of V. In some embodiments, the new 6XXX aluminum alloys include from 0.05 to 0.16% by weight of V. In other embodiments, the new 6XXX aluminum alloys include from 0.06 to 0.14% by weight of V, in yet other embodiments, the new 6XXX aluminum alloys include from 0.07 to 0.13% by weight of V. Other combinations of the limits described above can be used.
    [0012] In other modalities, the new 6XXX aluminum alloys are substantially free of vanadium and, in these modalities, the new 6XXX aluminum alloys contain less than 0.05% by weight of V. In these modalities, chromium, magnesium and / or zirconium can be used as a substitute for vanadium. In one embodiment, the new 6XXX aluminum alloys contain less than 0.05% by weight of V, but contain a total of 0.15 to 0.60% by weight of chromium, magnesium and / or zirconium (ie, Cr + Mn + Zr is 0.15% by weight to 0.60% by weight). In another embodiment, the new 6XXX aluminum alloys contain less than 0.05% by weight of V, but contain from 0.20 to 0.45% by weight of chromium, magnesium and / or zirconium. In embodiments where the new 6XXX aluminum alloys are substantially vanadium free (ie, the aluminum alloy contains less than 0.05% by weight. V), the amount of copper in the new 6XXX aluminum alloys should be at least 0.35% by weight of Cu. In some of these vanadium-free modalities, the new 6XXX aluminum alloys include at least 0.375% Cu by weight. In other of these vanadium-free modalities, the new 6XXX aluminum alloys include at least 0.40% Cu by weight.
    [0013] In modalities where chromium is present (with or without vanadium), the new aluminum alloys 6XXX in general include from 0.05 to 0.40% by weight of Cr. In one embodiment, the new 6XXX aluminum alloys include no more than 0.35% Cr by weight. In another embodiment, the new 6XXX aluminum alloys include no more than 0.30% Cr by weight. In yet another embodiment, the new 6XXX aluminum alloys include no more than 0.25% Cr by weight. In another embodiment, the new 6XXX aluminum alloys include no more than 0.20% by weight of Cr. In one embodiment, the new 6XXX aluminum alloys include at least 0.08% by weight of Cr. In some embodiments, the new 6XXX aluminum alloys include 0.05 to 0.25% by weight of Cr. In other embodiments, the new 6XXX aluminum alloys include 0.08 to 0.20% by weight of Cr. Other combinations of the limits described above can be used. In some embodiments, the new 6XXX aluminum alloys are substantially chromium-free, and in these embodiments, they contain less than 0.05% by weight. Cr.
    [0014] In modalities in which manganese is present (without or with vanadium), the new aluminum alloys 6XXX, in general, include from 0.05 to 0.50% by weight of Mn. In some embodiments, the new 6XXX aluminum alloys include no more than 0.25% by weight of Mn. In other embodiments, the new 6XXX aluminum alloys include no more than 0.20% by weight of Mn. In yet other embodiments, the new 6XXX aluminum alloys include no more than 0.15% by weight of Mn. In some embodiments, the new 6XXX aluminum alloys include 0.05 to 0.25% by weight of Mn. In other embodiments, the new 6XXX aluminum alloys include 0.05 to 0.20% by weight of Mn. In yet other embodiments, the new 6XXX aluminum alloys include 0.05 to 0.15% by weight of Mn. Other combinations of the limits described above can be used. In some embodiments, the new 6XXX aluminum alloys are substantially free of manganese, and in these embodiments, they contain less than 0.05% by weight of Mn.
    [0015] In modalities in which zirconium is present (without or with vanadium), the new aluminum alloys 6XXX, in general, include from 0.05 to 0.25% by weight Zr. In some embodiments, the new 6XXX aluminum alloys include no more than 0.20% by weight of Zr. In other embodiments, the new 6XXX aluminum alloys include no more than 0.18% by weight of Zr. In yet other embodiments, the new 6XXX aluminum alloys include no more than 0.15% by weight of Zr. In one embodiment, the new 6XXX aluminum alloys include at least 0.06% by weight of Zr. In yet other embodiments, the new 6XXX aluminum alloys include at least 0.07% by weight of Zr. In some embodiments, the new 6XXX aluminum alloys include 0.05 to 0.20% by weight of Zr. In other embodiments, the new 6XXX aluminum alloys include from 0.06 to 0.18% by weight of Zr. In yet other embodiments, the new 6XXX aluminum alloys include from 0.07 to 0.15% by weight of Zr. Other combinations of the limits described above can be used. In some embodiments, aluminum alloys are substantially free of zirconium, and in these embodiments, they contain less than 0.05% by weight of Zr.
    [0016] Iron is generally present in the alloy, and can be present in the range of 0.01% by weight to 0.80% by weight of Fe. In some embodiments, the new 6XXX aluminum alloys include no more than 0.50% by weight of Fe. In other embodiments, the new 6XXX aluminum alloys include no more than 0.40% by weight of Fe. In still other embodiments, the new 6XXX aluminum alloys include no more than than 0.30% by weight of Fe. In one embodiment, the new 6XXX aluminum alloys include at least 0.08% by weight of Fe. In still other embodiments, the new 6XXX aluminum alloys include at least 0.10% by weight of Fe. In some embodiments, the new 6XXX aluminum alloys include 0.05 to 0.50% by weight of Fe. In other embodiments, the new 6XXX aluminum alloys include from 0.08 to 0.40% by weight of Fe. In still other modalities, the new 6XXX aluminum alloys include from 0.10 to 0.30% by weight of Fe. In still other modalities, the new 6XXX aluminum alloys include from 0.10 to 0, two 5% by weight of Fe. Other combinations of the limits described above can be used. Higher levels of iron may be tolerable in the new 6XXX aluminum alloy products when the lower fatigue strength properties are tolerable. In some embodiments, the new 6XXX aluminum alloys are substantially iron-free, and in these embodiments, they contain less than 0.01% by weight of Fe.
    [0017] In modalities in which titanium is present (without or with vanadium), the new aluminum alloys 6XXX, in general, include from 0.001 to 0.10% by weight of Ti. In some modalities, the new aluminum alloys 6XXX include no more than 0.05% by weight of Ti. In other embodiments, the new 6XXX aluminum alloys include no more than 0.04% by weight of Ti. In still other embodiments, the new 6XXX aluminum alloys include no more than 0.03% by weight of Ti. In one embodiment, the new 6XXX aluminum alloys include at least 0.005% by weight of Ti. In still other embodiments, the new 6XXX aluminum alloys include at least 0, 01% by weight of Ti. In some modalities, the new 6XXX aluminum alloys include from 0.005 to 0.05% by weight of Ti. In other modalities, the new 6XXX aluminum alloys include from 0.01 to 0.04% by weight of Ti. In yet other embodiments, the new aluminum alloys 6XXX include from 0.01 to 0.03% by weight of Ti. Other combinations of the limits described ac ima can be used. In some embodiments, the new 6XXX aluminum alloys are substantially free of titanium, and in these embodiments, they contain less than 0.001% by weight of Ti.
    [0018] The new 6XXX aluminum alloys can be substantially free of other elements. As used herein, "other elements" means any other elements of the periodic table other than magnesium, silicon, copper, vanadium, iron, chromium, titanium, zirconium and iron listed above, as described above . In the context of that paragraph, the phrase "substantially free" means that the new 6XXX aluminum alloys contain no more than 0.10% by weight of each of any element of the other elements, with the total combined amount of those other elements not exceeds 0.35% by weight in the new 6XXX aluminum alloys. In another embodiment, each of these other elements, individually, does not exceed 0.05% by weight in 6XXX aluminum alloys, and the total combined amount of these other elements does not exceed 0.15% by weight in 6XXX aluminum alloys. In another embodiment, each of these other elements, individually, does not exceed 0.03% by weight in 6XXX aluminum alloys, and the total combined amount of these other elements does not exceed 0.10% by weight in 6XXX aluminum alloys.
    [0019] The new 6XXX aluminum alloys can achieve high strength. In one embodiment, a worked product made from the new 6XXX aluminum alloys ("new worked 6XXX aluminum alloy product") performs a yield stress in the L (longitudinal) direction of at least 310.26 MPa (45 ksi). In another modality, a new worked aluminum alloy 6XXX product performs a yield stress in the L direction of at least 317.15 MPa (46 ksi). In other embodiments, a new worked aluminum alloy 6XXX product performs a yield stress in the L direction of at least 324.05 MPa (47 ksi), or at least 330.94 MPa (48 ksi), or at least 337, 84 MPa (49 ksi), or at least about 344.73 MPa (50 ksi), or at least about 351.63 MPa (51 ksi), or at least about 358.52 MPa (52 ksi), or at least about 365.42 MPa (53 ksi), or at least about 372.31 MPa (54 ksi), or at least about 379.21 MPa (55 ksi), or more.
    [0020] The new 6XXX aluminum alloys can achieve good elongation. In one embodiment, a new worked 6XXX aluminum alloy product elongates at least 6% in the L direction. In another embodiment, a new worked 6XXX aluminum alloy product elongates in the L direction by at least 8%. In other embodiments, a new worked 6XXX aluminum alloy product performs at least 1.0%, or at least 12%, or at least 14%, or more in the L direction. The strength and elongation properties are measured according to ASTM E8 and B557.
    [0021] The new 6XXX aluminum alloys can achieve good hardness. In one embodiment, a new worked 6XXX aluminum alloy product performs a hardness of at least 47.45 Nm (35 ft. Ibs.) As measured by a Charpy impact test, in which the Charpy impact test is performed according to with ASTM E23-07a. In another embodiment, a new crafted 6XXX aluminum alloy product performs a hardness of at least 54.23 N.m (40 ft. -Ibs.) As measured by a Charpy impact test. In other embodiments, a new worked aluminum alloy 6XXX product has a hardness of at least 61.01 Nm (45 ft.-Ibs.), Or at least 67.79 Nm (50 ft.-Ibs.), Or at least at least 74.57 Nm (55 ft.-Ibs.), or at least 81.35 Nm (60 ft.-Ibs.), or at least 88.13 Nm (65 ft.-Ibs.), or at least 94 , 91 Nm (70 ft.-Ibs.), Or at least 101.69 Nm (75 ft. -Ibs.), Or at least 108.47 Nm (80 ft.-Ibs.), Or at least 115.24 Nm (85 ft.-lbs.), Or more, as measured by a Charpy impact test.
    [0022] The new 6XXX aluminum alloys can achieve good resistance to fatigue. In one embodiment, a new crafted 6XXX aluminum alloy product achieves an average rotational fatigue life that is at least 10% better than the average rotational fatigue life of the same product worked (for example, the same form of product, dimensions, geometry, temperament), but made of conventional 6061 alloy, where the average rotational fatigue life is the average rotational fatigue life of at least 5 specimens of the 6XXX aluminum alloy product worked as tested in according to ISO 1143 (2010) ("Metallic materials a Rotating bar bending fatigue testing"), that is, rotational beam fatigue. In another embodiment, a new crafted 6XXX aluminum alloy product achieves an average rotational fatigue life that is at least 20% better than the average rotational fatigue life of the same worked product made from conventional 6061 alloy. modalities, a new crafted 6XXX aluminum alloy product achieves an average rotational fatigue life that is at least 25% better, or at least 30% better, or at least 40% better, or at least 45% better, or more than the average rotational fatigue life of the same product made from the conventional 6061 alloy.
    [0023] In one embodiment, the new worked 6XXX aluminum alloy product is a forged wheel product, and the forged 6XXX aluminum alloy wheel product achieves an average radial fatigue life of at least 1,000,000 cycles as tested. according to SAE J267 (2007), with a load factor of 2.8X applied. In another embodiment, the forged 6XXX aluminum alloy wheel product achieves an average radial fatigue life of at least 1,050,000 cycles. In other embodiments, the forged 6XXX aluminum alloy wheel product achieves an average radial fatigue life of at least 1,100,000 cycles, or at least 1,150,000 cycles, or at least 1,200,000 cycles, or at least 1,250. 000 cycles, or at least 1,300,000 cycles, or at least 1,350,000 cycles, or more.
    [0024] In one embodiment, a new worked 6XXX aluminum alloy product achieves an average radial fatigue life that is at least 10% better than the average radial fatigue life of the same product worked (for example, the same product shape, dimensions, geometry, temperament), but made of conventional 6061 alloy as tested according to SAE J267 (2007), with a 2.8X load suit applied. In another embodiment, a new crafted 6XXX aluminum alloy product achieves an average radial fatigue life that is at least 20% better than the average radial fatigue life of the same worked product made from conventional 6061 alloy. modalities, a new crafted 6XXX aluminum alloy product achieves an average radial fatigue life that is at least 25% better, or at least 30% better, or at least 40% better, or at least 45% better, or more, than the average service life of radial fatigue of the same worked product made of conventional alloy 6061.
    [0025] The new 6XXX aluminum alloys can achieve good corrosion resistance. In one embodiment, a new worked 6XXX aluminum alloy product performs an average depth of attack of no more than 0.008 inches at the T / 10 location when measured according to ASTM G110 (24 hour exposure; minimum of 5 samples). In another embodiment, a new crafted 6XXX aluminum alloy product performs an average attack depth of no more than 0.006 inches at the T / 10 location. In other embodiments, a new worked 6XXX aluminum alloy product performs an average attack depth of no more than 0.004 inches, or no more than 0.002 inches, or no more than 0.001 inches, or less at the T / 10 location .
    [0026] In one embodiment, a new 6XXX aluminum alloy product crafted achieves a maximum attack depth of no more than 0.011 inches at the T / 10 location when measured according to ASTM G110 (24 hour exposure; minimum 5 samples). In another embodiment, a new crafted 6XXX aluminum alloy product achieves a maximum depth of attack of no more than 0.009 inches at the T / 10 location. In other embodiments, a new crafted 6XXX aluminum alloy product achieves a maximum depth of attack of no more than 0.007 inches, or no more than 0.005 inches, or no more than 0.003 inches, or less at the T / 10 location .
    [0027] In one embodiment, a new worked aluminum alloy 6XXX product performs an average attack depth of no more than 0.008 inches on the surface when measured according to ASTM G110 (24 hours of exposure; minimum of 5 samples). In another embodiment, a new worked 6XXX aluminum alloy product performs an average depth of attack of no more than 0.007 inches on the surface. In other embodiments, a new crafted 6XXX aluminum alloy product performs an average depth of attack of no more than 0.006 inches, or no more than 0.005 inches, or no more than 0.004 inches, or less on the surface.
    [0028] In one embodiment, a new 6XXX aluminum alloy product worked out achieves a maximum depth of attack of no more than 0.010 inches on the surface when measured according to ASTM G110 (24 hours of exposure; minimum of 5 samples). In another embodiment, a new 6XXX aluminum alloy product crafted achieves a maximum depth of attack of no more than 0.009 inches on the surface. In other embodiments, a new crafted 6XXX aluminum alloy product achieves a maximum depth of attack of no more than 0.008 inches, or no more than 0.007 inches, or no more than 0.006 inches, or less on the surface.
    [0029] The combinations of the properties described above can be achieved, as shown by the examples below. BRIEF DESCRIPTION OF THE DRAWINGS
    [0030] Figures 1a to 1f are graphs showing the results of Example 1.
    [0031] Figures 1 g to 1 to 1 g to 4 are micrographs of Example 1. DETAILED DESCRIPTION EXAMPLE 1 - BOOK TEMPLATE STUDY
    [0032] Nine book mold ingots were produced, the compositions of which are provided in Table 1, below (all weight percent values). TABLE 1 - ALLOY COMPOSITIONS OF EXAMPLE 1

    [0033] Alloys 6061 and 6069 are conventional 6XXX aluminum alloys. All alloys contained the listed elements, the balance being aluminum and other impurities, where the other impurities do not exceed more than 0.05% by weight each, and no more than 0.15% by weight of the total other impurities. The alloys of the invention have an Mg / Si ratio of 1.46 to 1.59.
    [0034] The alloys were cast as ingots 2.875 inches (ST) x 4.75 inches (LT) x 17 inches (L) which were scaled to a thickness of 2 inches and then homogenized. The ingots were then hot rolled to about 0.5 inches of plates, which corresponds to approximately a 75% reduction. The plates were subsequently heat treated and quenched with cold water (37.77 ° C (100 ° F)). The plates were then aged at 196.1 ° C (385 ° F) and 176.67 ° C (350 ° F) for different times, and the aging curves were generated. Based on the results of the aging curve, two aging conditions (196.1 ° C (385 ° F) for 2 hours, and 176.67 ° C (350 ° F) for 8 hours) were selected to test various properties. The aging condition of 196.1 ° C (385 ° F) for 2 hours generally represents about the peak force, and the aging condition of 176.67 ° C (350 ° F) for 8 hours represents, in general, an un aged condition. The test results are illustrated in Figures 1a to 1f and provided in Tables 2 to 7, below. The strength and elongation properties were measured according to ASTM E8 and B557. Charpy impact tests were measured according to ASTM 1323-07a. The rotational fatigue life tests were conducted according to ISO 1143 (2010) and a tension of 103.42 MPa (15 ksi), with RE - 1 and with Kt = - 3, the corrosion resistance was tested according to with ASTM Gl 10 for 24 hours. TABLE 2 - MECHANICAL PROPERTIES OF ALLOYS - CONDITION OF PEAK RESISTANCE (196.1 ° C (385 ° F) FOR 2 HOURS)
    TABLE 3 - MECHANICAL PROPERTIES OF ALLOYS - UNDER AGED CONDITION (176.67 ° C (350 ° F) FOR 8 HOURS)

    TABLE 4- ALLOY CORROSION PROPERTIES - PEAK RESISTANCE CONDITION (196.11 ° C (385 ° F) FOR 2 HOURS)
    TABLE 5 - ALLOY CORROSION PROPERTIES - UNDER AGED CONDITION (176.67 ° C (350 ° F) FOR 8 hours)

    [0035] Figures 1a to 1c illustrate the stress properties of the alloys. All tested alloys have a higher peak strength than the conventional 6061 alloy.
    [0036] Figure 1d illustrates the rotational fatigue life of the alloys. Alloys that have a high content of more than 0.7% by weight of Fe (ie 6XXX-8 and 6XXX-9 alloys) have a lower fatigue life. Alloys 6XXX-8 and 6XXX-9 may also contain more than 1.0% by weight of the secondary elements of vanadium (V), magnesium (Mn), iron (Fe), chromium (Cr), zirconium (Zr) and titanium (11), which contributes to its low fatigue performance. In addition, alloys 6 and 8, which have about 0.7% Cu by weight, perform worse than their counterpart alloys, which illustrate the importance of maintenance copper below 0.55% in Weight.
    [0037] Figure 1e illustrates the impact energy of charpy without notch of the alloys. Charpy impact energy is an indicator of fracture hardness. Unexpectedly, the impact energy of charpy decreases with the increasing constituent forming elements (for example, Fe, Cr, and V). A correlation coefficient is given in Figure 1f. This trend is reversed from the normal trend, in which the impact energy of charpy decreases, in general, with the increased constituent particle concentration in aluminum alloys,
    [0038] Tables 4 and 5 provide corrosion data in relation to the depth of the attack test by ASTM G110 (24 hour test). All alloys show better or similar corrosion resistance compared to conventional 6061 alloy.
    [0039] The color and glass of the alloys were also tested. The alloys of the invention achieved glass and color performance comparable to the conventional 6061 alloy, both before and after DURA-BRIGHT processing (see, U.S. Patent No. 6,440,290).
    [0040] The micrographs of several other alloys were also obtained, some of which are illustrated in Figures 1g to 1 to 1g to 4. Both the amount of dispersoids and the uniformity of disperso distribution were improved by the combined additions of V and Cr . In addition, the microstructures of alloys with additions of V + Cr are no longer recrystallized, as shown in Figure 1g to 3 and 1g to 4. EXAMPLE 2 - ADDITIONAL BOOK TEMPLATE STUDY
    [0041] Seven additional free mold ingots were produced by the procedure of Example 1, except the alloys that were all aged at 196.1 ° C (385 ° F) for 2 hours. The alloy compositions of Example 2 are provided in Table 6, below (all weight percent values). TABLE 6 - ALLOY COMPOSITIONS OF EXAMPLE 2

    [0042] All alloys contained the listed elements, the balance being aluminum and other impurities, where the other impurities do not exceed more than 0.05% by weight each, and not more than 0.15% in weight of the total other impurities. These alloys have an Mg / Si ratio of 1.64 to 1.75.
    [0043] The mechanical properties of these alloys have been tested, the results of which are provided in Table 7, below. The strength and elongation properties were measured according to ASTM E8 and B557. The rotational fatigue life tests were conducted according to ISO 1143 (2010) at a stress of 103.42 MPa (15 ksi), with R = -1 and with Kt = 3, as shown in Table 7, the alloys which have an appropriate amount of Si, Mg and the appropriate Si / Mg ratio achieved improved fatigue strength properties with high strength. Certainly, alloys, in general, have negligible amounts of excess Si and Mg, which help the alloys to achieve improved properties; all alloys achieved improved properties over alloy 6061 (6XXX-I from Example 1) due to, at least in part, the amount of Si, Mg and the Si / Mg ratio, and regardless of the amount of Mn, Cr , and V used. It was observed, however, that the alloys that have vanadium with at least one among manganese and chromium reached, in general, high strength in combination with the improved resistance to fatigue. TABLE 7 - MECHANICAL ALLOY PROPERTIES - 196.1 ° C (385 ° F) FOR 2 HOURS
    EXAMPLE 3 - WHEEL STUDY
    [0044] The two compositions of the invention and seven comparative compositions were produced as wheels. Specifically, nine ingots that have the compositions provided in Table 8, below, were produced by direct cooling casting, after which they were homogenized, and then forged on a wheel, after which the wheels were treated by hot solution, cooled, and then artificially aged at 196.1 ° C (385 ° F) for about 2 hours. TABLE 8 - ALLOY COMPOSITIONS OF EXAMPLE 3

    [0045] All alloys contained the listed elements and about 0.02% by weight of Ti, the balance which is aluminum and other impurities, in which the other impurities do not exceed more than 0.05% by weight each , and not more than 0.15% by weight of the total of the other impurities. The alloys of the invention have an Mg / Si ratio of 1.43 to 1.63.
    [0046] The mechanical properties of the wheel products have been tested, the results of which are provided in Table 9, below.
    [0047] The strength and elongation properties were measured according to ASTM E8 and B557. The radial fatigue life was conducted according to SAE J267 (2007), with a load factor of 2.8X applied. As shown in Table 9, the alloys of the invention, in general, achieve both improved fatigue life and greater strength compared to conventional and non-inventive alloys. TABLE 9 - MECHANICAL PROPERTIES OF WHEELS - 196.1 ° C (385 ° F) FOR 2 HOURS
    EXAMPLE 4 - ADDITIONAL FREE TEMPLATE STUDY
    [0049] Ten additional book mold ingots were produced by the procedure of Example 1, except the alloys which were all aged at 196.1 ° C (385 ° F) for 2 hours. The alloy compositions of Example 4 are provided in Table 10, below (all weight percent values). TABLE 10 - ALLOY COMPOSITIONS OF EXAMPLE 4

    [0048] All alloys contained the listed elements and about 0.02% by weight of Ti, the balance that is aluminum and other impurities, in which the other impurities do not exceed more than 0.05% by weight each, and not more than 0.15% by weight of the total other impurities. The alloys of the invention have an Mg / Si ratio of 1.52 to 1.62.
    [0049] The alloys were cast as ingots of 2.875 inches (ST) x 4.75 inches (LT) x 17 inches (L) which were scaled to a thickness of 2 inches and then homogenized. The ingots were then machined into about 1.5 inch (3 inch high) diameter cylinders and then deformed into disks that have a final thickness of about 0.52 inches. The discs were subsequently treated by hot solution and quenched with cold water (37.77 ° C (100 ° F)), and then aged at 196.1 ° C (385 ° F) for 2 hours. The strength and elongation properties were measured according to ASTM E8 and B557. The rotational fatigue life tests were conducted according to ISO 1143 (2010) at a stress of 103.42 MPa (15 ksi), with R = -1 and with t = 3. The results are provided in Table 11, below. TABLE 11 - MECHANICAL PROPERTIES OF ALLOYS IN EXAMPLE 4

    [0050] As shown, the alloys of the invention have improved properties compared to alloy 33 that is not of the invention (type 6061). Alloys 24-26, 28-29 and 31 that have vanadium have achieved an approximately equivalent or improved strength compared to alloy 33 that is not of the invention (type 6061) and with improved rotational fatigue life and good elongation. Alloys 27 and 30, which do not contain vanadium, but contain chromium and manganese, have achieved an improved rotational fatigue life compared to alloy 33 which is not of the invention (type 6061) and with good elongation. Alloy 32 which is not of the invention, which has 1.14 Si and a Mg / Si ratio of 1.07, performs low elongation. EXAMPLE 5 - STUDY OF ADDITIONAL FREE TEMPLATE
    [0051] Seven additional book mold ingots were produced, the compositions of which are provided in Table 13. Below (all weight percent values). TABLE 13 - ALLOY COMPOSITIONS OF EXAMPLE 5

    [0052] All alloys contained the listed elements and about 0.01 to 0.02% by weight of Ti, the balance that is aluminum and other impurities, in which the other impurities do not exceed more than 0.05% each by weight, and not more than 0.15% by weight of the total other impurities. The alloys of the invention have an Mg / Si ratio of 1.55 to 1.58. The alloys were processed in the same way as in Example 1, except that they were only aged at 196.1 ° C (385 ° F) for 2 hours. The strength and elongation properties were measured according to ASTM E8 and B557. The results are provided in Table 14, below. TABLE 14 - MECHANICAL PROPERTIES OF THE ALLOYS IN EXAMPLE 5

    [0053] As shown, the alloys of the invention have improved properties over alloy 40 which is not of the invention (type 6061). Specifically, alloys 34-35 achieved an improved yield stress (TYS) in relation to alloy 40 which is not of the invention (type 601) and with good elongation, although alloy 34 with vanadium achieved greater strength. Alloy 36 which is not of the invention with 0.62 wt% Si, 0.96 wt% Mg, 0.28 wt% Cu, and without vanadium achieved about the same yield strength and elongation such as alloy 40 which is not of the invention (type 6061). Alloy 37, which is not of the invention, with 0.92 Si by weight% and an Mg / Si ratio of 1.24 achieved a low elongation. Alloy 38 that is not of the invention with 0.30 Cu of wt% and an Mg / Si ratio of 1.61, but without vanadium achieved a tensile strength lower than alloy 40 that is not of the invention (type 6061) . The non-invention alloy 39 with 0.19% Cu by weight achieved a lower tensile strength than alloy 40 which is not of the invention (type 6061).
    [0054] The above results indicate that alloys with at least 0.05% by weight of vanadium can achieve improved properties when they use, among other things, at least 0.275% Cu by weight and the appropriate amount of Si and Mg, as shown above. The above results also indicate that alloys without at least 0.05% by weight of vanadium can achieve the enhanced properties using at least 0.35% by weight of Cu, and with the appropriate amount of Si, Mg and using Cr, Mn and / or Zr as a substitute for V.
    [0055] As the various modalities of the new technology described in this document are described in detail, it is evident that the modifications and adaptations of these modalities will occur to those skilled in the art. However, it is expressly understood that such modifications and adaptations are within the spirit and scope of the technology currently described.
    权利要求:
    Claims (19)
    [0001]
    1. Forged 6XXX aluminum alloy wheel product, consisting of: (a) 1.15 to 1.40 Mg by weight; (b) 0.70 to 0.95% by weight of Si; where (% by weight of Mg) / (% by weight of Si) is from 1.40 to 1.90; (c) 0.35 to 0.50% by weight of Cu; (d) less than 0.05% by weight of V (e) less than 0.05% by weight of Zr, from 0.05 to 0.30% by weight of Fe, from 0.05 to 0, 15 wt% Mn, not more than 0.30 wt% Cr and 0.01 to 0.10 wt% Ti; (f) the balance being aluminum and other elements, with each of the other elements not exceeding 0.05% by weight in the forged 6XXX aluminum alloy wheel product, and the total of the other elements being no more than 0.15% by weight in the forged 6XXX aluminum alloy wheel product, said forged 6XXX aluminum alloy wheel product being characterized by the fact that it performs a longitudinal yield stress of at least 310.26 MPa (45 ksi ) and a longitudinal elongation of at least 0.8%, when tested according to ASTM E8 and B557; and the said forged 6XXX aluminum alloy wheel product achieves an average radial fatigue life of at least 1,000. 000 cycles, as tested according to SAE Standard No. J267 (2007), with a load factor of 2.8X applied.
    [0002]
    2. Forged 6XXX aluminum alloy wheel product according to claim 1, characterized by the fact that it includes both chromium and manganese, and that includes a total of chromium plus magnesium from 0.15 to 0.60% by weight .
    [0003]
    3. Forged 6XXX aluminum alloy wheel product according to claim 2, characterized by the fact that it includes 0.01 to 0.05% by weight of Ti.
    [0004]
    4. Forged 6XXX aluminum alloy wheel product, according to claim 1, characterized by the fact that it includes 0.70 to 0.90% by weight of Si.
    [0005]
    5. Forged 6XXX aluminum alloy wheel product, according to claim 1, characterized by the fact that it includes 0.70 to 0.85% by weight of Si.
    [0006]
    6. Forged 6XXX aluminum alloy wheel product according to claim 1, characterized by the fact that it includes 0.70 to 0.80% by weight of Si.
    [0007]
    7. Forged 6XXX aluminum alloy wheel product according to claim 4, characterized by the fact that it includes from 1.20 to 1.40% by weight of Mg.
    [0008]
    8. Forged 6XXX aluminum alloy wheel product according to claim 5, characterized by the fact that it includes from 1.15 to 1.35% by weight of Mg.
    [0009]
    9. Forged 6XXX aluminum alloy wheel product according to claim 6, characterized by the fact that it includes from 1.15 to 1.30% by weight of Mg.
    [0010]
    10. Forged 6XXX aluminum alloy wheel product according to claim 7, characterized by the fact that it includes 0.375 to 0.50% by weight of Cu.
    [0011]
    11. Forged 6XXX aluminum alloy wheel product according to claim 8, characterized by the fact that it includes 0.40 to 0.50% by weight of Cu.
    [0012]
    12. Forged 6XXX aluminum alloy wheel product according to claim 9, characterized by the fact that it includes from 0.35 to 0.475% by weight of Cu.
    [0013]
    13. Forged 6XXX aluminum alloy wheel product according to claim 9, characterized by the fact that it includes from 0.35 to 0.45% by weight of Cu.
    [0014]
    14. Forged 6XXX aluminum alloy wheel product according to claim 10, characterized by the fact that (% by weight of Mg) / (% by weight of Si) is not more than 1.85.
    [0015]
    15. Forged aluminum alloy wheel product 6XXX according to claim 11, characterized in that (% by weight of Mg) / (% by weight of Si) is not more than 1.75.
    [0016]
    16. Forged 6XXX aluminum alloy wheel product according to claim 12, characterized in that (% by weight of Mg) / (% by weight of Si) is not more than 1.70.
    [0017]
    17. Forged 6XXX aluminum alloy wheel product according to claim 13, characterized in that (% by weight of Mg) / (% by weight of Si) is not more than 1.65.
    [0018]
    18. Forged 6XXX aluminum alloy wheel product according to claim 17, characterized in that (% by weight of Mg) / (% by weight of Si) is at least 1.45.
    [0019]
    19. Forged 6XXX aluminum alloy wheel product according to claim 13, characterized in that the combined amount of Cr, Mn and Zr in the forged 6XXX aluminum alloy wheel product is from 0.20 to 0.45% by weight.
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    同族专利:
    公开号 | 公开日
    EP3299483B1|2020-03-11|
    RU2015105005A|2016-09-20|
    EP2872662A4|2016-08-10|
    US9890443B2|2018-02-13|
    CA2877781C|2021-05-18|
    US20160340760A1|2016-11-24|
    RU2662758C2|2018-07-30|
    AU2013290484A1|2015-01-29|
    US20140017116A1|2014-01-16|
    HUE050625T2|2020-12-28|
    CA2877781A1|2014-01-23|
    US20140017117A1|2014-01-16|
    MX362963B|2019-02-28|
    EP3299483A3|2018-07-18|
    EP2872662A1|2015-05-20|
    ES2691304T3|2018-11-26|
    KR20150030273A|2015-03-19|
    JP2015528856A|2015-10-01|
    KR102176996B1|2020-11-10|
    CA3074090A1|2014-01-23|
    CN104428434A|2015-03-18|
    WO2014014795A1|2014-01-23|
    MX2015000665A|2015-04-08|
    AU2013290484C1|2017-06-08|
    HUE041876T2|2019-06-28|
    US10590515B2|2020-03-17|
    BR112015000878A2|2017-06-27|
    EP3299483A2|2018-03-28|
    AU2013290484B2|2017-03-09|
    JP6445432B2|2018-12-26|
    US9556502B2|2017-01-31|
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    法律状态:
    2017-08-15| B25D| Requested change of name of applicant approved|Owner name: ARCONIC INC. (US) |
    2018-12-04| B06F| Objections, documents and/or translations needed after an examination request according [chapter 6.6 patent gazette]|
    2019-04-09| B07A| Application suspended after technical examination (opinion) [chapter 7.1 patent gazette]|
    2020-01-28| B06A| Patent application procedure suspended [chapter 6.1 patent gazette]|
    2020-04-07| B09A| Decision: intention to grant [chapter 9.1 patent gazette]|
    2020-10-27| B16A| Patent or certificate of addition of invention granted [chapter 16.1 patent gazette]|Free format text: PRAZO DE VALIDADE: 20 (VINTE) ANOS CONTADOS A PARTIR DE 15/07/2013, OBSERVADAS AS CONDICOES LEGAIS. |
    2021-10-26| B25D| Requested change of name of applicant approved|Owner name: HOWMET AEROSPACE INC. (US) |
    2021-11-16| B25G| Requested change of headquarter approved|Owner name: HOWMET AEROSPACE INC. (US) |
    优先权:
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    US201261671969P| true| 2012-07-16|2012-07-16|
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    US13/861,443|2013-04-12|
    PCT/US2013/050433|WO2014014795A1|2012-07-16|2013-07-15|Improved 6xxx aluminum alloys, and methods for producing the same|
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