6xxx Alloy With High Recycled Material Content

Abstract

The present invention is directed to a 6xxx series aluminum alloy composition, comprising, consisting essentially of, or consisting of (by weight %) of 0.5-1.5% Si, 0.1-0.7% Cu, 0.5-1.5% Mg, 0.3-1.2% Zn, 0.05-0.35% Cr and allowable impurities of 0.8% Fe, 0.8% Mn, 0.15% Zr, 0.15% Ti, with other elements restricted as unavoidable impurities limited to 0.05% each and 0.15% total with the balance being aluminum. This 6xxx series aluminum alloy is capable of being produced with high amounts of post-consumer recycled material which significantly reduces environmental impact from producing this material, while still meeting and in most cases exceeding material attribute requirements for general engineering applications.

Claims

1. A 6xxx series aluminum alloy having a composition comprising, (by weight %): 0.5-1.5% Si; 0.1-0.7% Cu; 0.5-1.5% Mg; 0.3-1.2% Zn; 0.050-0.35% Cr; 0.8% Fe; 0.8% Mn; 0.15% Zr; 0.15% Ti; with other elements restricted as unavoidable impurities limited to 0.05% each and 0.15% total with the balance being aluminum.

2. The 6xxx series aluminum alloy of claim 1 comprising, 0.8-1.4% Si; 0.1-0.7% Cu; 0.8-1.4% Mg; 0.3-1.1% Zn; 0.5.-0.30% Cr; 0.6% Fe; 0.8% Mn; 0.15% Zr; 0.15% Ti.

3. The 6xxx series aluminum alloy of claim 1 including greater than 75% scrap.

4. The 6xxx series aluminum alloy of claim 1 including greater than 90% scrap.

5. An extruded, forged or rolled product manufactured from the 6xxx series aluminum alloy of claim 1 having a yield tensile strength greater than 295 MPa (42.8 ksi).

6. An extruded, forged or rolled product manufactured from the 6xxx series aluminum alloy of claim 1 having a yield tensile strength greater than 320 MPa (46.4 ksi).

7. An extruded, rolled or forged product manufactured from the 6xxx series aluminum alloy of claim 1 having excellent machinability performance as defined by achieving a B grade or better in the ASM machinability test.

8. An extruded, rolled or forged product manufactured from the 6xxx series aluminum alloy of claim 1 having a thickness of 0.25-10 inches.

9. An extruded, rolled or forged product manufactured from the 6xxx series aluminum alloy of claim 8 having a thickness of 1-10 inches.

10. A method of manufacturing the 6xxx series aluminum alloy of claim 1 comprising, a) casting using conventional direct chill casting methods; b) homogenizing at 950 F. to 1060 F. (510-571 C.) for 2 to 10 hours; c) preheating to 800 F.-1000 F. (427-538 C.); d) hot working by extrusion, forging or rolling; e) water quenching; f) optionally stretching for stress relief and straightening, and g) artificially aging at a temperature between 250-375 F. for 6-20 hours.

11. A method of manufacturing the 6xxx series aluminum alloy of claim 10, wherein said hot working is extrusion.

12. A method of manufacturing the 6xxx series aluminum alloy of claim 1 comprising, a) casting using conventional direct chill casting methods; b) optionally homogenizing at 950 F. to 1060 F. (510-571 C.) for 2 to 10 hours; c) preheating to a rolling temperature of 600 F.-1000 F. (316-538 C.); d) hot rolling; e) solution heat treatment at a temperature of 950 F. to 1070 F., f) quenching to room temperature, g) optionally stretching for stress relief and straightening, and h) artificially aging at a temperature between 250-375 F. for 6-20 hours.

13. A method of manufacturing the 6xxx series aluminum alloy of claim 1 comprising, a) casting using conventional direct chill casting methods; b) homogenizing at 950 F. to 1060 F. (510-571 C.) for 2 to 10 hours; c) preheating to an extrusion temperature of 450 F.-1000 F. (232-538 C.) and then extruding; d) optionally drawing the extrusions; e) solution heat treatment at a temperature of 950 F. to 1070 F., f) quenching to room temperature, g) optionally stretching for stress relief and straightening, and h) artificially aging at a temperature between 250-375 F. for 6-20 hours.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

[0008] The features and advantages of the present invention will become apparent from the following detailed description of a preferred embodiment thereof, taken in conjunction with the accompanying drawings, in which:

[0009] FIG. 1 shows the mechanical properties from example 1;

[0010] FIG. 2 shows the typical grain structure from example 2;

[0011] FIG. 3 shows the anodize response from example 3 with Inventive Alloy (left) compared to 6061 (right);

[0012] FIG. 4 shows typical chips produced in turn operation on 1 rod; and

[0013] FIG. 5 shows parts produced during machinability testing of 2 rod.

DETAILED DESCRIPTION OF THE INVENTION

[0014] The present invention is directed to a 6xxx series aluminum alloy composition comprising, or consisting essentially of, or consisting of (by weight %): 0.50-1.50% Si, 0.10-0.70% Cu, 0.50-1.50% Mg, 0.05-0.35% Cr, 0.30-1.20% Zn; allowable impurities including 0.80% Fe, 0.80% Mn, 0.15% Ti, 0.15% Zr, and unavoidable impurities to 0.05% each and 0.15% total unavoidable impurities with the remainder being aluminum. The inventive alloy is capable of being produced utilizing high amounts of post-consumer recycled material while still achieving the performance required for use in the general engineering market.

[0015] In an alternate embodiment, the 6xxx series aluminum alloy composition comprising, or consisting essentially of, or consisting of (by weight %): 0.8-1.4% Si, 0.1-0.7% Cu, 0.8-1.4% Mg, 0.3-1.1% Zn, 0.05-0.30% Cr, 0.6% Fe, 0.8% Mn, 0.15% Zr, 0.15% Ti, and unavoidable impurities limited to 0.05% each and 0.15% total with the balance being aluminum.

[0016] The addition of Mg increases the strength of aluminum alloys, especially when combined with the addition of Si. These two elements combine to form a precipitate known as Mg.sub.2Si. This phase is a significant contributor to material strength in precipitation hardening elements. In addition, multiple other precipitation hardening phases are formed due to the high number of alloying elements present in this composition. These additional phases include MgZn.sub.2 as well as Al.sub.2CuMg, which is more commonly known as S-Phase. The ratio of these phases will depend on the relative amounts of Mg, Si and Zn that are present in a given composition. Mg.sub.2Si will form preferentially as compared to MgZn.sub.2 and as such, MgZn.sub.2 will only form if there is enough Mg leftover after the formation of the Mg.sub.2Si phase. As these are the primary strengthening phases present in this alloy the relative amounts of these elements need to be controlled to achieve optimal strength in this type of composition.

[0017] The addition of Cr is done to restrict recrystallization in this structure. Fully unrecrystalized structures are preferred in these applications as the presence of recrystallized grains can lead to poor machinability performance in certain machining operations. The Cr forms a dispersoid (Al12Mg2Cr) phase which restricts recrystallization. This phase helps to limit recrystallization by limiting the grain boundary movement. Limiting the amount of coarse grain present in this material helps to achieve optimal material performance.

[0018] It is understood that the ranges identified above for the 6xxx series aluminum alloy composition includes the upper or lower limits for the element selected and every numerical range provided within the range may be considered as upper or lower limits. For example, it is understood that within the range of 0.5-1.5 wt. % Si, the upper or lower limit for Si may be selected from 0.5, 0.6, 0.7, 0.8, 0.9, 1.0, 1.1, 1.2, 1.3, 1.4 and 1.5 wt. %. In addition, for example, it is understood that within the range of 0.1 0.7 wt. % Cu, the upper or lower limit for Cu may be selected from 0.1, 0.2, 0.3, 0.4, 0.5, 0.6, 0.7 wt.%. In addition, for example, it is understood that within the range of 0.5 - 1.5 wt. % Mg, the upper or lower limit for Mg may be selected from 0.5, 0.6, 0.7, 0.8, 0.9, 1.0, 1.1, 1.2, 1.3, 1.4 and 1.5 wt. %. In addition, for example it is understood that within the range of 0.05-0.35 wt. % Cr, the upper or lower limit for Cr may be selected from 0.08, 0.11, 0.14, 0.17, 0.20, 0.23, 0.26, 0.29, 0.32, and 0.35 wt. %. In addition, for example, it is understood that within the range of 0.3-1.2 wt. % Zn, the upper or lower limit for Zn may be selected from 0.3, 0.4, 0.5, 0.6, 0.7, 0.9, 1.0, 1.1, and 1.2 wt. %. In addition, for example, it is understood that within the range of allowable impurities of 0.8 wt. % Fe, the upper limit for Fe may be selected from 0.8, 0.7, 0.6, 0.5, 0.4, 0.3, 0.2, and 0.1 wt. %. In addition, for example, it is understood that within the range of allowable impurities of 0.8 wt. % Mn, the upper limit for Mn may be selected from 0.8, 0.7, 0.6, 0.5, 0.4, 0.3, and 0.1 wt. %. In addition, for example, it is understood that within the range of allowable impurities of 0.15 wt. % Ti, the upper limit for Ti may be selected from 0.15, 0.14, 0.13, 0.12, 0.11, 0.10, 0.09, 0.08, 0.07, 0.06, 0.05, 0.04, 0.03, and 0.01 wt. %. In addition, for example, it is understood that within the range of allowable impurities of 0.15 wt. % Zr, the upper limit for Zr may be selected from 0.15, 0.14, 0.13, 0.12, 0.11, 0.10, 0.09, 0.08, 0.07, 0.06, 0.05, 0.03, 0.02, and 0.01 wt. %. It is further understood that any and all permutations of the range identified above are included within the scope of the present invention.

[0019] The 6xxx series aluminum alloy composition of the present invention may also include low level of unavoidable impurities that are not included intentionally. The unavoidable impurities means any other elements except the above described Al, Si, Cu, Mg, Cr, Zn, Fe, Mn, Ti, and Zr. It is understood that the range of to 0.05 wt. % each and 0.15 wt. % total unavoidable impurities, includes the upper or lower limit 0.05, 0.04, 0.03, 0.02, and 0.01 wt. % each unavoidable impurities, and 0.15, 0.14, 0.13, 0.12, 0.11, 0.10, 0.09, 0.08, 0.07, 0.06, 0.05, 0.04, 0.03, 0.02, and 0.01 wt. % total unavoidable impurities.

[0020] In a preferred embodiment the 6xxx series aluminum alloy composition is manufactured by 1) casting using conventional direct chill casting methods; 2) then homogenizing at 950 F. to 1060 F. (510-571 C.) for 2 to 10 hours; 3) then preheating to 800 F.-1000 F. (427-538 C.) and then hot working; followed by water quenching, optionally stretching for stress relief and straightening, and artificially aging at a temperature between 250-375 F. for 6-20 hours. The 6xxx series aluminum alloy compositions may be subjected to hot working operation, such as extrusion, forging or rolling. A preferred hot working operation is extrusion.

[0021] In another preferred embodiment the 6xxx series aluminum alloy composition is manufactured by 1) casting using conventional direct chill casting methods; 2) then optionally homogenizing at 950 F. to 1060 F. (510-571 C.) for 2 to 10 hours; 3) then preheating to a rolling temperature of 600 F.-1000 F. (316-538 C.) and then hot rolling; followed by solution heat treatment at a temperature of 950 F. to 1070 F., followed by quenching to room temperature, optionally stretching for stress relief and straightening, and artificially aging at a temperature between 250-375 F. for 6-20 hours.

[0022] In another preferred embodiment the 6xxx series aluminum alloy composition is manufactured by 1) casting using conventional direct chill casting methods; 2) then homogenizing at 950 F. to 1060 F. (510-571 C.) for 2 to 10 hours; 3) then preheating to an extrusion temperature of 450 F.-1000 F. (232-538 C.) and then extruding; optionally drawing the extrusions; followed by solution heat treatment at a temperature of 950 F. to 1070 F., followed by quenching to room temperature, optionally stretching for stress relief and straightening, and artificially aging at a temperature between 250-375 F. for 6-hours.

[0023] The final product including the 6xxx series aluminum alloy composition may be a rod, bar, extruded shape, sheet, and/or plate with a thickness of 0.25-inches. The final product including the 6xxx series aluminum alloy preferably has tensile yield strengths in excess of 295 MPa (43 ksi), or in excess of 300 MPa, or in excess of 310 MPa, or in excess of 325 MPa, or in excess of 330 MPa, or in excess of 339 MPa. In addition to improved tensile yield strength, the final product including the 6xxx series aluminum alloy may have Ultimate Tensile Strength in excess of 340 MPa, or in excess of 345 MPa, or in excess of 349 MPa, or in excess of 355 MPa, or in excess of 360 MPa, or in excess of 364 MPa.

[0024] The 6xxx series aluminum alloy composition may be produced with greater than 75% scrap, or greater than 80% scrap, or greater than 85% scrap, or greater than 90% scrap, or greater than 95% scrap, or with 100% scrap. The scrap used may include, but is not limited to, post-consumer scrap and/or post-industrial scrap. When using greater than 75% scrap to produce the 6xxx series aluminum alloy composition of the present invention, the final product may have excellent machinability performance as defined by achieving a B grade or better in the ASM machinability test detailed in FIG. 1 of chapter on Machining of Aluminum and Aluminum Alloys in the ASM Handbook Aluminum and Aluminum Alloys (1993 Revision and Publication), the contents of which are expressly incorporated herein by reference.

[0025] The following examples illustrate various aspects of the invention and are not intended to limit the scope of the invention.

Example 1

[0026] Extrusion billets were cast in 10 (253 mm) diameter using convention direct chill casting methods. The composition of these billets is shown in Table 1.

TABLE-US-00001 TABLE 1 Compositions of Alloys Studied in Example 1 Alloy Si Fe Cu Mn Mg Zn Cr Ti 1350 1.01 0.28 0.62 0.57 0.95 0.41 0.15 0.02 1357 1.43 0.22 0.30 0.57 1.06 0.79 0.14 0.00

[0027] The billets were then homogenized at 950-1060 F. (510-571 C.) for 2-10 hours. These billets were then preheated to 800 F.-1000 F. (427-538 C.) and extruded. All samples were then water quenched from the hot working operation. After quenching samples were aged at 250-375 F. for 6-20 hours. After aging the mechanical properties of the samples were evaluated to determine the potential strength levels that these types of compositions can achieve. The results of the mechanical property evaluation is shown in Table 2.

TABLE-US-00002 TABLE 2 Mechanical Properties of Alloys in Example 1 YTS YTS UTS UTS Composition [MPa] [ksi] [MPa] [ksi] Elong. 6061 AA 241 35 262 38 10 Minimum 1350 340.1 49.3 369.1 53.5 12.2 1350 340.5 49.4 366.5 53.2 11.6 1350 341.3 49.5 366.2 53.1 12.4 1350 338.6 49.1 364.7 52.9 12.3 1350 339.6 49.3 364.9 52.9 11.5 1357 327.7 47.5 353.1 51.2 12.4 1357 326.3 47.3 350.7 50.9 11.8 1357 327.1 47.4 351.7 51.0 12.5 1357 325.6 47.2 350.9 50.9 11.7 1357 325.1 47.2 349.4 50.7 11.6

[0028] This shows that these types of compositions are capable of achieving strengths well in excess of what is necessary in the general engineering market, as demonstrated by the difference in properties to a typical general engineering alloy 6061.

Example 2

[0029] Extrusion billets were produced in 12 (305 mm) and 18 (457 mm) diameter using conventional direct chill casting methods. The compositions of these billets are shown in Table 3.

TABLE-US-00003 TABLE 3 Compositions of Alloys Studied in Example 3 Diam- Alloy eter Si Fe Cu Mn Mg Zn Cr Ti 1681 12 0.78 0.44 0.30 0.60 0.78 0.49 0.10 0.02 1683 12 1.04 0.42 0.61 0.58 0.56 0.49 0.10 0.02 1684 12 0.79 0.44 0.31 0.60 1.21 0.51 0.10 0.02 1687 12 1.30 0.43 0.30 0.60 1.19 0.50 0.10 0.02 1691 12 1.28 0.43 0.30 0.60 0.80 0.53 0.10 0.02 1698 12 1.03 0.43 0.29 0.58 0.99 0.50 0.09 0.01 1699 12 1.05 0.42 0.30 0.57 1.01 1.00 0.09 0.02 1717 18 1.05 0.44 0.30 0.60 1.00 0.49 0.09 0.02

[0030] All material was homogenized at 950-1060 F. (510-571 C.) for 2-10 hours. Then the 12 diameter billets were preheated to 800 F.-1000 F. (427-538 C.) and extruded into 1 (25.3 mm) and 2 (50.6 mm) diameter rod as well as 23 (50.6 mm76.2 mm) rectangular bar. The 18 material was preheated to the same temperature and extruded into 8 (203 mm) diameter rod as well as 46 (102 mm152 mm) rectangular bar. The material was then water quenched from the hot working operation and aged at 250-375 F. for 6-20 hours.

[0031] The resultant material demonstrated an excellent combination of tensile properties and machinability performance. The average yield and ultimate strengths for each composition and product combination can be seen in Table 4 and Table 5. Again, the improvement in strengths relative to the minimum requirements of a typical general engineering alloy like 6061 listed in Table 2 must be noted.

TABLE-US-00004 TABLE 4 Mechanical Properties of Products Extruded from 12 Diameter Billets Avg. YTS [ksi] Avg. UTS [ksi] Avg. Elong. 2 2 2 Alloy 1 2 3 1 2 3 1 2 3 1681 50.45 49.10 50.15 54.85 53.75 54.65 13.63 13.03 12.60 1683 53.30 55.38 52.25 56.68 58.93 55.98 12.58 10.50 11.50 1684 47.80 49.80 47.55 53.18 55.30 53.10 12.80 13.20 12.65 1687 52.75 54.93 53.40 55.93 58.38 56.60 11.45 11.48 10.93 1691 54.15 56.45 53.23 57.88 60.58 57.38 12.35 11.08 12.68 1698 52.40 56.28 51.58 56.00 60.03 55.43 11.98 11.83 11.73 1699 55.90 55.87 55.33 59.45 60.07 59.15 11.88 11.50 12.08

TABLE-US-00005 TABLE 5 Mechanical Properties of Products Extruded from 18 Diameter Billets Avg. YTS [ksi] Avg. UTS [ksi] Avg. Elong. Alloy 4 6 8 4 6 8 4 6 8 1717 50.23 47.83 54.55 52.78 9.85 10.23

[0032] The machinability performance of this material was evaluated by performing a number of different common machining operations on the samples and assessing the resultant chips to determine the size and weight characteristics. Smaller overall chips result in improved machining operations as it minimizes issues with the processes by reducing the amount of large messy tangled masses of machining chips. When this occurs, manual intervention by the operator is required to resolve this resulting in equipment downtime. The machining performance of these alloys is detailed in the following tables that show the total chips per gram produced in the various machining operations. These results are equivalent to achieving a grade of B or better in the ASM Handbook machinability test (1993 Revision and Publication).

TABLE-US-00006 TABLE 6 Machinability Results of Products Extruded from 12 Diameter Billet 2 3 Rec Bar 1 Diameter 2 Diameter 0.25 Alloy Drill Cutoff Turn Form Drill Cutoff Turn Form Drill Mill Mill 1681 2.12 2.38 4.33 2.34 2.32 0.39 0.23 0.99 8.31 19.38 44.41 1683 2.56 2.10 4.25 5.01 3.05 0.63 1.15 2.04 10.24 18.76 58.01 1684 2.51 2.48 2.27 2.92 2.13 0.99 0.52 3.34 8.00 18.71 57.41 1687 2.58 2.64 4.39 8.53 3.32 0.79 0.69 1.55 10.80 18.65 60.60 1691 2.08 2.25 2.69 8.09 3.08 0.60 0.64 0.54 7.13 18.40 62.73 1698 2.71 2.89 3.67 7.05 2.88 0.59 0.61 2.23 8.68 19.10 53.99 1699 2.78 1.97 3.57 6.91 3.19 1.07 0.98 3.57 10.46 18.58 58.01

TABLE-US-00007 TABLE 7 Machinability Results of Products Extruded from 18 Diameter Billet 4 6 Rec Bar End End 8 Diameter Long Short 0.250 Mill - Mill OD ID Alloy Drill Drill Drill Long Short Turn Drill Turn Groove 1717 9.28 9.53 78.27 17.86 16.86 19.13 5.57 11.89 0.27

[0033] The grain structure developed in these extruded products was unrecrystalized with minimal to no peripheral coarse grain (PCG). Peripheral coarse grain is a thin band of coarse recrystallized grains that appear on the outer perimeter of a profile with an otherwise unrecrystalized grain structure. A typical example of the grain structure in the 2 diameter rod product can be seen in FIG. 2.

[0034] Samples were also anodized to compare the performance to that of typical 6061 material. The overall anodize were quite good and in line with the performance that can be expected from 6061 when it is being anodized. The anodize performance compared to 6061 material can be seen in FIG. 3.

[0035] Overall this demonstrates these compositions ability to achieve excellent mechanical property and machinability while maintain good anodizing performance with an unrecrystalized grain structure with minimal PCG.

Example 3

[0036] The compositions shown in the table below were cast and extruded as per the previous example with some of the compositions being produced in 12 (305 mm) and some being produced in 18 (457 mm).

TABLE-US-00008 TABLE 8 Compositions of Alloys Studied in Example 3 Diam- Alloy eter Si Fe Cu Mn Mg Zn Cr Ti 1771 12 1.30 0.45 0.30 0.60 1.21 0.52 0.16 0.02 1772 12 0.89 0.48 0.29 0.58 0.90 0.49 0.16 0.02 1773 12 1.09 0.46 0.30 0.60 1.04 0.50 0.17 0.02 1774 18 1.10 0.44 0.29 0.59 1.05 0.51 0.17 0.02

[0037] The amount of scrap utilized in each charge when producing these compositions was tracked and the percentage breakdown of scrap vs. prime in each charge is included in the following table.

TABLE-US-00009 TABLE 9 Charge Makeup for Casts Complete in Example 3 Alloy % Scrap in Charge % Prime in Charge 1771 97.14 2.86 1772 100.00 0.00 1773 100.00 0.00 1774 100.00 0.00

[0038] Again, as per the previous example, this material was homogenized at 950-1060 F. (510-571 C.) for 2-10 hours. The billets were preheated to 800 F.-1000 F. (427-538 C.) and the 12 diameter billets were extruded into 1 (25.3 mm) and 2 (50.6 mm) diameter rod as well as 23 (50.6 mm76.2 mm) rectangular bar while the 18 diameter billets were extruded into 8 (203 mm) diameter rod as well as 46 (102 mm152 mm) rectangular bar. The material was quenched and aged with the same practices that were utilized in the previous example.

[0039] The mechanical properties and machinability performance of this material as again evaluated through the same test methods as the previous example. The results of the testing were in line with the previous material performance over the range of sizes and compositions evaluated. These results are detailed in the following tables.

TABLE-US-00010 TABLE 10 Mechanical Properties of Products Extruded from 12 Diameter Billets Avg. YTS [ksi] Avg. UTS [ksi] Avg. Elong. 2 2 2 Alloy 1 2 3 1 2 3 1 2 3 1771 53.43 54.35 51.70 56.60 57.55 55.03 11.18 11.78 12.03 1772 52.81 50.51 49.80 56.49 54.49 54.33 12.09 12.36 11.65 1773 52.68 53.88 51.70 56.28 57.08 55.50 11.55 12.75 10.73

TABLE-US-00011 TABLE 11 Mechanical Properties of Products Extruded from 18 Diameter Billets Avg. YTS [ksi] Avg. UTS [ksi] Avg. Elong. Alloy 4 6 8 4 6 8 4 6 8 1774 48.70 48.38 53.35 53.05 9.78 9.35

TABLE-US-00012 TABLE 12 Machinability Results of Products Extruded from 12 Diameter Billets 2 3 Rec Bar 1 Diameter 2 Diameter 0.25 Alloy Drill Cutoff Turn Form Drill Cutoff Turn Form Drill Mill Mill 1771 4.93 3.31 7.56 10.28 3.08 1.25 1.03 2.22 5.23 14.00 29.28 1772 2.99 2.33 7.21 5.39 2.29 0.70 0.38 2.47 3.94 13.84 23.39 1773 3.42 2.82 7.95 7.12 3.09 0.74 0.74 2.24 5.22 13.85 26.17

TABLE-US-00013 TABLE 13 Machinability Results of Products Extruded from 18 Diameter Billets 4 6 Rec Bar End End 8 Diameter Long Short 0.250 Mill - Mill OD ID Alloy Drill Drill Drill Long Short Turn Drill Turn Groove 1774 5.00 5.14 29.53 15.56 14.87 21.71 4.94 15.73 0.09

[0040] All casts in this evaluation were produced with scrap making up more than 90% of the charge showing that these properties can be achieved while using high levels of scrap material in the production process.

Example 4

[0041] Rolling ingots were produced in 2346 (584 mm1168 mm) using conventional direct chill casting methods. The compositions for the ingots are included in Table 14.

TABLE-US-00014 TABLE 14 Compositions of Alloys Studied in Example 4 Alloy Si Fe Cu Mn Mg Zn Cr Ti 1781 0.90 0.41 0.28 0.56 0.88 0.47 0.15 0.02 1789 1.09 0.37 0.35 0.54 0.99 0.48 0.12 0.02 1791 1.31 0.44 0.30 0.59 1.21 0.53 0.16 0.02

[0042] These ingots were then homogenized at 950-1060 F. (510-571 C.) before being rolled into 1 (25.3 mm) thick plate. After rolling the plates were solution heat treat between 950-1150 F. (510-621 C.) before being quenched. Finally, the plates were aged at 250-375 F. for 6-20 hours.

[0043] After completion of aging tensile samples were taken from the plates and the results of the mechanical property testing can be seen in the following table.

TABLE-US-00015 TABLE 15 Mechanical Properties of Plate Products Produced in Example 4 Avg. YTS [ksi] Avg. UTS [ksi] Avg. Elong. Alloy LT Orientation LT Orientation LT Orientation 1781 50.30 53.10 9.60 1789 48.90 52.80 8.40 1791 46.60 50.50 11.70

[0044] This example demonstrates that these compositions are capable of achieving the same mechanical properties when produced in a rolled product as compared to an extruded product.

[0045] While specific embodiments of the invention have been disclosed, it will be appreciated by those skilled in the art that various modifications and alterations to those details could be developed in light of the overall teachings of the disclosure. Accordingly, the particular arrangements disclosed are meant to be illustrative only and not limiting as to the scope of the invention which is to be given the full breadth if the appended claims and any and all equivalents thereof.