CORROSION RESISTANT HIGH STRENGTH WELDABLE ALUMINUM ALLOY FOR STRUCTURAL APPLICATIONS

Abstract

A new 7 xxx aluminum alloy provides a unique combination of quantifiable physical characteristics. The alloy may be generally described as a corrosion resistant aluminum-zinc- magnesium based alloy that is copper free or only includes slight amounts of copper as an impurity.

Claims

1-52. (canceled)

53. A 7xxx aluminum alloy, comprising: 4.0-8.0 wt.% zinc; 1.5-3.0 wt.% magnesium; 0.01-0.8 wt.% of a material selected from a group consisting of a rare earth element, cerium, misch metal, lanthanum, neodymium, samarium or combinations thereof; a dispersoid forming element selected from a group consisting of up to 1.2 wt.% manganese, between 0.01-0.25 wt.% titanium, up to 1.0 wt.% of zirconium, up to 1.0 wt.% of chromium, and combinations thereof; up to 1.0 wt.% impurities; and remainder as aluminum.

54. The 7xxx aluminum alloy of claim 53, wherein the impurities include up to 0.5 wt.% iron.

55. The 7xxx aluminum alloy of claim 53, wherein the impurities include up to 0.5 wt.% silicon.

56. The 7xxx aluminum alloy of claim 53, wherein the impurities include less than 0.3 wt.% copper.

57. The 7xxx aluminum alloy of claim 53, wherein the impurities include less than 0.1 wt.% copper.

58. The 7xxx aluminum alloy of claim 53 is free of copper.

59. The 7xxx aluminum alloy of claim 53, wherein the rare earth element is selected from a group consisting of yttrium, praseodymium, promethium, gadolinium, terbium, dysprosium, holmium, erbium, thulium, ytterbium, lutetium and combinations thereof.

60. A 7xxx aluminum alloy, consisting of: 5.0-7.5 wt.% zinc; 1.5-2.6 wt.% magnesium; 0.01-1.0 wt.% manganese; 0.01-0.3 wt.% of a material selected from a group consisting of a rare earth element, cerium, misch metal, lanthanum, neodymium, samarium or combinations thereof; 0.01-0.25 wt.% titanium; up to 0.3 wt.% zirconium; up to 1 wt.% impurities; and remainder as aluminum.

61. The 7xxx aluminum alloy of claim 60, wherein the rare earth element is selected from a group consisting of yttrium, praseodymium, promethium, gadolinium, terbium, dysprosium, holmium, erbium, thulium, ytterbium, lutetium and combinations thereof.

62. The 7xxx aluminum alloy of claim 60, wherein the 7xxx aluminum alloy has a post weld ductility of at least 3.0% elongation.

63. The 7xxx alloy of claim 62, wherein the 7xxx alloy has a stress corrosion cracking resistance of at least 26 ksi for 20 days per G47.

64. The 7xxx aluminum alloy of claim 63, wherein the 7xxx alloy has an ultimate strength of at least 65 ksi.

65. The 7xxx aluminum alloy of claim 64, wherein the 7xxx alloy has a tensile yield strength of at least 60 ksi.

66. The 7xxx aluminum alloy of claim 65, wherein the 7xxx alloy has an elongation of at least 4%.

67. The 7xxx alloy of claim 60, wherein the 7xxx alloy has a stress corrosion cracking resistance of at least 26 ksi for 20 days per G47 as of Dec. 1, 2020.

68. The 7xxx aluminum alloy of claim 60, wherein the 7xxx alloy has an ultimate strength of at least 65 ksi.

69. The 7xxx aluminum alloy of claim 69, wherein the 7xxx alloy has a tensile yield strength of at least 60 ksi.

70. The 7xxx aluminum alloy system of claim 60, wherein the 7xxx alloy has an elongation of at least 4%.

71. A composition of matter, comprising an aluminum, zinc and magnesium alloy system having a post weld ductility of at least 3% elongation.

72. The composition of matter of claim 71 free of copper.

Description

DETAILED DESCRIPTION

[0017] The new and improved 7xxx alloy and composition of matter that is the subject matter of this document provides a unique combination of quantifiable physical properties including very high strength and ductility and acceptable stress corrosion resistance as well as excellent weldability with high post-weld mechanical properties. As a result, the new 7xxx aluminum alloy and composition of matter is particularly suited as wrought product for armored military vehicles and other structural applications.

[0018] The new and improved 7xxx aluminum alloy comprises; (a) 4.0-8.0 wt.% zinc, (b) 1.5-3.0 wt.% magnesium, (c) 0.01-0.8 wt.% of a material selected from a group consisting of a rare earth element, cerium, misch metal or combinations thereof, (d) a dispersoid forming element selected from a group consisting of up to 1.2 wt.% manganese, between 0.01-0.25 wt.% titanium, up to 1.0 wt.% of zirconium, up to 1.0 wt.% of chromium, and combinations thereof (e) up to 1.0 wt.% impurities and (f) remainder as aluminum. For purposes of this document, “misch metal” refers to an alloy containing cerium (Ce), lanthanum (La), neodymium (Nd) and other rare earth elements. In one particularly useful embodiment of the new improved 7xxx aluminum alloy, the rare earth element is selected from a group of elements consisting of yttrium (Y), praseodymium (Pr), promethium (Pm), gadolinium (Gd), terbium (Tb), dysprosium (Dy), holmium (Ho), erbium (Er), thulium (Tm),ytterbium (Yb), lutetium (Lu) and combinations thereof.

[0019] The impurities may include up to 0.5 wt.% iron and/or up to 0.5 wt.% silicon. In one or more embodiments, the 7xxx aluminum alloy is copper free. In other embodiments, the 7xxx aluminum alloy includes less than 0.1 wt.% copper as an impurity. In other embodiments, the 7xxx aluminum alloy includes less than 0.3 wt.% as an impurity.

[0020] In one or more embodiments, the 7xxx aluminum alloy is scandium free. In other embodiments, the 7xxx aluminum alloy includes less than 0.3 wt.% scandium. In other embodiments, the 7xxx aluminum alloy includes less than 0.8 wt.% scandium.

[0021] In one or more embodiments, the 7xxx aluminum alloy is nickel free. In other embodiments, the 7xxx aluminum alloy includes less than 0.3 wt.% nickel. In other embodiments, the 7xxx alloy includes less than 0.8 wt.% nickel.

[0022] In one or more embodiments, the 7xxx aluminum alloy is vanadium free. In other embodiments, the 7xxx aluminum alloy includes less than 0.15 wt.% vanadium. In other embodiments, the 7xxx aluminum alloy includes less than 0.25 wt.% vanadium.

[0023] In some embodiments, the 7xxx aluminum alloy includes 0.1-0.5 wt.% manganese. In some embodiments, the 7xxx aluminum alloy includes between 0.1-1.0 wt.% nickel. In some embodiments, the 7xxx aluminum alloy includes between 0.1-1.0 wt.% chromium. In some embodiments, the 7xxx aluminum alloy includes both nickel and chromium in these amounts. In some embodiments, the 7xxx aluminum alloy includes 0.1-0.8 wt.% scandium, 0.1-1.0 wt.% nickel and 0.1-1.0 wt.% chromium. Any of these embodiments may be copper free or contain less than 0.3 wt.% copper as an impurity or less than 0.1 wt.% copper as an impurity.

[0024] Any of these embodiments may be scandium free or contain less than 0.8 wt.% scandium as an impurity or less than 0.3 wt.% scandium as an impurity. Any of these embodiments may be nickel free or contain less than 0.8 wt.% nickel as an impurity or less than 0.3 wt.% nickel as an impurity. Any of these embodiments may be vanadium free or contain less than 0.25 wt.% vanadium as an impurity or less than 0.15 wt.% vanadium as an impurity.

[0025] The 7xxx aluminum alloy may be described as consisting of (a) 5.0-7.5 wt.% zinc, (b) 1.5-2.6 wt.% magnesium, (c) 0.01-1.0 wt.% manganese, (d) 0.01-0.8 wt.% of a material selected from a group consisting of a rare earth element, cerium, misch metal or combinations thereof, (e) 0.01-0.25 wt.% titanium, (f) up to 0.3 wt.% zirconium and (g) the remainder aluminum with 1.0 wt.% or less in impurities. In one particularly useful embodiment of the new improved 7xxx aluminum alloy, the rare earth element is selected from a group of elements consisting of yttrium (Y), praseodymium (Pr), promethium (Pm), gadolinium (Gd), terbium (Tb), dysprosium (Dy), holmium (Ho), erbium (Er), thulium (Tm),ytterbium (Yb), lutetium (Lu) and combinations thereof.

[0026] In one possible embodiment, the 7xxx aluminum alloy includes up to 0.5 wt.% scandium and up to 0.2 wt.% zirconium.

[0027] That 7xxx aluminum alloy exhibits a post weld ductility of at least 3.0% elongation. The 7xxx aluminum alloy exhibits a stress corrosion cracking resistance of at least 26 ksi for 20 days per G47 as of Dec. 1, 2020. The 7xxx aluminum alloy exhibits an ultimate strength of at least 65 ksi. The 7xxx aluminum alloy exhibits a tensile yield strength of at least 60 ksi. The 7xxx aluminum alloy exhibits an elongation of at least 4%. Further, it should be appreciated that the 7xxx aluminum alloy exhibits a combination of all five of these physical characteristics or properties. This unique combination of physical characteristics or properties make the new 7xxx aluminum alloy particularly useful for armored military vehicle applications as well as for other applications requiring very high strength and ductility and excellent weldability with high post-weld mechanical properties and acceptable stress corrosion resistance.

[0028] Consistent with the above description, a composition of matter is provided. That composition of matter comprises or consists of an aluminum, zinc and magnesium alloy system having a post weld ductility of at least 3% elongation.

[0029] That composition of matter may also have at least one or more of the following properties: (a) a stress corrosion cracking resistance of at least 26 ksi for 20 days per G47, (b) an ultimate strength of at least 65 ksi, (c) a tensile yield strength of at least 60 ksi and (d) an elongation of at least 4% per ASTM B557-15.

[0030] The 7xxx aluminum alloy or composition of matter may be cast into billets or ingots. Those billets or ingots may then be subject to conventional transformation techniques. For example, the billets or ingots may be subject to a homogenization stage at temperatures between 454.4° C. (850° F.) and 493.3° C. (920° F.), followed by hot rolling, forging, extruding or wire drawing, then a solution heat treatment at temperatures between 454.4° C. (850° F.) and 498.8° C. (930° F.) followed by quenching and stress relieving operations. Finally, an aging treatment, preferably by two step age, may be conducted in order to obtain a product in temper T6.

[0031] The 7xxx aluminum alloy or composition of matter made may be used to produce plate, sheet, extrusion and forgings that exhibit the unique combination of material properties outlined above.

Experimental Results

[0032] Eleven (11) 30 lbs. rectangular ingots of high strength 7xxx alloys were cast. Those ingots were then subject to conventional transformation techniques, comprising of a homogenization stage, followed by hot rolling, a solution heat treatment followed by quenching and stress relieving operations. Finally an aging treatment was conducted in order to obtain a product in temper T651 having a thickness of 3.81 cm to conduct mechanical property testing. Welding tests were conducted 1.27 cm plate of T651 Temper.

[0033] The chemistries of the eleven ingots are presented in the following Table:

TABLE-US-00001 Chemistry (all in wt.%) alloy Cu Mg Mn Ti Zr Zn Cr Ce Ni AA7085 1.6 1.8 0 0.02 0.12 7.5 0 0 0 AA7050 2 2.2 0 0.02 0.08 6.3 0 0 0 alloy PA1 0.5 2.2 0 0.08 0.08 5.9 0 0 0 alloy PA2 0.1 2.3 0.4 0.1 0 6 0.25 0.1 0.3 alloy PA3 0 2.2 0.4 0.11 0.1 6.1 0.35 0.2 0 alloy PA4 0 2.2 0.35 0.08 0.1 6.3 0 0.1 0.1 alloy PA5 0 2.2 0.5 0.1 0 6.4 0.13 0.15 misch metal 0 alloy PA6 0 2.2 0.5 0.12 0 6.2 0 0.1 0 alloy PA7 0 2.3 0.5 0.12 0.03 6.5 0 0.15 0 alloy PA8 0 2.5 0.5 0.12 0.11 6.5 0.075 0.075 0 alloy PA9 0 2.3 0.3 0.12 0.12 6.3 0.05 0.05 0

2. Weldability Test

[0034] The first test was to conduct post-weld tensile tests to evaluate the weldability of the alloys. Weldability tests were conducted on 1.27 cm gauge plate by TIG welding. TIG welding stick alloy, WA1, was developed specifically for 7xxx alloy welding at ATI Inc. as follows:

TABLE-US-00002 Chemistry of Welding stick alloy WA1. (all in wt.%) alloy Cu Mg Mn Ti Zr Zn WA1 0 4 0.5 0.15 0 2.5

[0035] Post-weld tensile tests were conducted on 1.27 cm thick alloy plate welded by TIG welding with the welding stick of WA1 alloy. Weldability was tested by conducting duplicate tensile tests across the welded joint. To avoid the big difference of welded joint width within the specimen of the beveled welded joint, the tensile tests were conducted across weldment on 1.27 cm gauge plate with 60 degree beveled edges with flat tensile test specimens of 0.3175 cm thick by 0.635 cm wide by 2.54 cm gauge length. The 2.54 cm gauge length consisted of 1.27 cm of weldment with 0.635 cm of HAZ (Heat Affected Zone) on either side.

2.A. Weldability of AA7085

[0036] Post-weld tensile test results of welded joint of AA7085 are as follows:

TABLE-US-00003 alloy UTS(ksi) TYS(ksi) Elong.(%) 7085-T6-LT1 not avail. not avail. 0 7085-T6-LT2 not avail. not avail. 0

[0037] Post-weld tensile tests of welded joint of AA7085 show zero ductility. Therefore, AA7085 is not weldable.

2.B. Weldability of AA7050

[0038] Post-weld tensile test results of welded joint of AA7050 are as follows:

TABLE-US-00004 alloy UTS(ksi) TYS(ksi) Elong.(%) 7050-T6-LT1 not avail. not avail. 0 7050-T6-LT2 not avail. not avail. 0

[0039] Post-weld tensile tests of welded joint of AA7050 show zero ductility. Therefore, AA7050 is not weldable.

2.C. Weldability of Alloy PA1

[0040] In an attempt to improve weldability, reduced Cu containing alloy PA1 was tested. Post-weld tensile test results of welded joint of alloy PA1 are as follows:

TABLE-US-00005 alloy UTS(ksi) TYS(ksi) Elong.(%) PA1-LT1 not avail. not avail. 0 PA1-LT2 not avail. not avail. 0

[0041] Post-weld tensile tests of the welded joint of alloy PA1 show zero ductility. Therefore, alloy PA1 is not weldable.

2.D. Weldability of Alloy PA2

[0042] Post-weld tensile test results of welded joint of alloy PA2 are as follows:

TABLE-US-00006 S.No UTS(ksi) TYS(ksi) Elong.(%) PA2-LT1 50.2 n.a. 14.3 PA2-LT2 50.5 n.a. 13.9

[0043] Post-weld tensile tests of welded joint of alloy PA2 show ductility of 14.3% and 13.9% elongation. Therefore, alloy PA2 is weldable.

2.E. Weldability of Alloy PA3

[0044] Post-weld tensile test results of welded joint of alloy PA3 are as follows

TABLE-US-00007 alloy UTS(ksi) TYS(ksi) Elong.(%) PA3-LT1 54.1 not avail. 14.9 PA3-LT2 51.7 not avail. 11.3

[0045] Post-weld tensile test of welded joint of alloy PA3 show ductility of 14.9% and 11.3% elongation. Therefore, alloy PA3 is weldable.

2.F. Weldability of Alloy PA4

[0046] Post-weld tensile test results of welded alloy PA4 are as follows:

TABLE-US-00008 alloy UTS(ksi) TYS(ksi) Elong.(%) PA4-LT1 50.2 not avail. 13.9 PA4-LT2 51.5 not avail. 16.2

[0047] Post-weld tensile tests of welded joint of alloy PA4 show ductility of 13.9% and 16.2% elongation. Therefore, alloy PA4 is weldable.

2.G. Weldability of Alloy PA5

[0048] Post-weld tensile test results of welded alloy PA5 are as follows:

TABLE-US-00009 alloy UTS(ksi) TYS(ksi) Elong.(%) PA5-LT1 52.6 not avail. 13.7 PA5-LT2 53.4 not avail. 14.5

[0049] Post-weld tensile tests of welded joint of alloy P43 show ductility of 13.7% and 14.5% elongation. Therefore, alloy PA5 is weldable.

[0050] This alloy contained misch metal and Cr instead of Cerium and Cr. Misch metal is an alloy containing cerium(Ce), lanthanum(La), neodymium(Nd) and other rare earth elements. This proves that Ce can be replaced with a combination of other rare earth elements and show good weldability and SCC Resistance.

2.H. Weldability of Alloy PA6

[0051] Post-weld tensile test results of welded joint of alloy PA5 are as follows:

TABLE-US-00010 alloy UTS(ksi) TYS(ksi) Elong.(%) PA6-LT1 54.8 not avail. 14.1 PA6-LT2 55 not avail. 12.3

[0052] Post-weld tensile tests of welded joint of alloy PA6 show ductility of 14.1% and 12.3% elongation. Therefore, alloy PA6 is weldable.

2.I. Weldability of Alloy PA7

[0053] Post-weld tensile test results of welded joint of alloy PA7 are as follows:

TABLE-US-00011 alloy UTS(ksi) TYS(ksi) Elong.(%) PA7-LT1 50.2 not avail. 11.8 PA7-LT2 52.5 not avail. 13.6

[0054] Post-weld tensile test of welded joint of alloy PA7 show ductility of 11.8% and 13.6% elongation. Therefore, alloy PA7 is weldable.

2.J. Weldability of Alloy PA8

[0055] Post-weld tensile test results of welded joint of alloy PA8 are as follows:

TABLE-US-00012 alloy UTS(ksi) TYS(ksi) Elong.(%) PA8-LT1 52.7 not avail. 12.3 PA8-LT2 51.4 not avail. 11.9

[0056] Post-weld tensile test of welded joint of alloy PA8 show ductility of 12.3% and 11.9% elongation. Therefore, alloy PA8 is weldable.

2.K. Weldability of Alloy PA9

[0057] Post-weld tensile test results of welded joint of alloy PA9 are as follows;

TABLE-US-00013 alloy UTS(ksi) TYS(ksi) Elong.(%) PA7-LT1 50.2 not avail. 11.8 PA7-LT2 52.5 not avail. 13.6

[0058] Post-weld tensile test of welded joint of alloy PA9 show ductility of 12.5% and 14.7% Elongation. Therefore, alloy PA9 is weldable.

3. Stress Corrosion Cracking Resistance (SCCR)

[0059] For plate gauge product, Stress Corrosion Cracking Resistance (SCCR) is a very important characteristic in determining engineering worthiness. Among the 11 alloys, 8 alloys are weldable. For the eight (8) weldability-proven alloys, SCCR tests were conducted on 38.1 mm plate at 26 ksi for 20 day tests per ASTM G-47. 26 ksi was selected because the most recently developed aluminum amor grade AA7085 is rated as SCCR at 26 ksi for 20 day test per G-47 as of Dec. 1, 2020.

3.A. Stress Corrosion Cracking Test Results of Alloy PA2

[0060] SCCR tests of alloy PA2 (tested at 26 ksi for 20 day per G-47)

TABLE-US-00014 sample location modulus orientation size (inch) Stress (ksi) Duration (days) Pitting Rating Disposition SCC-1 T/2 10.3 ST 0.125 26 11 Light Unacceptable SCC-2 T/2 10.3 ST 0.125 26 12 Light-Moderate Discontinue testing SCC-3 T/2 10.3 ST 0.125 26 6 Light Unacceptable

[0061] All three samples have to pass 20 day test to be rated as “PASSED”. Therefore, Alloy PA2 failed to pass SCCR test at 26 ksi for 20 day test period.

3.B. Stress Corrosion Cracking Resistance Test Results of Alloy PA3

[0062] SCCR tests of alloy PA3 (tested at 26 ksi for 20 day per G-47)

TABLE-US-00015 sample location modulus orientation size (inch) Stress (ksi) Duration (days) Pitting Rating Disposition SCC-1 T/2 10.3 ST 0.125 26 20 Light Acceptable SCC-2 T/2 10.3 ST 0.125 26 20 Light Acceptable SCC-3 T/2 10.3 ST 0.125 26 20 Light Acceptable

[0063] All three samples have to pass 20 day test to be rated as “PASSED”. Therefore, Alloy PA3 passed SCCR test at 26 ksi for 20 day test per G-47.

3.C. Stress Corrosion Cracking Resistance Test Results of Alloy PA4

[0064] SCCR tests of alloy PA4 (tested at26 ksi for 20 day per G-47)

TABLE-US-00016 sample location modulus orientation size (inch) Stress (ksi) Duration (days) Pitting Rating Disposition SCC-1 T/2 10.3 ST 0.125 26 20 Light Acceptable SCC-2 T/2 10.3 ST 0.125 26 20 Light Acceptable SCC-3 T/2 10.3 ST 0.125 26 20 Light Acceptable

All three samples passed 20 day test to be rated as “PASSED”. Therefore, Alloy PA4 passed SCCR test at 26 ksi for 20 day test per G-47.

3.D. Stress Corrosion Cracking Resistance Test Results of Alloy PA5

[0065] SCCR tests of alloy PA5 (tested at 26 ksi for 20 day per G-47)

TABLE-US-00017 sample location modulus orientation size (inch) Stress (ksi) Duration (days) Pitting Rating Disposition SCC-1 T/2 10.3 ST 0.125 26 20 Light Acceptable SCC-2 T/2 10.3 ST 0.125 26 20 Light Acceptable SCC-3 T/2 10.3 ST 0.125 26 20 Light Acceptable

[0066] All three samples passed at 26 ksi for 20 day test to be rated as “PASSED”. Therefore, Alloy PA5 passed SCCR test at 26 ksi for 20 day test per G-47.

[0067] This alloy contained misch metal and Cr instead of Cerium and Cr. Misch metal is an alloy containing cerium(Ce), lanthanum(La), neodymium(Nd) and other rare earth elements. This proves that Ce can be replaced with combination of other rare earth elements and show good stress corrosion cracking resistance.

3.E. Stress Corrosion Cracking Resistance Test Results of Alloy PA6

[0068] SCCR tests of alloy PA6 (tested at 26 ksi for 20 day per G-47)

TABLE-US-00018 sample location modulus orientation size (inch) Stress (ksi) Duration (days) Pitting Rating Disposition SCC-1 T/2 10.3 ST 0.125 26 20 Light Acceptable SCC-2 T/2 10.3 ST 0.125 26 20 Light Acceptable SCC-3 T/2 10.3 ST 0.125 26 20 Light Acceptable

[0069] All three samples passed at 26 ksi for 20 day test to be rated as “PASSED”.

[0070] Therefore, Alloy PA6 passed SCCR test at 26 ksi for 20 day test per G-47.

[0071] There were some concerns that Stress Corrosion Cracking Resistance (SCCR) at 26 ksi stress level is too low of testing threshold stress level. Therefore, further tests were conducted at 30 ksi stress level.

3.F. Stress Corrosion Cracking Resistance Test Results of Alloy PA7

[0072] SCCR tests of alloy PA7 (tested at 30 ksi for 20 day per G-47)

TABLE-US-00019 sample location modulus orientation size (inch) Stress (ksi) Duration (days) Pitting Rating Disposition SCC-1 T/2 10.3 ST 0.125 30 20 Light Acceptable SCC-2 T/2 10.3 ST 0.125 30 20 Light Acceptable SCC-3 T/2 10.3 ST 0.125 30 20 Light Acceptable

[0073] All three samples passed 20 day test at 30 ksi stress level. The test results of alloy PA7 shows good Stress Corrosion Cracking Resistance (SCCR). However, alloy PA7 is containing 0.15 wt.% of Ce. The price of Ce is expensive. Therefore, containing 0.15 wt.% Ce as an alloying element makes the alloy expensive. A better solution is desirable.

3.G. Stress Corrosion Cracking Resistance Test Results of Alloy PA8

[0074] As an attempt to reduce the price of the alloy without losing SCCR property, 0.15 wt.% of Ce is replaced with 0.075 wt.% of Ce and 0.075 wt.% of Cr. The price of Cr is not expensive.

[0075] SCCR tests of alloy PA8(tested at 30 ksi for 20 day per G-47)

TABLE-US-00020 sample location modulus orientation size (inch) Stress (ksi) Duration (days) Pitting Rating Disposition SCC-1 T/2 10.3 ST 0.125 30 20 Light Acceptable SCC-2 T/2 10.3 ST 0.125 30 20 Light Acceptable SCC-3 T/2 10.3 ST 0.125 30 20 Light Acceptable

[0076] Alloy PA8 passed SCCR test at 30 ksi for 20 day test per G-47

3.H. Stress Corrosion Cracking Resistance Test Results of Alloy PA9

[0077] In order to reduce the price of the alloy further, 0.075 wt. % Ce and 0.075 wt. % Cr were replaced with 0.05 wt.% Ce and 0.05 wt.% Cr in Alloy PA9.

[0078] SCCR tests of alloy PA9 (tested at 30 ksi for 20 day per G-47)

TABLE-US-00021 sample location modulus orientation size (inch) Stress (ksi) Duration (days) Pitting Rating Disposition SCC-1 T/2 10.3 ST 0.125 30 20 Light Acceptable SCC-2 T/2 10.3 ST 0.125 30 20 Light Acceptable SCC-3 T/2 10.3 ST 0.125 30 20 Light Acceptable

[0079] Alloy PA9 passed SCCR test at 30 ksi for 20 day test per G-47.

[0080] Among the seven alloys tested for weldability and Stress Corrosion Cracking Resistance (SCCR), only seven alloys, namely alloy PA3, alloy PA4, alloy PA5, alloy PA6, alloy PA7, alloy PA8 and alloy PA9, showed acceptable weldability and Stress Corrosion Cracking Resistance. Only these seven alloys will be tested for mechanical properties.

4. Mechanical Properties of 3.81 Cm Thick Plate

[0081] Mechanical properties of 3.81 cm thick plate are tested on seven alloys with acceptable SCCR: alloy PA3, alloy PA4, alloy PA5, alloy PA6, alloy PA7, alloy PA8 and alloy PA9.

4.A. Mechanical Property of Alloy PA3

[0082] Duplicate tensile tests per ASTM B557-15 (as of Dec. 1, 2020) are conducted on 3.81 cm plate of PA3 alloy. The test direction was in long transverse (LT) direction. The Ultimate Strength (UTS), Tensile Yield Stress (TYS) and Elongation (Elong.) are as follows:

TABLE-US-00022 alloy direction UTS (ksi) TYS (ksi) Elong. (%) alloy PA3 LT1 69.5 64.6 4.1 alloy PA3 LT2 66 61.4 4.4

4.B. Mechanical Property of Alloy PA4

[0083] Duplicate tensile tests are conducted on 3.81 cm Plate of alloy PA4 in LT direction. The test results are as follows:

TABLE-US-00023 alloy direction UTS (ksi) TYS (ksi) Elong. (%) alloy PA4 LT1 70.8 65.6 5 alloy PA4 LT2 77.8 66.2 5.5

4.C. Mechanical Property of Alloy PA5

[0084] Duplicate tensile tests are conducted on 3.81 cm Plate of alloy PA5 in LT direction. The test results are as follows:

TABLE-US-00024 alloy direction UTS (ksi) TYS (ksi) Elong. (%) alloy PA5 LT1 70.9 64.9 12 alloy PA5 LT2 71 64.7 10

4.D. Mechanical Property of Alloy PA6

[0085] Duplicate tensile tests are conducted on 3.81 cm Plate of alloy PA6 in LT direction. The test results are as follows:

TABLE-US-00025 alloy direction UTS (ksi) TYS (ksi) Elong. (%) alloy PA6 LT1 75.3 70.2 10 alloy PA6 LT2 76.4 71.2 10

4.E. Mechanical Property of Alloy PA7

[0086] Duplicate tensile tests are conducted on 3.81 cm Plate of PA7 alloy. The test direction was in Long Transverse direction (LT direction). The ultimate tensile strength (UTS), tensile yield stress (TYS) and elongation (Elong.) are as follows:

TABLE-US-00026 alloy direction UTS (ksi) TYS (ksi) Elong. (%) alloy PA7 LT1 75.1 69.4 10 alloy PA7 LT2 75.6 70 10

[0087] The test results of alloy PA7 show good tensile properties.

4.F. Mechanical Property of Alloy PA8

[0088] Duplicate tensile tests are conducted on 3.81 cm Plate of PA8 alloy in LT direction. The test results are as follows:

TABLE-US-00027 alloy direction UTS (ksi) TYS (ksi) Elong. (%) alloy PA8 LT1 76.3 70.3 11.5 alloy PA8 LT2 78.1 72.3 9

[0089] The test results of alloy PA8 show good tensile properties.

4.G. Mechanical Property of Alloy PA9

[0090] Duplicate tensile tests are conducted on 3.81 cm Plate of PA9 alloy in LT direction. The test results are as follows:

TABLE-US-00028 alloy direction UTS (ksi) TYS (ksi) Elong. (%) alloy PA9 LT1 76.9 71.4 11.5 alloy PA9 LT2 76.6 70.9 9.5

[0091] The test results of alloy PA9 show good tensile properties.

5. The Summary of the Test Results of the Most Preferred Embodiment of Invented Alloy PA9

[0092] 5.A. Chemistry of alloy PA9:

TABLE-US-00029 alloy Cu Mg Mn Ti Zr Zn Cr Ce Ni alloy PA9 0 2.3 0.3 0.12 0.12 6.3 0.05 0.05 0

[0093] Remainders are aluminum and impurities such as Fe and Si and others.

[0094] 5.B. Post-weld tensile property of alloy PA9:

TABLE-US-00030 alloy UTS (ksi) TYS (ksi) Elong. (%) PA9-LT1 52.6 not avail. 12.5 PA9-LT2 53.1 not avail. 14.7

[0095] 5.C. Stress Corrosion Cracking Resistance of alloy PA9 (tested at 30 ksi for 20 day test per G47)

TABLE-US-00031 sample location modulus orientation size (inch) Stress (ksi) Duration (days) Pitting Rating Disposition SCC-1 T/2 10.3 ST 0.125 30 20 Light Acceptable SCC-2 T/2 10.3 ST 0.125 30 20 Light Acceptable SCC-3 T/2 10.3 ST 0.125 30 20 Light Acceptable

[0096] 5.D. Mechanical properties of alloy PA9:

TABLE-US-00032 alloy direction UTS (ksi) TYS (ksi) Elong. (%) alloy PA9 LT1 76.9 71.4 11.5 alloy PA9 LT2 76.6 70.9 9.5

[0097] The disclosure may be considered to relate to the following items:

[0098] 1. A 7xxx aluminum alloy, comprising: [0099] 4.0-8.0 wt.% zinc; [0100] 1.5-3.0 wt.% magnesium; [0101] 0.01-0.8 wt.% of a material selected from a group consisting of a rare earth element, cerium, misch metal, lanthanum, neodymium, samarium or combinations thereof; [0102] a dispersoid forming element selected from a group consisting of up to 1.2 wt.% manganese, between 0.01-0.25 wt.% titanium, up to 1.0 wt.% of zirconium, up to 1.0 wt.% of chromium, and combinations thereof; [0103] up to 1.0 wt.% impurities; and [0104] remainder as aluminum.

[0105] 2. The 7xxx aluminum alloy of item 1, wherein the impurities include up to 0.5 wt.% iron.

[0106] 3. The 7xxx aluminum alloy of item 1, wherein the impurities include up to 0.5 wt.% silicon.

[0107] 4. The 7xxx aluminum alloy of item 1, wherein the impurities include less than 0.3 wt.% copper.

[0108] 5. The 7xxx aluminum alloy of item 1, wherein the impurities include less than 0.1 wt.% copper.

[0109] 6. The 7xxx aluminum alloy of item 1 is free of copper.

[0110] 7. The 7xxx aluminum alloy of item 1, wherein the rare earth element is selected from a group consisting of yttrium, praseodymium, promethium, gadolinium, terbium, dysprosium, holmium, erbium, thulium, ytterbium, lutetium and combinations thereof.

[0111] 8. The 7xxx aluminum alloy of any of items 1-7, including less than 0.8 wt.% scandium.

[0112] 9. The 7xxx aluminum alloy of any of items 1-7, including less than 0.3 wt.% scandium.

[0113] 10. The 7xxx aluminum alloy of any of items 1-7, wherein said 7xxx aluminum alloy is free of scandium.

[0114] 11. The 7xxx aluminum alloy of any of items 1-10, including less than 0.8 wt.% nickel.

[0115] 12. The 7xxx aluminum alloy of any of items 1-10, including less than 0.3 wt.% nickel.

[0116] 13. The 7xxx aluminum alloy of any of items 1-10, wherein said 7xxx aluminum alloy is free of nickel.

[0117] 14. The 7xxx aluminum alloy of any of items 1-13, including less than 0.25 wt.% vanadium.

[0118] 15. The 7xxx aluminum alloy of any of items 1-13, including less than 0.15 wt.% vanadium.

[0119] 16. The 7xxx aluminum alloy of any of items 1-13, wherein said 7xxx aluminum alloy is free of vanadium.

[0120] 17. A 7xxx aluminum alloy, consisting of: [0121] 5.0-7.5 wt.% zinc; [0122] 1.5-2.6 wt.% magnesium; [0123] 0.01-1.0 wt.% manganese; [0124] 0.01-0.3 wt.% of a material selected from a group consisting of a rare earth element, cerium, misch metal, lanthanum, neodymium, samarium or combinations thereof; [0125] 0.01-0.25 wt.% titanium; [0126] up to 0.3 wt.% zirconium; [0127] up to 1 wt.% impurities; and [0128] remainder as aluminum.

[0129] 18. The 7xxx aluminum alloy of item 17 wherein the rare earth element is selected from a group consisting of yttrium, praseodymium, promethium, gadolinium, terbium, dysprosium, holmium, erbium, thulium, ytterbium, lutetium and combinations thereof.

[0130] 19. The 7xxx aluminum alloy of item 17, further including 0.1-1.0 wt.% chromium.

[0131] 20. The 7xxx aluminum alloy of items 17-19, having 0.1-0.5 wt.% manganese.

[0132] 21. The 7xxx aluminum alloy of any of items 17-20, wherein the impurities include less than 0.3 wt.% copper.

[0133] 22. The 7xxx aluminum alloy of any of items 17-20, wherein the impurities include less than 0.1 wt.% copper.

[0134] 23. The 7xxx aluminum alloy of any of items 17-20, wherein the 7xxx aluminum alloy is free of copper.

[0135] 24. The 7xxx aluminum alloy of any of items 17-23, including less than 0.8 wt.% scandium.

[0136] 25. The 7xxx aluminum alloy of any of items 17-23, including less than 0.3 wt.% scandium.

[0137] 26. The 7xxx aluminum alloy of any of items 17-23, wherein the 7xxx aluminum alloy is free of scandium.

[0138] 27. The 7xxx aluminum alloy of any of items 17-26, including less than 0.8 wt.% nickel.

[0139] 28. The 7xxx aluminum alloy of any of items 17-26, including less than 0.3 wt.% nickel.

[0140] 29. The 7xxx aluminum alloy of any of items 17-26, wherein the 7xxx aluminum alloy is free of nickel.

[0141] 30. The 7xxx aluminum alloy of any of items 17-29, including less than 0.25 wt.% vanadium.

[0142] 31. The 7xxx aluminum alloy of any of items 17-29, including less than 0.15 wt.% vanadium.

[0143] 32. The 7xxx aluminum alloy of any of items 17-29, wherein the 7xxx aluminum alloy is free of vanadium.

[0144] 33. The 7xxx aluminum alloy of item 17, wherein the 7xxx aluminum alloy has a post weld ductility of at least 3.0% elongation.

[0145] 34. The 7xxx alloy of item 33, wherein the 7xxx alloy has a stress corrosion cracking resistance of at least 26 ksi for 20 days per G47.

[0146] 35. The 7xxx aluminum alloy of item 34, wherein the 7xxx alloy has an ultimate strength of at least 65 ksi.

[0147] 36. The 7xxx aluminum alloy of item 35, wherein the 7xxx alloy has a tensile yield strength of at least 60 ksi.

[0148] 37. The 7xxx aluminum alloy of item 36, wherein the 7xxx alloy has an elongation of at least 4%.

[0149] 38. The 7xxx alloy of item 17, wherein the 7xxx alloy has a stress corrosion cracking resistance of at least 26 ksi for 20 days per G47 as of Dec. 1, 2020.

[0150] 39. The 7xxx aluminum alloy of any of items 17-32, wherein the 7xxx alloy has an ultimate strength of at least 65 ksi.

[0151] 40. The 7xxx aluminum alloy of any of items 17-32, wherein the 7xxx alloy has a tensile yield strength of at least 60 ksi.

[0152] 41. The 7xxx aluminum alloy system of any of items 17-32, wherein the 7xxx alloy has an elongation of at least 4%.

[0153] 42. A composition of matter, comprising an aluminum, zinc and magnesium alloy system having a post weld ductility of at least 3% elongation.

[0154] 43. The composition of matter of item 42, further having a stress corrosion cracking resistance of at least 26 ksi for 20 days per G47.

[0155] 44. The composition of matter of item 43, further having an ultimate strength of at least 65 ksi.

[0156] 45. The composition of matter of item 44, further having a tensile yield strength of at least 60 ksi.

[0157] 46. The composition of matter of item 45 further having an elongation of at least 4%.

[0158] 47. The composition of matter of item 42, further having an ultimate strength of at least 65 ksi.

[0159] 48. The composition of matter of item 42, further having a tensile yield strength of at least 60 ksi.

[0160] 49. The composition of matter of item 42, further having an elongation of at least 4%.

[0161] 50. The composition of matter of item 42, including less than 0.3 wt.% copper.

[0162] 51. The composition of matter of item 42, including less than 0.1 wt.% copper.

[0163] 52. The composition of matter of item 42 free of copper.

[0164] Each of the following terms: “includes”, “including”, “has”, “having”, “comprises”, and “comprising”, and, their linguistic / grammatical variants, derivatives, or/and conjugates, as used herein, means “including, but not limited to”, and is to be taken as specifying the stated component(s), feature(s), characteristic(s), parameter(s), integer(s), or step(s), and does not preclude addition of one or more additional component(s), feature(s), characteristic(s), parameter(s), integer(s), step(s), or groups thereof. Each of these terms is considered equivalent in meaning to the phrase “consisting essentially of”. Each of the phrases “consisting of” and “consists of”, as used herein, means “including and limited to”. The phrase “consisting essentially of” means that the stated entity or item (system, system unit, system sub-unit device, assembly, sub-assembly, mechanism, structure, component element or, peripheral equipment utility, accessory, or material, method or process, step or procedure, sub-step or sub-procedure), which is an entirety or part of an exemplary embodiment of the disclosed invention, or/and which is used for implementing an exemplary embodiment of the disclosed invention, may include at least one additional feature or characteristic being a system, unit system, sub-unit device, assembly, sub-assembly, mechanism, structure, component or element or, peripheral equipment utility, accessory, or material, step or procedure, sub-step or sub-procedure, but only if each such additional feature or characteristic does not materially alter the basic novel and inventive characteristics or special technical features, of the claimed item.

[0165] Terms of approximation, such as the terms about, substantially, approximately, etc., as used herein, refers to ± 10 % of the stated numerical value.

[0166] The foregoing has been presented for purposes of illustration and description. It is not intended to be exhaustive or to limit the embodiments to the precise form disclosed. Obvious modifications and variations are possible in light of the above teachings. All such modifications and variations are within the scope of the appended claims when interpreted in accordance with the breadth to which they are fairly, legally and equitably entitled.