US2002150498A1PendingUtilityA1
Aluminum alloy having superior strength-toughness combinations in thick gauges
Priority: Jan 31, 2001Filed: Jan 31, 2001Published: Oct 17, 2002
Est. expiryJan 31, 2021(expired)· nominal 20-yr term from priority
C22C 21/10C22F 1/053
38
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Claims
Abstract
A 7XXX series aluminum alloy having reduced quench sensitivity suitable for use in aerospace structural components, such as integral wing spars, ribs, extrusions and forgings comprises, in weight %: 6 to 10 Zn, 1.3 to 1.9 Mg, 1.4 to 2.2 Cu, wherein Mg≦Cu+0.3, one or more of 0 to 0.4 Zr, up to 0.4 Sc, up to 0.2 Hf, up to 0.4 Cr, up to 1.0 Mn and the balance Al plus incidental additions including Si, Fe, Ti and the like plus impurities. By controlling the Mg content to 1.3 to 1.7 wt. %, limiting Mg≦Cu+0.3 and 6.5≦Zn≦8.5, the alloy provides significantly improved combined strength and fracture toughness in heavy gauges. For example, in a six-inch thick plate there is provided a combination of about 75 ksi quarter-plane tensile yield strength (L) with a fracture toughness (L−T) of about 33 ksi{square root}in which progresses by artificial aging/tempering to a combined strength and fracture toughness of about 67 ksi tensile yield strength (L) and a fracture toughness (L−T) of about 40 ksi{square root}in. The alloy product possesses equally attractive combinations of strength and fracture toughness when intentionally quenched slowly following solution heat treatment so as to lessen dimensional distortion, particularly in shapes of varying cross section.
Claims
exact text as granted — not AI-modifiedWe claim:
1 . A 7XXX series aluminum alloy possessing superior strength and fracture toughness properties consisting essentially of, in % by weight, about:
6 to 10 Zn, 1.3 to 1.9 Mg, 1.4 to 2.2 Cu, 0 to 0.4 Zr 0 to 0.4 Sc 0 to 0.2 Hf 0 to 0.4 Cr 0 to 1.0 Mn, and the balance being Al and incidental additions and impurities.
2 . The aluminum alloy of claim 1 in gauges greater than 1.5 inches.
3 . The aluminum alloy of claim 1 in gauges between about 3 to about 8 inches.
4 . The aluminum alloy of claim 1 in gauges between about 6 to about 12 inches.
5 . The aluminum alloy of claim 1 in gauges of about 12 inches or greater.
6 . The aluminum alloy of claim 1 wherein:
Mg≦1.7.
7 . The aluminum alloy of claim 1 wherein:
Mg≦Cu+0.3.
8 . The aluminum alloy of claim 1 wherein:
Mg≦1.7, and Mg≦Cu+0.3.
9 . The aluminum alloy of claim 1 wherein:
Mg≦1.7,
Mg≦Cu+0.3, and
6≦Zn≦8.5
10 . The aluminum alloy of claim 1 wherein:
Mg≦Cu.
11 . A 7XXX series aluminum alloy possessing superior strength and fracture toughness properties consisting essentially of, in % by weight, about:
6 to 8.5 Zn, 1.3 to 1.8 Mg, 1.4to 2.0 Cu, up to about 0.4 Zr,
one or more elements selected from the group consisting of:
up to about 0.4 Sc,
up to about 0.2 Hf.
up to about 0.4 Cr,
up to about 1.0 Mn, and
the balance being Al and incidental additions and impurities.
12 . The aluminum alloy of claim 11 in gauges greater than 1.5 inches.
13 . The aluminum alloy of claim 11 in gauges between about 3 to about 8 inches.
14 . The aluminum alloy of claim 11 in gauges between about 6 to about 12 inches.
15 . The aluminum alloy of claim 11 in gauges of about 12 inches or more.
16 . A 7XXX series aluminum alloy possessing superior strength and fracture toughness combination properties consisting essentially of, in % by weight, about:
6.5 to 8.5 Zn, 1.3 to 1.7 Mg, 1.4 to 2.0 Cu, 0 to 0.4 Zr, 0 to 0.4 Sc, 0 to 0.2 Hf, 0 to 0.4 Cr, 0 to 1 Mn, and
the balance being Al and incidental additions and impurities.
17 . The aluminum alloy of claim 16 in gauges greater than 1.5 inches.
18 . The aluminum alloy of claim 16 in gauges between about 2 inches to about 12 inches.
19 . The aluminum alloy of claim 16 in gauges of about 6 inches to about 12 inches or more.
20 . The aluminum alloy of claim 16 having a quarter-plane tensile yield strength (TYS) in the longitudinal direction (L) greater than about 69 ksi and a fracture toughness (K Ic ) in the L/−T direction greater than about 30 to 34 ksi{square root}in wherein said alloy has been processed in a thickness of about 6 inches and in a solution heat treated, quenched, stretched and artificially aged condition.
21 . An aluminum alloy structural component made from plate, extrusion or forging for a commercial jet aircraft, said structural component made from a 7XXX series aluminum alloy consisting essentially of, in % by weight, about:
6 to 10 Zn, 1.3 to 1.9 Mg, 1.4 to 2.2 Cu, 0 to 0.4 Zr 0 to 0.4 Sc 0 to 0.2 Hf 0 to 0.4Cr 0 to 1.0 Mn, and
the balance being Al and incidental additions and impurities.
22 . The aluminum alloy structural component of claim 21 wherein:
Mg≦1.7.
23 . The aluminum alloy structural component of claim 21 wherein:
Mg≦Cu+0.3.
24 . The aluminum alloy structural component of claim 21 wherein:
Mg≦1.7, and Mg≦Cu+0.3.
25 . The aluminum alloy structural component of claim 21 wherein:
Mg≦1.7,
Mg≦Cu+0.3, and
6≦Zn≦8.5.
26 . The aluminum alloy structural component of claim 21 wherein:
Cu≧Mg.
27 . The aluminum structural component of claim 21 having a thickness of between about 4 to about 8 inches or more.
28 . An aluminum alloy structural component made from plate, extrusion or forging for a commercial jet aircraft, said structural component made from a 7XXX series aluminum alloy consisting essentially of, in % by weight, about:
6 to 8.5 Zn, 1.3 to 1.8 Mg, 1.4 to 2.0 Cu, up to about 0.4 Zr up to about 0.4 Sc up to about 0.2 Hf up to about 0.4 Cr up to about 1.0 Mn, and the balance being Al and incidental additions and impurities.
29 . The aluminum structural component of claim 28 having a thickness of greater than about 1.5 inches.
30 . The aluminum structural component of claim 28 having a thickness of greater than 6 inches.
31 . The aluminum structural component of claim 28 in the form of an integral or built-up structural component for use in an aircraft.
32 . The aluminum structural component of claim 28 in the form of an integral spar for use in an aircraft wing structure.
33 . The aluminum structural component of claim 28 having a quarter-plane tensile yield strength, TYS (L), greater than about 69 ksi and a fracture toughness, K Ic , (L−T), greater than about 30 to 34 ksi{square root}in wherein said alloy has been processed in a thickness of about 6 inches and in a solution heat treated, quenched, stretched and artificially aged condition.
34 . An aluminum alloy structural component made from plate, extrusion or forging for a commercial jet aircraft, said structural component made from a 7XXX series aluminum alloy consisting essentially of, in % by weight, about:
6 to 8.5 Zn, 1.3to 1.7 Mg, 1.4 to 2.0 Cu, up to about 0.4 Zr up to about 0.4 Sc up to about 0.2 Hf up to about 0.4 Cr up to about 1.0 Mn, and the balance being Al and incidental additions and impurities.
35 . The aluminum structural component of claim 34 having a thickness of greater than about 1.5 inches.
36 . The aluminum structural component of claim 34 having a thickness of greater than 6 inches.
37 . An aluminum alloy structural component for a commercial jet aircraft, said structural component made from a 7XXX series aluminum alloy consisting essentially of, in % by weight, about:
6 to 8.5 Zn, 1.3 to 1.8 Mg, 1.4 to 2.0 Cu,
wherein Cu≧Mg, and (Cu+Mg+Zn)<12.5,
up to about 0.4 Zr,
one or more elements selected from the group consisting of:
up to about 0.4 Sc,
up to about 0.2 Hf,
up to about 0.4 Cr,
up to about 1.0 Mn, and
the balance being Al and incidental additions and impurities.
38 . The aluminum structural component of claim 37 in the form of an integral spar for use in an aircraft wing structure.
39 . The aluminum structural component of claim 37 in the form of an integral wing panel and stringer for use in an aircraft wing structure.
40 . The aluminum structural component of claim 37 in the form of a rib for use in an aircraft wing structure.
41 . The aluminum alloy structural component of claim 37 in the form of a stepped extrusion or extruded spar for use in an aircraft structure.
42 . The aluminum alloy structural component of claim 37 in the form of a forged spar for use in an aircraft wing structure.
43 . The aluminum structural component of claim 37 wherein the component is a wrought product having both thick and thin sections and is intentionally quenched slowly following a solution heat treatment to minimize quench distortion.
44 . The aluminum structural component of claim 37 having a quarter-plane tensile yield strength, TYS (L), greater than about 69 ksi and a fracture toughness, K Ic (L−T), greater than about 30 to 34 ksi{square root}in wherein said alloy has been processed in a solution heat treated, quenched, stretched and artificially aged condition.
45 . The aluminum structural component of claim 37 wherein the alloy contains Mg≦Cu+0.3.
46 . The aluminum structural component of claim 37 wherein the alloy contains Cu≧Mg.
47 . An aluminum alloy structural component for a commercial jet aircraft, said structural component made from a 7XXX series aluminum alloy consisting essentially of, in % by weight, about:
6.5 to 8.5 Zn, 1.3 to 1.7 Mg, 1.4 to 2.0 Cu, 0 to 0.4 Zr, 0 to about 0.38 Sc, 0 to about 0.20 Hf, 0 to about 0.37 Cr, 0 to about 1.0 Mn, and
the balance being Al and incidental additions and impurities.
48 . The aluminum structural component of claim 47 having a thickness of greater than about 1.5 inches.
49 . The aluminum structural component of claim 47 having a thickness of between about 3 to about 8 inches or more.
50 . The aluminum structural component of claim 47 wherein the component is a wrought product and is intentionally quenched slowly following a solution heat treatment.
51 . The aluminum structural component of claim 47 in the form of an integral spar for use in an aircraft wing structure.
52 . The aluminum structural component of claim 47 in the form of a rib for use in an aircraft wing structure.
53 . The aluminum structural component of claim 47 in the form of a forged product for use in an aircraft wing structure.
54 . The aluminum structural component of claim 47 in the form of an extruded product for use in an aircraft wing structure.
55 . The aluminum structural component of claim 47 having a quarter-plane tensile yield strength, TYS (L), greater than about 69 ksi and a fracture toughness, K Ic , (L−T), greater than about 30 to 34 ksi{square root}in wherein said alloy has been processed in a solution heat treated, quenched, stretched and artificially aged condition.
56 . A mold plate made from an aluminum alloy consisting essentially of, in % by weight, about:
6 to 10 Zn, 1.3 to 1.9 Mg, 1.4 to 2.2 Cu, 0 to 0.4 Zr 0 to 0.4 Sc 0 to 0.2 Hf 0 to 0.4 Cr 0 to 1.0 Mn, and
the balance being Al and incidental additions and impurities.
57 . A process for making a structural component for a commercial jet aircraft comprising the steps of:
(a) providing a 7XXX series aluminum alloy consisting essentially of, in % by weight, about 6 to 10 Zn, 1.3 to 1.9 Mg, 1.4 to 2.2 Cu, wherein Mg≦Cu+0.3, 0 to about 0.4 Zr, 0 to about 0.4 Sc, 0 to about 0.2 Hf. 0 to about 0.4 Cr, 0 to about 1.0 Mn, and the balance being Al and incidental additions and impurities; (b) homogenizing and hot forming said alloy by one of rolling, extruding or forging to a desired workpiece form; (c) solution heat treating said hot formed workpiece at a temperature and time sufficient to place into solid solution all soluble constituents in the alloy; (d) quenching said solution heat treated workpiece by one of spray quenching or immersion quenching in water or other quenching media; (e) artificially aging said quenched workpiece to achieve a desired temper; and (f) machining said workpiece to provide a desired configuration of said structural component.
58 . The process of claim 57 including the step of stress relieving the workpiece after said quenching step (d) by one of stretching, compressing or cold working.
59 . The process of claim 57 wherein said quenched workpiece has a thickness of greater than about 1.5 inches.
60 . The process of claim 57 wherein said quenched workpiece has a thickness of greater than about 2 inches.
61 . The process of claim 57 wherein said quenched workpiece has a thickness of greater than about 3 inches.
62 . The process of claim 57 wherein the quenched workpiece has a thickness of greater than 6 inches, up to about 12 inches.
63 . The process of claim 57 wherein t he workpiece is intentionally quenched slowly following the solution heat treating step (c).
64 . The process of claim 57 wherein the provided 7XXX series aluminum alloy of step (a) consists essentially of:
6.5 to 8.5 Zn,
1.3 to 1.7 Mg,
1.4 to 2.0Cu,
wherein Mg≦1.7 and Mg≦Cu+0.3
0 to 0.4 Zr,
0 to about 0.38 Sc,
0 to about 0.20 Hf,
0 to about 0.37 Cr,
0 to about 1.0 Mn, and
the balance being Al and incidental additions and impurities.
65 . The process of claim 64 wherein said quenched workpiece has a thickness of greater than about 1.5 inches.
66 . The process of claim 64 wherein said quenched workpiece has a thickness of greater than about 2 inches.
67 . The process of claim 64 wherein said quenched workpiece has a thickness of greater than about 3 inches.
68 . The process of claim 64 wherein the quenched workpiece has a thickness of greater than 6 inches, up to about 12 inches.
69 . The process of claim 64 wherein the workpiece is intentionally quenched slowly following the solution heat treating step (c).
70 . The process of claim 57 wherein the structural component has a quarter-plane tensile yield strength, TYS (L), greater than about 69 ksi and a fracture toughness, K Ic (L−T), greater than about 30 to 34 ksi{square root}in.
71 . A process for making a mold plate comprising the steps of:
(a) providing a 7XXX series aluminum alloy consisting essentially of, in % by weight, about 6 to 10 Zn, 1.3 to 1.9 Mg, 1.4 to 2.2 Cu, wherein Mg≦Cu+0.3, 0 to about 0.4 Zr, 0 to about 0.4 Sc, 0 to about 0.2 Hf, 0 to about 0.4 Cr, 0 to about 1.0 Mn, and the balance being Al and incidental additions and impurities; (b) homogenizing and hot forming said alloy by one of rolling, extruding or forging to a desired workpiece form; (c) solution heat treating said hot formed workpiece at a temperature and time sufficient to place into solid solution all soluble constituents in the alloy; (d) quenching said solution heat treated workpiece by one of spray quenching or immersion quenching in water or other quenching media; (e) artificially aging said quenched workpiece to achieve a desired temper; and (f) machining said workpiece to provide a desired configuration of said structural component.
72 . The process of claim 71 wherein the workpiece is intentionally quenched slowly following the solution heat treating of step (c).Join the waitlist — get patent alerts
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