US2005072497A1PendingUtilityA1
Al-Zn-Mg-Cu alloys and products with high mechanical characteristics and structural members suitable for aeronautical construction made thereof
Priority: Apr 5, 2002Filed: Apr 4, 2003Published: Apr 7, 2005
Est. expiryApr 5, 2022(expired)· nominal 20-yr term from priority
C22F 1/053C22C 21/10
49
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Claims
Abstract
The present invention further relates to 7xxx alloys and products produced therewith that can be flat rolled, extruded or forged, as well as associated methods. Al—Zn—Mg—Cu alloys of the present invention preferably comprise (in mass percentage): a) Zn 8.3−14.0 Cu 0.3−2.0 Mg 0.5−4.5 Zr 0.03−0.15 Fe+Si<0.25 b) at least one element selected from the group consisting of Sc, Hf, La, Ti, Ce, Nd, Eu, Gd, Th, Dy, Ho, Er, Y and Yb, where the content of each of the elements, if selected, is between 0.02 and 0.7%, c) remainder aluminum and inevitable impurities. The present invention further is directed to products wherein Mg/Cu>2.4 and (7.9−0.4 Zn)>(Cu+Mg)>(6.4−0.4 Zn). The disclosed products can be used for example, as structural members in aeronautical construction, especially as stiffeners capable for use in fuselages of civilian and other aircrafts as well as in related applications.
Claims
exact text as granted — not AI-modified1 . An Al—Zn—Mg—Cu alloy, comprising (in mass percentage):
a)
Zn
8.3-14.0
Cu
0.3-2.0
Mg
0.5-4.5
Zr
0.03-0.15
Fe + Si
<0.25
b) at least one element selected from the group consisting of Sc, Hf, La, Ti, Ce, Nd, Eu, Gd, Th, Dy, Ho, Er, Y and Yb, the content of each of said elements, if selected, being between 0.02 and 0.7%,
c) remainder aluminum and inevitable impurities, and
wherein
Mg/Cu>2.4 and
(7.9−0.4 Zn)>(Cu+Mg)>(6.4−0.4 Zn).
2 . An alloy according to claim 1 , wherein Mg/Cu>2.8.
3 . An alloy according to claim 1 , wherein Mg/Cu>3.5.
4 . An alloy according to claim 1 , wherein Mg/Cu>4.0.
5 . An alloy according to claim 1 , wherein the maximum content of the elements Sc, Hf, La, Ti, Ce, Nd, Eu, Gd, Th, Dy, Ho, Er, Y and Yb does not exceed 1.5% in total.
6 . An alloy according to claim 1 , comprising only Ti from said group consisting of Sc, Hf, La, Ti, Ce, Nd, Eu, Gd, Tb, Dy, Ho, Er, Y and Yb.
7 . An Al—Zn—Mg—Cu alloy, comprising (in mass percentage):
a)
Zn
9.5-14.0
Cu
0.3-2.0
Mg
0.5-4.5
Fe + Si
<0.25
b) at least one element selected from the group consisting of Zr Sc, Hf, La, Ti, Ce, Nd, Eu, Gd, Th, Dy, Ho, Er, Y and Yb, the content of each of said elements, if selected, being between 0.02 and 0.7%,
c) remainder aluminum and inevitable impurities, and
wherein
Mg/Cu>2.4 and
(7.9−0.4 Zn)>(Cu+Mg)>(6.4−0.4 Zn).
8 . An alloy according to claim 7 , wherein the maximum content of the elements Zr, Sc, Hf, La, Ti, Ce, Nd, Eu, Gd, Th, Dy, Ho, Er, Y and Yb does not exceed 1.5% in total.
9 . An alloy according to claim 1 , wherein Zn>9.0%.
10 . An alloy according to claim 9 , wherein Zn>9.5%.
11 . An alloy according to claim 9 , wherein zinc is between 9.0% and 11.0%.
12 . An alloy according to claim 1 , wherein Cu>0.6%.
13 . An alloy according to claim 7 , wherein Cu>0.6%.
14 . An alloy according to claim 12 , wherein Cu 0.6−1.2% and Mg 2.2-3.0%.
15 . An alloy according to claim 12 , wherein Cu 0.8−1.5% and Mg 2.2-3.0%.
16 . An alloy according to claim 1 , wherein Mg 0.5−3.6%.
17 . An alloy according to claim 7 , wherein Mg 0.5−3.6%.
18 . An alloy according to claim 7 , wherein Mg/Cu>2.8.
19 . An alloy according to claim 7 , wherein Mg/Cu>3.5.
20 . An alloy according to claim 7 , wherein Mg/Cu>4.0.
21 . A rolled, forged or extruded material comprising an alloy according to claim 18 .
22 . An alloy according to claim 1 , wherein
Mg>1.95+0.5 (Cu−2.3)+0.16 (Zn−6)+1.9 (Si−0.04).
23 . An alloy according to claim 7 , wherein
Mg>1.95+0.5 (Cu−2.3)+0.16 (Zn−6)+1.9 (Si−0.04).
24 . An alloy according to claim 1 , wherein the maximum mass percentage of the following elements is not exceeded:
Cr 0.40 Mn 0.60 Sc 0.50
Zr 0.15 Hf 0.60 Ti 0.15
Ce 0.35 Nd 0.35 La Eu 0.35
Gd 0.35 Tb 0.35 Dy 0.40 Ho 0.40 Er 0.40 Yb 0.40 and Y 0.20.
25 . An alloy according to claim 7 , wherein the maximum mass percentage of the following elements is not exceeded:
Cr 0.40 Mn 0.60 Sc 0.50
Zr 0.15 Hf 0.60 Ti 0.15
Ce 0.35 Nd 0.35 La Eu 0.35
Gd 0.35 Tb 0.35 Dy 0.40 Ho 0.40 Er 0.40 Yb 0.40 and Y 0.20.
26 . An alloy according to claim 1 , further comprising at least one element selected from the group consisting of Ag, Sn, Cd, Ge and In, the content of each of said at least one element, if selected, being present in an amount of between 0.02% and 0.15%.
27 . An alloy according to claim 7 , further comprising at least one element selected from the group consisting of Ag, Sn, Cd, Ge and In, the content of each of said at least one element, if selected, being present in an amount of between 0.02% and 0.15%.
28 . An extruded product prepared from an alloy according to claim 1 , wherein said product exhibits in temper T6511, measured on test pieces cut from a plane zone of the profile,
a) a bending angle, determined at 130° C. by means of a three point bending test according to DIN 50 111 (section 3.1) on a specimen of 1.6 mm thickness and expressed as the mean value computed from several individual measurements performed on specimens cut from different locations over the length of the profile, of at least 34°, and b) a tensile yield strength (TYS) of at least 720 MPa.
29 . An extruded product prepared from an alloy according to claim 7 , wherein said product exhibits in temper T6511, measured on test pieces cut from a plane zone of the profile,
a) a bending angle, determined at 130° C. by means of a three point bending test according to DIN 50 111 (section 3.1) on a specimen of 1.6 mm thickness and expressed as the mean value computed from several individual measurements performed on specimens cut from different locations over the length of the profile, of at least 34°, and b) a tensile yield strength (TYS) of at least 720 MPa.
30 . An extruded product of claim 28 having a bending angle of at least 35° and a TYS of at least 750 MPa.
31 . An extruded product of claim 29 having a bending angle of at least 35° and a TYS of at least 750 MPa.
32 . An extruded product according claim 28 , wherein said product exhibits in temper T76511, measured on test pieces cut from a plane zone of the profile,
a) a bending angle, determined at 130° C. by means of a three point bending test according to DIN 50 111 (section 3.1) on a specimen of 1.6 mm thickness and expressed as the mean value computed from several individual measurements performed on specimens cut from different locations over the length of the profile, of at least 37°, and b) an ultimate tensile strength (UTS) of at least 670 MPa.
33 . An extruded product according claim 29 , wherein said product exhibits in temper T76511, measured on test pieces cut from a plane zone of the profile,
a) a bending angle, determined at 130° C. by means of a three point bending test according to DIN 50 111 (section 3.1) on a specimen of 1.6 mm thickness and expressed as the mean value computed from several individual measurements performed on specimens cut from different locations over the length of the profile, of at least 37°, and b) an ultimate tensile strength (ITS) of at least 670 MPa.
34 . An extruded product according to claim 32 , having a stress corrosion resistance, determined by an EXCO test according to ASTM G34 in the T6511 temper on unmachined test pieces, of at least level EB.
35 . An extruded product according to claim 33 , having a stress corrosion resistance, determined by an EXCO test according to ASTM G34 in the T6511 temper on unmachined test pieces, of at least level EB.
36 . A structural aircraft member manufactured from an alloy according to claim 1 .
37 . A structural aircraft member manufactured from an alloy according to claim 7 .
38 . A structural aircraft member according to claim 36 , wherein said structural member comprises a fuselage stringer.
39 . A structural aircraft member according to claim 37 , wherein said structural member comprises a fuselage stringer.
40 . A structural aircraft member according to claim 36 , wherein said structural member comprises a seat track.
41 . A structural aircraft member according to claim 37 , wherein said structural member comprises a seat track.
42 . A structural member according to claim 40 , having a ultimate tensile strength in the T76511 temper in a zone of fixation of the seats of at least 670 MPa.
43 . A structural member according to claim 36 , having a ultimate tensile strength in the T76511 temper of at least 670 MPa.
44 . A structural member according to claim 41 , having a ultimate tensile strength in the T76511 temper in a zone of fixation of the seats of at least 670 MPa.
45 . A structural member according to claim 37 , having a ultimate tensile strength in the T76511 temper of at least 670 MPa.
46 . A structural member according to claim 40 , having an ultimate tensile strength of at least 680 MPa.
47 . A structural member according to claim 40 , having a tensile yield strength in the T76511 temper in a zone of fixation of the seats of at least 640 MPa.
48 . A structural member according to claim 41 , having a tensile yield strength in the T76511 temper in a zone of fixation of the seats of at least 640 MPa.
49 . A structural member according to claim 36 , having a tensile yield strength in the T76511 temper of at least 640 MPa.
50 . A structural member according to claim 37 , having a tensile yield strength in the T76511 temper of at least 640 MPa.
51 . A structural member according to claim 40 , having a tensile yield strength of at least 660 MPa.
52 . A structural member according to claim 41 , having a tensile yield strength of at least 660 MPa.
53 . A structural member according to claim 36 , having a tensile yield strength of at least 660 MPa.
54 . A structural member according to claim 37 , having a tensile yield strength of at least 660 MPa.
55 . A structural aircraft member according to claim 36 , wherein said structural member comprises a floor beam.
56 . A structural aircraft member according to claim 37 , wherein said structural member comprises a floor beam.
57 . An aircraft comprising a fuselage assembled from a plurality of stringers and a plurality of sheets, wherein at least part of said stringers comprise structural members according to claim 36 .
58 . An aircraft comprising a fuselage assembled from a plurality of stringers and a plurality of sheets, wherein at least part of said stringers comprise structural members according to claim 37 .
59 . An extruded product comprising a bending angle of at least 34° in the T6511 temper determined at 130° C. by a 3 point bending test according to DIN 50111 on a sample thereof 1.6 mm in thickness cut from a plane area of said product, and said product further comprising a TYS of at least 720 MPa.
60 . An extruded product comprising a bending angle of at least 36° in the T76511 temper determined at 130° C. by a 3 point bending test according to DIN 50111 on a sample thereof 1.6 mm in thickness cut from a plane area of said product, and said product further comprising a TYS of at least 660 MPa.
61 . An extruded product according to claim 60 , further comprising a corrosion resistance rating of at least EB (EXCO test according to ASTM G34).
62 . A floor beam of an aircraft comprising an alloy according to claim 1 .
63 . A floor beam of an aircraft comprising an alloy according to claim 7 .
64 . A seat track of an aircraft comprising an alloy according to claim 1 .
65 . A seat track of an aircraft comprising an alloy according to claim 7 .
66 . A rolled product comprising an alloy according to claim 1 .
67 . A rolled product comprising an alloy according to claim 7 .
68 . An extruded product comprising an alloy according to claim 1 .
69 . An extruded product comprising an alloy according to claim 7 .
70 . A forged product comprising an alloy according to claim 1 .
71 . A forged product comprising an alloy according to claim 7 .
72 . A 7xxx alloy wherein after being subjected to homogenization and scalping and being extruded at 400° C. at a speed of below 0.50 m/min, extrusion forces required to obtain extrusion profiles of said alloy decrease as the content of magnesium is increased in said alloy.
73 . A 7xxx alloy comprising up to 0.15% Sc, up to 12% Zn, and a Mg/Cu ratio of >2.4, said alloy possessing an R p0,2(L) of from 680−700 MPa and R M(L) of from 686−700 MPa.
74 . A fuselage structure comprising at least one stringer that is not 2024, wherein if prepared with a stringer pitch of 200 mm and a stiffening ratio of 0.25, said structure exhibits an SIF that is reduced up to 5% as compared to a fuselage structure with 2024 T3 alloy stringers.
75 . A fuselage structure comprising at least one stringer that is not 2024, wherein if prepared with a stringer pitch of 200 mm and a a stiffening ratio of 0.25, said structure exhibits an SIF that is reduced up to 15% as compared to a fuselage structure with 2024 plastic domain stringers.
76 . A stringer that is not 2024, wherein if utilized in a fuselage with a stringer pitch of 200 mm and a a stiffening ratio of 0.25, said structure exhibits an SIF that is reduced up to 5% as compared to a fuselage structure with 2024 T3 alloy stringers.
77 . A stringer that is not 2024, wherein if utilized in a fuselage with a stringer pitch of 200 mm and a stiffening ratio of 0.25, said structure exhibits an SIF that is reduced up to 15% as compared to a fuselage structure with 2024 plastic domain stringers.
78 . A stringer geometry selected from one or more of the following:
Z1
Z2
Z3
Z4
Z5
Z6
Z7
Z8
Free flange width [mm]
12.7
12.7
12.7
12.7
12.7
12.7
12.7
12.7
Fastened flange width [mm]
25.4
25.4
25.4
25.4
25.4
25.4
25.4
25.4
Height [mm]
38.1
38.1
38.1
38.1
38.1
38.1
38.1
38.1
Free flange thickness [mm]
1.0
1.5
1.5
2.0
1.0
1.5
1.5
1.5
Fastened flange thickness [mm]
1.0
1.0
1.5
1.5
1.0
1.0
1.0
1.5
Web thickness [mm]
1.0
1.0
1.0
1.0
1.5
1.5
1.5
1.5
Section [mm 2 ]
76
83
95
102
95
102
102
114
Equivalent thickness [mm]
1.0
1.1
1.3
1.3
1.3
1.3
1.3
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