CA2485524A1 - Method for producing a high strength al-zn-mg-cu alloy - Google Patents
Method for producing a high strength al-zn-mg-cu alloy Download PDFInfo
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- CA2485524A1 CA2485524A1 CA002485524A CA2485524A CA2485524A1 CA 2485524 A1 CA2485524 A1 CA 2485524A1 CA 002485524 A CA002485524 A CA 002485524A CA 2485524 A CA2485524 A CA 2485524A CA 2485524 A1 CA2485524 A1 CA 2485524A1
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- 238000004519 manufacturing process Methods 0.000 title claims abstract 3
- 229910000881 Cu alloy Inorganic materials 0.000 title 1
- 238000010438 heat treatment Methods 0.000 claims abstract 17
- 238000000034 method Methods 0.000 claims abstract 16
- 229910045601 alloy Inorganic materials 0.000 claims abstract 7
- 239000000956 alloy Substances 0.000 claims abstract 7
- 229910017818 Cu—Mg Inorganic materials 0.000 claims abstract 6
- 230000032683 aging Effects 0.000 claims abstract 6
- 238000005266 casting Methods 0.000 claims abstract 6
- 238000005482 strain hardening Methods 0.000 claims abstract 4
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims abstract 3
- 229910052782 aluminium Inorganic materials 0.000 claims abstract 3
- 239000004411 aluminium Substances 0.000 claims abstract 3
- 230000006835 compression Effects 0.000 claims abstract 3
- 238000007906 compression Methods 0.000 claims abstract 3
- 239000000203 mixture Substances 0.000 claims abstract 3
- 238000010791 quenching Methods 0.000 claims abstract 3
- 230000000171 quenching effect Effects 0.000 claims abstract 3
- 230000007797 corrosion Effects 0.000 claims 3
- 238000005260 corrosion Methods 0.000 claims 3
- 238000004299 exfoliation Methods 0.000 claims 2
- 238000005096 rolling process Methods 0.000 claims 1
- 241000283014 Dama Species 0.000 abstract 1
- JNSGIVNNHKGGRU-JYRVWZFOSA-N diethoxyphosphinothioyl (2z)-2-(2-amino-1,3-thiazol-4-yl)-2-methoxyiminoacetate Chemical compound CCOP(=S)(OCC)OC(=O)C(=N/OC)\C1=CSC(N)=N1 JNSGIVNNHKGGRU-JYRVWZFOSA-N 0.000 abstract 1
Classifications
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C21/00—Alloys based on aluminium
- C22C21/10—Alloys based on aluminium with zinc as the next major constituent
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22F—CHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS AND NON-FERROUS ALLOYS
- C22F1/00—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
- C22F1/04—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon
- C22F1/053—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon of alloys with zinc as the next major constituent
Abstract
The present invention relates to a method for producing a high strength AI-Z n- Cu-Mg alloy with an improved fatigue crack growth resistance and a high dama ge tolerance, comprising the steps of casting an ingot with the following composition (in weight percent) Zn 5.5- 9.5, Cu 1.5 - 3.5, Mg 1.5 - 3.5, Mn < 0.25, Zr < 0.25, Cr < 0.10, Fe < 0.25, Si < 0.25, Ti < 0.10, Hf and/or V < 0.25, other elements each less than 0.05 and less than 0.15 in total, balanc e aluminium, homogenising and/or pre-heating the ingot after casting, hot working the ingot and optionally cold working into a worked product of more than 50 mm thickness, solution heat treating, quenching the heat treated product, and artificially aging the worked and heat-treated product, wherein the aging step comprises a first heat treatment at a temperature in a range of 105~C to 135~C for more than 2 hours and less than 8 hours and a second heat treatment at a higher temperature than 135~C but below 170~C for more than 5 hours and less than 15 hours. The product achieved by the method exhibits a compression yield strengh of at least 510 Mpa and an ST elongation at S/2 of at least 3.0 %. The invention concerns a weldable plate product of such high strength Al-Zn-Cu-Mg having a thickness of more than 50 mm and an aircraft structural member produced from such alloy.
Claims (23)
1. Method for producing a high strength Al-Zn-Cu-Mg alloy with a high damage tolerance and an improved corrosion resistance, comprising the steps of:
a) casting an ingot with the following composition (in weight percent):
Zn 5.5 to 9.5 Cu 1.5 to 3.5 Mg 1.5 to 3.5 Mn < 0.25 Zr < 0.25, preferably 0.06 to 0.16 Cr < 0.10 Fe < 0.25 Si < 0.25 Ti < 0.10 Hf and/or V < 0.25 other elements each less than 0.05 and less than 0.15 in total, balance aluminium, b) homogenising and/or pre-heating the ingot after casting, c) hot-working the ingot and optionally cold working into a worked product of more than 50 mm thickness, d) solution heat treating, e) quenching the solution heat treated product, and f) artificially ageing the worked and heat-treated product, wherein the ageing step comprises a first heat treatment at a temperature in a range of 105°C
to 135°C for more than 2 hours and less than 8 hours and a second heat treatment at a higher temperature than 135°C but below 170°C for more than 5 hours and less than 15 hours to achieve a product with a compression yield strength in L-direction at S/4 of at least 475 MPa, an ultimate tensile strength of at least 510 MPa and an ST elongation at S/2 of at least 3.0%.
a) casting an ingot with the following composition (in weight percent):
Zn 5.5 to 9.5 Cu 1.5 to 3.5 Mg 1.5 to 3.5 Mn < 0.25 Zr < 0.25, preferably 0.06 to 0.16 Cr < 0.10 Fe < 0.25 Si < 0.25 Ti < 0.10 Hf and/or V < 0.25 other elements each less than 0.05 and less than 0.15 in total, balance aluminium, b) homogenising and/or pre-heating the ingot after casting, c) hot-working the ingot and optionally cold working into a worked product of more than 50 mm thickness, d) solution heat treating, e) quenching the solution heat treated product, and f) artificially ageing the worked and heat-treated product, wherein the ageing step comprises a first heat treatment at a temperature in a range of 105°C
to 135°C for more than 2 hours and less than 8 hours and a second heat treatment at a higher temperature than 135°C but below 170°C for more than 5 hours and less than 15 hours to achieve a product with a compression yield strength in L-direction at S/4 of at least 475 MPa, an ultimate tensile strength of at least 510 MPa and an ST elongation at S/2 of at least 3.0%.
2. Method according to claim 1, wherein the ageing step consists of two heat treatments, the first heat treatment is performed for 2 to 5 hours at temperatures in the range of 105°C to 135°C, and the second heat treatment is performed for to 15 hours at temperatures in the range of 155°C to 169°C.
3. Method according to claim 1 or 2, wherein the first heat treatment is performed at temperatures in the range 115°C to 125°C.
4. Method according to any one of claims 1 to 3, wherein the first heat treatment is performed for 2 to 5 hours at about 120°C.
5. Method according to any one of claims 1 to 4, wherein the second heat treatment is performed at temperatures in the range 161 °C to 167°C.
6. Method according to any one of claim 1 to 5, wherein the second heat treatment is performed for about 13 hours.
7. Method according to any one of claims 1 or 6, wherein the improved corrosion resistance has exfoliation properties ("EXCO") of EB or better according to ASTM G34.
8. Method according to any one of the preceding claims, wherein in the amount of Mg is in a range of 1.5 to 2.5, preferably in a range of 1.6 to 2.3, and more preferably in a range of 1.90 to 2.10.
9. Method according to any of the preceding claims, wherein the amount of Cu is in a range of 1.5 to 2.5, preferably in a range of 1.6 to 2.3, and more preferably in a range of 1.85 to 2.10.
10. Method according to any one of the preceding claims, wherein the amount of Mg depends on the amount of Zn as follows: [Mg] is in between 2.4-0.1 [Zn] and 1.5+0.1 [Zn].
11. Method according to any one of the preceding claims, wherein the amount of Zn is in a range of 5.9 to 6.2, or in a range of 6.8 to 7.1,or in a range of 7.8 to 8.1.
12. Method according to any one of the preceding claims, wherein said high strength AI-Zn-Cu-Mg alloy is selected from the group of AA7010, AA7x50, AA7040, AA7020, AA7x75, AA7349, AA7x55, AA7x85.
13. Method according to any one of the preceding claims, wherein after homogenising and/or pre-heating the ingot after casting, hot working the ingot and optionally cold working into a worked product of 60 to 220 mm, and whereby the working is preferably carried out by means of rolling.
14. Method according to claim 13, wherein after homogenising and/or pre-heating the ingot after casting, hot working the ingot and optionally cold working into a worked product of 60 to 160 mm, and more preferably of 110 to 160 mm.
15. A plate product of high strength AI-Zn-Cu-Mg alloy produced in accordance with a method as defined in any one of the claims 1 to 14 and having a thickness of more than 50 mm, and preferably more than 60 mm.
16. A plate product according to claim 15, wherein said plate product is a structural member of an aircraft.
17. A plate product according to claim 15, wherein said plate product is a bar or a spar of a wing of an aircraft.
18. A plate product according to claim 15, wherein said plate product is an upper-wing member of an aircraft.
19. An aircraft structural member produced from a high strength AI-Zn-Cu-Mg alloy produced in accordance with a method as defined in one of the claims 1 to 14.
20. An aircraft structural member having a thickness of at least 50 mm, and preferably in a range of 50 to 160 mm, manufactured from a rolled product made of an alloy with a composition, consisting of, in % by weight:
Zn 5.5 to 9.5 Cu 1.5 to 3.5 Mg 1.5 to 3.5 Mn < 0.25 Zr < 0.25, preferably 0.06 to 0.16 Cr < 0.10 Fe < 0.25 Si < 0.25 Ti < 0.10 Hf and/or V < 0.25 other elements each less than 0.05 and less than 0.15 in total, balance aluminium, and treated by solution heat treating, quenching, and ageing practice consisting of a first heat treatment at a temperature in a range of 105°C to 135°C for more than 2 hours and less than 8 hours and a second heat treatment at a higher temperature than 135°C but below 170°C for more than 5 hours and less than 15 hours, the product having a compression yield strength in L-direction at S/4 of at least 475 MPa, an ultimate tensile strength of at least 510 MPa and an ST
elongation at S/2 of at least 3.0%.
Zn 5.5 to 9.5 Cu 1.5 to 3.5 Mg 1.5 to 3.5 Mn < 0.25 Zr < 0.25, preferably 0.06 to 0.16 Cr < 0.10 Fe < 0.25 Si < 0.25 Ti < 0.10 Hf and/or V < 0.25 other elements each less than 0.05 and less than 0.15 in total, balance aluminium, and treated by solution heat treating, quenching, and ageing practice consisting of a first heat treatment at a temperature in a range of 105°C to 135°C for more than 2 hours and less than 8 hours and a second heat treatment at a higher temperature than 135°C but below 170°C for more than 5 hours and less than 15 hours, the product having a compression yield strength in L-direction at S/4 of at least 475 MPa, an ultimate tensile strength of at least 510 MPa and an ST
elongation at S/2 of at least 3.0%.
21. An aircraft structural member according to claim 20, wherein the improved corrosion resistance has exfoliation properties ("EXCO") of EB or better according to ASTM G34.
22. An aircraft structural member according to claim 20, forming a part of an aircraft upper wing.
23. An aircraft structural member according to claim 20, forming a spar or bar of an aircraft wing.
Applications Claiming Priority (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| EP02077549.0 | 2002-06-24 | ||
| EP02077549 | 2002-06-24 | ||
| PCT/EP2003/006208 WO2004001080A1 (en) | 2002-06-24 | 2003-06-11 | METHOD FOR PRODUCING A HIGH STRENGTH Al-Zn-Mg-Cu ALLOY |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CA2485524A1 true CA2485524A1 (en) | 2003-12-31 |
| CA2485524C CA2485524C (en) | 2010-11-16 |
Family
ID=29719740
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CA2485524A Expired - Lifetime CA2485524C (en) | 2002-06-24 | 2003-06-11 | Method for producing a high strength al-zn-mg-cu alloy |
Country Status (9)
| Country | Link |
|---|---|
| US (1) | US20050006010A1 (en) |
| CN (1) | CN100451149C (en) |
| AU (1) | AU2003277929A1 (en) |
| BR (1) | BR0312101B1 (en) |
| CA (1) | CA2485524C (en) |
| DE (2) | DE10392805B4 (en) |
| FR (1) | FR2841264B1 (en) |
| GB (1) | GB2402943B (en) |
| WO (1) | WO2004001080A1 (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2011091645A1 (en) * | 2010-01-29 | 2011-08-04 | 北京有色金属研究总院 | Aluminum alloy product adapted to produce structure piece and producing method thereof |
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| US20050034794A1 (en) * | 2003-04-10 | 2005-02-17 | Rinze Benedictus | High strength Al-Zn alloy and method for producing such an alloy product |
| DE112004000603B4 (en) * | 2003-04-10 | 2022-11-17 | Novelis Koblenz Gmbh | Al-Zn-Mg-Cu alloy |
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| EP1544315B1 (en) * | 2003-12-16 | 2012-08-22 | Constellium France | Wrought product in the form of a rolled plate and structural part for aircraft in Al-Zn-Cu-Mg alloy |
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| US5863359A (en) * | 1995-06-09 | 1999-01-26 | Aluminum Company Of America | Aluminum alloy products suited for commercial jet aircraft wing members |
| ATE245207T1 (en) * | 1996-09-11 | 2003-08-15 | Aluminum Co Of America | ALUMINUM ALLOY FOR COMMERCIAL AIRCRAFT WINGS |
| US6315842B1 (en) * | 1997-07-21 | 2001-11-13 | Pechiney Rhenalu | Thick alznmgcu alloy products with improved properties |
| US7135077B2 (en) | 2000-05-24 | 2006-11-14 | Pechiney Rhenalu | Thick products made of heat-treatable aluminum alloy with improved toughness and process for manufacturing these products |
| CN1489637A (en) * | 2000-12-21 | 2004-04-14 | �Ƹ��� | Aluminum alloy products and artificial aging method |
| FR2820438B1 (en) * | 2001-02-07 | 2003-03-07 | Pechiney Rhenalu | PROCESS FOR THE MANUFACTURE OF A CORROSIVE PRODUCT WITH HIGH RESISTANCE IN ALZNMAGCU ALLOY |
| US6569271B2 (en) * | 2001-02-28 | 2003-05-27 | Pechiney Rolled Products, Llc. | Aluminum alloys and methods of making the same |
| EP1373591A2 (en) * | 2001-03-20 | 2004-01-02 | Alcoa Inc. | Method for aging 7000 series aluminium |
-
2003
- 2003-06-09 US US10/456,183 patent/US20050006010A1/en not_active Abandoned
- 2003-06-11 CN CNB038118270A patent/CN100451149C/en not_active Expired - Lifetime
- 2003-06-11 GB GB0423402A patent/GB2402943B/en not_active Expired - Lifetime
- 2003-06-11 BR BRPI0312101-1A patent/BR0312101B1/en not_active IP Right Cessation
- 2003-06-11 CA CA2485524A patent/CA2485524C/en not_active Expired - Lifetime
- 2003-06-11 DE DE10392805.7A patent/DE10392805B4/en not_active Expired - Lifetime
- 2003-06-11 AU AU2003277929A patent/AU2003277929A1/en not_active Abandoned
- 2003-06-11 DE DE10392805T patent/DE10392805T5/en active Granted
- 2003-06-11 WO PCT/EP2003/006208 patent/WO2004001080A1/en not_active Application Discontinuation
- 2003-06-23 FR FR0307560A patent/FR2841264B1/en not_active Expired - Lifetime
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2011091645A1 (en) * | 2010-01-29 | 2011-08-04 | 北京有色金属研究总院 | Aluminum alloy product adapted to produce structure piece and producing method thereof |
| US9993865B2 (en) | 2010-01-29 | 2018-06-12 | Grimat Engineering Institute Co., Ltd. | Aluminum alloy products for manufacturing structural components and method of producing the same |
Also Published As
| Publication number | Publication date |
|---|---|
| WO2004001080A1 (en) | 2003-12-31 |
| AU2003277929A1 (en) | 2004-01-06 |
| FR2841264A1 (en) | 2003-12-26 |
| CN1656240A (en) | 2005-08-17 |
| GB0423402D0 (en) | 2004-11-24 |
| BR0312101A (en) | 2005-03-29 |
| DE10392805B4 (en) | 2022-11-17 |
| CA2485524C (en) | 2010-11-16 |
| DE10392805T5 (en) | 2005-06-02 |
| GB2402943A (en) | 2004-12-22 |
| BR0312101B1 (en) | 2013-05-14 |
| GB2402943B (en) | 2006-03-29 |
| US20050006010A1 (en) | 2005-01-13 |
| CN100451149C (en) | 2009-01-14 |
| FR2841264B1 (en) | 2007-05-11 |
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