WO2004001080A1 - 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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- WO2004001080A1 WO2004001080A1 PCT/EP2003/006208 EP0306208W WO2004001080A1 WO 2004001080 A1 WO2004001080 A1 WO 2004001080A1 EP 0306208 W EP0306208 W EP 0306208W WO 2004001080 A1 WO2004001080 A1 WO 2004001080A1
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- 229910045601 alloy Inorganic materials 0.000 title claims abstract description 66
- 239000000956 alloy Substances 0.000 title claims abstract description 66
- 238000004519 manufacturing process Methods 0.000 title claims abstract description 9
- 229910018569 Al—Zn—Mg—Cu Inorganic materials 0.000 title description 2
- 238000010438 heat treatment Methods 0.000 claims abstract description 31
- 238000000034 method Methods 0.000 claims abstract description 31
- 230000032683 aging Effects 0.000 claims abstract description 27
- 229910017818 Cu—Mg Inorganic materials 0.000 claims abstract description 12
- 239000004411 aluminium Substances 0.000 claims abstract description 12
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims abstract description 12
- 229910052782 aluminium Inorganic materials 0.000 claims abstract description 12
- 238000005266 casting Methods 0.000 claims abstract description 10
- 239000000203 mixture Substances 0.000 claims abstract description 8
- 238000010791 quenching Methods 0.000 claims abstract description 8
- 230000000171 quenching effect Effects 0.000 claims abstract description 8
- 230000006835 compression Effects 0.000 claims abstract description 7
- 238000007906 compression Methods 0.000 claims abstract description 7
- 238000005482 strain hardening Methods 0.000 claims abstract description 5
- 238000005260 corrosion Methods 0.000 claims description 36
- 230000007797 corrosion Effects 0.000 claims description 34
- 238000004299 exfoliation Methods 0.000 claims description 18
- 238000005096 rolling process Methods 0.000 claims description 4
- 239000011777 magnesium Substances 0.000 description 27
- 239000010949 copper Substances 0.000 description 22
- FYYHWMGAXLPEAU-UHFFFAOYSA-N Magnesium Chemical compound [Mg] FYYHWMGAXLPEAU-UHFFFAOYSA-N 0.000 description 21
- 229910052749 magnesium Inorganic materials 0.000 description 21
- 239000011701 zinc Substances 0.000 description 21
- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical compound [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 description 16
- 229910052802 copper Inorganic materials 0.000 description 16
- 229910000838 Al alloy Inorganic materials 0.000 description 14
- 230000035882 stress Effects 0.000 description 12
- 229910052725 zinc Inorganic materials 0.000 description 11
- HCHKCACWOHOZIP-UHFFFAOYSA-N Zinc Chemical compound [Zn] HCHKCACWOHOZIP-UHFFFAOYSA-N 0.000 description 10
- XEEYBQQBJWHFJM-UHFFFAOYSA-N Iron Chemical compound [Fe] XEEYBQQBJWHFJM-UHFFFAOYSA-N 0.000 description 6
- 239000011572 manganese Substances 0.000 description 6
- 238000012360 testing method Methods 0.000 description 6
- 239000012535 impurity Substances 0.000 description 3
- 230000008569 process Effects 0.000 description 3
- 239000010936 titanium Substances 0.000 description 3
- 229910052804 chromium Inorganic materials 0.000 description 2
- 238000001816 cooling Methods 0.000 description 2
- 239000000126 substance Substances 0.000 description 2
- 229910052719 titanium Inorganic materials 0.000 description 2
- 229910052726 zirconium Inorganic materials 0.000 description 2
- 229910000861 Mg alloy Inorganic materials 0.000 description 1
- XUIMIQQOPSSXEZ-UHFFFAOYSA-N Silicon Chemical compound [Si] XUIMIQQOPSSXEZ-UHFFFAOYSA-N 0.000 description 1
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 description 1
- QCWXUUIWCKQGHC-UHFFFAOYSA-N Zirconium Chemical compound [Zr] QCWXUUIWCKQGHC-UHFFFAOYSA-N 0.000 description 1
- 238000005275 alloying Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000011651 chromium Substances 0.000 description 1
- 238000005336 cracking Methods 0.000 description 1
- 238000001125 extrusion Methods 0.000 description 1
- 238000005242 forging Methods 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 229910052742 iron Inorganic materials 0.000 description 1
- 238000003754 machining Methods 0.000 description 1
- 229910052748 manganese Inorganic materials 0.000 description 1
- WPBNNNQJVZRUHP-UHFFFAOYSA-L manganese(2+);methyl n-[[2-(methoxycarbonylcarbamothioylamino)phenyl]carbamothioyl]carbamate;n-[2-(sulfidocarbothioylamino)ethyl]carbamodithioate Chemical compound [Mn+2].[S-]C(=S)NCCNC([S-])=S.COC(=O)NC(=S)NC1=CC=CC=C1NC(=S)NC(=O)OC WPBNNNQJVZRUHP-UHFFFAOYSA-L 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000004881 precipitation hardening Methods 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
- 229910052710 silicon Inorganic materials 0.000 description 1
- 239000010703 silicon Substances 0.000 description 1
- 229910052720 vanadium Inorganic materials 0.000 description 1
Classifications
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- 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
Definitions
- the present invention relates to a method for producing a high strength AI-Zn- Cu-Mg alloy with an improved corrosion resistance while at the same time maintaining a high damage tolerance, a plate product of a high strength AI-Zn-Cu-Mg alloy produced in accordance with the inventive method having a thickness of more than 50 mm and an aircraft structural member produced from such alloy. More specifically, the present invention relates to a high strength AI-Zn-Cu-Mg alloy designated by the 7000- series of the international nomenclature of the Aluminium Association for structural aeronautical applications. Even more specifically, the present invention relates to a thick aluminium alloy product having improved combinations of strength, toughness and corrosion resistance, particularly a good strength-corrosion balance.
- Aluminium alloys AA7050 and AA7150 exhibit high strength in T6-type tempers, see for example US-6,315,842. Also precipitation-hardened AA7x75 alloy products exhibit high strength values in the T6 temper.
- the T6 temper is known to enhance the strength of the alloy, wherein the aforementioned AA7050, AA7x50 and AA7x75 alloy products which contain high amounts of zinc, copper and magnesium are known for their high strength-to-weight ratios and, therefore, find application in particular in the aircraft industry.
- these applications result in exposure to a wide variety of climatic conditions necessitating careful control of working and ageing conditions to provide adequate strength and resistance to corrosion, including both stress corrosion and exfoliation.
- T79, T76, T74 or T73-type temper their resistance to stress corrosion, exfoliation corrosion and fracture toughness improve in the order stated (T73 being best and T79 being close to T6) but at some cost to strength compared to the T6 temper condition.
- An acceptable temper condition is the T74-type temper which is a limited over-aged condition, between T73 and T76, in order to obtain an acceptable level of tensile strength, stress corrosion resistance, exfoliation corrosion resistance and fracture toughness.
- Such a T74 temper is performed by over-ageing the aluminium alloy product at temperatures of 121°C for 6 to 24 hours and 171 °C for about 14 hours.
- toughness or corrosion resistance result in weight savings, which translate to fuel economy over the life time of the aircraft.
- US Patent No. 4,954,188 discloses a method for providing a high strength aluminium alloy characterised by improved resistance to exfoliation using an alloy consisting of the following alloying elements, in wt.%: Zn: 5.9 - 8.2
- AA7075 and other AA7000-series alloys, in the T6 temper condition have not given sufficient resistance to corrosion under certain conditions.
- the T7-type tempers which improve the resistance of the alloys to stress-corrosion cracking, however, decrease strength significantly vis-a-vis the T6 condition.
- US Patent No. 4,863,528 therefore discloses a method for producing an improved aluminium alloy product, the method including providing an alloy consisting essentially of, in wt.%: Zn: 6 - 16 Cu: 1 - 3 Mg: 1.5 - 4.5, one or more elements selected from Zr, Cr, Mn, Ti, V, or Hf, the total of said elements not exceeding 1.0 wt.%, the balance aluminium and incidental impurities.
- the aluminium alloy is solution heat-treated after casting, precipitation-hardened to increase its strength to a level exceeding the as-solution heat treated strength level by about 30% of the difference between as-solution heat-treated strength and peak- strength and thereafter subjected to a treatment at a sufficient temperature or temperatures for improving its corrosion resistance properties. Thereafter, the alloy is again precipitation-hardened to raise its yield strength and produce a corrosion resistant alloy product.
- the ageing temperatures disclosed therein are between 170°C and 260°C in a range of 0.2 min. to 3 hours.
- the artificial ageing step is thereby preceded and succeeded by a precipitation-hardening step, also known as T77 ageing.
- Tensile strength values were obtained of between 460 MPa and 486 MPa and yield strength of 400 MPa to 434 MPa.
- US Patent No. 5,035,754 discloses a heat-treating method for a high strength aluminium alloy comprising the steps of solution heat-treating an aluminium alloy consisting essentially of, in wt.%:
- Mg: 1 - 6 at least one element selected from the group consisting of Cr: 0.1 - 0.5
- Mn 0.2 - 1.0, the balance being aluminium, heating of the alloy to a temperature of a lower temperature zone of 100°C to 140°C, optionally maintaining the alloy at a temperature within the lower temperature zone for a certain duration of time, re-heating the alloy to a temperature of an upper temperature zone of from 160°C to 200°C, optionally maintaining the alloy at a temperature within the upper temperature zone for a second duration of time, cooling of the alloy to a temperature of a lower temperature zone and repeating the above mentioned steps at least twice.
- Such alloy improves the properties of AA7075 and AA7050 aluminium alloys by obtaining a good corrosion resistance and a high strength characteristic.
- EP-0377779 discloses a process for producing an alloy for sheet or thin plate applications in the field of aerospace such as upper-wing members with high toughness and good corrosion properties which comprises the steps of working a body having a composition consisting of, in wt.%:
- Hf 0.03 - 0.5, the total of said elements not exceeding 0.6 wt.%, the balance aluminium plus incidental impurities, solution heat treating and quenching said product and artificially ageing the product by either heating the product three times in a row to one or more temperatures from 79°C to 163°C or heating such product first to one or more temperatures from 79°C to 141 °C for two hours or more or heating the product to one or more temperatures from 148°C to 174°C.
- These products show an improved exfoliation corrosion resistance of "EB" or better with about 15% greater yield strength than similar sized AA7x50 counter parts in the T76-temper condition. They still have at least about 5% greater strength than their similarly-sized AA7x50-T77 counter-part.
- US Patent No. 5,312,498 discloses another method for producing an aluminium- based alloy product having improved exfoliation resistance and fracture toughness with balanced zinc, copper and magnesium levels such that there is no excess of copper and magnesium.
- the method of producing the aluminium-based alloy product utilizes either a one-step or two-step ageing process in conjunction with the stoichiometrically balancing of copper, magnesium and zinc.
- a two-step ageing sequence is disclosed wherein the alloy is first aged at about 121°C for about 9 hours followed by a second ageing step at about 157°C for about 10 to 16 hours followed by air cooling.
- Such ageing method is directed to thin plate or sheet products that are used for lower-wing skin applications or fuselage skin.
- EP-1158068A1 discloses a heat-treatable aluminium alloy for producing thick products having a thickness of more than 12 mm, the alloy is an AI-Zn-Cu-Mg alloy with the following composition, in wt.%: Zn: 4 - 10
- Si ⁇ 0.25, preferably ⁇ 0.10
- Hf and/or V ⁇ 0.25, and 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, preferably by means of rolling, and optionally cold working, preferably by means of rolling, into a worked product of more than 50 mm thickness, d) solution heat treating, e) quenching the solution heat treated product, and 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%.
- the two-step ageing practice of the present invention utilizes a first heat treatment for 2 to 5 hours, at temperatures in the range of 115°C to 125°C, preferably about 4 hours at 120°C and a second heat treatment for 5 to 15 hours, at temperatures in the range of 155°C to 169°C, preferably for about 13 hours at temperatures between 161 °C to 167°C.
- the product may optionally be stretched or compressed or otherwise cold worked to relieve stresses as known in the art.
- Preferred amounts (in wt.%) of magnesium are in a range of 1.5 to 2.5, preferably in a range of 1.6 to 2.3, and more preferably in the range of 1.90 to 2.10.
- Preferred amounts (in wt.%) of copper are in a range of 1.5 to 2.5, preferably in a range of 1.6 to 2.3, and more preferably in the range of 1.85 to 2.10.
- Preferred amounts (in wt.%) of zinc are 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.
- Copper and magnesium are important elements for adding amongst others strength to the alloy.
- the preferred range of copper and magnesium is above 1.6 wt.% and lower than 2.3 wt.% since too low amounts of magnesium and copper result in a decrease of strength while too high amounts of magnesium and copper result in a lower corrosion performance and problems with the weldability of the alloy product.
- the balance of copper and magnesium to zinc, especially the balance of magnesium to zinc is of importance.
- the amount (in wt.%) of magnesium is preferably in between 2.4- 0.1 [Zn] and 1.5+0.1 [Zn]. That means that the amount of magnesium depends on the chosen amount of zinc.
- the amount (in wt.%) of magnesium is between 1.8 and 2.1 , when Zn is approx. 7 % the amount of magnesium is between 1.7 and 2.2 and if Zn is approx. 8 % the amount of magnesium is between 1.6 and 2.3.
- the alloy of the present invention is preferably selected from the group consisting of AA7010, AA7x50, AA7040, AA7020, AA7x75, AA7349 or AA7x55 or AA7x85, preferably AA7055, AA7085.
- a plate product of high strength aluminium-zinc-copper-magnesium-alloy produced in accordance with a method as defined above having a thickness of more than 50 mm, preferably 100 mm to 220 mm.
- Such plate product is preferably a part of an aircraft such as a bar or a spar of a wing.
- the plate product according to the present invention is an upper-wing member of an aircraft.
- the alloys of Table 1 show good compression yield strength ("Rp") in the L-direction of more than 476 MPa, most of them more than 500 MPa while the ultimate tensile strength (“Rm”) in the L-direction is above 529 MPa for all alloys and thickness, one example even above 600 MPa for 63.5 mm.
- the ST- elongation at position S/2 of all but two alloys is 3 % or above, even up to 6 %.
- the exfoliation properties are EA or EC.
- the exfoliation testing was done in accordance to ASTM G34 at S/10 position.
- the exfoliation properties are similar for similar ageing steps as shown in Table 3 but surprisingly deteriorate if the first heat treatment is longer and the second heat treatment is shorter.
- Alloy 4 has been tested with a plate thickness of 110 mm.
- the results of toughness and elongation are shown in Table 4.
- Table 4. Toughness and elongation properties of selected alloys of Table 1 , all plates of 110 mm thickness, ageing according to a two-step method, first heat treatment at 120°C for 4 hours, second heat treatment at 165°C for 13 hours, alloy 5 with a copper content of 2.25; K
- alloys 1 and 4 were tested with thickness of 152 mm. Two different ageing procedures were selected in accordance with Table 5. The load level was 172 MPa. The test direction is S-L. Samples were taken from the S/2 position. Table 5 shows the number of days till failure was given. After 30 days the test was terminated. "NF” means no failure after 30 days, "30” means failure after 30 days. In total at least three specimens are tested per variant. The test was done in accordance with ASTM G47.
- the toughness of the inventive alloy is controlled by the copper and magnesium levels while zinc has an influence in particular on the tensile properties.
- the preferred balance of each of copper and magnesium is in between 1.6 and 2.0 wt.%.
Abstract
Description
Claims
Priority Applications (6)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
CA2485524A CA2485524C (en) | 2002-06-24 | 2003-06-11 | Method for producing a high strength al-zn-mg-cu alloy |
AU2003277929A AU2003277929A1 (en) | 2002-06-24 | 2003-06-11 | METHOD FOR PRODUCING A HIGH STRENGTH Al-Zn-Mg-Cu ALLOY |
GB0423402A GB2402943B (en) | 2002-06-24 | 2003-06-11 | Method for producing a high strength Al-Zn-Mg-Cu alloy |
DE10392805.7A DE10392805B4 (en) | 2002-06-24 | 2003-06-11 | Process for producing high-strength Al-Zn-Mg-Cu alloy |
DE10392805T DE10392805T5 (en) | 2002-06-24 | 2003-06-11 | A method of producing a high strength Al-Zn-Mg-Cu alloy |
BRPI0312101-1A BR0312101B1 (en) | 2002-06-24 | 2003-06-11 | Method for producing a high strength al-zn-mg-cu alloy, plate product and structural member of aircraft. |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP02077549 | 2002-06-24 | ||
EP02077549.0 | 2002-06-24 |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2004001080A1 true WO2004001080A1 (en) | 2003-12-31 |
Family
ID=29719740
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/EP2003/006208 WO2004001080A1 (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) | DE10392805T5 (en) |
FR (1) | FR2841264B1 (en) |
GB (1) | GB2402943B (en) |
WO (1) | WO2004001080A1 (en) |
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US8002913B2 (en) | 2006-07-07 | 2011-08-23 | Aleris Aluminum Koblenz Gmbh | AA7000-series aluminum alloy products and a method of manufacturing thereof |
US8608876B2 (en) | 2006-07-07 | 2013-12-17 | Aleris Aluminum Koblenz Gmbh | AA7000-series aluminum alloy products and a method of manufacturing thereof |
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US9890448B2 (en) | 2008-06-24 | 2018-02-13 | Aleris Aluminum Koblenz Gmbh | Al—Zn—Mg alloy product with reduced quench sensitivity |
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Also Published As
Publication number | Publication date |
---|---|
FR2841264A1 (en) | 2003-12-26 |
CA2485524A1 (en) | 2003-12-31 |
BR0312101A (en) | 2005-03-29 |
AU2003277929A1 (en) | 2004-01-06 |
GB0423402D0 (en) | 2004-11-24 |
CN100451149C (en) | 2009-01-14 |
DE10392805B4 (en) | 2022-11-17 |
DE10392805T5 (en) | 2005-06-02 |
GB2402943B (en) | 2006-03-29 |
GB2402943A (en) | 2004-12-22 |
BR0312101B1 (en) | 2013-05-14 |
US20050006010A1 (en) | 2005-01-13 |
FR2841264B1 (en) | 2007-05-11 |
CA2485524C (en) | 2010-11-16 |
CN1656240A (en) | 2005-08-17 |
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