CN101068943B - High strength, high toughness a1-zn alloy product and method for producing such product - Google Patents
High strength, high toughness a1-zn alloy product and method for producing such product Download PDFInfo
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Abstract
The invention relates to a Al-Zn alloy wrought product, and to a method of manufacturing such a product, with an improved combination of high toughness and high strength by maintaining good corrosion resistance, said alloy including (in weight percent): Zn 6.0-11.0, Cu 1.4-2.2, Mg 1.4-2.4, Zr 0.05-0.15, Ti < 0.05, Hf and/or V < 0.25, and optionally Sc and/or Ce 0.05-0.25, and Mn 0.05-0.12, other elements each less than 0.05 and less than 0.50 in total, balance aluminium, wherein such alloy has an essentially fully unrecrystallized microstructure at least at the position T/10 of the finished product.
Description
Invention field
The present invention relates to the Al-Zn alloy deformation product of high-intensity high-tenacity, this alloy has the Zn amount of raising with the maintenance good anti-corrosion, and relates to the method for this high-intensity high-tenacity of production Al-Zn alloy product and the panel products of this alloy.More specifically, the present invention relates to the high strength, the high tenacity Al-Zn alloy that are used for the structure aerospace applications and name by ABAL's international nomenclature AA7000 series.More specifically, the present invention relates to have the new chemical constitution window that intensity and flexible improvement group merge the Al-Zn alloy that keeps good corrosion resistance, it need not special timeliness or state processing.
Background of invention
Known use heat treatable aluminium alloy, for example airframe, vehicle component and other application in the many application that relate to relative high strength, high tenacity and rotproofness in this area.Aluminium alloy AA7050 and under T6 type state, show high intensity level from 7150.The AA7 of precipitation-hardening * 75, AA7 * 55 alloy products also show high intensity level under the T6 state.Known T6 state can improve the intensity of alloy, wherein contain high zinc, copper and magnesium amount above-mentioned AA7 * 50, AA7 * 75 and AA7 * 55 alloy products since its high strength/weight ratio and known therefore, in aircraft industry, be applied especially.Yet these application cause with various weather condition and contact, and this needs careful control processing and aging condition so that enough intensity and corrosion (comprise stress corrosion and peel off) resistivity to be provided.
Resistivity and fracture toughness property in order to improve the counter stress corrosion and to peel off are known that these AA7000 series alloys are carried out artificial overaging.When artificial aging when T79, T76, T74 or the T73 type state, their counter stress burn intos peel off the corrosive resistivity and fracture toughness property improves (T73 is best, and T79 and T6 are approaching) by described order, still with the T6 conditions mutually specific tenacity incur loss.More satisfied conditions is the T74 type state of the limited overaging condition between T73 and the T76, so that obtain tensile strength, anticorrosion stress-resistant, the anti-corrodibility and the fracture toughness property of peeling off of satisfactory level.By under 121 ℃ temperature, alloy product being carried out then carrying out this T74 state down in lasting about 14 hours at 171 ℃ in overaging 6-24 hour.
According to the standard of specific aircraft components, even the little raising of intensity, toughness or erosion resistance also can cause the saving of weight, this is converted into conservation of fuel in the work-ing life of aircraft.In order to satisfy these requirements, some other 7000 series alloys have been developed.
EP-0377779 for example, US-5,221,377 and US-5,496, each of 426 piece all discloses alloy product and has produced the modification method of 7055 alloys, this alloy is applicable to that sheet material in the aviation field or sheet applications for example have the top wing member of high tenacity and good corrosive nature, this method comprises the steps: to process base substrate, this base substrate consist of (approximately in weight %) Zn7.6-8.4, Cu 2.2-2.6, Mg 1.8-2.1 or 2.2 and be selected from Zr, Mn, one or more elements of V and Hf (total amount of these elements is no more than 0.6 weight %), surplus is that Al adds incidental impurities; Product is carried out solution heat treatment and quenching; And by otherwise continuous three heating products to 79 ℃ to one or more temperature of 163 ℃, or at first heating products to 79 ℃ is to one or more temperature of 141 ℃ and be incubated two hours or longer heating products to 148 then ℃ to one or more temperature of 174 ℃ are carried out artificial aging to product.It is reported that these products have " EB " or better improve the anti-corrodibility of peeling off, have yield strength than 7 * 50 corresponding product (Counter-part) high about 15% of the T76 conditions of similar size.They also have 7 * 50-T77 corresponding product height than their similar sizes at least about 5% intensity (hereinafter using 7150-T77 as the reference alloy).
Summary of the invention
The purpose of this invention is to provide the improvement Al-Zn alloy that is preferred for panel products with height (resistance to compression) intensity and high tenacity.Erosion resistance is not answered deterioration.
More specifically, the purpose of this invention is to provide and can be used for the alloy product that the aircraft top wing is used, this alloy product has the improvement compressive yield strength of performance of the conventional AA7055 alloy that is better than the T77 state and high unit propagates energy.
Another object of the present invention is the alloy product that obtains a kind of AA7000 series, and this product shows intensity and interior toughness and the erosion resistance of T73 type state range in the T6 type state range.
Another object of the present invention provides the method for manufacturing according to alloy product of the present invention.
By the property feature of independent claim, the present invention has satisfied one or more these purposes.In addition, in the dependent claims other preferred embodiment is described and stipulates.
DESCRIPTION OF THE PREFERRED
Should be understood that hereinafter if not indicated otherwise, then the name of the name of alloy and state is meant the ABAL's name among the Aluminum Standards and Data and theRegistration Records that association of Alcoa publishes.
The Al-Zn alloy product that has high tenacity and high-intensity improved combination and maintenance good corrosion resistance by use has been realized one or more above-mentioned purpose of the present invention, described alloy comprises following composition, and preferably forms (by weight percentage) by following compositions:
Zn 6.0-11.0
Cu 1.4-2.2
Mg 1.4-2.4
Zr 0.05-0.15
Ti ＜0.05
Hf and/or V＜0.25
Optionally Sc and/or Ce 0.05-0.25 and
Optional Mn 0.05-0.12,
With the aluminium of unavoidable impurities and surplus, preferably every kind of other element be less than 0.05 and total amount be less than 0.50, and wherein this alloy product has the microstructure of complete substantially non-recrystallize in the T/10 position of the finished product.
When producing the panel products of relative thin, this chemical constitution window of AA7000 series alloy shows excellent performance, and this alloy preferably can be used for being of a size of in the aircraft top wing application of 20-60mm scope.
Above the chemical constitution of Xian Dinging have with AA7 * 50 of T77 state or AA7 * existing alloy phase of 55 series when or better properties, and need not to use above-mentioned loaded down with trivial details and complicated T77 three steps timeliness circulation.Owing to only need less treatment step, so this chemical constitution causes the more economical and simpler aluminium product of production of cost.In addition, this chemical constitution allows new manufacturing technology, as inapplicable age forming or timeliness creep forming when adopting the alloy of T77 state.Even better, also can be with the chemical constitution timeliness that above limits to the T77 state, thus erosion resistance further improved.
According to the present invention, have been found that and use higher Zn amount and the Mg of specified range and the specific combination of Cu, the selected scope of element has shown a lot of intensity and flexible combination and has kept good corrosion energy, for example anti-corrodibility and the anticorrosion stress-resistant cracking behavior of peeling off.
As mentioned below, the present invention uses this chemical constitution and combines with the method for being produced rolled products by this chemical constitution, so that obtain the microstructure of complete non-recrystallize basically in the position of T/10 at least of the finished product.More preferably product is non-recrystallize on whole thickness.Non-recrystallize, we mean final rolled products size more than 80%, preferably be essentially non-recrystallize more than 90%.Therefore, the invention discloses and a kind ofly be particularly suitable for that aircraft top wing covering is used and thickness is the alloy product of 20-60mm, preferred 30-50mm.
Have been found that and need not rolled products is quenched at a slow speed or the size that increases rolled products obtains excellent compressive yield strength and toughness properties.
Copper and magnesium are the important elements that increases alloy strength.Cross low magnesium and copper amount and cause the reduction of intensity, and too high magnesium and copper amount cause lower corrosive nature of alloy product and weldability problem.Prior art is used special ag(e)ing process and is used low magnesium and copper amount to obtain the good corrosion energy simultaneously so that improve intensity.In order to realize taking into account of intensity, toughness and corrosive nature, found that magnesium is that 1.7-2.2%, preferred 1.7-2.1% and copper are that the amount (weight %) of copper and the magnesium of 1.8-2.1% can give light sheet products good balance.By chemical constitution of the presently claimed invention, can realize that now the strength level in the T6 state alloyed region keeps and corrosive nature like the T74 state alloy phase simultaneously.
Outside demagging and the copper amount, magnesium that the invention discloses and copper amount are to the balance, particularly magnesium of the zinc balance to zinc, and this gives alloy these performance characteristics.Improvement erosion resistance according to alloy of the present invention has EB or better, preferred EA or better spalling resistance (" EXCO ").
Zinc amount (weight %) is preferably in the 7.4-9.6% scope, more preferably in 8.0-9.6%, most preferably in the 8.4-8.9% scope.Test finds that best zinc level is about 8.6%.Provide further details in an embodiment, as hereinafter more detailed description.
Show that in addition according to the preferred embodiments of the invention, containing the Sc alloy is to obtain high strength and (versus) the excellence selection of high notch toughness level.By in the alloy that comprises copper, magnesium, zinc, zirconium and titanium, adding Sc, found that microstructure keeps non-recrystallize, demonstrate relevant intensity and flexible excellent properties thus.Therefore, preferred Sc amount (weight %) is at [Zr]+1.5[Sc]＜0.15% scope in.When Zn amount for about 8.70% and Mg and Cu be about 2.10% the time, preferred Sc amount or Ce amount (weight %) are in the 0.03-0.06% scope.For the alloy with other Sc, Ce or Mn alloy element, unit propagates and can be on close level.
Production may further comprise the steps according to high strength of the present invention, high tenacity and preferred method with Al-Zn alloy product of good corrosion resistance:
A. casting has the ingot casting (by weight percentage) of following composition:
Zn 6.0-11.0
Cu 1.4-2.2
Mg 1.4-2.4
Zr 0.05-0.15
T?i ＜0.05
Hf and/or V＜0.25
Optionally Sc and/or Ce 0.05-0.25 and
Optional Mn 0.05-0.12,
With the aluminium of unavoidable impurities and surplus, preferably every kind of other element be less than 0.05 and total amount be less than 0.50,
B. homogenizing and/or preheating are carried out to ingot casting in the casting back,
C. ingot casting is thermally processed into the preprocessing product,
D. heat once more the preprocessing product and or
D1. final size is arrived in the heating product hot rolling once more, or
D2. incite somebody to action heating product hot rolling once more and be cold rolled to final size,
E. solution heat treatment and the product of solution heat treatment quenched,
F. optional to the alloy product that quenches stretch suppress or carry out cold working with release stress and
G. optional product to this quenching and optional stretching, extension or compacting carries out timeliness obtaining required state, and wherein in the T/10 position of the finished product, alloy product has the microstructure of complete substantially non-recrystallize.
Have been found that the microstructure of alloy product keeps complete substantially non-recrystallize in its lower face when using the preprocessing product and the preprocessing product carried out hot rolling and/or cold rolling the inventive method step.
According to embodiment of the present invention, this method comprises at first carries out hot rolling to homogenizing to the ingot casting of preprocessing product, heating product is hot-rolled down to about 150-250 (final size %) once more, then the hot rolled product is cold rolled to final size, perhaps heating product is hot-rolled down to about 105-140 (final size %) and then the hot rolled product is cold rolled to final size once more." final size % " is meant the per-cent of comparing thickness with the thickness of the finished product.200 final size % are meant that thickness is the twice of final converted products thickness.This means and have been found that advantageously, at first the product with preheating is hot-rolled down to the thickness that is about the final product thickness twice, then the hot rolled product is cold-rolled to final thickness, perhaps pre-hot product is hot-rolled down to than the thickness of the thickness of the finished product about 20% cold-rolled products then, obtains the other minimizing of hot-rolled product size about 20% thus.
According to another embodiment of the present invention, under the low temperature of 300-420 ℃ of scope heating product once more being carried out hot rolling, to make alloy that recrystallize not take place be favourable.Alternatively, if improvement SCC performance can or be used T77 three step state processing by two step T79 or T76 state processing (temper), artificial aging is carried out in processing and heat treated product.
The present invention is applicable to after casting ingot casting is carried out hot-work and the optional converted products that is of a size of 20-60mm that is cold worked into.
The present invention also relates to the high strength of above-mentioned composition, the panel products of high tenacity Al-Zn alloy, the aircraft component that this panel products is preferably thin, even the structural shapes member that more preferably prolongs, for example top wing member, top wing thin skin member or aircraft longeron.
Can further improve the performance of the alloy that requires by the artificial aging step, this artificial aging step is included in and continues 2-20 hour, preferred about 8 hours first thermal treatment under 105-135 ℃, preferred about 120 ℃ of temperature and be higher than 135 ℃ but be lower than under 210 ℃, preferred about 155 ℃ temperature and continue 4-12 hour, preferred 8-10 hour second thermal treatment.
By the following detailed description of preferred embodiment, will become apparent according to the above-mentioned or further feature and the advantage of alloy of the present invention.
Embodiment 1
With laboratory scale, 14 kinds of different aluminum alloys are cast as ingot casting, homogenizing surpasses 6 hours in about 410 ℃ of preheatings, and is rolled into the 4mm plate.Under 475 ℃, carry out solution heat treatment, carry out shrend afterwards.By two step T76 ag(e)ing processes quenching product carried out timeliness thereafter.
List chemical constitution in the table 1
The chemical constitution of the alloy of table 1 sheet form (weight %), surplus are aluminium and unavoidable impurities, Fe 0.06, Si 0.05, Ti 0.04 and Zr 0.12.
| Alloy | Cu | Mg | Zn | Other |
| 1 2 3 4 5 6 7 8 9 10 11 12 13 14 | 2.0 2.1 1.7 2.1 2.4 1.7 2.1 2.4 1.7 2.1 2.5 2.1 2.1 2.1 | 2.1 2.1 1.75 1.7 1.7 2.2 2.1 2.1 2.5 2.4 2.5 2.1 2.1 2.1 | 8.0 8.1 8.7 8.6 8.6 8.7 8.6 8.7 8.7 8.6 8.7 9.2 8.7 8.7 | 0.08Mn - - - - - - - - - - - 0.03Ce 0.06Sc |
Use three handle variants (referring to the alloy of step 5) processing list 1:
1. carry out homogenizing as follows: the temperature speed with 40 ℃/h is heated to 460 ℃ of temperature, then 460 ℃ of soaking 12 hours, is elevated to 475 ℃ of temperature once more with 25 ℃/h then, and soaking 24 hours once more under 475 ℃, and air cooling is to room temperature then.
2. under 420 ℃, carry out preheating 6 hours with the heating rate of 40 ℃/h.
With laboratory scale ingot casting from the 80mm hot rolling to 25mm, thereby every time about 6-8mm reduced in size.
4. heat the thick product to 420 of 25mm ℃ once more, continue about 30 minutes.
5. variant 1: heating product is hot-rolled down to 40mm once more.
Variant 2: heating product is hot-rolled down to 8.0mm and is cold-rolled to 4.0mm then once more.
Variant 3: heating product is hot-rolled down to 5.0mm and is cold-rolled to 4.0mm then once more.
6. under 475 ℃, carry out solution heat treatment 1 hour, shrend then.
7. carry out the stretching, extension of 1.5-2.0% after quenching in about 1 hour.
8. then, according to the T76 ag(e)ing process product that stretches is carried out timeliness, thereby with the speed elevated temperature to 120 of 30 ℃/h ℃, and 120 ℃ of insulations 5 hours, with the temperature of 15 ℃/h speed elevated temperature to 160 ℃ and soaking 6 hours, with the product air cooling of timeliness to room temperature.
Utilize little European standard (Euronorm) measured intensity, and measure toughness according to ASTM B-871 (1996).In table 2a-2c, demonstrate the result of three above-mentioned variants.
Show 2a. according to variant 1, the intensity of alloy shown in the table 1 and toughness (MPa) and notch toughness (TYR).
| Alloy | Rp | UPE | TYR |
| 1 2 3 4 5 6 7 8 9 10 11 12 13 14 | 582 564 534 550 579 592 595 605 612 613 603 - 597 587 | 211 215 243 214 208 84 120 98 30 54 33 - 163 121 | 1.31 1.48 1.49 1.48 1.44 1.34 1.32 1.32 1.31 1.12 1.11 - 1.27 1.35 |
Show 2b. according to variant 2, the intensity of alloy shown in the table 1 and toughness (MPa) and notch toughness (TYR).
| Alloy | Rp | UPE | TYR |
| 1 2 3 4 5 6 7 8 9 10 11 12 13 14 | 599 567 533 587 563 569 - 616 - 601 612 - 595 626 | 125 268 143 205 178 134 - 72 - 22 5 - 88 71 | 1.30 1.45 1.53 1.38 1.45 1.35 - 1.10 - 1.00 1.05 - 1.16 1.26 |
Show 2c. according to variant 3, the intensity of alloy shown in the table 1 and toughness (MPa) and notch toughness (TYR).
| Alloy | Rp | UPE | TYR |
| 1 2 3 4 5 6 7 8 9 10 11 12 13 14 | 600 575 535 575 604 587 613 627 - 607 614 606 601 616 | 170 211 232 260 252 185 199 185 - 31 26 58 148 122 | 1.35 1.47 1.59 1.46 1.39 1.43 1.26 1.18 - 1.09 0.92 1.11 1.26 1.35 |
Can be clear by the given result of table 2a-2c, the cold rolling toughness and the strength balance that helps the best of less degree (10-20%).Simple hot rolled material (table 2a) according to variant 1 approaches the best, but the alloy of variant 3 is better usually.
In addition, high strength and high notch toughness if desired as can be seen, the alloy 14 that then contains Sc is favourable.A small amount of manganese has improved intensity really but has lost some toughness.
Embodiment 2
Handle other chemical constitution according to above-mentioned treatment step 1-8, thereby use the variant 3 and the T76 timeliness of the foregoing description 1 step 5.
Table 3: the chemical constitution of sheet alloy (weight %) is aluminium and unavoidable impurities for all alloy surpluses, and Fe 0.06, and Si 0.05.
| Alloy | Cu | Mg | Zn | Zr | Ti | Other |
| 1 2 3 4 5 6 7 8 9 10 11 | 2.0 2.1 1.7 2.1 2.4 2.1 2.1 2.1 1.7 1.6 2.1 | 2.1 2.1 2.2 2.1 2.1 2.1 2.1 2.1 2.1 2.5 2.4 | 8.0 8.1 8.7 8.6 8.7 9.2 8.7 8.7 9.3 9.2 9.2 | 0.11 0.12 0.12 0.12 0.12 0.12 0.12 0.10 0.12 0.12 0.12 | 0.03 0.03 0.03 0.03 0.03 0.03 0.04 0.04 0.03 0.04 0.04 | 0.08Mn - - - - - 0.04Ce 0.06Sc - - - |
Test chart 3 interalloy performances are in L direction test intensity and in L-T direction test toughness.
Table 4: according to variant 3, the intensity of alloy shown in the table 3 and toughness (MPa) and notch toughness (TS/Rp).
| Alloy | Rp(MPa) | Rm(MPa) | UPE(KJ/m 2) | TS/Rp |
| 1 2 3 4 5 6 7 8 9 10 11 | 601 575 591 613 624 608 601 618 613 618 619 | 637 603 610 647 645 638 639 652 632 650 654 | 177 221 194 199 178 63 163 132 75 5 26 | 1.35 1.48 1.45 1.34 1.18 1.13 1.27 1.35 1.25 1.29 1.18 |
Toughness shown in the table 4 and tensile yield strength (Rp) are clear to be shown, obtains best toughness and tensile yield strength value for the alloy with about 8.6-8.7 weight % zinc.Alloy with low zinc level has shown similar toughness value, but tensile strength (usually) is lower, yet high-caliber zinc causes higher strength level but lower toughness levels.A small amount of manganese has improved intensity really but has lost toughness.
Embodiment 3
Thereby the zinc level to 8.6 and 8.7 changes copper and the magnesium level is carried out other test.Can demonstrate, can under identical strength level, improve toughness levels.With similar among the embodiment 2 other alloys are handled, thereby used the variant 3 of above-mentioned treatment step 1-8 and embodiment 1 step 5.
The chemical constitution of table 5. sheet alloy (weight %) is aluminium and unavoidable impurities for all alloy surpluses, Fe 0.06, Si 0.05.
| Alloy | Cu | Mg | Zn | Zr | Ti | Other |
| 3 4 5 12 13 14 15 16 17 | 1.7 2.1 2.4 2.5 2.1 1.7 1.7 2.4 2.1 | 2.2 2.1 2.1 2.5 2.4 2.5 1.7 1.7 1.7 | 8.7 8.6 8.7 8.7 8.6 8.7 8.7 8.6 8.6 | 0.12 0.12 0.12 0.11 0.12 0.12 0.12 0.12 0.12 | 0.03 0.03 0.03 0.03 0.03 0.03 0.03 0.03 0.04 | - - - 0.08Mn - - - - - |
Table 6. is according to variant 3, the intensity of alloy shown in the table 5 and toughness (MPa) and notch toughness (TS/Rp).
| Alloy | Rp(MPa) | UPE(kJ/m 2) | TS/Rp |
| 3 4 5 12 13 14 15 16 17 | 591 613 624 614 607 621 535 604 573 | 194 199 178 26 31 55 232 252 260 | 1.45 1.34 1.18 0.92 1.09 1.01 1.59 1.39 1.46 |
As shown in Figure 6, have that to be less than 2.4% magnesium level be favourable, best about 1.7%.When the magnesium level is about 1.7% the time, obtain excellent toughness properties but strength level reduces.When having about 2.1% magnesium level, obtain best strength level.Therefore, magnesium is preferably 1.7-2.1%.
According to ASTM G-34 all above-mentioned alloys are peeled off corrosion test.They all show EB or better properties.
In addition, shown that interpolation Ce or Sc can improve the microstructure of alloy, therefore reduced to reply and handle.Because the answer in the alloy material is low, even use solution heat treatment according to standard routes, recrystallize takes place hardly also.Sc restrains recrystallize makes common light sheet products thickness more than 90% keep non-recrystallize.
Fully describe the present invention now, it will be apparent to those skilled in that, under the situation that does not deviate from scope of invention described here and purport, can carry out many variations and modification.
Claims (25)
1. production has the high strength of good corrosion resistance, the method for high tenacity Al-Zn alloy product, and this method may further comprise the steps:
A.) casting has the ingot casting of forming below, by weight percentage:
Unavoidable impurities and surplus aluminium,
B.) after casting, ingot casting is carried out homogenizing and/or preheating,
C.) ingot casting is thermally processed into the preprocessing product,
D.) heat the product of preprocessing once more, and the heating product hot rolling is cold rolled to final size then once more,
E.) solution heat treatment and the product of solution heat treatment quenched, the product that wherein is in its final state has the microstructure of complete non-recrystallize at least in the T/10 position of the finished product,
And wherein incite somebody to action once more the 150-250% that heating product is hot-rolled down to final size, then hot-rolled product is cold-rolled to final size, or wherein incite somebody to action once more the 105-140% that heating product is hot-rolled down to final size, then the hot rolled product is cold-rolled to final size.
2. the method for claim 1 also comprises the step that the alloy product that quenches is stretched or suppresses, i.e. step f.).
3. according to the method for claim 2, also comprise quenching and stretching or the product of compacting carries out timeliness to obtain the step of required state, i.e. step g .), step g .) timeliness in the process is the artificial aging of timeliness to the state that is selected from T79 and T76.
4. according to the method for claim 1 or 2, be included under the low temperature of 300-420 ℃ of scope heating product is once more carried out hot rolling to prevent the alloy product recrystallize.
5. according to the method for claim 3, step g wherein .) artificial aging in the process is that timeliness is to the state that is selected from T79 and T76, by two step ageing treatment.
6. according to the method for claim 3, step g wherein .) artificial aging in the process is by the first timeliness step that continues 2-20 hour under 105-135 ℃ of temperature, with be higher than 135 ℃ but be lower than the second timeliness step that continues 4-12 hour under 210 ℃ the temperature and form, with timeliness to the state that is selected from T79 and T76 state.
7. according to the method for claim 6, step g wherein .) artificial aging in the process is by 120 ℃ of lasting 2-20 hours the first timeliness step, with be higher than 135 ℃ but be lower than the second timeliness step that continues 4-12 hour under 210 ℃ the temperature and form, with timeliness to the state that is selected from T79 and T76 state.
8. according to the method for claim 6, step g wherein .) artificial aging in the process is by forming 120 ℃ of lasting 2-20 hours the first timeliness step with 155 ℃ of second timeliness steps that continue 4-12 hour down, with timeliness to the state that is selected from T79 and T76 state.
9. claim 1 or 2 method wherein are used for step a.) composition also comprise Sc and/or the Ce of 0.05-0.25%.
10. claim 1 or 2 method wherein are used for step a.) composition also comprise the Mn of 0.05-0.12%.
11. according to the method for claim 1 or 2, wherein the Zn amount is in 7.4-9.6 weight % scope.
12. according to the method for claim 11, wherein the Zn amount is in 8.0-9.6 weight % scope.
13. according to the method for claim 11, wherein the Zn amount is in 8.4-8.9 weight % scope.
14. according to the method for claim 1 or 2, wherein the Cu amount is in 1.7-2.2 weight % scope.
15. according to the method for claim 1 or 2, wherein the Cu amount is in 1.8-2.1 weight % scope.
16. according to the method for claim 14, wherein the Mg amount is in 1.7-2.2 weight % scope.
17. according to the method for claim 14, wherein the Mg amount is in 1.7-2.1 weight % scope.
18. according to the method for claim 9, wherein Sc amount is at [Zr]+1.5[Sc]＜0.15 weight % scope in.
19. according to the method for claim 1 or 2, wherein the amount of unavoidable impurities is every kind and is less than 0.05 weight %, and total amount is less than 0.5 weight %.
20. according to the method for claim 1 or 2, wherein final rolled products has the microstructure of non-recrystallize more than 80% size.
21. according to the method for claim 1 or 2, wherein final rolled products has the microstructure of non-recrystallize more than 90% size.
22. according to the method for claim 1 or 2, wherein the Al-Zn alloy product is the thin plate that is of a size of 20-60mm.
23. according to the method for claim 1 or 2, wherein the Al-Zn alloy product is the thin plate that is of a size of 30-50mm.
24. according to the method for claim 1 or 2, wherein A l-Zn alloy product is the product that is selected from thin aircraft component, top wing member and aircraft longeron.
25. according to the method for claim 1 or 2, wherein the Al-Zn alloy product is a top wing thin skin member.
Applications Claiming Priority (3)
| Application Number | Priority Date | Filing Date | Title |
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| EP04077721 | 2004-10-05 | ||
| EP04077721.1 | 2004-10-05 | ||
| PCT/EP2005/010809 WO2006037648A1 (en) | 2004-10-05 | 2005-10-04 | HIGH STRENGTH, HIGH TOUGHNESS Al-Zn ALLOY PRODUCT AND METHOD FOR PRODUCING SUCH PRODUCT |
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| JP (1) | JP5068654B2 (en) |
| CN (1) | CN101068943B (en) |
| AT (1) | ATE426050T1 (en) |
| BR (1) | BRPI0517538B1 (en) |
| CA (1) | CA2592132C (en) |
| DE (2) | DE102005045341A1 (en) |
| FR (1) | FR2876118B1 (en) |
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| WO (1) | WO2006037648A1 (en) |
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- 2005-09-29 FR FR0509944A patent/FR2876118B1/en active Active
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- 2005-10-04 RU RU2007116979/02A patent/RU2404276C2/en active
- 2005-10-04 BR BRPI0517538-0A patent/BRPI0517538B1/en active IP Right Grant
- 2005-10-04 WO PCT/EP2005/010809 patent/WO2006037648A1/en active Application Filing
- 2005-10-04 JP JP2007533966A patent/JP5068654B2/en active Active
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- 2005-10-04 DE DE602005013429T patent/DE602005013429D1/en active Active
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| Publication number | Publication date |
|---|---|
| ATE426050T1 (en) | 2009-04-15 |
| JP2008516079A (en) | 2008-05-15 |
| FR2876118B1 (en) | 2010-08-20 |
| BRPI0517538B1 (en) | 2015-06-16 |
| CA2592132C (en) | 2014-08-05 |
| RU2007116979A (en) | 2008-11-20 |
| CN101068943A (en) | 2007-11-07 |
| JP5068654B2 (en) | 2012-11-07 |
| EP1831415B1 (en) | 2009-03-18 |
| RU2404276C2 (en) | 2010-11-20 |
| FR2876118A1 (en) | 2006-04-07 |
| WO2006037648A1 (en) | 2006-04-13 |
| EP1831415A1 (en) | 2007-09-12 |
| DE102005045341A1 (en) | 2006-07-20 |
| DE602005013429D1 (en) | 2009-04-30 |
| BRPI0517538A (en) | 2008-10-14 |
| EP1831415B2 (en) | 2014-10-15 |
| CA2592132A1 (en) | 2006-04-13 |
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