CA2519387A1 - High strength al-zn alloy and method for producing such an alloy product - Google Patents
High strength al-zn alloy and method for producing such an alloy product Download PDFInfo
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- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
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- C22C21/00—Alloys based on aluminium
- C22C21/10—Alloys based on aluminium with zinc as the next major constituent
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- 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 high strength AI-Zn alloy product with an improved combination of corrosion resistance and toughness, said alloy comprising essentially (in weight percent): Zn: 6.0 - 9.5, Cu: 1.3 - 2.4, Mg : 1.5 - 2.6, Mn and Zr < 0.25 but preferably in a range between 0.05 and 0. 15 for higher Zn contents, other elements each less than 0.05 and less than 0.2 5 in total, balance aluminium, wherein (in weight percent): 0.1[Cu] + 1.3 < [Mg] < 0.2[Cu] + 2.15, preferably 0.2[Cu] + 1.3 < [Mg] < 0.l[Cu] + 2.15. The invention also relates to a method to produce these alloy products, and to some preferred applications thereof such as upper wing applications in aerospace.
Description
High strength AI-Zn alloy and method for producing such an alloy product The present invention relates to a wrought high strength AI-Zn alloy with an improved combination of corrosion resistance and toughness according to claim 1, a method for producing a wrought high strength AI-Zn alloy with an improved combination of corrosion resistance and toughness according to claim 9 and a plate product of such alloy, optionally produced in accordance with the method. More specifically, the present invention relates to a wrought high strength AI-Zn alloy designated by the 7000-series of the international nomenclature of the Aluminium to Association for structural aeronautical applications. Even more specifically, the present invention relates to a new chemistry window for an AI-Zn alloy having improved combinations of strength, toughness and corrosion resistance, which does not need specific ageing or temper treatments.
It is known in the art to use heat treatable aluminium alloys in a number of applications involving relatively high strength, high toughness and corrosion resistance such as aircraft fuselages, vehicular members and other applications.
Aluminium alloys AA7050 and AA7150 exhibit high strength in T6-type tempers, see e.g. US-6,315,842. Also precipitation-hardened AA7x75, AA7x55 alloy products 2o exhibit high strength values in the T6 temper. The T6 temper is known to enhance the strength of the alloy, wherein the aforementioned AA7x50, AA7x75 and AA7x55 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. However, 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.
In order to enhance resistance against stress corrosion and exfoliation as well as fracture toughness it is known to artificially over-age these AA7000-series alloys.
3o When artificially aged to a 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 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 T74 temper is performed by CONFIRMATION COPY
over-ageing the aluminium alloy product at temperatures of 121 °C for 6 to 24 hours and 171 °C for about 14 hours.
Depending on the design criteria for a particular airplane component even small improvements in strength, toughness or corrosion resistance result in weight savings, which translate to fuel economy over the lifetime of the aircraft. To meet these demands several other 7000-series type alloys have been developed:
EP-0377779 discloses an improved process for producing a 7055 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 to steps of working a body having a composition consisting of, in wt.%:
Zn: 7.6 - 8.4 Cu: 2.2 - 2.6 Mg: 1.8 - 2.1, one or more elements selected from Zr: 0.5 - 0.2 Mn: 0.05 - 0.4 V: 0.03 - 0.2 Hf: 0.03 - 0.5, the total of said elements not exceeding 0.6 wt.%, the balance aluminium plus 2o 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 7x50-T77 counterpart (AA7150-T77 will be used herein below as a reference alloy).
3o US-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- or two-step ageing process in conjunction with the stochiometrically balancing of copper, magnesium and zinc. A two-step ageing sequence is disclosed wherein the alloy is first aged at approx. 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, which are used for lower-wing, skin applications or fuselage skin.
US-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 Cu: 1.5 - 3.0 Mg: 1.5 - 4.0 1o Cr: < 0.04, other elements such as zirconium, manganese, iron, silicon and titanium in total less than 0.5, the balance aluminium, working the alloy into a product of a pre-determined shape, solution heat treating the reshaped product, quenching, and ageing the heat treated and quenched product to a temperature of from 132°C to 140°C for a period of from 6 to 30 hours. The desired properties of having high strength, high toughness and high corrosion resistance were achieved in this alloy by lowering the ageing temperature rather than raising the temperature as taught previously from e.g. US-3,881,966 or US-3,794,531.
It has been reported that the known precipitation-hardened aluminium alloys 2o 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-5,221,377 therefore discloses an alloy product consisting essentially of about 7.6 to 8.4 wt.% Zn, about 1.8 to 2.2 wt.% Mg and about 2.0 to 2.6 wt.%
Cu.
Such alloy product exhibits a yield strength, which is about 10 % greater than its 7x50-T6 counterpart with good toughness and corrosion resistance. The yield strength was reported to be over 579 MPa with an exfoliation resistance (EXCO) level of "EC" or better.
3o US-5,496,426 discloses an alloy as disclosed in US-5,221,377 and a process including hot rolling, annealing and cold rolling within a preferred cold reduction range of 20 % to 70 % which, in turn, is preferably followed by controlled annealing thereby displaying characteristics which are better than AA7075-T6 characteristics.
While the AA7075-T6 failed the stress corrosion resistance test (SCC
resistance 40 days in the 35% NaCI alternate immersion test) at 138 MPa the disclosed processed alloy had a SCC resistance of 241 MPa.
US-5,108,520 and US-4,477,292 disclose an ageing process for solution-heat-treated, precipitation hardening metal alloy including three steps of ageing, comprising (1) ageing the alloy at one or more temperatures substantially above room temperature but below 163°C to substantially below peak yield strength, (2) subsequently ageing the alloy at one or more temperatures at about 190°C for increasing the resistance of the alloy to corrosion and thereafter, (3) ageing the alloy at one or more temperatures substantially above room temperature but below about 163°C for increasing yield strength. The resultant product displayed good strengthw properties and a good corrosion performance. However, the three step to ageing procedure is cumbersome and difficult to perform so that the costs for producing such alloy increase.
It is therefore the object of the present invention to provide an improved AI-Zn alloy preferably for plate products with high strength and an improved balance of toughness and corrosion performance. More specifically, it is the object of the is present invention to provide an alloy, which can be used for upper wing applications in aerospace with an improved compression yield strength with properties, which are better than the properties of a conventional AA7055-alloy in the T77 temper.
It is another object of the invention to obtain an AA7000-series aluminium alloy, which exhibits strength in the range of T6-type tempers and toughness and 2o corrosion resistance properties in the range of T73-type tempers.
It is furthermore an object of the present invention to provide an alloy that can be used in an age-creep forming process, which is an alloy, which does not need a complicated or cumbersome ageing process.
The present invention has a number of preferred objects.
25 The above objects of the invention are achieved by using the characterizing features of claim 1. Further preferred embodiments are described and specified within the sub-claims. A preferred method to produce such alloy is defined in claim 9 and a respective plate product is claimed and described in claim 14 and corresponding sub-claims.
3o As will be appreciated herein below, except otherwise indicated, alloy designations and temper designations refer to the Aluminum Association designations in Aluminum Standards and Data and the Registration Records, all published by the US Aluminum Association. All percentages are in weight percents, unless otherwise indicated.
35 The above mentioned objects of the invention are achieved by using a high strength AI-Zn alloy product with an improved combination of corrosion resistance -S-and toughness, the alloy comprising essentially (in wt.%):
Zn about 6.0 to 9.5 Cu about 1.3 to 2.4 Mg about 1.5 to 2.6 Mn < 0.12 Zr < 0.20, and preferably 0.05 - 0.15 Cr < 0.10 Fe < 0.25, and preferably < 0.12 Si < 0.25, and preferably < 0.12 1o Ti < 0.10 Hf and/or V < 0.25, and optionally Ce and/or Sc < 0.20, especially in a range of 0.05 to 0.15, other elements each less than 0.05 and less than 0.25 in total, balance aluminium, wherein (in weight percent):
0.1 [Cu] + 1.3 < [Mg] < 0.2[Cu) + 2.15, and preferably 0.2[Cu] + 1.3 < [Mg] < 0.1 [Cu] + 2.15.
Such chemistry window for an AA7000-series alloy exhibits excellent properties when produced to thin plate products which is preferably useable in aerospace upper-wing applications.
2o The above-defined chemistry has properties, which are comparable or better than existing alloys of the AA7x50 or AA7x55 series in the T77-temper, without using the above-described cumbersome and complicated T77 ageing cycles. The chemistry leads to an aluminium product which is not only superior with regard to the question of costs but also simpler to produce since less processing steps are necessary. Additionally, the chemistry allows new manufacturing techniques like age creep forming which is not feasible when a T77-temper alloy is applied.
Even better, the chemistry as defined above can also be aged to the T77-temper wherein the corrosion resistance further improves as compared to the two-step ageing procedure, which is described herein below, wherein especially the exfoliation 3o corrosion performance is enhanced.
By way of this invention it has been found.that a selected range of elements, using a higher amount of Zn and a specific combination of a particular range of Mg and Cu, exhibit substantially better combinations of strength, toughness and corrosion performance such as exfoliation corrosion resistance and stress corrosion cracking resistance.
While it has been reported that copper contents should be maintained higher, preferably above about 2.2 wt.% in order to improve the exfoliation and stress corrosion cracking performance, better combinations of strength and density were reported to be achievable with relatively low zinc contents.
In this invention, however, it has been found that elevated amounts of zinc together with an optimised relation of magnesium to copper results in better strength while maintaining a good corrosion performance and a toughness which is better than conventional T77-temper alloys. It is therefore advantageous to have a combined zinc, magnesium and copper content in a range of between about 11.50 and 12.50 (in wt.%) without any manganese and below 11.00 in the presence of to manganese, which is preferably between 0.06 and 0.12 (in wt.%).
A preferred amount of magnesium is in a range of 0.2[Cu] + 1.3 < [Mg] <
0.1 [Cu] + 2.15, most preferably in a range of 0.2[Cu] + 1.4 < [Mg] < 0.1 [Cu]
+ 1.9.
Copper is in a range of about 1.5 to 2.1, more preferably in a range of 1.5 to less than 2Ø The balance of magnesium and copper is important for the inventive chemistry.
Copper and magnesium are important elements for adding strength to the alloy. 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. Prior art 2o techniques used special ageing procedures to ameliorate the strength and low amounts of magnesium and copper are used in order to achieve a good corrosion performance. In order to achieve a compromise in strength, toughness and corrosion performance copper and magnesium amounts (in wt.%) of between about 1.5 and 2.3 have been found to give a good balance for thick alloy products.
However, the corrosion performance is the vital parameter for thin alloy products so that less amounts of copper and magnesium must be used, thereby resulting in a lower strength. Throughout the claimed chemistry of the present invention it is now possible to achieve strength levels in the region of a T6-temper alloy while maintaining corrosion performance characteristics similar to those of T74-temper alloys.
Apart from the amounts of magnesium and copper the invention discloses a balance of magnesium and copper amounts to zinc, especially the balance of magnesium to zinc, which gives the alloy these performance characteristics.
The improved corrosion resistance of the alloy according to the invention has exfoliation resistance properties ("EXCO") of EB or better, preferably EA or better.
These exfoliation properties are measured in accordance with the standards for resistance to stress corrosion cracking ("SCC") and exfoliation resistance ("EXCO") currently required for AA7075, AA7050 and AA7150-products aged to the T73, T74 and T76, along with typical performance of T6, tempers. To determine whether commercial alloys. meet the SCC standards, a given test specimen is subjected to predefined test conditions. Bar-shaped specimens are exposed to cycles of immersing in a 3.5% NaCI aqueous solution for 10 minutes, followed by 50 minutes of air drying while being pulled from both ends under a constant strain (stress level). Such testing is usually carried out for a minimum of 20 days (or for less time should the specimen fail or crack before 20 days have passed). This test to is the ASTM standard G47 (G47-98) test.
Another preferred SCC-test, conducted in accordance with ASTM standard G47, (G38-73) is used for extruded alloy products that include thin plate products.
This test consists of compressing the opposite ends of a C-shaped ring using constant strain levels and alternate immersion conditions substantially similar to those as described above. While an AA7075, AA7050 or AA7150-T6 tempered alloy fails the SCC test in less than 20 days and while the exfoliation properties are EC or ED, the corrosion resistance performance increases with tempers T76-, T74-, T73. The exfoliation properties of T73 are EA or better. Specific examples are described herein below.
2o The inventive alloy has a chemistry with a preferred amount of magnesium and copper of about 1.93 when the amount (in wt.%) of zinc is about 8.1.
However, the amount (in wt.%) of zinc is in a range of 6.1 to 8.3, more preferably in a range of 6.1 to 7.0 if manganese is lower than 0.05, and preferably lower than 0.02.
Some preferred embodiments of the present invention are described within the examples herein below.
The amount of manganese (in wt.%) is preferably in a range of about 0.06 to 0.12 when the amount of zinc is above 7.6. Manganese contributes to or aids in grain size control during operations that can cause the alloy microstructure to recrystallize. The preferred levels of manganese are lower than in conventional 3o AA7000-series alloys but may be raised when zinc is raised.
The amount of the additional alloying elements Ce and/or Sc is smaller than 0.20, preferably in a range of 0.05 to 0.15, most preferably around 0.10.
A preferred method for producing a wrought high strength AI-Zn alloy product with an improved combination of corrosion resistance and toughness comprises the steps of -g_ a) ~ casting an ingot with the following composition (in weight percent):
Zn about 6.0 to 9.5 Cu about 1.3 to 2.4 Mg about 1.5 to 2.6 Mn < 0.12 Zr < 0.20, preferably 0.05 - 0.15 Cr < 0.10 Fe < 0.25 Si < 0.25 to Ti < 0.10 Hf and/or V < 0.25, optionally Ce and/or Sc < 0.20, other elements each less than 0.05 and less than 0.25 in total, balance aluminium, and wherein (in weight percent):
0.1 [Cu] + 1.3 < [Mg] < 0.2[Cu] + 2.15, b) homogenising and/or pre-heating the ingot after casting, c) hot working the ingot and optionally cold working into a worked product, d) solution heat treating at a temperature and time sufficient to place into solid solution essentially all soluble constituents in the alloy, and e) quenching the solution heat-treated product by one of spray quenching or 2o immersion quenching in water or other quenching media.
The properties of the invention may be further achieved throughout a preferred method which includes artificially ageing the worked and solution heat-treated product, wherein the ageing step comprises a first heat treatment at a temperature in a range of 105°C to 135°C, preferably around 120°C for 2 to 20 hours, preferably around 8 hours, and a second heat treatment at a higher temperature than 135°C but below 210°C, preferably around 155°C for 4 to 12 hours, preferably 8 to 10 hours.
Throughout such two-step aging treatment a corrosion performance is achieved which is similar to the corrosion performance of a T76-temper alloy.
3o However, it is also possible to artificially ageing the worked and heat treated product wherein the ageing step comprises a third heat treatment at a temperature in a range of 105°C to 135°C for more than 20 hours and less than 30 hours. This T77-temper ageing procedure is known and even increases the performance characteristics as compared to the two-step ageing procedure. However, the two-step ageing procedure results in thin aluminium alloy products, which are partially comparable and partially better than T77-temper products.
It is furthermore possible to artificially ageing the worked and heat-treated product with a two-step ageing procedure to a T79- or T76-temper. After homogenizing and/or pre-heating the ingot after casting it is preferably advisable to hot working the ingot and optionally cold working the hot worked products into a worked product of 15 mm to 45 mm, thereby obtaining a thin plate.
Such plate product of high strength AI-Zn alloy may be obtained by an alloy having a composition as described above or being produced in accordance with a method as described above. Such plate product is preferably useable as thin aircraft member, more preferably as an elongated structural shape member. Even 1o more preferred is a plate product for use as an upper-wing member, preferably a thin skin member of an upper-wing or of a stringer of an aircraft.
The foregoing and other features and advantages of the alloys according to the invention will become readily apparent from the following detailed description of preferred embodiments.
Example 1 Tests were performed comparing the performance of the alloy according to the present invention and AA7150-T77 alloys. It has been found that the examples of the alloy of the present invention show an improvement over conventional 2o AA7150-T77-temper alloys.
On an industrial scale four different aluminium alloys have been cast into ingots, homogenized, preheated for more than 6 hours at 410°C and hot rolled to 30 mm plates. Thereafter, the plates were solution heat treated at 475°C and water quenched. Thereafter, the quenched product was aged by a two-step T79-T76 ageing procedure. The chemical compositions are set out in Table 1.
Table 1 Chemical composition of thin plate alloys, in wt.%, balance aluminium and inevitable impurities, Alloys 1 to 4 with Mn _< 0.02:
Si Fe Cu Mn Mg Cr Zn Ti Zr Alloy 0.03 0.06 2.23 0.00 2.08 0.00 6.24 0.03 0.10 (7050) Alloy 0.05 0.08 2.05 0.01 2.04 0.01 6.18 0.04 0.11 Alloy 0.05 0.09 2.20 0.01 2.30 0.01 7.03 0.04 0.10 Alloy 0.04 0.07 1.91 0.02 2.13 0.00 6.94 0.03 0.11 The aged alloys were thereafter tested in accordance with the following test conditions:
Tensile yield strength was measured according to EN 10.002, exfoliation resistance properties ("EXCO") were measured according to ASTM G-34-97, stress corrosion cracking ("SCC") was measured according to ASTM G-47-98, all in ST-direction, Kahn-Tear (toughness) was measured according to ASTM E-399 and the compression yield strength ("CYS") was measured according to ASTM E-9.
The results of the T79-T76 aged plate products of the four alloys as shown in Table 1 are shown in Table 2a when compared with conventional AA7150-T77 1o tempered alloys, and in Table 2b when compared with conventional AA7150-T76/T74/T6 tempered alloys:
Table 2a Overview of strength and toughness of the alloys of Table 1 (30 mm plates) compared to three reference alloys (AA7150-T77); alloys 1 to 4 aged to T79-T76:
Rp-L CYS-LT EXCO K~~-LT
(MPa) (MPa) (MPa~m) Alloy 1 555 565 EC 35.1 Alloy 2 561 604 EA/B 34.5 Alloy 3 565 590 EB 29.1 Alloy 4 591 632 EB 28.9 AA7150-T77 586 - EB 28.6 AA7150-T77 579 - EB 29.2 AA7150-T77 537 - EA 33.2 NF = no failure after 40 days.
Table 2b Overview of corrosion performance of the alloys of Table 1 (30 mm plates) compared to three reference alloys (AA7150-T76, AA7150-T74, AA7150-T6); alloys 1-4 aged to T79-T76:
SCC threshold Alloy 1 NF at 172 MPa Alloy 2 NF at 240 MPa Alloy 3 NF at 240 MPa Alloy 4 NF at 240 MPa AA7150-T76 117 - 172 MPa AA7150-T74 240 MPa AA7150-T6 < 48 MPa NF = no failure after 40 days.
As can be seen from Table 2a,b alloys 1, 2 and 4 show better strength/toughness combinations. Alloys 2, 3 and 4 all have an acceptable EXCO
performance wherein alloys 2, 3 and 4 have a significant higher compression yield 1o strength than alloy No. 1 (AA7050-alloy). Alloys 2 and 4 exhibit a property balance that makes them very suitable for upper-wing applications in aerospace thereby showing a balance of properties, which is better than those of conventional T77 alloys. However, it is still possible to use a T77-temper for the inventive alloys as shown in Table 3.
Table 3 Alloys 2 and 4 tempered according to T77 temper conditions, overview of strength, toughness and corrosion performance.
Rp-L CYS-LT EXCO K~~-LT SCC threshold (MPa) (MPa) (MPa~m) Alloy 585 613 EA 32.2 NF at 240 MPa Alloy 607 641 EA 26.4 NF at 240 MPa 2o Further SCC testing was performed on the promising alloy No. 4 wherein alloy 4-samples were prepared according to the procedure described in ASTM G-47-98 (standard test methods for determining susceptibility to stress corrosion cracking of AA7000-series aluminium alloy products) and exposed to the corrosive atmosphere according to ASTM G-44-94 (alternate immersion in accordance with the standard practice for evaluating stress corrosion cracking resistance of metals and alloys by alternate immersion in 3.5% NaCI solution).
Four different stress levels were chosen for samples of alloy 4 as shown in Table 4. For each stress level three samples were exposed to the test environment s (ASTM G-44). One was taken out after 1 week while the other two were exposed for 40 days. When no cracking had occurred during the exposure the tensile properties were determined as shown in Table 4.
Table 4 1o Overview of tensile strength properties of alloy 4 after exposure to four different stress levels, pre-stress was acting in LT direction.
Alloy 4 Pre-stress Tensile strength [MPa]
[MPa] 1 week 40 days 300 524.3 428.0 340 513.1 416.9 380 503.1 424.5 420 515.5 425.1 As can be seen from Table 4, no decrease in residual strength was measured with increasing load, which means that no measurable stress corrosion appeared is after 40 days as far as tensile strength properties are concerned.
Example 2 When higher strength levels are required and toughness properties are less important conventional AA7055-T77 alloys are preferred instead of AA7150-T77 2o alloys as an alloy for upper wing applications. The present invention therefore discloses optimised copper and magnesium windows, which show properties equal or better than conventional AA7055-T77 alloys.
11 different aluminium alloys were cast into ingots having the following chemical composition as set out in Table 5.
2s Table 5 Chemical composition of 11 alloys, in wt.%, balance aluminium and inevitable impurities, Zr = 0.08, Si = 0.05, Fe = 0.08.
Alloy Cu Mg Zn Mn 1 2.40 2.20 8.2 0.00 2 1.94 2.33 8.2 0.00 3 1.26 2.32 8.1 0.00 4 2.36 1.94 8.1 0.00 1.94 1.92 8.1 0.00 6 1.30 2.09 8.2 0.00 7 1.92 1.54 8.1 0.00 8 1.27 1.57 8.1 0.00 9 2.34 2.25 8.1 0.07 2.38 2.09 8.1 0.00 11 2.35 1.53 8.2 0.00 5 Strength and toughness properties were measured after pre-heating the cast alloys for 6 hours at 410°C and then hot rolling the alloys to a gauge of 28 mm.
Thereafter, solution heat treating was applied at 475°C and water quenching.
Ageing was done for 8 hours at 120°C and 8 to 10 hours at 155°C (T79-T76-temper). The results are shown in Table 6.
Table 6 Overview of strength and toughness of 11 alloys according to Table 5 in the identified directions.
Rp Rm Kq Alloy L LT L LT L - T
1 628 596 651 633 28.9 2 614 561 642 604 29.3 3 566 544 596 582 39.0 4 614 568 638 604 33.0 595 556 620 590 37.1 6 562 513 590 552 38.6 7 549 509 573 542 41.7 8 530 484 556 522 41.9 9 628 584 644 618 26.6 614 575 631 606 28.1 11 568 529 594 568 36.6 5 While alloys 3 to 8 and 11 displayed good toughness properties alloys 1 to 5 and 9 and 10 displayed good strength properties. Hence, alloys 3, 4 and 5 show a good balance of strength and toughness so that it is clear to have a copper content of above 1.3 and a magnesium content of above 1.6 (in wt.%) when zinc is present in an amount of 8.1. Such amounts are lower limits for the copper and magnesium 1o windows. As can be seen from Table 6 the toughness will drop to un-acceptable low-levels when copper and magnesium levels are too high (alloys 1, 2, 9 and 10).
Example 3 The influence of manganese was investigated on the properties of the inventive alloy. An optimum manganese level was found between 0.05 and 0.12 in alloys with a high amount of zinc. The results are shown in Tables 7 and 8.
All not mentioned chemistry properties and processing parameters are similar to those of Example 2.
Table 7 Chemical composition of three alloys (Mn-0, Mn-1 and Mn-2), in wt.%, balance aluminium and inevitable impurities, Zr = 0.08, Si = 0.05, Fe = 0.08.
Alloy Cu Mg Zn Mn M n-0 1. 94 2. 33 8.2 0. 00 Mn-1 1.94 2.27 8.1 0.06 Mn-2 1.96 2.29 8.2 0.12 Table 8 Overview of strength and toughness of three alloys according to Table 7 in the identified directions.
AI loy Rp Rm Kq L LT L LT L - T
Mn-0 614 561 642 604 29.3 Mn-1 612 562 635 602 31.9 Mn-2 612 560 639 596 29.9 As shown in Table 8 the toughness properties decrease while strength to properties increase. For alloys with high amounts of zinc an optimised manganese level is between 0.05 and 0.12.
Example 4 When higher strength levels are required and toughness properties are less important conventional AA7055-T77 alloys are preferred instead of AA7150-T77 alloys as an alloy for upper wing applications. The present invention therefore discloses optimised copper and magnesium windows, which show properties equal or better to conventional AA7055-T77 alloys.
Two different aluminium alloys were cast into ingots having the following 2o chemical composition as set out in Table 9.
Table 9 Chemical composition of three alloys, in wt.%, balance aluminium and inevitable impurities, Zr = 0.08, Si = 0.05, Fe = 0.08; (Ref = AA7055 alloy).
Alloy Si Fe Cu Mn Mg Cr Zn Ti Zr 1 0.05 0.09 2.24 0.01 2.37 0.01 7.89 0.04 0.10 2 0.04 0.07 1.82 0.08 2.18 0.00 8.04 0.03 0.10 Ref. 2.1- 1.8- 7.6-2.6 2.2 8.4 ~ Alloys 1 and 2 were tested with regard to their strength properties. These properties are shown in Table 10. Alloy 2 has been tempered in accordance with two temper conditions (T79-T76 and T77). Reference alloy AA7055 has been measured in T77 temper (M-Ref) while the technical data of an AA7055 reference alloy in a T77 temper are given as well (as identified by Ref).
to Table 10 Overview of strength of the two inventive alloys of Table 9, alloy No. 2 in two temper conditions, reference alloy (AA7055) measured (M-Ref) and tech sheet (Ref).
Alloy Temper Rp-L Rp-LT Rp-ST Rm-L Rm-LT Rm-ST
Ref T77 614 614 - 634 641 -M-Ref T77 621 611 537 638 634 599 The toughness properties in LT and TL direction as well as the compression yield strength properties in L and LT direction as well as the corrosion performance characteristics are shown in Table 11.
Table 11 Toughness and CYS properties of the two inventive alloys of Table 9 in different temper conditions and different test directions, NF = no failure after 40 days at designated stress levels, otherwise days are stated after which the specimen failed.
Alloy Temper K,~ K,~ CYS-L CYS-LT EXCO SCC
(L-T) (T-L) 1 T79-T76 21.0 - 596 621 EC 2,3,8 2 T79-T76 28.9 27.1 630 660 EB NF at 172MPa 2 T77 28.8 26.5 628 656 EA NF at 210MPa Ref T77 28.6 26.4 621 648 EB NF at 103MPa M-Ref T77 - - - - EB NF at 103MPa s The inventive alloy has similar tensile properties as a conventional AA7055-T77 alloy. However, the properties in the ST direction are better than those of the conventional AA7055-T77 alloy. Also the stress corrosion performance is better than of an AA055-T77 alloy. The inventive alloy can therefore be used as an 1o inexpensive substitute for AA7055-T77 tempered alloys which is also useable for age-creep forming, thereby showing a superior compression yield strength and corrosion resistance.
Having now fully described the invention, it will be apparent to one of ordinary skill in the art that many changes and modifications can be made without departing is from the spirit or scope of the invention as herein described. The present invention is defined by the claims appended hereto.
It is known in the art to use heat treatable aluminium alloys in a number of applications involving relatively high strength, high toughness and corrosion resistance such as aircraft fuselages, vehicular members and other applications.
Aluminium alloys AA7050 and AA7150 exhibit high strength in T6-type tempers, see e.g. US-6,315,842. Also precipitation-hardened AA7x75, AA7x55 alloy products 2o exhibit high strength values in the T6 temper. The T6 temper is known to enhance the strength of the alloy, wherein the aforementioned AA7x50, AA7x75 and AA7x55 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. However, 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.
In order to enhance resistance against stress corrosion and exfoliation as well as fracture toughness it is known to artificially over-age these AA7000-series alloys.
3o When artificially aged to a 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 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 T74 temper is performed by CONFIRMATION COPY
over-ageing the aluminium alloy product at temperatures of 121 °C for 6 to 24 hours and 171 °C for about 14 hours.
Depending on the design criteria for a particular airplane component even small improvements in strength, toughness or corrosion resistance result in weight savings, which translate to fuel economy over the lifetime of the aircraft. To meet these demands several other 7000-series type alloys have been developed:
EP-0377779 discloses an improved process for producing a 7055 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 to steps of working a body having a composition consisting of, in wt.%:
Zn: 7.6 - 8.4 Cu: 2.2 - 2.6 Mg: 1.8 - 2.1, one or more elements selected from Zr: 0.5 - 0.2 Mn: 0.05 - 0.4 V: 0.03 - 0.2 Hf: 0.03 - 0.5, the total of said elements not exceeding 0.6 wt.%, the balance aluminium plus 2o 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 7x50-T77 counterpart (AA7150-T77 will be used herein below as a reference alloy).
3o US-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- or two-step ageing process in conjunction with the stochiometrically balancing of copper, magnesium and zinc. A two-step ageing sequence is disclosed wherein the alloy is first aged at approx. 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, which are used for lower-wing, skin applications or fuselage skin.
US-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 Cu: 1.5 - 3.0 Mg: 1.5 - 4.0 1o Cr: < 0.04, other elements such as zirconium, manganese, iron, silicon and titanium in total less than 0.5, the balance aluminium, working the alloy into a product of a pre-determined shape, solution heat treating the reshaped product, quenching, and ageing the heat treated and quenched product to a temperature of from 132°C to 140°C for a period of from 6 to 30 hours. The desired properties of having high strength, high toughness and high corrosion resistance were achieved in this alloy by lowering the ageing temperature rather than raising the temperature as taught previously from e.g. US-3,881,966 or US-3,794,531.
It has been reported that the known precipitation-hardened aluminium alloys 2o 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-5,221,377 therefore discloses an alloy product consisting essentially of about 7.6 to 8.4 wt.% Zn, about 1.8 to 2.2 wt.% Mg and about 2.0 to 2.6 wt.%
Cu.
Such alloy product exhibits a yield strength, which is about 10 % greater than its 7x50-T6 counterpart with good toughness and corrosion resistance. The yield strength was reported to be over 579 MPa with an exfoliation resistance (EXCO) level of "EC" or better.
3o US-5,496,426 discloses an alloy as disclosed in US-5,221,377 and a process including hot rolling, annealing and cold rolling within a preferred cold reduction range of 20 % to 70 % which, in turn, is preferably followed by controlled annealing thereby displaying characteristics which are better than AA7075-T6 characteristics.
While the AA7075-T6 failed the stress corrosion resistance test (SCC
resistance 40 days in the 35% NaCI alternate immersion test) at 138 MPa the disclosed processed alloy had a SCC resistance of 241 MPa.
US-5,108,520 and US-4,477,292 disclose an ageing process for solution-heat-treated, precipitation hardening metal alloy including three steps of ageing, comprising (1) ageing the alloy at one or more temperatures substantially above room temperature but below 163°C to substantially below peak yield strength, (2) subsequently ageing the alloy at one or more temperatures at about 190°C for increasing the resistance of the alloy to corrosion and thereafter, (3) ageing the alloy at one or more temperatures substantially above room temperature but below about 163°C for increasing yield strength. The resultant product displayed good strengthw properties and a good corrosion performance. However, the three step to ageing procedure is cumbersome and difficult to perform so that the costs for producing such alloy increase.
It is therefore the object of the present invention to provide an improved AI-Zn alloy preferably for plate products with high strength and an improved balance of toughness and corrosion performance. More specifically, it is the object of the is present invention to provide an alloy, which can be used for upper wing applications in aerospace with an improved compression yield strength with properties, which are better than the properties of a conventional AA7055-alloy in the T77 temper.
It is another object of the invention to obtain an AA7000-series aluminium alloy, which exhibits strength in the range of T6-type tempers and toughness and 2o corrosion resistance properties in the range of T73-type tempers.
It is furthermore an object of the present invention to provide an alloy that can be used in an age-creep forming process, which is an alloy, which does not need a complicated or cumbersome ageing process.
The present invention has a number of preferred objects.
25 The above objects of the invention are achieved by using the characterizing features of claim 1. Further preferred embodiments are described and specified within the sub-claims. A preferred method to produce such alloy is defined in claim 9 and a respective plate product is claimed and described in claim 14 and corresponding sub-claims.
3o As will be appreciated herein below, except otherwise indicated, alloy designations and temper designations refer to the Aluminum Association designations in Aluminum Standards and Data and the Registration Records, all published by the US Aluminum Association. All percentages are in weight percents, unless otherwise indicated.
35 The above mentioned objects of the invention are achieved by using a high strength AI-Zn alloy product with an improved combination of corrosion resistance -S-and toughness, the alloy comprising essentially (in wt.%):
Zn about 6.0 to 9.5 Cu about 1.3 to 2.4 Mg about 1.5 to 2.6 Mn < 0.12 Zr < 0.20, and preferably 0.05 - 0.15 Cr < 0.10 Fe < 0.25, and preferably < 0.12 Si < 0.25, and preferably < 0.12 1o Ti < 0.10 Hf and/or V < 0.25, and optionally Ce and/or Sc < 0.20, especially in a range of 0.05 to 0.15, other elements each less than 0.05 and less than 0.25 in total, balance aluminium, wherein (in weight percent):
0.1 [Cu] + 1.3 < [Mg] < 0.2[Cu) + 2.15, and preferably 0.2[Cu] + 1.3 < [Mg] < 0.1 [Cu] + 2.15.
Such chemistry window for an AA7000-series alloy exhibits excellent properties when produced to thin plate products which is preferably useable in aerospace upper-wing applications.
2o The above-defined chemistry has properties, which are comparable or better than existing alloys of the AA7x50 or AA7x55 series in the T77-temper, without using the above-described cumbersome and complicated T77 ageing cycles. The chemistry leads to an aluminium product which is not only superior with regard to the question of costs but also simpler to produce since less processing steps are necessary. Additionally, the chemistry allows new manufacturing techniques like age creep forming which is not feasible when a T77-temper alloy is applied.
Even better, the chemistry as defined above can also be aged to the T77-temper wherein the corrosion resistance further improves as compared to the two-step ageing procedure, which is described herein below, wherein especially the exfoliation 3o corrosion performance is enhanced.
By way of this invention it has been found.that a selected range of elements, using a higher amount of Zn and a specific combination of a particular range of Mg and Cu, exhibit substantially better combinations of strength, toughness and corrosion performance such as exfoliation corrosion resistance and stress corrosion cracking resistance.
While it has been reported that copper contents should be maintained higher, preferably above about 2.2 wt.% in order to improve the exfoliation and stress corrosion cracking performance, better combinations of strength and density were reported to be achievable with relatively low zinc contents.
In this invention, however, it has been found that elevated amounts of zinc together with an optimised relation of magnesium to copper results in better strength while maintaining a good corrosion performance and a toughness which is better than conventional T77-temper alloys. It is therefore advantageous to have a combined zinc, magnesium and copper content in a range of between about 11.50 and 12.50 (in wt.%) without any manganese and below 11.00 in the presence of to manganese, which is preferably between 0.06 and 0.12 (in wt.%).
A preferred amount of magnesium is in a range of 0.2[Cu] + 1.3 < [Mg] <
0.1 [Cu] + 2.15, most preferably in a range of 0.2[Cu] + 1.4 < [Mg] < 0.1 [Cu]
+ 1.9.
Copper is in a range of about 1.5 to 2.1, more preferably in a range of 1.5 to less than 2Ø The balance of magnesium and copper is important for the inventive chemistry.
Copper and magnesium are important elements for adding strength to the alloy. 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. Prior art 2o techniques used special ageing procedures to ameliorate the strength and low amounts of magnesium and copper are used in order to achieve a good corrosion performance. In order to achieve a compromise in strength, toughness and corrosion performance copper and magnesium amounts (in wt.%) of between about 1.5 and 2.3 have been found to give a good balance for thick alloy products.
However, the corrosion performance is the vital parameter for thin alloy products so that less amounts of copper and magnesium must be used, thereby resulting in a lower strength. Throughout the claimed chemistry of the present invention it is now possible to achieve strength levels in the region of a T6-temper alloy while maintaining corrosion performance characteristics similar to those of T74-temper alloys.
Apart from the amounts of magnesium and copper the invention discloses a balance of magnesium and copper amounts to zinc, especially the balance of magnesium to zinc, which gives the alloy these performance characteristics.
The improved corrosion resistance of the alloy according to the invention has exfoliation resistance properties ("EXCO") of EB or better, preferably EA or better.
These exfoliation properties are measured in accordance with the standards for resistance to stress corrosion cracking ("SCC") and exfoliation resistance ("EXCO") currently required for AA7075, AA7050 and AA7150-products aged to the T73, T74 and T76, along with typical performance of T6, tempers. To determine whether commercial alloys. meet the SCC standards, a given test specimen is subjected to predefined test conditions. Bar-shaped specimens are exposed to cycles of immersing in a 3.5% NaCI aqueous solution for 10 minutes, followed by 50 minutes of air drying while being pulled from both ends under a constant strain (stress level). Such testing is usually carried out for a minimum of 20 days (or for less time should the specimen fail or crack before 20 days have passed). This test to is the ASTM standard G47 (G47-98) test.
Another preferred SCC-test, conducted in accordance with ASTM standard G47, (G38-73) is used for extruded alloy products that include thin plate products.
This test consists of compressing the opposite ends of a C-shaped ring using constant strain levels and alternate immersion conditions substantially similar to those as described above. While an AA7075, AA7050 or AA7150-T6 tempered alloy fails the SCC test in less than 20 days and while the exfoliation properties are EC or ED, the corrosion resistance performance increases with tempers T76-, T74-, T73. The exfoliation properties of T73 are EA or better. Specific examples are described herein below.
2o The inventive alloy has a chemistry with a preferred amount of magnesium and copper of about 1.93 when the amount (in wt.%) of zinc is about 8.1.
However, the amount (in wt.%) of zinc is in a range of 6.1 to 8.3, more preferably in a range of 6.1 to 7.0 if manganese is lower than 0.05, and preferably lower than 0.02.
Some preferred embodiments of the present invention are described within the examples herein below.
The amount of manganese (in wt.%) is preferably in a range of about 0.06 to 0.12 when the amount of zinc is above 7.6. Manganese contributes to or aids in grain size control during operations that can cause the alloy microstructure to recrystallize. The preferred levels of manganese are lower than in conventional 3o AA7000-series alloys but may be raised when zinc is raised.
The amount of the additional alloying elements Ce and/or Sc is smaller than 0.20, preferably in a range of 0.05 to 0.15, most preferably around 0.10.
A preferred method for producing a wrought high strength AI-Zn alloy product with an improved combination of corrosion resistance and toughness comprises the steps of -g_ a) ~ casting an ingot with the following composition (in weight percent):
Zn about 6.0 to 9.5 Cu about 1.3 to 2.4 Mg about 1.5 to 2.6 Mn < 0.12 Zr < 0.20, preferably 0.05 - 0.15 Cr < 0.10 Fe < 0.25 Si < 0.25 to Ti < 0.10 Hf and/or V < 0.25, optionally Ce and/or Sc < 0.20, other elements each less than 0.05 and less than 0.25 in total, balance aluminium, and wherein (in weight percent):
0.1 [Cu] + 1.3 < [Mg] < 0.2[Cu] + 2.15, b) homogenising and/or pre-heating the ingot after casting, c) hot working the ingot and optionally cold working into a worked product, d) solution heat treating at a temperature and time sufficient to place into solid solution essentially all soluble constituents in the alloy, and e) quenching the solution heat-treated product by one of spray quenching or 2o immersion quenching in water or other quenching media.
The properties of the invention may be further achieved throughout a preferred method which includes artificially ageing the worked and solution heat-treated product, wherein the ageing step comprises a first heat treatment at a temperature in a range of 105°C to 135°C, preferably around 120°C for 2 to 20 hours, preferably around 8 hours, and a second heat treatment at a higher temperature than 135°C but below 210°C, preferably around 155°C for 4 to 12 hours, preferably 8 to 10 hours.
Throughout such two-step aging treatment a corrosion performance is achieved which is similar to the corrosion performance of a T76-temper alloy.
3o However, it is also possible to artificially ageing the worked and heat treated product wherein the ageing step comprises a third heat treatment at a temperature in a range of 105°C to 135°C for more than 20 hours and less than 30 hours. This T77-temper ageing procedure is known and even increases the performance characteristics as compared to the two-step ageing procedure. However, the two-step ageing procedure results in thin aluminium alloy products, which are partially comparable and partially better than T77-temper products.
It is furthermore possible to artificially ageing the worked and heat-treated product with a two-step ageing procedure to a T79- or T76-temper. After homogenizing and/or pre-heating the ingot after casting it is preferably advisable to hot working the ingot and optionally cold working the hot worked products into a worked product of 15 mm to 45 mm, thereby obtaining a thin plate.
Such plate product of high strength AI-Zn alloy may be obtained by an alloy having a composition as described above or being produced in accordance with a method as described above. Such plate product is preferably useable as thin aircraft member, more preferably as an elongated structural shape member. Even 1o more preferred is a plate product for use as an upper-wing member, preferably a thin skin member of an upper-wing or of a stringer of an aircraft.
The foregoing and other features and advantages of the alloys according to the invention will become readily apparent from the following detailed description of preferred embodiments.
Example 1 Tests were performed comparing the performance of the alloy according to the present invention and AA7150-T77 alloys. It has been found that the examples of the alloy of the present invention show an improvement over conventional 2o AA7150-T77-temper alloys.
On an industrial scale four different aluminium alloys have been cast into ingots, homogenized, preheated for more than 6 hours at 410°C and hot rolled to 30 mm plates. Thereafter, the plates were solution heat treated at 475°C and water quenched. Thereafter, the quenched product was aged by a two-step T79-T76 ageing procedure. The chemical compositions are set out in Table 1.
Table 1 Chemical composition of thin plate alloys, in wt.%, balance aluminium and inevitable impurities, Alloys 1 to 4 with Mn _< 0.02:
Si Fe Cu Mn Mg Cr Zn Ti Zr Alloy 0.03 0.06 2.23 0.00 2.08 0.00 6.24 0.03 0.10 (7050) Alloy 0.05 0.08 2.05 0.01 2.04 0.01 6.18 0.04 0.11 Alloy 0.05 0.09 2.20 0.01 2.30 0.01 7.03 0.04 0.10 Alloy 0.04 0.07 1.91 0.02 2.13 0.00 6.94 0.03 0.11 The aged alloys were thereafter tested in accordance with the following test conditions:
Tensile yield strength was measured according to EN 10.002, exfoliation resistance properties ("EXCO") were measured according to ASTM G-34-97, stress corrosion cracking ("SCC") was measured according to ASTM G-47-98, all in ST-direction, Kahn-Tear (toughness) was measured according to ASTM E-399 and the compression yield strength ("CYS") was measured according to ASTM E-9.
The results of the T79-T76 aged plate products of the four alloys as shown in Table 1 are shown in Table 2a when compared with conventional AA7150-T77 1o tempered alloys, and in Table 2b when compared with conventional AA7150-T76/T74/T6 tempered alloys:
Table 2a Overview of strength and toughness of the alloys of Table 1 (30 mm plates) compared to three reference alloys (AA7150-T77); alloys 1 to 4 aged to T79-T76:
Rp-L CYS-LT EXCO K~~-LT
(MPa) (MPa) (MPa~m) Alloy 1 555 565 EC 35.1 Alloy 2 561 604 EA/B 34.5 Alloy 3 565 590 EB 29.1 Alloy 4 591 632 EB 28.9 AA7150-T77 586 - EB 28.6 AA7150-T77 579 - EB 29.2 AA7150-T77 537 - EA 33.2 NF = no failure after 40 days.
Table 2b Overview of corrosion performance of the alloys of Table 1 (30 mm plates) compared to three reference alloys (AA7150-T76, AA7150-T74, AA7150-T6); alloys 1-4 aged to T79-T76:
SCC threshold Alloy 1 NF at 172 MPa Alloy 2 NF at 240 MPa Alloy 3 NF at 240 MPa Alloy 4 NF at 240 MPa AA7150-T76 117 - 172 MPa AA7150-T74 240 MPa AA7150-T6 < 48 MPa NF = no failure after 40 days.
As can be seen from Table 2a,b alloys 1, 2 and 4 show better strength/toughness combinations. Alloys 2, 3 and 4 all have an acceptable EXCO
performance wherein alloys 2, 3 and 4 have a significant higher compression yield 1o strength than alloy No. 1 (AA7050-alloy). Alloys 2 and 4 exhibit a property balance that makes them very suitable for upper-wing applications in aerospace thereby showing a balance of properties, which is better than those of conventional T77 alloys. However, it is still possible to use a T77-temper for the inventive alloys as shown in Table 3.
Table 3 Alloys 2 and 4 tempered according to T77 temper conditions, overview of strength, toughness and corrosion performance.
Rp-L CYS-LT EXCO K~~-LT SCC threshold (MPa) (MPa) (MPa~m) Alloy 585 613 EA 32.2 NF at 240 MPa Alloy 607 641 EA 26.4 NF at 240 MPa 2o Further SCC testing was performed on the promising alloy No. 4 wherein alloy 4-samples were prepared according to the procedure described in ASTM G-47-98 (standard test methods for determining susceptibility to stress corrosion cracking of AA7000-series aluminium alloy products) and exposed to the corrosive atmosphere according to ASTM G-44-94 (alternate immersion in accordance with the standard practice for evaluating stress corrosion cracking resistance of metals and alloys by alternate immersion in 3.5% NaCI solution).
Four different stress levels were chosen for samples of alloy 4 as shown in Table 4. For each stress level three samples were exposed to the test environment s (ASTM G-44). One was taken out after 1 week while the other two were exposed for 40 days. When no cracking had occurred during the exposure the tensile properties were determined as shown in Table 4.
Table 4 1o Overview of tensile strength properties of alloy 4 after exposure to four different stress levels, pre-stress was acting in LT direction.
Alloy 4 Pre-stress Tensile strength [MPa]
[MPa] 1 week 40 days 300 524.3 428.0 340 513.1 416.9 380 503.1 424.5 420 515.5 425.1 As can be seen from Table 4, no decrease in residual strength was measured with increasing load, which means that no measurable stress corrosion appeared is after 40 days as far as tensile strength properties are concerned.
Example 2 When higher strength levels are required and toughness properties are less important conventional AA7055-T77 alloys are preferred instead of AA7150-T77 2o alloys as an alloy for upper wing applications. The present invention therefore discloses optimised copper and magnesium windows, which show properties equal or better than conventional AA7055-T77 alloys.
11 different aluminium alloys were cast into ingots having the following chemical composition as set out in Table 5.
2s Table 5 Chemical composition of 11 alloys, in wt.%, balance aluminium and inevitable impurities, Zr = 0.08, Si = 0.05, Fe = 0.08.
Alloy Cu Mg Zn Mn 1 2.40 2.20 8.2 0.00 2 1.94 2.33 8.2 0.00 3 1.26 2.32 8.1 0.00 4 2.36 1.94 8.1 0.00 1.94 1.92 8.1 0.00 6 1.30 2.09 8.2 0.00 7 1.92 1.54 8.1 0.00 8 1.27 1.57 8.1 0.00 9 2.34 2.25 8.1 0.07 2.38 2.09 8.1 0.00 11 2.35 1.53 8.2 0.00 5 Strength and toughness properties were measured after pre-heating the cast alloys for 6 hours at 410°C and then hot rolling the alloys to a gauge of 28 mm.
Thereafter, solution heat treating was applied at 475°C and water quenching.
Ageing was done for 8 hours at 120°C and 8 to 10 hours at 155°C (T79-T76-temper). The results are shown in Table 6.
Table 6 Overview of strength and toughness of 11 alloys according to Table 5 in the identified directions.
Rp Rm Kq Alloy L LT L LT L - T
1 628 596 651 633 28.9 2 614 561 642 604 29.3 3 566 544 596 582 39.0 4 614 568 638 604 33.0 595 556 620 590 37.1 6 562 513 590 552 38.6 7 549 509 573 542 41.7 8 530 484 556 522 41.9 9 628 584 644 618 26.6 614 575 631 606 28.1 11 568 529 594 568 36.6 5 While alloys 3 to 8 and 11 displayed good toughness properties alloys 1 to 5 and 9 and 10 displayed good strength properties. Hence, alloys 3, 4 and 5 show a good balance of strength and toughness so that it is clear to have a copper content of above 1.3 and a magnesium content of above 1.6 (in wt.%) when zinc is present in an amount of 8.1. Such amounts are lower limits for the copper and magnesium 1o windows. As can be seen from Table 6 the toughness will drop to un-acceptable low-levels when copper and magnesium levels are too high (alloys 1, 2, 9 and 10).
Example 3 The influence of manganese was investigated on the properties of the inventive alloy. An optimum manganese level was found between 0.05 and 0.12 in alloys with a high amount of zinc. The results are shown in Tables 7 and 8.
All not mentioned chemistry properties and processing parameters are similar to those of Example 2.
Table 7 Chemical composition of three alloys (Mn-0, Mn-1 and Mn-2), in wt.%, balance aluminium and inevitable impurities, Zr = 0.08, Si = 0.05, Fe = 0.08.
Alloy Cu Mg Zn Mn M n-0 1. 94 2. 33 8.2 0. 00 Mn-1 1.94 2.27 8.1 0.06 Mn-2 1.96 2.29 8.2 0.12 Table 8 Overview of strength and toughness of three alloys according to Table 7 in the identified directions.
AI loy Rp Rm Kq L LT L LT L - T
Mn-0 614 561 642 604 29.3 Mn-1 612 562 635 602 31.9 Mn-2 612 560 639 596 29.9 As shown in Table 8 the toughness properties decrease while strength to properties increase. For alloys with high amounts of zinc an optimised manganese level is between 0.05 and 0.12.
Example 4 When higher strength levels are required and toughness properties are less important conventional AA7055-T77 alloys are preferred instead of AA7150-T77 alloys as an alloy for upper wing applications. The present invention therefore discloses optimised copper and magnesium windows, which show properties equal or better to conventional AA7055-T77 alloys.
Two different aluminium alloys were cast into ingots having the following 2o chemical composition as set out in Table 9.
Table 9 Chemical composition of three alloys, in wt.%, balance aluminium and inevitable impurities, Zr = 0.08, Si = 0.05, Fe = 0.08; (Ref = AA7055 alloy).
Alloy Si Fe Cu Mn Mg Cr Zn Ti Zr 1 0.05 0.09 2.24 0.01 2.37 0.01 7.89 0.04 0.10 2 0.04 0.07 1.82 0.08 2.18 0.00 8.04 0.03 0.10 Ref. 2.1- 1.8- 7.6-2.6 2.2 8.4 ~ Alloys 1 and 2 were tested with regard to their strength properties. These properties are shown in Table 10. Alloy 2 has been tempered in accordance with two temper conditions (T79-T76 and T77). Reference alloy AA7055 has been measured in T77 temper (M-Ref) while the technical data of an AA7055 reference alloy in a T77 temper are given as well (as identified by Ref).
to Table 10 Overview of strength of the two inventive alloys of Table 9, alloy No. 2 in two temper conditions, reference alloy (AA7055) measured (M-Ref) and tech sheet (Ref).
Alloy Temper Rp-L Rp-LT Rp-ST Rm-L Rm-LT Rm-ST
Ref T77 614 614 - 634 641 -M-Ref T77 621 611 537 638 634 599 The toughness properties in LT and TL direction as well as the compression yield strength properties in L and LT direction as well as the corrosion performance characteristics are shown in Table 11.
Table 11 Toughness and CYS properties of the two inventive alloys of Table 9 in different temper conditions and different test directions, NF = no failure after 40 days at designated stress levels, otherwise days are stated after which the specimen failed.
Alloy Temper K,~ K,~ CYS-L CYS-LT EXCO SCC
(L-T) (T-L) 1 T79-T76 21.0 - 596 621 EC 2,3,8 2 T79-T76 28.9 27.1 630 660 EB NF at 172MPa 2 T77 28.8 26.5 628 656 EA NF at 210MPa Ref T77 28.6 26.4 621 648 EB NF at 103MPa M-Ref T77 - - - - EB NF at 103MPa s The inventive alloy has similar tensile properties as a conventional AA7055-T77 alloy. However, the properties in the ST direction are better than those of the conventional AA7055-T77 alloy. Also the stress corrosion performance is better than of an AA055-T77 alloy. The inventive alloy can therefore be used as an 1o inexpensive substitute for AA7055-T77 tempered alloys which is also useable for age-creep forming, thereby showing a superior compression yield strength and corrosion resistance.
Having now fully described the invention, it will be apparent to one of ordinary skill in the art that many changes and modifications can be made without departing is from the spirit or scope of the invention as herein described. The present invention is defined by the claims appended hereto.
Claims (29)
1. A wrought high strength Al-Zn alloy product with an improved combination of corrosion resistance and toughness, said alloy comprising essentially of (in weight percent):
Zn 6.0 to 9.5 Cu 1.3 to 2.4 Mg 1.5 to 2.6 Mn < 0.12 Zr < 0.20 Cr < 0.10 Fe < 0.25 Si < 0.25 Ti < 0.10 Hf and/or V < 0.25, and optionally Ce and/or Sc < 0.20, other elements each less than 0.05 and less than 0.25 in total, balance aluminium, and wherein (in weight percent):
0.1[Cu] + 1.3 < [Mg] < 0.2[Cu] + 2.15.
Zn 6.0 to 9.5 Cu 1.3 to 2.4 Mg 1.5 to 2.6 Mn < 0.12 Zr < 0.20 Cr < 0.10 Fe < 0.25 Si < 0.25 Ti < 0.10 Hf and/or V < 0.25, and optionally Ce and/or Sc < 0.20, other elements each less than 0.05 and less than 0.25 in total, balance aluminium, and wherein (in weight percent):
0.1[Cu] + 1.3 < [Mg] < 0.2[Cu] + 2.15.
2. Alloy according to claim 1, wherein the amount (in weight %) of Mg is in a range of 0.2[Cu] + 1.3 < [Mg] < 0.1[Cu] + 2.15.
3. Alloy according to claim 1, wherein the amount (in weight %) of Mg is in a range of 0.2[Cu] + 1.4 < [Mg] < 0.1[Cu] + 1.9.
4. Alloy according to claim 1, wherein the alloy product has an exfoliation corrosion resistance ("EXCO") of EB or better.
5. Alloy according to claim 1, wherein the alloy product has an exfoliation corrosion resistance ("EXCO") of EA or better.
6. Alloy according to claim 1, wherein the amount (in weight %) of Cu is in a range of 1.5 to 2.1.
7. Alloy according to claim 1, wherein the amount (in weight %) of Cu is in a range of 1.5 to 2Ø
8. Alloy according to claim 1, wherein the amount (in weight %) of Zr is in a range of 0.05 to 0.15:
9. Alloy according to claim 1, wherein the amount (in weight %) of Mg and Cu is about 1.93 when the amount (in weight %) of Zn is about 8.1.
10. Alloy according to claim 1, wherein the amount (in weight %) of Zn is in a range of 6.1 to 8.3, preferably in a range of 6.1 to 7.0 if Mn is lower than 0.05.
11. Alloy according to claim 1, wherein the amount (in weight %) of Zn is in a range of 6.1 to 8.3, preferably in a range of 6.1 to 7.0 if Mn is lower than 0.02.
12. Alloy according to claim 1, wherein the amount (in weight %) of Mn is in a range of 0.06 to 0.12 when the amount of Zn is above 7.6.
13. Alloy according to claim 1, wherein the amount (in weight %) of Fe is less than 0.12.
14. Alloy according to claim 1, wherein the amount (in weight %) of Si is less than 0.12.
15. Alloy according to claim 1, wherein the alloy has been artificially aged to a T79 or T76 temper in a two-step ageing procedure.
16. Alloy according to claim 15, wherein the two-step ageing procedure consists of a first heat treatment at a temperature in a range of 105°C to 135°C for 2 to 20 hours, and a second heat treatment at a higher temperature than 135°C
but below 210°C for 4 to 12 hours.
but below 210°C for 4 to 12 hours.
17. Alloy according to claim 1, wherein the product is a plate product.
18. Alloy according to claim 1, wherein the product is a plate product having a thickness is a range of 15 to 45 mm.
19. Alloy according to claim 18, wherein the plate product is a thin aircraft member.
20. Alloy according to claim 18, wherein the plate product is an elongate structural shape member of an aircraft.
21. Alloy according to claim 18, wherein the plate product is an upper-wing member of an aircraft.
22. Alloy according to claim 18, wherein the plate product is a thin skin member of an upper-wing of an aircraft.
23. Alloy according to claim 18, wherein the plate product is stringer of an aircraft.
24. Alloy according to claim 18, wherein the plate product is stringer of an upper-wing of an aircraft.
25. Method for producing a wrought high-strength Al-Zn alloy product according to claim 1 with an improved combination of corrosion resistance and toughness, comprising the steps of:
a) casting an ingot with the following composition (in weight percent):
Zn 6.0 to 9.5 Cu 1.3 to 2.4 Mg 1.5 to 2.6 Mn < 0.12 Zr < 0.20, preferably 0.05 - 0.15 Cr < 0.10 Fe < 0.25 Si < 0.25 Ti < 0.10 Hf and/or V < 0.25, optionally Ce and/or Sc < 0.20, other elements each less than 0.05 and less than 0.25 in total, balance aluminium, wherein (in weight percent):
0.1[Cu] + 1.3 < [Mg] < 0.2[Cu] + 2.15, b) homogenising and/or pre-heating the ingot after casting, c) hot working the ingot and optionally cold working into a worked product, d) solution heat treating and e) quenching the solution heat-treated product.
25. Method according to claim 24, wherein the worked and solution heat-treated product is artificially aged, and wherein the ageing step comprises a first heat treatment at a temperature in a range of 105°C to 135°C for 2 to 20 hours, and a second heat treatment at a higher temperature than 135°C but below 210°C for 4 to 12 hours.
a) casting an ingot with the following composition (in weight percent):
Zn 6.0 to 9.5 Cu 1.3 to 2.4 Mg 1.5 to 2.6 Mn < 0.12 Zr < 0.20, preferably 0.05 - 0.15 Cr < 0.10 Fe < 0.25 Si < 0.25 Ti < 0.10 Hf and/or V < 0.25, optionally Ce and/or Sc < 0.20, other elements each less than 0.05 and less than 0.25 in total, balance aluminium, wherein (in weight percent):
0.1[Cu] + 1.3 < [Mg] < 0.2[Cu] + 2.15, b) homogenising and/or pre-heating the ingot after casting, c) hot working the ingot and optionally cold working into a worked product, d) solution heat treating and e) quenching the solution heat-treated product.
25. Method according to claim 24, wherein the worked and solution heat-treated product is artificially aged, and wherein the ageing step comprises a first heat treatment at a temperature in a range of 105°C to 135°C for 2 to 20 hours, and a second heat treatment at a higher temperature than 135°C but below 210°C for 4 to 12 hours.
26. Method according to in claim 25, wherein the worked and solution heat-treated product is artificially aged, and wherein the ageing step comprises a third heat treatment at a temperature in a range of 105°C to 135°C for more than 20 hours and less than 30 hours.
27. Method according to claim 25, wherein the worked and solution heat-treated product is artificially aged, and wherein the ageing step consists of a first heat treatment at a temperature in a range of 105°C to 135°C for 2 to 20 hours, and a second heat treatment at a higher temperature than 135°C but below 210°C for 4 to 12 hours.
28. Method according to claim 24, characterized by artificially ageing the worked and solution heat-treated product with a two-step ageing procedure to a T79 or T76 temper.
29. Method according to claim 24, wherein after homogenising and/or pre-heating the ingot after casting, hot working the ingot and optionally cold working into a worked product having a thickness in the range of 15 mm to 45 mm.
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| CA2881183A CA2881183C (en) | 2003-04-10 | 2004-04-09 | High strength al-zn alloy and method for producing such an alloy product |
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| EP03076049.0 | 2003-04-10 | ||
| EP03076049 | 2003-04-10 | ||
| PCT/EP2004/003997 WO2004090183A1 (en) | 2003-04-10 | 2004-04-09 | High strength al-zn alloy and method for producing such an alloy product |
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| JP (1) | JP4964586B2 (en) |
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| ES (2) | ES2398002B2 (en) |
| FR (1) | FR2853666B1 (en) |
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Families Citing this family (79)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP4932473B2 (en) * | 2003-03-17 | 2012-05-16 | アレリス、アルミナム、コブレンツ、ゲゼルシャフト、ミット、ベシュレンクテル、ハフツング | Method of manufacturing an integrated monolithic aluminum structure and aluminum products machined from the structure |
| DE112004000603B4 (en) * | 2003-04-10 | 2022-11-17 | Novelis Koblenz Gmbh | Al-Zn-Mg-Cu alloy |
| US20060085528A1 (en) * | 2004-10-01 | 2006-04-20 | Steve Thomas | System and method for monitoring network communications for pestware |
| US7883591B2 (en) * | 2004-10-05 | 2011-02-08 | Aleris Aluminum Koblenz Gmbh | High-strength, high toughness Al-Zn alloy product and method for producing such product |
| EP1683882B2 (en) * | 2005-01-19 | 2010-07-21 | Otto Fuchs KG | Aluminium alloy with low quench sensitivity and process for the manufacture of a semi-finished product of this alloy |
| CN100441715C (en) * | 2005-03-07 | 2008-12-10 | 东北轻合金有限责任公司 | Super large-scale aluminium alloy free forging piece and its prodn. method |
| US9410229B2 (en) * | 2005-03-24 | 2016-08-09 | Kaiser Aluminum Fabricated Products, Llc | High strength aluminum alloys and process for making the same |
| US20060213591A1 (en) | 2005-03-24 | 2006-09-28 | Brooks Charles E | High strength aluminum alloys and process for making the same |
| US8157932B2 (en) * | 2005-05-25 | 2012-04-17 | Alcoa Inc. | Al-Zn-Mg-Cu-Sc high strength alloy for aerospace and automotive castings |
| US20060289093A1 (en) * | 2005-05-25 | 2006-12-28 | Howmet Corporation | Al-Zn-Mg-Ag high-strength alloy for aerospace and automotive castings |
| CN1303237C (en) * | 2005-09-19 | 2007-03-07 | 陈继忠 | Aluminium alloy screw and its manufacturing method |
| US8083871B2 (en) | 2005-10-28 | 2011-12-27 | Automotive Casting Technology, Inc. | High crashworthiness Al-Si-Mg alloy and methods for producing automotive casting |
| US8608876B2 (en) | 2006-07-07 | 2013-12-17 | Aleris Aluminum Koblenz Gmbh | AA7000-series aluminum alloy products and a method of manufacturing thereof |
| CN101484603B (en) * | 2006-07-07 | 2011-09-21 | 阿勒里斯铝业科布伦茨有限公司 | Aa7000-series aluminium alloy products and a method of manufacturing thereof |
| US8673209B2 (en) * | 2007-05-14 | 2014-03-18 | Alcoa Inc. | Aluminum alloy products having improved property combinations and method for artificially aging same |
| US8840737B2 (en) | 2007-05-14 | 2014-09-23 | Alcoa Inc. | Aluminum alloy products having improved property combinations and method for artificially aging same |
| WO2009156283A1 (en) * | 2008-06-24 | 2009-12-30 | Aleris Aluminum Koblenz Gmbh | Al-zn-mg alloy product with reduced quench sensitivity |
| CN101407876A (en) * | 2008-09-17 | 2009-04-15 | 北京有色金属研究总院 | Aluminum alloy material for manufacturing large cross section main load-carrying structure member and preparation thereof |
| US8206517B1 (en) | 2009-01-20 | 2012-06-26 | Alcoa Inc. | Aluminum alloys having improved ballistics and armor protection performance |
| US9163304B2 (en) | 2010-04-20 | 2015-10-20 | Alcoa Inc. | High strength forged aluminum alloy products |
| RU2449047C1 (en) * | 2010-10-29 | 2012-04-27 | Федеральное государственное образовательное учреждение высшего профессионального образования "Национальный исследовательский технологический университет "МИСиС" | Method for obtaining superplastic sheet of high-strength aluminium alloy |
| EP2714954A4 (en) * | 2011-05-21 | 2015-08-19 | Questek Innovations Llc | Aluminum alloys |
| CN102251158A (en) * | 2011-07-09 | 2011-11-23 | 浙江巨科铝业有限公司 | Aluminium alloy for vehicle hub and preparation method thereof |
| CN102489973B (en) * | 2011-12-23 | 2013-08-28 | 东北轻合金有限责任公司 | Method for manufacturing aluminum alloy hollow section for sedan bumper |
| EP2662467A1 (en) * | 2012-04-22 | 2013-11-13 | Kaiser Aluminum Fabricated Products, LLC | Ultra-thick high strength 7xxx series aluminum alloy products and methods of making such products |
| CN102760508B (en) * | 2012-07-18 | 2014-05-28 | 中南大学 | High-conductivity creep-resistant aluminium alloy cable conductor containing Hf and Ce and preparation method thereof |
| CN102978544B (en) * | 2012-11-21 | 2014-08-20 | 中南大学 | Method for multilevel creep age forming of Al-Zn-Mg-Cu series aluminium alloy plate |
| CN102978549A (en) * | 2012-11-21 | 2013-03-20 | 中南大学 | Method for bending creep age forming of Al-Zn-Mg-Cu series aluminium alloy plate |
| CN103540875A (en) * | 2013-03-09 | 2014-01-29 | 中南大学 | Bending, creeping and ageing method for Al-Zn-Mg-Cu aluminum-alloy plate |
| CN103409710A (en) * | 2013-07-05 | 2013-11-27 | 中南大学 | Aging heat treatment method of Al-Zn-Mg-Cu aluminum alloy |
| CN103667825B (en) * | 2013-12-30 | 2016-04-13 | 上海华峰新材料研发科技有限公司 | A kind of ultra-high-strength/tenacity anticorodal and manufacture method thereof |
| RU2553781C1 (en) * | 2014-03-07 | 2015-06-20 | Закрытое акционерное общество "Военно-промышленная инвестиционная группа "ВИЛС" | High-strength heat-treatable aluminium alloy and article made thereof |
| CN104789836B (en) * | 2014-05-07 | 2017-05-24 | 天长市正牧铝业科技有限公司 | Lightweight high-strength aluminum alloy |
| CN104789838A (en) * | 2014-05-07 | 2015-07-22 | 天长市正牧铝业科技有限公司 | Strong and tough aluminum alloy for baseball bat |
| CN104789835A (en) * | 2014-05-07 | 2015-07-22 | 天长市正牧铝业科技有限公司 | High-strength and high-toughness aluminum alloy for baseball bat |
| CN104789839B (en) * | 2014-05-07 | 2017-06-30 | 天长市正牧铝业科技有限公司 | A kind of lightweight tenacity aluminum alloy |
| CN104789837A (en) * | 2014-05-07 | 2015-07-22 | 天长市正牧铝业科技有限公司 | Aluminum alloy material used for manufacturing baseball bat |
| CN104047502B (en) * | 2014-05-26 | 2016-05-18 | 安徽盛达前亮铝业有限公司 | Door jamb |
| CN104060915B (en) * | 2014-05-26 | 2016-07-06 | 安徽盛达前亮铝业有限公司 | Inside open interior wing side plate |
| CN104060917B (en) * | 2014-05-26 | 2016-02-10 | 安徽盛达前亮铝业有限公司 | Side plate aluminium extruded sections under interior wing |
| CN104294116A (en) * | 2014-10-29 | 2015-01-21 | 严静儿 | High-performance aluminum alloy |
| CN104294117A (en) * | 2014-10-29 | 2015-01-21 | 严静儿 | High-ductility aluminum alloy |
| CN105838944B (en) * | 2015-01-16 | 2017-09-19 | 昆山捷安特轻合金科技有限公司 | A kind of carbody high strength weldable aluminium and preparation method thereof |
| CN106555086A (en) * | 2015-09-24 | 2017-04-05 | 湖南稀土金属材料研究院 | A kind of high strength anti-corrosion Al-Zn-Mg- (Cu) line aluminium alloy bar and preparation method thereof |
| CN105112746B (en) * | 2015-09-25 | 2017-05-17 | 沈阳工业大学 | High-strength Al-Zn-Mg-Cu-Ce-Y-Er-La-Sc wrought aluminum alloy and manufacturing method thereof |
| RU2613270C1 (en) * | 2015-10-20 | 2017-03-15 | Открытое акционерное общество "Всероссийский институт легких сплавов" (ОАО "ВИЛС") | HIGH-STRENGTH ALUMINIUM-BASED WROUGHT ALLOY OF Al-Zn-Mg-Cu-SYSTEM AND ARTICLE MADE THEREOF |
| CA3003158C (en) * | 2015-10-29 | 2020-07-07 | Xinyan Yan | Improved wrought 7xxx aluminum alloys, and methods for making the same |
| PL3265595T3 (en) * | 2015-10-30 | 2019-07-31 | Novelis, Inc. | High strength 7xxx aluminum alloys and methods of making the same |
| RU2610190C1 (en) * | 2015-11-05 | 2017-02-08 | Федеральное государственное унитарное предприятие "Всероссийский научно-исследовательский институт авиационных материалов" (ФГУП "ВИАМ") | High-strength aluminium alloy and article made of it |
| EP3181711B1 (en) * | 2015-12-14 | 2020-02-26 | Apworks GmbH | Aluminium alloy containing scandium for powder metallurgy technologies |
| DE102016001500A1 (en) * | 2016-02-11 | 2017-08-17 | Airbus Defence and Space GmbH | Al-Mg-Zn alloy for the integral construction of ALM structures |
| CN106435303B (en) * | 2016-03-07 | 2018-08-03 | 中安顺兴（北京）安全技术有限公司 | A kind of high intensity, high-ductility rare earth aluminum alloy material and preparation method thereof |
| CN105964849A (en) * | 2016-06-14 | 2016-09-28 | 山东南山铝业股份有限公司 | Isothermal die forging technology for large-size high-strength aluminum alloy parts |
| CN105935733A (en) * | 2016-06-14 | 2016-09-14 | 山东南山铝业股份有限公司 | Preparation method of large-size high-strength aluminum alloy forged cake |
| CA3032261A1 (en) | 2016-08-26 | 2018-03-01 | Shape Corp. | Warm forming process and apparatus for transverse bending of an extruded aluminum beam to warm form a vehicle structural component |
| WO2018078527A1 (en) * | 2016-10-24 | 2018-05-03 | Shape Corp. | Multi-stage aluminum alloy forming and thermal processing method for the production of vehicle components |
| CN106399775A (en) * | 2016-11-11 | 2017-02-15 | 湖北万佳宏铝业股份有限公司 | High-strength aluminum alloy material formula and preparation method thereof |
| RU2654224C1 (en) * | 2016-12-26 | 2018-05-17 | Российская Федерация, от имени которой выступает Государственная корпорация по космической деятельности "РОСКОСМОС" | Aluminum-based alloy for anti-meteorite protection |
| WO2018222065A1 (en) * | 2017-05-30 | 2018-12-06 | Общество с ограниченной ответственностью "Объединенная Компания РУСАЛ Инженерно-технологический центр" | High-strength aluminium-based alloy |
| CN107245617B (en) * | 2017-06-13 | 2019-07-05 | 上海新益电力线路器材有限公司 | A kind of power circuit power transmission and transformation aluminium alloy element and preparation method thereof |
| FR3068370B1 (en) * | 2017-07-03 | 2019-08-02 | Constellium Issoire | AL-ZN-CU-MG ALLOYS AND PROCESS FOR PRODUCING THE SAME |
| CN107447140B (en) * | 2017-07-26 | 2019-02-05 | 广西大学 | A kind of high strength alumin ium alloy and preparation method thereof haveing excellent performance |
| FR3071513B1 (en) | 2017-09-26 | 2022-02-11 | Constellium Issoire | HIGH STRENGTH AL-ZN-CU-MG ALLOYS AND METHOD OF MANUFACTURING |
| CN108220845A (en) * | 2017-12-29 | 2018-06-29 | 西南铝业（集团）有限责任公司 | A kind of solid solution aging technique of the strong 7 line aluminium alloy material of superelevation for heavy haul train draw bar |
| CN107937776A (en) * | 2017-12-29 | 2018-04-20 | 西南铝业（集团）有限责任公司 | A kind of strong 7 line aluminium alloy material of inexpensive superelevation for heavy haul train draw bar |
| CN108179332A (en) * | 2017-12-29 | 2018-06-19 | 西南铝业（集团）有限责任公司 | A kind of strong 7 line aluminium alloy material of inexpensive superelevation for heavy haul train draw bar and its production method |
| CN108149095A (en) * | 2017-12-29 | 2018-06-12 | 西南铝业（集团）有限责任公司 | A kind of production method of the strong 7 line aluminium alloy material of inexpensive superelevation for heavy haul train draw bar |
| CN107937847A (en) * | 2017-12-29 | 2018-04-20 | 西南铝业（集团）有限责任公司 | A kind of homogenizing heat treatment of the strong 7 line aluminium alloy material of superelevation for heavy haul train draw bar |
| RU2691475C1 (en) * | 2018-09-24 | 2019-06-14 | Федеральное государственное автономное образовательное учреждение высшего образования "Национальный исследовательский технологический университет "МИСиС" | Cast aluminum alloy with cerium additive |
| BR112021004434B1 (en) * | 2018-11-12 | 2024-01-02 | Novelis Koblenz Gmbh | 7XXX SERIES ALUMINUM ALLOY PRODUCT |
| EP3670690A1 (en) | 2018-12-20 | 2020-06-24 | Constellium Issoire | Al-zn-cu-mg alloys and their manufacturing process |
| KR102578370B1 (en) | 2019-06-03 | 2023-09-15 | 노벨리스 인크. | Ultra-high-strength aluminum alloy products and manufacturing methods thereof |
| CA3143806A1 (en) * | 2019-06-24 | 2020-12-30 | Arconic Technologies Llc | Improved thick wrought 7xxx aluminum alloys, and methods for making the same |
| CN110592443B (en) * | 2019-08-27 | 2021-03-23 | 江苏大学 | Heat-resistant corrosion-resistant 680MPa-730MPa Ti alloyed aluminum alloy and preparation method thereof |
| CN111575618B (en) * | 2020-05-15 | 2021-07-02 | 江苏理工学院 | Treatment method for reducing cracking tendency of large-deformation rolling Al-Zn alloy |
| US20220145439A1 (en) * | 2020-11-11 | 2022-05-12 | Kaiser Aluminum Fabricated Products, Llc | High Strength and High Fracture Toughness 7xxx Aerospace Alloy Products |
| CN112941379A (en) * | 2021-01-22 | 2021-06-11 | 宁波胶点密封工业有限公司 | Aluminum alloy plate for producing die and preparation process thereof |
| CN113373356B (en) * | 2021-06-21 | 2023-03-28 | 哈尔滨工程大学 | Al-Zn-Mg-Cu-Re aluminum alloy and preparation method thereof |
| CN117161121A (en) * | 2023-09-06 | 2023-12-05 | 大庆冬青技术开发有限公司 | High-strength high-toughness rare aluminum alloy toughness ceramic oil pipe and downhole tool pipe column |
Family Cites Families (105)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2249349A (en) * | 1939-08-23 | 1941-07-15 | Aluminum Co Of America | Method of hot working an aluminum base alloy and product thereof |
| BE639908A (en) * | 1962-11-15 | |||
| US3305410A (en) * | 1964-04-24 | 1967-02-21 | Reynolds Metals Co | Heat treatment of aluminum |
| US3418090A (en) * | 1966-03-14 | 1968-12-24 | Reynolds Metals Co | Composite aluminum article |
| US3674448A (en) * | 1969-04-21 | 1972-07-04 | Aluminum Co Of America | Anodic aluminum material and articles and composite articles comprising the material |
| DE2052000C3 (en) * | 1970-10-23 | 1974-09-12 | Fa. Otto Fuchs, 5882 Meinerzhagen | Use of a high-strength aluminum alloy |
| US3826688A (en) * | 1971-01-08 | 1974-07-30 | Reynolds Metals Co | Aluminum alloy system |
| US3881966A (en) * | 1971-03-04 | 1975-05-06 | Aluminum Co Of America | Method for making aluminum alloy product |
| US3857973A (en) * | 1971-03-12 | 1974-12-31 | Aluminum Co Of America | Aluminum alloy container end and sealed container thereof |
| US3791880A (en) * | 1972-06-30 | 1974-02-12 | Aluminum Co Of America | Tear resistant sheet and plate and method for producing |
| US3791876A (en) * | 1972-10-24 | 1974-02-12 | Aluminum Co Of America | Method of making high strength aluminum alloy forgings and product produced thereby |
| US4477292A (en) * | 1973-10-26 | 1984-10-16 | Aluminum Company Of America | Three-step aging to obtain high strength and corrosion resistance in Al-Zn-Mg-Cu alloys |
| US4140549A (en) * | 1974-09-13 | 1979-02-20 | Southwire Company | Method of fabricating an aluminum alloy electrical conductor |
| US3984259A (en) * | 1975-08-22 | 1976-10-05 | Aluminum Company Of America | Aluminum cartridge case |
| FR2393070A1 (en) * | 1977-06-02 | 1978-12-29 | Cegedur | THERMAL TREATMENT PROCESS OF ALUMINUM ALLOY SHEETS |
| FR2409319A1 (en) * | 1977-11-21 | 1979-06-15 | Cegedur | THERMAL TREATMENT PROCESS FOR THIN 7000 SERIES ALUMINUM ALLOY PRODUCTS |
| US4305763A (en) * | 1978-09-29 | 1981-12-15 | The Boeing Company | Method of producing an aluminum alloy product |
| JPS5953347B2 (en) * | 1979-09-29 | 1984-12-24 | 住友軽金属工業株式会社 | Manufacturing method of aircraft stringer material |
| US5108520A (en) * | 1980-02-27 | 1992-04-28 | Aluminum Company Of America | Heat treatment of precipitation hardening alloys |
| JPS5929663B2 (en) * | 1980-12-24 | 1984-07-21 | 三菱アルミニウム株式会社 | High-strength Al alloy for baseball bats with excellent extrusion processability |
| JPS57161045A (en) * | 1981-03-31 | 1982-10-04 | Sumitomo Light Metal Ind Ltd | Fine-grain high-strength aluminum alloy material and its manufacture |
| JPS5852386A (en) * | 1981-09-24 | 1983-03-28 | Mitsubishi Oil Co Ltd | Preparation of raw material pitch for carbon fiber |
| GB2114601B (en) * | 1981-12-23 | 1986-05-08 | Aluminum Co Of America | High strength aluminum alloy resistant to exfoliation and method of heat treatment |
| US4954188A (en) * | 1981-12-23 | 1990-09-04 | Aluminum Company Of America | High strength aluminum alloy resistant to exfoliation and method of making |
| US4828631A (en) * | 1981-12-23 | 1989-05-09 | Aluminum Company Of America | High strength aluminum alloy resistant to exfoliation and method of making |
| JPS5928555A (en) * | 1982-08-06 | 1984-02-15 | Sumitomo Light Metal Ind Ltd | High tensile aluminum alloy good in extrudability and excellent in strength and toughness |
| US4711762A (en) * | 1982-09-22 | 1987-12-08 | Aluminum Company Of America | Aluminum base alloys of the A1-Cu-Mg-Zn type |
| US4589932A (en) * | 1983-02-03 | 1986-05-20 | Aluminum Company Of America | Aluminum 6XXX alloy products of high strength and toughness having stable response to high temperature artificial aging treatments and method for producing |
| JPS6013047A (en) * | 1983-06-30 | 1985-01-23 | Showa Alum Corp | High-strength aluminum alloy with superior cold workability |
| US4618382A (en) * | 1983-10-17 | 1986-10-21 | Kabushiki Kaisha Kobe Seiko Sho | Superplastic aluminium alloy sheets |
| US4713216A (en) * | 1985-04-27 | 1987-12-15 | Showa Aluminum Kabushiki Kaisha | Aluminum alloys having high strength and resistance to stress and corrosion |
| FR2601967B1 (en) * | 1986-07-24 | 1992-04-03 | Cerzat Ste Metallurg | AL-BASED ALLOY FOR HOLLOW BODIES UNDER PRESSURE. |
| JPS63297180A (en) * | 1987-05-27 | 1988-12-05 | 昭和アルミニウム株式会社 | Bicycle frame by adhesive structure |
| US5221377A (en) * | 1987-09-21 | 1993-06-22 | Aluminum Company Of America | Aluminum alloy product having improved combinations of properties |
| US4988394A (en) * | 1988-10-12 | 1991-01-29 | Aluminum Company Of America | Method of producing unrecrystallized thin gauge aluminum products by heat treating and further working |
| US4927470A (en) * | 1988-10-12 | 1990-05-22 | Aluminum Company Of America | Thin gauge aluminum plate product by isothermal treatment and ramp anneal |
| US4946517A (en) * | 1988-10-12 | 1990-08-07 | Aluminum Company Of America | Unrecrystallized aluminum plate product by ramp annealing |
| CA1340618C (en) * | 1989-01-13 | 1999-06-29 | James T. Staley | Aluminum alloy product having improved combinations of strength, toughness and corrosion resistance |
| US4976790A (en) * | 1989-02-24 | 1990-12-11 | Golden Aluminum Company | Process for preparing low earing aluminum alloy strip |
| FR2645546B1 (en) * | 1989-04-05 | 1994-03-25 | Pechiney Recherche | HIGH MODULATED AL MECHANICAL ALLOY WITH HIGH MECHANICAL RESISTANCE AND METHOD FOR OBTAINING SAME |
| JPH03140433A (en) * | 1989-10-27 | 1991-06-14 | Nkk Corp | High strength aluminum alloy having excellent corrosion resistance |
| US5213639A (en) * | 1990-08-27 | 1993-05-25 | Aluminum Company Of America | Damage tolerant aluminum alloy products useful for aircraft applications such as skin |
| US5186235A (en) * | 1990-10-31 | 1993-02-16 | Reynolds Metals Company | Homogenization of aluminum coil |
| US5277719A (en) * | 1991-04-18 | 1994-01-11 | Aluminum Company Of America | Aluminum alloy thick plate product and method |
| US5356495A (en) * | 1992-06-23 | 1994-10-18 | Kaiser Aluminum & Chemical Corporation | Method of manufacturing can body sheet using two sequences of continuous, in-line operations |
| US5496423A (en) * | 1992-06-23 | 1996-03-05 | Kaiser Aluminum & Chemical Corporation | Method of manufacturing aluminum sheet stock using two sequences of continuous, in-line operations |
| US5313639A (en) * | 1992-06-26 | 1994-05-17 | George Chao | Computer with security device for controlling access thereto |
| US5312498A (en) * | 1992-08-13 | 1994-05-17 | Reynolds Metals Company | Method of producing an aluminum-zinc-magnesium-copper alloy having improved exfoliation resistance and fracture toughness |
| US5376192A (en) * | 1992-08-28 | 1994-12-27 | Reynolds Metals Company | High strength, high toughness aluminum-copper-magnesium-type aluminum alloy |
| FR2716896B1 (en) * | 1994-03-02 | 1996-04-26 | Pechiney Recherche | Alloy 7000 with high mechanical resistance and process for obtaining it. |
| JPH07316601A (en) * | 1994-03-28 | 1995-12-05 | Toyo Alum Kk | Production of rapidly solidified aluminum powder and aluminum alloy compact |
| US5919323A (en) * | 1994-05-11 | 1999-07-06 | Aluminum Company Of America | Corrosion resistant aluminum alloy rolled sheet |
| US5496426A (en) * | 1994-07-20 | 1996-03-05 | Aluminum Company Of America | Aluminum alloy product having good combinations of mechanical and corrosion resistance properties and formability and process for producing such product |
| FR2726007B1 (en) * | 1994-10-25 | 1996-12-13 | Pechiney Rhenalu | PROCESS FOR PRODUCING ALSIMGCU ALLOY PRODUCTS WITH IMPROVED INTERCRYSTALLINE CORROSION RESISTANCE |
| US5624632A (en) * | 1995-01-31 | 1997-04-29 | Aluminum Company Of America | Aluminum magnesium alloy product containing dispersoids |
| JP4208156B2 (en) * | 1995-02-24 | 2009-01-14 | 住友軽金属工業株式会社 | Manufacturing method of high strength aluminum alloy extruded material |
| US5681405A (en) * | 1995-03-09 | 1997-10-28 | Golden Aluminum Company | Method for making an improved aluminum alloy sheet product |
| AU5422096A (en) * | 1995-03-21 | 1996-10-08 | Kaiser Aluminum & Chemical Corporation | A method of manufacturing aluminum aircraft sheet |
| EP0826072B1 (en) * | 1995-05-11 | 2003-07-02 | KAISER ALUMINUM & CHEMICAL CORPORATION | Improved damage tolerant aluminum 6xxx alloy |
| US5865911A (en) * | 1995-05-26 | 1999-02-02 | Aluminum Company Of America | Aluminum alloy products suited for commercial jet aircraft wing members |
| US5863359A (en) * | 1995-06-09 | 1999-01-26 | Aluminum Company Of America | Aluminum alloy products suited for commercial jet aircraft wing members |
| FR2737225B1 (en) * | 1995-07-28 | 1997-09-05 | Pechiney Rhenalu | AL-CU-MG ALLOY WITH HIGH FLUID RESISTANCE |
| US5718780A (en) * | 1995-12-18 | 1998-02-17 | Reynolds Metals Company | Process and apparatus to enhance the paintbake response and aging stability of aluminum sheet materials and product therefrom |
| US6027582A (en) * | 1996-01-25 | 2000-02-22 | Pechiney Rhenalu | Thick alZnMgCu alloy products with improved properties |
| EP0799900A1 (en) * | 1996-04-04 | 1997-10-08 | Hoogovens Aluminium Walzprodukte GmbH | High strength aluminium-magnesium alloy material for large welded structures |
| DE69629113T2 (en) * | 1996-09-11 | 2004-04-22 | Aluminum Company Of America | Aluminum alloy for airliner wings |
| CA2279985C (en) * | 1997-02-19 | 2003-10-14 | Alcan International Limited | Process for producing aluminium alloy sheet |
| JP3705320B2 (en) * | 1997-04-18 | 2005-10-12 | 株式会社神戸製鋼所 | High strength heat treatment type 7000 series aluminum alloy with excellent corrosion resistance |
| US6315842B1 (en) * | 1997-07-21 | 2001-11-13 | Pechiney Rhenalu | Thick alznmgcu alloy products with improved properties |
| JP4786791B2 (en) * | 1997-12-12 | 2011-10-05 | アルコア インコーポレイテッド | 2000 series aluminum alloy |
| US6224992B1 (en) * | 1998-02-12 | 2001-05-01 | Alcoa Inc. | Composite body panel and vehicle incorporating same |
| FR2789406B1 (en) * | 1999-02-04 | 2001-03-23 | Pechiney Rhenalu | ALCuMg ALLOY PRODUCT FOR AIRCRAFT STRUCTURAL ELEMENT |
| CA2362978A1 (en) * | 1999-03-01 | 2000-09-08 | Alcan International Limited | Aa6000 aluminium sheet method |
| AU760996B2 (en) * | 1999-03-18 | 2003-05-29 | Corus Aluminium Walzprodukte Gmbh | Weldable aluminium alloy structural component |
| FR2792001B1 (en) * | 1999-04-12 | 2001-05-18 | Pechiney Rhenalu | PROCESS FOR MANUFACTURING TYPE 2024 ALUMINUM ALLOY SHAPED PARTS |
| JP3494591B2 (en) * | 1999-06-23 | 2004-02-09 | 株式会社デンソー | Aluminum alloy brazing sheet with good corrosion resistance for vacuum brazing and heat exchanger using the same |
| RU2165995C1 (en) * | 1999-10-05 | 2001-04-27 | Государственное предприятие "Всероссийский научно-исследовательский институт авиационных материалов" | Highly string aluminium-based alloy and product made of said alloy |
| FR2802946B1 (en) * | 1999-12-28 | 2002-02-15 | Pechiney Rhenalu | AL-CU-MG ALLOY AIRCRAFT STRUCTURAL ELEMENT |
| FR2805282B1 (en) * | 2000-02-23 | 2002-04-12 | Gerzat Metallurg | A1ZNMGCU ALLOY PRESSURE HOLLOW BODY PROCESS |
| 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 |
| US6562154B1 (en) * | 2000-06-12 | 2003-05-13 | Aloca Inc. | Aluminum sheet products having improved fatigue crack growth resistance and methods of making same |
| RU2184166C2 (en) * | 2000-08-01 | 2002-06-27 | Государственное предприятие "Всероссийский научно-исследовательский институт авиационных материалов" | Aluminum-based high-strength alloy and product manufactured therefrom |
| CN1489637A (en) * | 2000-12-21 | 2004-04-14 | �Ƹ��� | Aluminum alloy products and artificial aging method |
| JP4285916B2 (en) * | 2001-02-16 | 2009-06-24 | 株式会社神戸製鋼所 | Manufacturing method of aluminum alloy plate for structural use with high strength and high corrosion resistance |
| US20030051784A1 (en) * | 2001-03-20 | 2003-03-20 | Denzer Diana K. | Method for increasing the strength and/or corrosion resistance of 7000 series Al aerospace alloy products |
| US6543122B1 (en) * | 2001-09-21 | 2003-04-08 | Alcoa Inc. | Process for producing thick sheet from direct chill cast cold rolled aluminum alloy |
| JP4022491B2 (en) * | 2002-03-27 | 2007-12-19 | 株式会社神戸製鋼所 | Aluminum alloy bat |
| FR2838136B1 (en) * | 2002-04-05 | 2005-01-28 | Pechiney Rhenalu | ALLOY PRODUCTS A1-Zn-Mg-Cu HAS COMPROMISED STATISTICAL CHARACTERISTICS / DAMAGE TOLERANCE IMPROVED |
| FR2838135B1 (en) * | 2002-04-05 | 2005-01-28 | Pechiney Rhenalu | CORROSIVE ALLOY PRODUCTS A1-Zn-Mg-Cu WITH VERY HIGH MECHANICAL CHARACTERISTICS, AND AIRCRAFT STRUCTURE ELEMENTS |
| BR0312098A (en) * | 2002-06-24 | 2005-03-29 | Corus Aluminium Walzprod Gmbh | Method for the production of high strength balanced al-mg-si alloy and weldable alloy product |
| US20050006010A1 (en) * | 2002-06-24 | 2005-01-13 | Rinze Benedictus | Method for producing a high strength Al-Zn-Mg-Cu alloy |
| FR2842212B1 (en) * | 2002-07-11 | 2004-08-13 | Pechiney Rhenalu | A1-CU-MG ALLOY AIRCRAFT STRUCTURAL ELEMENT |
| FR2846669B1 (en) * | 2002-11-06 | 2005-07-22 | Pechiney Rhenalu | PROCESS FOR THE SIMPLIFIED MANUFACTURE OF LAMINATED PRODUCTS OF A1-Zn-Mg ALLOYS AND PRODUCTS OBTAINED THEREBY |
| US7060139B2 (en) * | 2002-11-08 | 2006-06-13 | Ues, Inc. | High strength aluminum alloy composition |
| WO2004046403A2 (en) * | 2002-11-15 | 2004-06-03 | Alcoa Inc. | Aluminum alloy product having improved combinations of properties |
| JP4932473B2 (en) * | 2003-03-17 | 2012-05-16 | アレリス、アルミナム、コブレンツ、ゲゼルシャフト、ミット、ベシュレンクテル、ハフツング | Method of manufacturing an integrated monolithic aluminum structure and aluminum products machined from the structure |
| DE112004000603B4 (en) * | 2003-04-10 | 2022-11-17 | Novelis Koblenz Gmbh | Al-Zn-Mg-Cu alloy |
| US8043445B2 (en) * | 2003-06-06 | 2011-10-25 | Aleris Aluminum Koblenz Gmbh | High-damage tolerant alloy product in particular for aerospace applications |
| JP2005016937A (en) * | 2003-06-06 | 2005-01-20 | Denso Corp | Aluminum heat exchanger with excellent corrosion resistance |
| US20050095447A1 (en) * | 2003-10-29 | 2005-05-05 | Stephen Baumann | High-strength aluminum alloy composite and resultant product |
| US20070151636A1 (en) * | 2005-07-21 | 2007-07-05 | Corus Aluminium Walzprodukte Gmbh | Wrought aluminium AA7000-series alloy product and method of producing said product |
| US20070204937A1 (en) * | 2005-07-21 | 2007-09-06 | Aleris Koblenz Aluminum Gmbh | Wrought aluminium aa7000-series alloy product and method of producing said product |
| US8608876B2 (en) * | 2006-07-07 | 2013-12-17 | Aleris Aluminum Koblenz Gmbh | AA7000-series aluminum alloy products and a method of manufacturing thereof |
| CN101484603B (en) * | 2006-07-07 | 2011-09-21 | 阿勒里斯铝业科布伦茨有限公司 | Aa7000-series aluminium alloy products and a method of manufacturing thereof |
| EP2977483A1 (en) * | 2009-01-22 | 2016-01-27 | Alcoa Inc. | Improved aluminum-copper alloys containing vanadium |
-
2004
- 2004-04-07 US US10/819,130 patent/US20050034794A1/en not_active Abandoned
- 2004-04-09 RU RU2005134846/02A patent/RU2353699C2/en active
- 2004-04-09 AT AT0911004A patent/AT502294B1/en active
- 2004-04-09 WO PCT/EP2004/003997 patent/WO2004090183A1/en not_active Application Discontinuation
- 2004-04-09 JP JP2006505139A patent/JP4964586B2/en not_active Expired - Lifetime
- 2004-04-09 FR FR0403746A patent/FR2853666B1/en not_active Expired - Lifetime
- 2004-04-09 ES ES201131194A patent/ES2398002B2/en not_active Expired - Lifetime
- 2004-04-09 CA CA2519387A patent/CA2519387C/en not_active Expired - Lifetime
- 2004-04-09 CA CA2881183A patent/CA2881183C/en not_active Expired - Lifetime
- 2004-04-09 GB GB0520502A patent/GB2415203B/en not_active Expired - Lifetime
- 2004-04-09 CN CN200480009567.XA patent/CN1780925B/en not_active Expired - Lifetime
- 2004-04-09 DE DE112004000596T patent/DE112004000596B4/en not_active Revoked
- 2004-04-09 CN CN201310039039.XA patent/CN103146969B/en not_active Expired - Lifetime
- 2004-04-09 ES ES200550065A patent/ES2288389A1/en active Pending
- 2004-04-09 BR BRPI0409360-7A patent/BRPI0409360A/en not_active Application Discontinuation
-
2009
- 2009-08-25 US US12/547,466 patent/US20090320969A1/en not_active Abandoned
Also Published As
| Publication number | Publication date |
|---|---|
| CN103146969A (en) | 2013-06-12 |
| FR2853666A1 (en) | 2004-10-15 |
| CA2519387C (en) | 2015-06-02 |
| AT502294B1 (en) | 2010-02-15 |
| RU2353699C2 (en) | 2009-04-27 |
| ES2398002B2 (en) | 2015-01-22 |
| CA2881183C (en) | 2018-06-12 |
| DE112004000596B4 (en) | 2011-03-24 |
| AT502294A1 (en) | 2007-02-15 |
| US20050034794A1 (en) | 2005-02-17 |
| FR2853666B1 (en) | 2007-05-11 |
| ES2288389A1 (en) | 2008-01-01 |
| GB2415203B (en) | 2007-01-03 |
| BRPI0409360A (en) | 2006-04-25 |
| WO2004090183A1 (en) | 2004-10-21 |
| CA2881183A1 (en) | 2004-10-21 |
| GB0520502D0 (en) | 2005-11-16 |
| JP4964586B2 (en) | 2012-07-04 |
| US20090320969A1 (en) | 2009-12-31 |
| CN1780925B (en) | 2013-03-27 |
| RU2005134846A (en) | 2006-04-10 |
| DE112004000596T5 (en) | 2006-03-09 |
| JP2006522872A (en) | 2006-10-05 |
| CN1780925A (en) | 2006-05-31 |
| GB2415203A (en) | 2005-12-21 |
| ES2398002A1 (en) | 2013-03-13 |
| CN103146969B (en) | 2015-07-08 |
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