EP1492895A2 - Al-zn-mg-cu alloy products displaying an improved compromise between static mechanical properties and tolerance to damage - Google Patents
Al-zn-mg-cu alloy products displaying an improved compromise between static mechanical properties and tolerance to damageInfo
- Publication number
- EP1492895A2 EP1492895A2 EP03740568A EP03740568A EP1492895A2 EP 1492895 A2 EP1492895 A2 EP 1492895A2 EP 03740568 A EP03740568 A EP 03740568A EP 03740568 A EP03740568 A EP 03740568A EP 1492895 A2 EP1492895 A2 EP 1492895A2
- Authority
- EP
- European Patent Office
- Prior art keywords
- content
- product according
- elements
- product
- alloy
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
- 230000003068 static effect Effects 0.000 title description 20
- 229910000881 Cu alloy Inorganic materials 0.000 title 1
- 229910045601 alloy Inorganic materials 0.000 claims abstract description 96
- 239000000956 alloy Substances 0.000 claims abstract description 96
- 229910018569 Al—Zn—Mg—Cu Inorganic materials 0.000 claims abstract description 23
- 229910052782 aluminium Inorganic materials 0.000 claims abstract description 13
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims abstract description 13
- 229910052684 Cerium Inorganic materials 0.000 claims abstract description 12
- 229910052692 Dysprosium Inorganic materials 0.000 claims abstract description 12
- 229910052693 Europium Inorganic materials 0.000 claims abstract description 12
- 229910052688 Gadolinium Inorganic materials 0.000 claims abstract description 12
- 229910052689 Holmium Inorganic materials 0.000 claims abstract description 12
- 229910052779 Neodymium Inorganic materials 0.000 claims abstract description 12
- 229910052771 Terbium Inorganic materials 0.000 claims abstract description 12
- 229910052769 Ytterbium Inorganic materials 0.000 claims abstract description 12
- 229910052746 lanthanum Inorganic materials 0.000 claims abstract description 12
- 229910052719 titanium Inorganic materials 0.000 claims abstract description 12
- 229910052691 Erbium Inorganic materials 0.000 claims abstract description 11
- 238000010276 construction Methods 0.000 claims abstract description 11
- 239000012535 impurity Substances 0.000 claims abstract description 11
- 229910052727 yttrium Inorganic materials 0.000 claims abstract description 11
- 239000011701 zinc Substances 0.000 claims description 64
- 239000011777 magnesium Substances 0.000 claims description 42
- 239000010949 copper Substances 0.000 claims description 39
- 229910052725 zinc Inorganic materials 0.000 claims description 30
- HCHKCACWOHOZIP-UHFFFAOYSA-N Zinc Chemical compound [Zn] HCHKCACWOHOZIP-UHFFFAOYSA-N 0.000 claims description 28
- 238000012360 testing method Methods 0.000 claims description 14
- 229910052749 magnesium Inorganic materials 0.000 claims description 11
- 229910052802 copper Inorganic materials 0.000 claims description 8
- 229910052706 scandium Inorganic materials 0.000 claims description 8
- SIXSYDAISGFNSX-UHFFFAOYSA-N scandium atom Chemical compound [Sc] SIXSYDAISGFNSX-UHFFFAOYSA-N 0.000 claims description 8
- FYYHWMGAXLPEAU-UHFFFAOYSA-N Magnesium Chemical compound [Mg] FYYHWMGAXLPEAU-UHFFFAOYSA-N 0.000 claims description 7
- 239000003351 stiffener Substances 0.000 claims description 6
- 229910052804 chromium Inorganic materials 0.000 claims description 5
- 239000010455 vermiculite Substances 0.000 claims description 5
- 229910052726 zirconium Inorganic materials 0.000 claims description 5
- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical compound [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 claims description 4
- 229910052793 cadmium Inorganic materials 0.000 claims description 3
- 229910052738 indium Inorganic materials 0.000 claims description 3
- 229910052748 manganese Inorganic materials 0.000 claims description 3
- 229910052718 tin Inorganic materials 0.000 claims description 3
- 229910052732 germanium Inorganic materials 0.000 claims description 2
- 238000003754 machining Methods 0.000 claims description 2
- 229910052710 silicon Inorganic materials 0.000 claims description 2
- 229910052709 silver Inorganic materials 0.000 claims description 2
- XUIMIQQOPSSXEZ-UHFFFAOYSA-N Silicon Chemical compound [Si] XUIMIQQOPSSXEZ-UHFFFAOYSA-N 0.000 claims 1
- 239000010703 silicon Substances 0.000 claims 1
- 239000000047 product Substances 0.000 description 25
- 230000007797 corrosion Effects 0.000 description 13
- 238000005260 corrosion Methods 0.000 description 13
- 239000000203 mixture Substances 0.000 description 13
- 238000011282 treatment Methods 0.000 description 12
- 238000005266 casting Methods 0.000 description 8
- 238000000034 method Methods 0.000 description 7
- 239000000126 substance Substances 0.000 description 7
- 230000008569 process Effects 0.000 description 6
- 230000006835 compression Effects 0.000 description 5
- 238000007906 compression Methods 0.000 description 5
- 238000010586 diagram Methods 0.000 description 5
- 238000005496 tempering Methods 0.000 description 5
- 230000000694 effects Effects 0.000 description 4
- 238000004519 manufacturing process Methods 0.000 description 4
- 238000010791 quenching Methods 0.000 description 4
- 230000000171 quenching effect Effects 0.000 description 4
- 238000009987 spinning Methods 0.000 description 4
- 238000003466 welding Methods 0.000 description 4
- 239000002970 Calcium lactobionate Substances 0.000 description 3
- 230000008901 benefit Effects 0.000 description 3
- 239000000463 material Substances 0.000 description 3
- 229910052751 metal Inorganic materials 0.000 description 3
- 239000002184 metal Substances 0.000 description 3
- 239000002244 precipitate Substances 0.000 description 3
- 238000007711 solidification Methods 0.000 description 3
- 230000008023 solidification Effects 0.000 description 3
- 230000000930 thermomechanical effect Effects 0.000 description 3
- 230000007423 decrease Effects 0.000 description 2
- 238000004090 dissolution Methods 0.000 description 2
- 235000012438 extruded product Nutrition 0.000 description 2
- 238000000265 homogenisation Methods 0.000 description 2
- 238000005098 hot rolling Methods 0.000 description 2
- 238000005259 measurement Methods 0.000 description 2
- 238000001556 precipitation Methods 0.000 description 2
- 238000011160 research Methods 0.000 description 2
- 238000005096 rolling process Methods 0.000 description 2
- 239000011265 semifinished product Substances 0.000 description 2
- 229910000838 Al alloy Inorganic materials 0.000 description 1
- QCWXUUIWCKQGHC-UHFFFAOYSA-N Zirconium Chemical compound [Zr] QCWXUUIWCKQGHC-UHFFFAOYSA-N 0.000 description 1
- 230000006978 adaptation Effects 0.000 description 1
- 238000005275 alloying Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 230000009172 bursting Effects 0.000 description 1
- 238000007707 calorimetry Methods 0.000 description 1
- 238000012512 characterization method Methods 0.000 description 1
- 229910052729 chemical element Inorganic materials 0.000 description 1
- 238000005336 cracking Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 238000010348 incorporation Methods 0.000 description 1
- 229910052742 iron Inorganic materials 0.000 description 1
- 238000003475 lamination Methods 0.000 description 1
- 230000035800 maturation Effects 0.000 description 1
- 238000005457 optimization Methods 0.000 description 1
- 230000008092 positive effect Effects 0.000 description 1
- 230000001376 precipitating effect Effects 0.000 description 1
- 238000001953 recrystallisation Methods 0.000 description 1
- 230000002787 reinforcement Effects 0.000 description 1
- 230000004044 response Effects 0.000 description 1
- 239000004332 silver Substances 0.000 description 1
- 229910000679 solder Inorganic materials 0.000 description 1
- 238000005507 spraying Methods 0.000 description 1
- 238000010561 standard procedure Methods 0.000 description 1
- 238000009864 tensile test Methods 0.000 description 1
- 230000009466 transformation Effects 0.000 description 1
Classifications
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C21/00—Alloys based on aluminium
- C22C21/10—Alloys based on aluminium with zinc as the next major constituent
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22F—CHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS AND NON-FERROUS ALLOYS
- C22F1/00—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
- C22F1/04—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon
- C22F1/053—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon of alloys with zinc as the next major constituent
Definitions
- the present invention relates to Al-Zn-Mg-Cu alloys with compromise static mechanical characteristics - improved damage tolerance, with a Zn content greater than 8.3%, as well as structural elements for aeronautical construction incorporating half wrought products made from these alloys.
- Alloys of the Al-Zn-Mg-Cu type (belonging to the family of 7xxx alloys) are commonly used in aeronautical construction, and in particular in the construction of the wings of civil aircraft.
- These alloy designations well known to those skilled in the art. trade, correspond to those of The Aluminum Association.
- alloys 7075 and 7175 have been known for decades, such as alloys 7075 and 7175 (zinc content between 5.1 and 6.1% by weight), 7050 (zinc content between 5.7 and 6.7%) , 7150 (zinc content between 5.9 and 6.9%) and 7049 (zinc content between 7.2 and 8.2%). They have a high elastic limit, as well as good toughness and good resistance to stress corrosion and exfoliating corrosion. More recently, it has become apparent that for certain applications, the use of an alloy with a higher zinc content may have advantages since this makes it possible to further increase the elastic limit. Alloys 7349 and 7449 contain between 7.5 and 8.7% zinc. of the wrought alloys richer in zinc have been described in the literature, but do not seem to be used in aeronautical construction.
- EP 257 167 Al (German Métallurgique de Gerzat) notes that none of the known Al-Zn-Mg-Cu type alloys can safely and reproducibly meet the severe technical requirements imposed by this specific application; it proposes to move towards a lower zinc content, namely between 6.25% and 8.0%.
- the problem to which the present invention is trying to respond is therefore to propose new wrought products of Al-Zn-Mg-Cu type alloy with high zinc content, greater than 8.3%, which are characterized by an improved compromise between toughness and static mechanical characteristics (yield strength, yield strength), which have sufficient corrosion resistance and high elongation at break, and which can be manufactured industrially under conditions of reliability compatible with the high requirements of the industry aeronautics.
- a first object of the present invention consists of a rolled, extruded or forged product of Al-Zn-Mg-Cu alloy, characterized in that it contains (in percent by mass): a) Zn 8.3 - 14.0 Cu 0.3 - 4.0 and preferably 0.3 - 3.0 Mg 0.5 - 4.5 and preferably 0.5 - 3.0 Zr 0.03 - 0.15 Fe + Si ⁇ 0.25 b ) at least one element selected from the group consisting of Se, Hf, La, Ti, Ce, Nd, Eu, Gd, Tb, Dy, Ho, Er, Y, Yb, the content of each of said elements, if it is selected, being between 0.02 and 0.7%, c) the remainder of aluminum and inevitable impurities, and in that it satisfies the conditions
- a second object of the present invention consists of a rolled, extruded or forged product of Al-Zn-Mg-Cu alloy, characterized in that it contains (in percent by mass): a) Zn 9.5 - 14.0 Cu 0.3 - 4.0 and preferably 0.3 - 3.0 Mg 0.5 - 4.5 and preferably 0.5 - 3.0
- Fe + Si ⁇ 0.25 b) at least one element selected from the group consisting of Zr, Se, Hf, La, Ti, Ce, Nd, Eu, Gd, Tb, Dy, Ho, Er, Y, Yb, Cr , Mn, the content of each of said elements, if selected, being between 0.02 and 0.7%, c) the rest of the aluminum and inevitable impurities, and in that it satisfies the conditions d) Mg / Cu ⁇ 2.4 and e) (7.7 - 0.4 Zn)> (Cu + Mg)> (6.4 - 0.4 Zn).
- a third object of the present invention is a structural element for aeronautical construction which incorporates one of the said products, and in particular a structural element used in the construction of wing boxes of civil aircraft, such as a wing upper surface.
- Figure 1 schematically shows a wing box of an aircraft.
- the benchmarks are as follows:
- FIG. 2 represents the compromise between mechanical strength and damage tolerance in a diagram R p o, 2 - K app for the alloys of example 3.
- FIG. 3 represents the compromise between mechanical strength and damage tolerance in a diagram R p o > 2 - K app for the alloys of example 5.
- the parameter K app was measured according to the ASTM E561 standard on CT type testpieces of width W equal to 127 mm.
- the term “spun product” includes so-called “drawn products”, that is to say products which are produced by spinning followed by drawing. The applicant, in the course of a number of preparatory studies, has come to the conclusion that a new material presenting a significantly better compromise should in any event have a sufficient zinc content, typically greater than approximately 8.3 %. This condition is however not sufficient.
- the problem is solved by fine adjustment of the contents of the alloying elements and certain impurities, and by adding a controlled concentration of certain other elements to the composition of the alloy.
- the present invention applies to Al-Zn-Mg-Cu alloys containing:
- the alloys according to the invention must contain at least 0.5% magnesium, since it is not possible to obtain satisfactory static mechanical characteristics with a lower magnesium content. According to the Applicant's observations, with a zinc content of less than 8.3%, no result is obtained which is better than those obtained with known alloys.
- the zinc content is greater than 9.0%, and even more preferably greater than 9.5%. However, it is necessary to respect certain relationships between certain elements, as explained below.
- the zinc content is between 9.0 and 11.0%. In any event, it is not desired to exceed a zinc content of approximately 14%, because above this value, whatever the magnesium and copper content, the results are not satisfactory.
- the alloy must be sufficiently loaded with addition elements capable of precipitating during maturation or tempering treatment, in order to be able to exhibit advantageous static mechanical characteristics.
- addition elements capable of precipitating during maturation or tempering treatment, in order to be able to exhibit advantageous static mechanical characteristics.
- the content of these addition elements must fulfill the condition Mg + Cu> 6.4 - 0.4 Zn.
- anti-recrystallizing elements More specifically, for alloys with more than 9.5% zinc, at least one element selected from the group comprising the elements Zr, Se, Hf, La, Ti, Y, Ce, Nd, Eu, Gd, must be added. Tb, Dy, Ho, Er, Yb, Cr, Mn with, for each element present, a concentration of between 0.02 and 0.7%. It is preferable that the concentration of all the elements of said group does not exceed 1.5%.
- zirconium with a content of between 0.03% and 0.15%, and in addition at least an element selected from the group comprising the elements Se, Hf, La, Ti, Y, Ce, Nd, Eu, Gd, Tb, Dy, Ho, Er, Yb, with, for each element present, a concentration of between 0, 02 and 0.7%.
- the said anti-recrystallizing elements it is advantageous, whatever the zinc content, not to exceed the following maximum contents: Cr 0.40; Mn 0.60; Se 0.50; Zr 0.15; Hf 0.60; Ti 0.15; This 0.35 and preferably 0.30; Nd 0.35 and preferably 0.30; Eu 0.35 and preferably 0.30; Gd 0.35; Tb 0.35; Ho 0.40; Dy 0.40; Er 0.40; Yb 0.40; Y 0.20; The 0.35 and preferably 0.30.
- the total of these elements does not exceed 1.5%.
- This criterion is called in the context of the present invention the "flowability criterion".
- the alloys produced according to this variant of the invention complete their solidification at a temperature of between 473 ° C and 478 ° C, and make it possible to achieve industrial reliability in the processes for preparing the metal (that is to say a consistency of the quality of the cast plates) compatible with the high requirements of the aeronautical industry.
- Another technical characteristic of the invention is linked to the need to minimize as much as possible the amount of insoluble precipitates after the homogenization and dissolution treatments, since this reduces the toughness; for this, we choose a content of Mg, Cu and Zn such that Mg + Cu ⁇ 7.7 - 0.4 Zn. Said precipitates are typically ternary or quaternary Al-Zn-Mg-Cu phases of type S, M or T. And finally, the Applicant has found that the incorporation of a small amount, between 0.02 and 0.15% per element, of one or more elements chosen from the group composed of Sn, Cd, Ag, Ge, In improves the response of the alloy to the tempering treatment, and has beneficial effects on the mechanical strength and on the corrosion resistance of the product. A content of between 0.05 and 0.10% is preferred. Among these elements, money is the preferred element.
- the products according to the invention are in particular laminated or extruded products. They can be advantageously used for the manufacture of structural elements in aircraft construction.
- a preferred application of the products according to the invention is the application as a structural element in a wing box, and in particular in its upper part (upper surface) which is first of all dimensioned in resistance to compression.
- Figure 1 schematically shows a section of the wing box of a civil aircraft.
- a wing box typically has a length of between 10 m and 40 m and a width of between 2 m and 10 m; its height varies depending on the location on the wing and is typically between 0.2 m and 2 m.
- the box consists of the upper surface (1) and the lower surface (2).
- the upper surface (1) of a civil aircraft consists of a heavy plate of a typical thickness during delivery of between 15 mm and 60 mm, and stiffeners (5) which can be made from profiles and attached to the skin using mechanical fasteners (such as rivets or bolts) or by welding techniques (such as arc welding, laser beam welding, or friction welding).
- the upper surface structure can also be obtained by assembling other semi-products of aluminum alloy. It can also be obtained by integral machining of heavy plates or profiles, that is to say without assembly.
- the length of aircraft wings can exceed 20 m and even 30 m, which requires the use of sheets or profiles longer than 20 m or 30 m, in order to minimize assembly of structural elements.
- the manufacture of sheets or profiles of such a size from highly loaded Al-Zn-Mg-Cu alloys requires excellent mastery of the casting, rolling and thermal and thermo-mechanical treatment processes, and requires an adaptation of the chemical composition according to the invention.
- the products according to the invention can be used as structural elements in aeronautical construction.
- a metallurgical state of type T6, for example T651 is preferred.
- the product according to the invention is particularly suitable for use as a structural element in a wing box, for example in the form of an upper surface or a stiffener.
- the advantages of the products according to the invention allow in particular their use as structural elements of very large planes, in particular of civil planes, and in particular in the form of rolled and spun products. In a particularly advantageous application, these structural elements are manufactured from sheets of thickness greater than 60 mm.
- the addition of one or more anti-recrystallizing elements, such as scandium, is particularly advantageous; such an effect is also observed in the case of heavy plates.
- the anti-recrystallizing element added is scandium, a content of between 0.02 and 0.50% is advantageous.
- Adding a small amount of silver or other element such as Cd, Ge, In, Sn improves the efficiency of income, and a positive effects on the mechanical resistance and resistance to corrosion under stress of the product.
- Alloy A is an alloy 7449 according to the state of the art
- alloys B and C are alloys with a high content of Zn, not respecting the technical characteristics of the invention
- alloy D is an alloy according to l 'invention.
- alloy according to the invention has a better compromise between static characteristics and toughness than alloy 7449 according to the prior art (R p02 in higher tension and compression and K ⁇ similar), and that the alloys with high zinc content not respecting the technical characteristics of the invention are less efficient.
- Alloy E is an alloy 7449
- alloy F is an alloy according to the invention, containing an addition of 0.083% of Scandium.
- Alloy R is an alloy 7449
- alloy S is an alloy according to the invention, containing an addition of 0.078% of scandium.
- the toughness in plane deformation Kic was determined according to standard ASTM E399, at mid-thickness.
- the toughness under plane stresses was characterized at mid-thickness using the parameter K app , measured according to standard ASTM E561 on CCT type test pieces of width W equal to 406 mm.
- the results of the toughness measurements carried out during this test are presented in Table 8 below.
- FIG. 2 The compromise between mechanical strength and damage tolerance is shown in FIG. 2 in a diagram R p0> 2 - K app for the alloys of example 3.
- the reference alloy “R” presents the usual compromise (the toughness decreases when the mechanical resistance increases).
- the alloy according to the invention “S” exhibits a very slight decrease (thickness 10 mm) or even a clear increase (thickness 25 mm) in toughness when the mechanical strength increases.
- the alloy according to the invention has levels of mechanical resistance clearly higher than those of the reference alloy and a comparable or even higher toughness.
- the alloys G1, G2, G3 and G4 are outside the present invention, as well as the alloys B and C, described in example 1.
- the alloy D is an alloy according to the invention described in example 1. All of these alloys showed satisfactory flowability during the tests, that is to say that cracks or cracks were not observed during the casting tests on an industrial scale.
- the alloys G5, G6, G7, G8 are outside the present invention, and the alloy G9 is an alloy 7060 according to the state of the art; these alloys presented cracks during the casting tests.
- Lamination plates were produced by a process similar to that described in Example 1.
- the chemical composition is given in Table 10.
- it was prepared by hot rolling sheets with a thickness of 25 mm. They were dissolved for 2 hours at a temperature between 472 and 480 ° C. (these temperatures are determined by preliminary calorimetry tests on the raw rolling sheets, a standard procedure for those skilled in the art), quenched by spraying and pulled with a permanent elongation between 1, 5 and 2%. Then, the sheets were subjected to a tempering treatment at a temperature of 135 ° C.
- the K sheet with a lower Mg / Cu ratio shows significantly better toughness values than the N sheet.
- Spinning billets 291 mm in diameter were prepared by vertical casting with an alloy according to the invention, the composition of which is given in table 12.
- the homogenized (7h 460 ° C + 23h 466 ° C) and peeled billets were extradited, the temperature of the container and the tool being greater than 400 ° C, and the spinning speed being less than 0.50 m / min .
- the geometry of the profiles includes a sole (thickness 15 mm, width 152 mm), a rib (thickness 15 mm, height 38 mm) and a reinforcement (thickness 23 mm, width 76 mm).
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- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Materials Engineering (AREA)
- Mechanical Engineering (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- Crystallography & Structural Chemistry (AREA)
- Thermal Sciences (AREA)
- Physics & Mathematics (AREA)
- Heat Treatment Of Steel (AREA)
- Laminated Bodies (AREA)
- Extrusion Of Metal (AREA)
- Conductive Materials (AREA)
- Metal Rolling (AREA)
- Forging (AREA)
- Contacts (AREA)
Abstract
Description
Claims
Applications Claiming Priority (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR0204257 | 2002-04-05 | ||
FR0204257A FR2838136B1 (en) | 2002-04-05 | 2002-04-05 | ALLOY PRODUCTS A1-Zn-Mg-Cu HAS COMPROMISED STATISTICAL CHARACTERISTICS / DAMAGE TOLERANCE IMPROVED |
PCT/FR2003/001062 WO2003085145A2 (en) | 2002-04-05 | 2003-04-04 | Al-zn-mg-cu alloy products displaying an improved compromise between static mechanical properties and tolerance to damage |
Publications (2)
Publication Number | Publication Date |
---|---|
EP1492895A2 true EP1492895A2 (en) | 2005-01-05 |
EP1492895B1 EP1492895B1 (en) | 2009-12-16 |
Family
ID=28052141
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP03740568A Revoked EP1492895B1 (en) | 2002-04-05 | 2003-04-04 | Al-zn-mg-cu alloy products |
Country Status (9)
Country | Link |
---|---|
US (1) | US7550110B2 (en) |
EP (1) | EP1492895B1 (en) |
JP (1) | JP4535731B2 (en) |
AT (1) | ATE452216T1 (en) |
AU (1) | AU2003260001A1 (en) |
DE (2) | DE03740568T1 (en) |
ES (1) | ES2338314T3 (en) |
FR (1) | FR2838136B1 (en) |
WO (1) | WO2003085145A2 (en) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN111057920A (en) * | 2020-01-07 | 2020-04-24 | 西南交通大学 | Ultrahigh-strength aluminum alloy and preparation method thereof |
Families Citing this family (61)
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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 |
US20050034794A1 (en) * | 2003-04-10 | 2005-02-17 | Rinze Benedictus | High strength Al-Zn alloy and method for producing such an alloy product |
US7666267B2 (en) | 2003-04-10 | 2010-02-23 | Aleris Aluminum Koblenz Gmbh | Al-Zn-Mg-Cu alloy with improved damage tolerance-strength combination properties |
CN100547098C (en) * | 2003-04-10 | 2009-10-07 | 克里斯铝轧制品有限公司 | A kind of Al-zn-mg-cu alloy |
US20050217770A1 (en) * | 2004-03-23 | 2005-10-06 | Philippe Lequeu | Structural member for aeronautical construction with a variation of usage properties |
DE102005045341A1 (en) * | 2004-10-05 | 2006-07-20 | Corus Aluminium Walzprodukte Gmbh | High strength, high strength Al-Zn alloy product and method of making such a product |
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 |
EP1848835A2 (en) * | 2005-02-01 | 2007-10-31 | Timothy Langan | Aluminum-zinc-magnesium-scandium alloys and methods of fabricating same |
US9410229B2 (en) * | 2005-03-24 | 2016-08-09 | Kaiser Aluminum Fabricated Products, Llc | 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 |
US20070204937A1 (en) * | 2005-07-21 | 2007-09-06 | Aleris Koblenz Aluminum Gmbh | Wrought aluminium aa7000-series alloy product and method of producing said 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 |
US8083871B2 (en) | 2005-10-28 | 2011-12-27 | Automotive Casting Technology, Inc. | High crashworthiness Al-Si-Mg alloy and methods for producing automotive casting |
CN101479397B (en) * | 2006-06-30 | 2013-03-13 | 肯联铝业轧制品-雷文斯伍德有限公司 | High strength, heat treatable al-zn-mg aluminum alloy |
WO2008003503A2 (en) * | 2006-07-07 | 2008-01-10 | Aleris Aluminum Koblenz Gmbh | Method of manufacturing aa2000 - series aluminium alloy products |
FR2907796B1 (en) * | 2006-07-07 | 2011-06-10 | Aleris Aluminum Koblenz Gmbh | ALUMINUM ALLOY PRODUCTS OF THE AA7000 SERIES AND METHOD FOR MANUFACTURING THE SAME |
US7879162B2 (en) * | 2008-04-18 | 2011-02-01 | United Technologies Corporation | High strength aluminum alloys with L12 precipitates |
US20090263273A1 (en) | 2008-04-18 | 2009-10-22 | United Technologies Corporation | High strength L12 aluminum alloys |
US7875131B2 (en) | 2008-04-18 | 2011-01-25 | United Technologies Corporation | L12 strengthened amorphous aluminum alloys |
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Publication number | Priority date | Publication date | Assignee | Title |
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CN111057920A (en) * | 2020-01-07 | 2020-04-24 | 西南交通大学 | Ultrahigh-strength aluminum alloy and preparation method thereof |
CN111057920B (en) * | 2020-01-07 | 2022-05-06 | 西南交通大学 | Ultrahigh-strength aluminum alloy and preparation method thereof |
Also Published As
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DE60330547D1 (en) | 2010-01-28 |
JP2005528521A (en) | 2005-09-22 |
FR2838136A1 (en) | 2003-10-10 |
ATE452216T1 (en) | 2010-01-15 |
FR2838136B1 (en) | 2005-01-28 |
AU2003260001A1 (en) | 2003-10-20 |
US20030219353A1 (en) | 2003-11-27 |
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US7550110B2 (en) | 2009-06-23 |
WO2003085145A2 (en) | 2003-10-16 |
EP1492895B1 (en) | 2009-12-16 |
WO2003085145A3 (en) | 2004-04-01 |
ES2338314T3 (en) | 2010-05-06 |
JP4535731B2 (en) | 2010-09-01 |
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