EP1558778B1 - Vereinfachtes verfahren zur herstellung von gewalzten produkten aus al-zn-mg-legierungen, und dadurch hergestellte produkte - Google Patents

Vereinfachtes verfahren zur herstellung von gewalzten produkten aus al-zn-mg-legierungen, und dadurch hergestellte produkte Download PDF

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EP1558778B1
EP1558778B1 EP03767916A EP03767916A EP1558778B1 EP 1558778 B1 EP1558778 B1 EP 1558778B1 EP 03767916 A EP03767916 A EP 03767916A EP 03767916 A EP03767916 A EP 03767916A EP 1558778 B1 EP1558778 B1 EP 1558778B1
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temperature
alloy
mpa
sheet
welded
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French (fr)
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EP1558778A1 (de
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Ronan Dif
Jean-Christophe Ehrstrom
Bernard Grange
Vincent Hochenedel
Hervé Ribes
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Constellium Issoire SAS
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Alcan Rhenalu SAS
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    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C21/00—Alloys based on aluminium
    • C22C21/10—Alloys based on aluminium with zinc as the next major constituent
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22F—CHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS AND NON-FERROUS ALLOYS
    • C22F1/00—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
    • C22F1/04—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon
    • C22F1/053—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon of alloys with zinc as the next major constituent

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  • the present invention relates to Al-Zn-Mg type alloys with high mechanical strength, and more particularly alloys intended for welded constructions such as structures used in the field of shipbuilding, automobile bodywork, industrial vehicle and fixed or mobile tanks.
  • aluminum alloys of the 5xxx series (5056, 5083, 5383, 5086, 5186, 5182, 5054 ...) and 6xxx (6082, 6005A ”).
  • the weldable low-copper 7xxx alloys (such as 7020, 7108 7) are also suitable for producing welded parts as they have very good mechanical properties, even after welding. These alloys, however, are subject to problems of laminar corrosion (in the T4 state and in the affected area of the welds) and corrosion corrosion under stress (in the T6 state).
  • Alloys in the 5xxx family are usually used in H1x (hardened), H2x (hardened and then restored), H3x (hardened and stabilized) or O (annealed) states.
  • the choice of the metallurgical state depends on the compromise between mechanical strength, corrosion resistance and formability that is aimed for a given use.
  • the 7xxx alloys (Al-Zn-Mg) are said to be "structurally hardened", which means that they acquire their mechanical properties by precipitation of the additive elements (Zn, Mg).
  • the person skilled in the art knows that in order to obtain these mechanical properties, the hot transformation by rolling or spinning is followed by dissolution in solution, quenching and an income. These operations, carried out in the majority of cases separately, are respectively intended to dissolve the alloying elements, to maintain them in the form of super-saturated solid solution at room temperature, and finally to precipitate them in a controlled manner.
  • the alloys of the 6xxx (Al-Mg-Si) and 7xxx (Al-Zn-Mg) families are generally used in the reclaimed state.
  • the income giving the maximum mechanical strength is designated T6, when the shaping by rolling or spinning is followed by a separate dissolution and quenching.
  • the parameters that govern the user's choice are essentially the static mechanical characteristics, that is to say the breaking strength R m , the elastic limit R p0,2 , and the
  • the other parameters that come into play, depending on the specific needs of the intended application, are the mechanical characteristics of the welded joint, the corrosion resistance (laminating and stress) of the sheet and welded joint, fatigue strength of sheet and welded joint, resistance to crack propagation, toughness, dimensional stability after cutting or welding, resistance to abrasion. For each intended use, it is necessary to find a suitable compromise between these different properties.
  • the patent GB 1 419 491 (British Aluminum) discloses a weldable alloy containing 3.5 - 5.5% zinc, 0.7 - 3.0% magnesium, 0.05 - 0.30% zirconium, optionally up to 0.05% each of chromium and manganese, up to 0.10% iron, up to 0.075% silicon, and up to 0.25% copper.
  • the patent FR 1 501 662 (Ve occidentale Aluminum-Werke Aktiengesellschaft) discloses a weldable alloy of composition Zn 5.78% Mg 1.62% Mn 0.24% Cr 0.13% Cu 0.02% Zr 0.17% used in the form of sheets with a thickness of 4 mm, after being dissolved for one hour at 480 ° C., quenched with water and returned in two stages (24 hours at 120 ° C. and then 2 hours at 180 ° C.) , for the manufacture of shields.
  • the patent US 5,061,327 discloses a method of manufacturing an aluminum alloy rolled product comprising casting a plate, homogenizing, hot rolling, reheating the blank to a temperature of between 260 ° C and 582 ° C, its rapid cooling, a precipitation treatment at a temperature between 93 ° C and 288 ° C, and then cold rolling or hot rolling at a temperature not exceeding 288 ° C.
  • the problem to which the present invention tries to respond is first of all to improve the compromise of certain properties of Al-Zn-Mg alloys in the form of sheets or strips, namely the compromise between the mechanical characteristics (determined on the metal base and welded joint), and corrosion resistance (laminar corrosion and stress corrosion). Moreover, we seek to produce these products with a manufacturing range that is as simple and reliable as possible, allowing them to be manufactured with as little manufacturing cost as possible.
  • the first object of the present invention defined in claim 1 is a process for producing an intermediate laminated product of Al-Zn-Mg type aluminum alloy, comprising the following steps: a) a plate containing (in mass percents) is produced by semi-continuous casting Mg 0.5-2.0 Mn ⁇ 1.0 Zn 3.0 - 9.0 If ⁇ 0.50 Fe ⁇ 0.50 Cu ⁇ 0.50 Ti ⁇ 0.15 Zr ⁇ 0.20 Cr ⁇ 0.50 the rest of the aluminum with its inevitable impurities, in which Zn / Mg>1.7; b) the said plate is subjected to homogenization and / or reheating at a temperature T 1 , chosen such that 500 ° C ⁇ T 1 ⁇ (T S -20 ° C), where T S represents the burning temperature of l 'alloy, c) performing a first hot rolling step comprising one or more rolling passes on a hot rolling mill, the inlet temperature T 2 being chosen such that (T 1 - 60 ° C) ⁇ T 2 ⁇ (T
  • a second object defined in claim 11 is a product obtainable by the method according to the invention.
  • a third object defined in claims 14 to 19 is the use of the product obtained by the process according to the invention for the manufacture of welded constructions.
  • Another object defined in claims 22 and 24 is the welded construction made with at least two products obtainable by the process according to the invention, characterized in that its elastic limit R p0,2 in the welded joint between two of said products is at least 200 MPa.
  • the crack propagation rate da / dN is determined according to the ASTM E647 standard, the damage tolerance K R according to the ASTM E 561 standard, the resistance to exfoliating corrosion (also called laminar corrosion) is determined according to the ASTM G34 standard ( Exco test) or ASTM G85-A3 (Swaat test); for these tests, as well as for even more specific tests, additional information is given below in the description and in the examples.
  • the Applicant has surprisingly found that it is possible to manufacture 7xxx alloy rolled products which show a very good compromise of properties, in particular in the welded state, using a simplified process, in which the dissolution, quenching and tempering are carried out during hot rolling by rolling.
  • the process according to the invention can be carried out on Al-Zn-Mg alloys in a wide range of chemical composition: Zn 3.0 - 9.0%, Mg 0.5 - 2.0%, the alloy may also contain Mn ⁇ 1.0%, Si ⁇ 0.50%, Fe ⁇ 0.50%, Cu ⁇ 0.50%, Cr ⁇ 0.50%, Ti ⁇ 0.15%, Zr ⁇ 0.20 %, as well as the inevitable impurities.
  • the magnesium content must be between 0.5 and 2.0% and preferably between 0.7 and 1.5%. Below 0.5%, mechanical properties are obtained which are unsatisfactory for many applications, and above 2.0% there is a deterioration in the corrosion resistance of the alloy. Moreover, above 2.0% magnesium, the quenchability of the alloy is no longer satisfactory, which affects the efficiency of the process according to the invention.
  • the manganese content must be less than 1.0% and preferably less than 0.60%, to limit the sensitivity to flaky corrosion and to maintain good quenchability. A content not exceeding 0.20% is preferred.
  • the zinc content must be between 3.0 and 9.0%, and preferably between 4.0 and 6.0%. Below 3.0%, the mechanical characteristics are too low to be of technical interest, and above 9.0% there is a deterioration of the corrosion resistance of the alloy, as well as degradation of the quenchability.
  • the ratio Zn / Mg must be greater than 1.7 to allow to remain in the composition field which benefits from the structural hardening.
  • the silicon content must be less than 0.50% in order not to deteriorate the corrosion behavior or the tear resistance. For these same reasons, the iron content must also be less than 0.50%.
  • the copper content must be less than 0.50% and preferably less than 0.25%, which makes it possible to limit the sensitivity to pitting corrosion and to maintain good quenchability.
  • the chromium content must be less than 0.50%, which makes it possible to limit the sensitivity to flaky corrosion and to maintain good quenchability.
  • the titanium content must be less than 0.15% and that in zirconium less than 0.20%, in order to avoid the formation of harmful primary phases; for Zr it is preferred not to exceed 0.15%.
  • Hardness is understood here to mean the ability of an alloy to be quenched in a fairly wide range of quenching speeds.
  • An alloy said to be easily quenchable is therefore an alloy for which the cooling rate during quenching does not have a strong influence on the properties of use (such as strength or corrosion resistance).
  • the burn temperature T s is a quantity known to those skilled in the art, which determines it for example directly by calorimetry on a raw sample of casting, or by thermodynamic calculation taking into account the phase diagrams.
  • the temperatures T 2 and T 5 correspond to the temperature of the surface (usually the upper surface) of the plate or strip measured just before entering the hot rolling mill; the execution of this measurement can be done according to the methods known to those skilled in the art.
  • the temperature T 3 is chosen such that (T 1 -100 ° C) ⁇ T 3 ⁇ (T 1 - 30 ° C).
  • T 2 is chosen such that (T 1 - 30 ° C) ⁇ T 2 ⁇ (T 1 - 5 ° C).
  • T 6 is chosen such that (T 5 - 150 ° C) ⁇ T 6 ⁇ (T 5 - 50 ° C).
  • the temperature T 3 it is preferable to choose the temperature T 3 so that it is greater than the solvus temperature of the alloy.
  • the solvus temperature is determined by those skilled in the art using differential calorimetry. Keeping T 3 above the solvus temperature makes it possible to minimize the coarse precipitation of MgZn 2 phases. It is preferred that these phases are formed in a controlled manner in the form of fine precipitated during winding or after winding. The control of the temperature T 3 is therefore particularly critical.
  • the temperature T 4 is also a critical parameter of the process.
  • the temperature must not fall below the specified value.
  • the inlet temperature to the hot rolling mill during step (e), which is advantageously carried out on a tandem mill be substantially equal to the temperature of the strip after cooling, which requires either a sufficiently fast transfer of the strip from one mill to another, or, preferably, an in-line process.
  • the steps b), c) d) and e) are carried out in line, that is to say a given volume of metal element (in the form of a plate of rolling or rolled strip) goes from one stage to another without intermediate storage likely to lead to an uncontrolled drop in temperature which would require intermediate heating.
  • the process according to the invention is based on a precise evolution of the temperature during steps b), c), d) and e); the figure 1 illustrates an embodiment of the invention.
  • the cooling in step (d) can be done by any means ensuring sufficiently rapid cooling, such as: immersion, sprinkling, forced convection, or a combination of these means.
  • immersion, sprinkling, forced convection or a combination of these means.
  • natural convection cooling as the only means is not fast enough, whether in tape or coil. In general, at this stage of the process, coil cooling does not give satisfactory results.
  • the coil can be allowed to cool.
  • the product from step (e) can be subjected to other operations such as cold rolling, income, or cutting.
  • the intermediate rolled product according to the invention with a cold work hardening of between 1% and 9%, and / or with a complementary heat treatment comprising one or more steps at temperatures of between 80 ° C. and 250 ° C., said complementary heat treatment which can intervene before, after or during said cold work-hardening.
  • the process according to the invention is designed so as to be able to carry out in line three heat treatment operations which are usually carried out separately: the dissolving (carried out according to the invention during the first hot rolling step), quenching (performed according to the invention during the cooling of the strip), the income (made according to the invention during cooling of the coil). More particularly, the method according to the invention can be conducted so that it is not necessary to heat the product once it has entered the reversible hot rolling mill, each step of said process being at a temperature lower than the previous one. This saves energy.
  • the intermediate rolled product obtained by the process according to the invention can be used as it is, that is to say without subjecting it to other process steps which modify its metallurgical state; this is preferable. If necessary, it may be subjected to other process steps that change its metallurgical state, such as cold rolling.
  • the method according to the invention can sometimes lead, for a given alloy, to static mechanical characteristics slightly worse. On the other hand, in some cases, it leads to an improvement of the damage tolerance, as well as an improvement of the resistance to corrosion, especially after welding. This has been found in particular for a restricted composition domain, as will be explained later.
  • the compromise of properties that is obtained with the process according to the invention is at least as interesting as that obtained by a conventional manufacturing process, in which solution, quenching and tempering are carried out separately. and which leads to the T6 state.
  • the process according to the invention is much simpler and less expensive than the known processes. It advantageously leads to an intermediate product whose thickness is between 3 mm and 12 mm; above 12 mm, the winding becomes technically difficult, and below 3 mm, besides the technical difficulties of hot rolling in this zone of thickness, the band is likely to cool too much.
  • a preferred composition range for carrying out the process according to the invention is characterized by Zn 4.0 - 6.0, Mg 0.7 - 1.5, Mn ⁇ 0.60 and preferably Cu ⁇ 0.25. Alloys exhibiting good quenchability are preferred, and among these alloys, alloys 7020, 7003, 7004, 7005, 7008, 7011, 7018, 7022 and 7108 are preferred.
  • the Al-Zn-Mg alloy products according to the invention can be welded by all known welding processes, such as MIG or TIG welding, friction welding, laser welding, electron beam welding. Welding tests were carried out on X-chamfered plates welded by semi-automatic smooth-flow MIG welding with a 5183 alloy filler wire. The welding was carried out in the direction perpendicular to the rolling. The mechanical tests on the welded specimens were carried out according to a method recommended by Det Norske Veritas (DNV) in their document "Rules for classification of Ships - Newbuildings - Materials and Welding - Part 2 Chapter 3: Welding" of January 1996.
  • DNV Det Norske Veritas
  • the width of the tensile test piece is 25 mm
  • the cord is symmetrically leveled and the useful length of the specimen and the length of the extensometer used is given by (W + 2.e) where the parameter W designates the width of the bead and the parameter e designates the thickness of the specimen.
  • the Applicant has found that the MIG welding of the products according to the invention leads to welded joints characterized by a greater yield strength and rupture limit than with an alloy manufactured according to a conventional range. (T6).
  • T6 a conventional range for mechanically welded constructions, that is to say the constructions in which the welded zone has a structural role, is surprising insofar as the static properties of the unwelded metal are rather weaker than at T6.
  • the corrosion resistance of the base metal and welded joints was evaluated using SWAAT and EXCO tests.
  • the SWAAT test makes it possible to evaluate the resistance to corrosion (especially in flaky corrosion) of aluminum alloys in general. Since the method according to the present invention leads to a product with a highly fiber-reinforced structure, it is important to ensure that said product is resistant to exfoliating corrosion, which develops mainly on products showing a fiber structure.
  • the SWAAT test is described in Annex A3 of ASTM G85. This is a cyclic test. Each cycle, lasting two hours, consists of a humidification phase of 90 minutes (relative humidity of 98%) and a 30-minute spraying period, of a compound solution (for one liter) of salt.
  • the EXCO test which lasts 96 hours, is described in ASTM G34. It is primarily intended to establish the laminar corrosion resistance of aluminum alloys containing copper, but may also be suitable for AI-Zn-Mg alloys (see J.Marthinussen, S.Grjotheim, "Qualification of new aluminum alloys"). , 3 rd International Forum on Aluminum Ships, Haugesund, Norway, May 1998).
  • test pieces were used, one side of which was protected by an adhesive aluminum strip (in order to attack only the other side) and the face to be attacked was either left as it was it is machined to half thickness on half the surface of the sample, and left full thickness on the other half.
  • the diagrams of the test pieces used for each test are given to the figures 2 (laminar corrosion) and 3 (stress corrosion).
  • the product according to the invention has a resistance in flaky corrosion equivalent to that obtained for the standard product (alloy identical or neighboring T6 state).
  • a particularly preferred product according to the invention contains between 4.0 and 6.0% of zinc, between 0.7 and 1.5% of magnesium, less than 0.60%, and even more preferably less than 0.20%. of manganese, and less than 0.25% of copper.
  • Such a product shows a loss of mass of less than 1 g / dm 2 in the 100-day SWAT test (100 cycles) and less than 5.5 g / dm 2 in the 96-hour EXCO test before income or after income. corresponding at most to 15 h at 140 ° C.
  • the resistance to stress corrosion has been characterized using the Slow Strain Rate Testing method, described for example in the ASTM G129 standard. This test is faster and more discriminating than the methods of determining the stress of the non-breaking stress corrosion stress.
  • the principle of the slow traction test schematized in figure 4 , consists in comparing the tensile properties in an inert medium (laboratory air) and in an aggressive medium. The decrease in static mechanical properties in a corrosive environment corresponds to the sensitivity to stress corrosion.
  • the most sensitive tensile test characteristics are elongation at break A and maximum stress (at necking) R m . The elongation at break, which is a much more discriminating quantity than the maximum stress, was used.
  • the critical aspects of the slow tensile test are the selection of the tensile specimen, the rate of deformation and the corrosive solution.
  • Regarding the speed of stress it is recognized, especially on Al-Zn-Mg alloys (see the article "Stress Corrosion of Al-5Zn-1.2Mg Crystals in 30g / l NaCl Medium" by T. Magnin and C.
  • the process according to the invention makes it possible to obtain products which, for a domain of restricted composition with respect to the composition domain in which the process according to the invention can be implemented, namely Zn 4, 0 - 6.0%, Mg 0.7-1.5%, Mn ⁇ 0.60%, and Cu ⁇ 0.25%, have new microstructural characteristics. These microstructural characteristics lead to particularly advantageous use properties, and in particular to better resistance to corrosion.
  • the MgZn 2 precipitates at the grain boundaries have an average size greater than 150 nm, and preferably between 200 and 400 nm, whereas this size does not exceed 80 nm in the products according to the state of the technical.
  • the MgZn 2 type hardening precipitates are much coarser in a product according to the invention than in a comparable product according to the prior art.
  • the quenching is not as fast as in a conventional method with solution in a furnace followed by a separate quenching. It is clear that the method according to the invention makes it possible to avoid a certain precipitation of coarse phases from the temperature T 4 .
  • the product obtained by the process according to the invention has a fibered granular structure, that is to say grains whose thickness or whose thickness / length ratio is significantly lower than for the products according to the state. of the technique.
  • the grains have a size in the direction of the thickness (short-through) of less than 30 ⁇ m, preferably less than 15 ⁇ m and even more preferably less than 10 ⁇ m, and a length / thickness ratio of more than 60, and preferably of more than 100, whereas for a comparable product according to the state of the art, the grains have a size in the direction of the thickness (transverse-short) greater than 60 ⁇ m and a length / thickness ratio much less than 40.
  • the sheets and strips resulting from the process according to the present invention can be advantageously used for the construction of automobile parts, industrial vehicles, road or rail tanks, and for construction in the maritime environment.
  • All sheets and strips resulting from the process according to the present invention are particularly suitable for welded construction; they can be welded by all known welding processes which are suitable for this type of alloys.
  • Sheet metal according to the invention can be welded to one another, or to other sheets of aluminum or aluminum alloy, using a suitable filler wire.
  • a yield strength (measured as described above) of at least 200 MPa. In a preferred embodiment, this value is at least 220 MPa.
  • the breaking strength of the welded joint is at least 250 MPa, and in a preferred embodiment of at least 280 MPa, and preferably at least 300 MPa, measured after a maturation of at least one month.
  • a thermally affected zone which exhibits a hardness of at least 100 HV, preferably from minus 110 HV, and even more preferably at least 115 HV; this hardness is at least as great as that of the base plates which has the least hardness.
  • the Applicant has found that the product obtained by the process according to the invention, in the field of preferred composition (Zn 4.0 - 6.0%, Mg 0.7 - 1.5%, Mn ⁇ 0 , 60%), shows a higher resistance to abrasion by sand than comparable products. It notes that this resistance to abrasion does not depend in a simple way on the mechanical characteristics of the product, nor its hardness nor its ductility. The fiber structure in the TC direction seems to favor the resistance to abrasion by sand. For this property of use, the superiority of the product resulting from the process according to the invention is due to the combination between a particular fiber structure, inaccessible with the known processes, and the level of mechanical characteristics that its composition confers on it.
  • the sand abrasion resistance of the product obtainable by the process according to the invention expressed in the form of mass loss during a test described in Example 10 below. is less than 0.20 g, and preferably less than 0.19 g for an exposed flat surface of dimensions 15 x 10 mm.
  • the product according to the invention has good properties of damage tolerance. It can be used as structural element in aeronautical construction.
  • the product according to the invention and in particular that which belongs to the restricted composition range defined by Zn 4.0 - 6.0%, Mg 0.7 - 1.5%, Mn ⁇ 0.60%, is thus suitable. to be used as a structural element to meet specific requirements for damage tolerance (toughness, resistance to crack propagation) in fatigue).
  • structural element or “structural element” of a mechanical construction a mechanical part whose failure is likely to endanger the safety of said construction, its users, its users or others.
  • these structural elements include the elements that make up the fuselage (such as fuselage skin (fuselage skin in English), stiffeners or stringers, bulkheads, fuselage (circumferential frames)), the wings (such as the wing skin), the stiffeners (stringers or stiffeners), the ribs (ribs) and spars) and the empennage, as well as the floor beams, seat rails and doors.
  • the present invention relates only to structural elements that can be made from rolled sheets. More particularly, the product according to the invention is suitable for use as a fuselage coating sheet, in conventional assembly (especially riveted) or welded assembly.
  • the process according to the invention thus makes it possible to obtain a novel product having an advantageous combination of properties, such as mechanical strength, damage tolerance, weldability, resistance to exfoliating corrosion and stress corrosion, abrasion resistance, which is particularly suitable for use as a structural element in mechanical engineering.
  • it is suitable for use in industrial vehicles, as well as in equipment for storing, transporting or handling granular products, such as skips, tanks or conveyors.
  • the method according to the invention is particularly simple and fast; its operating cost is lower than that of the processes according to the state of the art likely to lead to products with comparable properties of use.
  • Examples 1 and 2 belong to the state of the art.
  • Examples 3, 4, 8 and 9 correspond to the invention.
  • Each of Examples 5, 6, 7, 9 and 10 compares the invention with the state of the art.
  • This example corresponds to a transformation range according to the state of the art.
  • Two plates A and B were prepared by semi-continuous casting. Their composition is indicated in Table 2.
  • the chemical analysis of the elements was carried out by X-ray fluorescence (for Zn and Mg elements) and by spark spectroscopy (other elements) on a pawn obtained from liquid metal taken from the casting channel.
  • the rolling plates were reheated for 22 hours at 530 ° C and hot rolled as soon as they reached a temperature of 515 ° C at the oven exit.
  • the hot-rolled strips were wound to a thickness of 6 mm, the process being conducted so that the temperature, measured on the banks of the coil after the complete winding (at mid-thickness of the winding) is between 265 ° C and 275 ° C, this value being the average between 2 measurements made at both sides of the coil.
  • the coils were cut and a portion of the sheets obtained was cold rolled to a thickness of 4 mm.
  • Table 2 Alloy mg Zn mn Yes Fe Cu Zr Ti Cr AT 1.20 4.48 0.12 0.12 0.21 0.10 0.12 0,036 0.25 B 1.15 4.95 0.006 0.04 0.10 0.13 0.11 0,011 0.05
  • the products in the T4 state have been characterized only in flaky corrosion (EXCO and SWAAT tests) because it is known (see in particular the article "Stress corrosion corrosion susceptibility of aluminum alloy 7020 welded sheets" by MC Reboul, B. Dubost and M. Lashermes, published in Corrosion Science, Vol 25, No. 11, p. 999-1018, 1985 ) that it is the most sensitive state to flaky corrosion for Al-Zn-Mg alloys.
  • the yield strength was measured in the Longitudinal direction and the resistance to flaky corrosion (loss of mass after SWAAT test on full thickness test specimen or machined test on half of its surface ) has been evaluated.
  • the sensitivity to stress corrosion has been determined in both directions only in the T6 state because it is known (see the article by Reboul et al., Cited above) that this is the most sensitive state. stress corrosion.
  • the results are given in Tables 3 and 4.
  • Example 2 The sheets from Example 1, rolled to 6 mm and put into solution at 560 ° C., designated ACH and BCH, were welded in the T6 state.
  • the weld was made in the Travers-Long direction, with an X chamfer, by a smooth-running semi-automatic MIG process, with a 5183 alloy filler wire (Mg 4.81%, Mn 0.651%, Ti 0.120%, Si 0.035%, Fe 0.130%, Zn 0.001%, Cu 0.001%, Cr 0.075%) of 1.2mm diameter, supplied by Soudure Auto constitutitie.
  • Tensile specimens (width 25 mm, symmetrically trimmed bead, effective length of test piece and length of extensometer equal to (W + 2 e) where W is the width of the bead and the thickness of the test piece) were taken in the long direction, perpendicular to the weld, so that the seal is in the middle.
  • the Characterization was made 19, 31 and 90 days after welding, because the skilled person knows that for this type of alloys, the mechanical properties after welding increase sharply during the first weeks of maturation. Test specimens machined at mid-thickness on half of their surface were also subjected to SWAAT and EXCO tests.
  • the alloy according to composition B has less advantageous mechanical properties after welding than the alloy according to composition A. After welding, the resistance in flaky corrosion of the two alloys is degraded with respect to the behavior of the base metal.
  • a plate C was prepared by semicontinuous casting. Its composition is identical to that of the plate B resulting from example 1.
  • the plate was hot rolled after reheating for 13 hours at 550 ° C. (time at the stage) followed by a rolling bearing at 540 ° C.
  • the first step reversible mill, brought the plate to a thickness of 15.5 mm, the exit temperature of the mill being about 490 ° C.
  • the rolled plate was then cooled by spraying and natural convection to a temperature of about 260 ° C. At this temperature, it was fed into a tandem mill (3 cages), rolled to the final thickness of 6 mm, and wound.
  • the winding temperature of the coil measured as in Example 1, is about 150 ° C. Once cooled naturally, the coil was discharged into sheets. These were hovered and did not undergo any other deformation operation.
  • the sheets obtained were characterized in terms of manufacturing (static mechanical characteristics Long and Travers-Long direction, stress corrosion and stress) and after welding (static mechanical characteristics, flaking corrosion). .
  • the welding was carried out simultaneously with the welding of Example 2, and according to the same method. Test specimens machined at half thickness on half of their surface were subjected to SWAAT and EXCO tests. The results are collated in Tables 7 and 8 (non-welded sheets) and in Table 9 (welded sheets).
  • the raw sheet (not welded) according to the invention has a lower resistance to flake corrosion than that of the sheet BCH, manufactured from the same composition but with a much more complex manufacturing process. On the other hand, its corrosion resistance under stress is equivalent.
  • the sheet according to the invention After welding, the sheet according to the invention has a mechanical strength very much greater than that of ACH and BCH sheets developed with a method according to the prior art. Its resistance to flaky corrosion on welded joint is equivalent.
  • the method according to the invention performs the winding at a temperature of about 120 ° C lower than the method according to the state of the art of Example 1.
  • Example 3 The sheet marked "C” derived from Example 3 was subjected to additional heat treatments of the tempered type at a temperature of 140 ° C. The samples thus obtained were then characterized as in Example 3 (static mechanical characteristics L direction and laminating corrosion). The results are summarized in Table 10 and on figure 5 (the black dots and the black line correspond to the elastic limit, and the bars to mass loss during the SWAAT test).
  • Table 10 Heat treatment R p0.2 (L) [MPa] R m (L) [MPa] A% (L) [%] Mass loss ⁇ m in g / dm 2 Rating in flaky corrosion SWAAT 100 cycles EXCO 96h SWAAT 100 cycles No (" VS ") 305 344 14.4 0.85 5.1 EA 3h 140 ° C.
  • microstructure of samples ACH, BCH, BFH and C of Examples 1, 2 and 3 was characterized by scanning electron microscopy with field emission cannon (FEG-SEM, in BSE (backscattered electron) mode, acceleration voltage 15 kV, diaphragm 30 ⁇ m, working distance 10 mm, polished to L-TC sampling direction with Pt / Pd conductive deposition) and transmission electron microscopy (TEM, L-TL sampling direction, slide preparation by double jet electrochemical thinning with 30% HNO 3 in methanol at -35 ° C with a potential of 20 V). All samples were taken at mid-thickness of the plate.
  • FEG-SEM field emission cannon
  • BSE backscattered electron
  • TEM transmission electron microscopy
  • HZ heat-affected zone
  • the heat-affected zone has a hardness greater than that of the base metal for sheet C produced by the process according to the invention, which is quite unusual.
  • the thickness of the test pieces is indicated in Table 12.
  • the test makes it possible to define the curve R of the material, giving the tear resistance K R as a function of the extension of the crack ⁇ a.
  • the results are summarized in Table 13 and on Figure 7 .
  • the product according to the invention shows a better toughness in plane stress K R than a known reference product, whereas the crack propagation speed da / dN (TL) at the high ⁇ K values is substantially comparable.
  • the temperature T s was 603 ° C. (value obtained by numerical calculation).
  • the final thickness of the strip was 6 mm, its width 2400 mm.
  • the final product shows no recrystallization.
  • a fibered microstructure is observed at mid-thickness, with a grain thickness of the order of 10 ⁇ m.
  • Corrosion resistance evaluated by the EXCO test, was EA at the surface and at mid-thickness.
  • the corrosion resistance evaluated by the SWAAT test, was P at the surface and at mid-thickness, and the mass loss was 0.52 g / dm 2 at the surface and 0.17 g / dm 2 at mid-thickness.
  • the temperature T S for the alloy U was 600 ° C. (value obtained by numerical calculation).
  • the thickness of the strips U3 and U4 was 6 mm, that of the strips U1, U2 and S2 8 mm.
  • microstructure and the abrasion resistance of different sheets obtained by the process according to the invention (reference 7108 F7) and according to the state of the art (marks 5086 H24, 5186 H24, 5383 H34, 7020 T6, 7075 T6 and 7108 T6).
  • Table 19 gathers results concerning the mechanical characteristics and the microstructure of these sheets.
  • the material 7108 T6 had the composition of the alloy B of Example 2, and was close to the BCH material.
  • the material 7108 F7 has the same composition B of Example 2.
  • the abrasion resistance has been characterized using an original device that reproduces the conditions such as they may occur for example when loading, transporting and unloading sand in a bucket.
  • This test consists in measuring the loss of mass of a sample subjected to a vertical movement back and forth in a tank filled with sand.
  • the diameter of the tank is about 30 cm, the height of the sand about 30 cm.
  • the sample holder is fixed on a vertical rod connected to a double-acting jack which ensures the vertical movement of the rod back and forth.
  • the sample holder is in the form of a pyramid with a 45 ° angle. This is the tip of the pyramid that plunges into the sand.
  • the samples to be tested are embedded in the faces of the pyramid so that their surface is tangent to that of the corresponding face of the pyramid; it is the face corresponding to the L-TL plane (dimension 15 x 10 mm) which is exposed to the sand.
  • the depth of penetration of the sample into the sand was 200 mm.
  • weight loss values given are the average of three tests; the confidence interval is in the range of ⁇ 0.01 to 0.02 g; this underlines the good repeatability of this test.
  • Table 19 shows the very particular microstructure of the product obtained by the process according to the present invention, by comparing the two alloy products 7108, one (reference T6) obtained according to a known method, the other (reference F7) according to the process which is the subject of the present invention.
  • Table 20 shows the effect of this microstructure on abrasion resistance. It is immediately apparent that the product according to the invention is more resistant to abrasion than the standard product 5086 H24. This highlights its good suitability for use in industrial vehicles, as well as storage and handling equipment for granular products, such as skips, tanks, or conveyors.

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Claims (27)

  1. Verfahren zur Herstellung eines gewalzten Zwischenerzeugnisses aus Aluminiumlegierung vom Typ Al-Zn-Mg, umfassend folgende Schritte:
    a) im halbkontinuierlichen Strangguss wird ein Barren hergestellt, enthaltend (in Masseprozenten) Mg 0,5 - 2,0 Mn < 1,0 Zn 3,0 - 9,0 Si < 0,50 Fe < 0,50 Cu < 0,50 Ti < 0,15 Zr < 0,20 Cr < 0,50
    Rest Aluminium mit seinen unvermeidbaren Verunreinigungen, bei dem Zn/Mg > 1,7,
    b) der Barren wird einer Homogenisierung oder Erwärmung auf eine Temperatur T1 unterworfen, die so gewählt wird, dass 500°C ≤ T1 ≤ (Ts - 20°C), wobei Ts die Verbrennungstemperatur der Legierung darstellt,
    c) es wird ein erster Warmwalzschritt durchgeführt, bestehend aus einem oder mehreren Walzstichen auf einem Warmwalzgerüst, wobei die Eintrittstemperatur T2 so gewählt wird, dass (T1 - 60°C) ≤ T2 ≤ (T1 - 5°C), und wobei das Walzverfahren in der Weise gesteuert wird, dass die Austrittstemperatur T3 so geregelt ist, dass (T1 - 150°C) ≤ T3 ≤ (T1 - 30°C) und T3 < T2,
    d) das Band aus dem ersten Warmwalzschritt wird rasch auf eine Temperatur T4 abgekühlt,
    e) es wird ein zweiter Warmwalzschritt an dem Band durchgeführt, wobei die Eintrittstemperatur T5 so gewählt wird, dass T5 ≤ T4 und 200°C ≤ T5 ≤ 300°C, und wobei das Walzverfahren in der Weise gesteuert wird, dass die Aufhaspeltemperatur T6 so geregelt ist, dass (T5 - 150°C) ≤ T6 ≤ (T5 - 20°C).
  2. Verfahren nach Anspruch 1, dadurch gekennzeichnet, dass der Zinkgehalt der Legierung zwischen 4,0 und 6,0 % liegt, der Mg-Gehalt zwischen 0,7 und 1,5 % liegt und der Mn-Gehalt unter 0,60 % liegt.
  3. Verfahren nach Anspruch 2, dadurch gekennzeichnet, dass Cu < 0,25 %.
  4. Verfahren nach Anspruch 2, dadurch gekennzeichnet, dass die Legierung aus der Gruppe bestehend aus den Legierungen 7020, 7108, 7003, 7004, 7005, 7008, 7011, 7022 gewählt wird.
  5. Verfahren nach irgendeinem der Ansprüche 1 bis 3, dadurch gekennzeichnet, dass die Legierung zusätzlich ein oder mehrere Elemente gewählt aus der Gruppe bestehend aus Sc, Y, La, Dy, Ho, Er, Tm, Lu, Hf, Yb enthält, mit einer Konzentration, die folgende Werte nicht übersteigt:
    Sc < 0,50 % und vorzugsweise < 0,20 %,
    Y < 0;34 % und vorzugsweise < 0,17 %,
    La, Dy, Ho, Er, Tm, Lu jeweils < 0,10 % und vorzugsweise jeweils < 0,05 %,
    Hf < 1,20 % und vorzugsweise < 0,50 %,
    Yb < 0,50 % und vorzugsweise < 0,25 %.
  6. Verfahren nach irgendeinem der Ansprüche 1 bis 5, dadurch gekennzeichnet, dass das gewalzte Zwischenerzeugnis eine Dicke zwischen 3 mm und 12 mm hat.
  7. Verfahren nach irgendeinem der Ansprüche 1 bis 6, dadurch gekennzeichnet, dass das gewalzte Zwischenerzeugnis einer 1 bis 9 %-igen Kaltumformung und/oder einer ein- oder mehrstufigen, zusätzlichen Wärmebehandlung bei Temperaturen zwischen 80°C und 250°C unterworfen wird, wobei die zusätzliche Wärmebehandlung vor, nach oder während der Kaltumformung erfolgen kann.
  8. Verfahren nach irgendeinem der Ansprüche 1 bis 7, dadurch gekennzeichnet, dass die Temperatur T3 so gewählt wird, dass (T1 - 100°C) ≤ T3 ≤ (T1 - 30°C), und/oder die Temperatur T2 so gewählt wird, dass (T1 - 30°C) ≤ T2 ≤ (T1 - 5°C).
  9. Verfahren nach irgendeinem der Ansprüche 1 bis 8, dadurch gekennzeichnet, dass die Temperatur T3 oberhalb der Solvustemperatur der Legierung liegt.
  10. Verfahren nach irgendeinem der Ansprüche 1 bis 9, dadurch gekennzeichnet, dass es sich bei der Legierung um die Legierung 7108 handelt und bei den Temperaturen T1 bis T6 um:
    T1 = 550°C, T2 = 540°C, T3 = 490°C, T4 = 270°C, T5 = 270°C, T6 = 150°C.
  11. Blech oder Band mit einer Dicke zwischen 3 mm und 12 mm, herstellbar durch das Verfahren nach irgendeinem der Ansprüche 1 bis 10, dadurch gekennzeichnet, dass seine Dehngrenze Rp0,2 mindestens 250 MPa beträgt, seine Bruchfestigkeit Rm mindestens 280 MPa beträgt und seine Bruchdehnung mindestens 8 % beträgt, dass sein Zinkgehalt zwischen 4,0 und 6,0 % liegt, sein Mg-Gehalt zwischen 0,7 und 1,5 % liegt, sein Mn-Gehalt unter 0,60 % liegt (und vorzugsweise unter 0,25 %), sein Kupfergehalt unter 0,25 % liegt, dass die Ausscheidungen vom Typ MgZn2 an den Korngrenzen eine mittlere Größe von mehr als 150 nm und vorzugsweise 200 bis 400 nm haben und dass es ein faseriges Gefüge aufweist, gekennzeichnet durch ein Verhältnis Kornlänge zu Korndicke von mehr als 60 und bevorzugt mehr als 100, mit Körnern, die in Kurz-Querrichtung eine Dicke von mindestens 30 µm, bevorzugt mindestens 15 µm und besonders bevorzugt mindestens 10 µm aufweisen.
  12. Blech oder Band nach Anspruch 11, dadurch gekennzeichnet, dass seine Dehngrenze Rp0,2 mindestens 290 MPa beträgt und seine Bruchfestigkeit Rm mindestens 330 MPa beträgt.
  13. Blech oder Band nach irgendeinem der Ansprüche 11 oder 12, dadurch gekennzeichnet, dass die Breite der ausscheidungsfreien Zonen an den Korngrenzen des Erzeugnisses mehr als 100 nm beträgt, bevorzugt zwischen 100 und 150 nm liegt und besonders bevorzugt zwischen 120 und 140 nm liegt.
  14. Verwendung eines Blechs oder Bandes nach irgendeinem der Ansprüche 11 bis 13 für die Herstellung von Schweißkonstruktionen.
  15. Verwendung eines Blechs oder Bandes nach irgendeinem der Ansprüche 11 bis 13 für den Bau von Straßen- oder Schienentankwagen.
  16. Verwendung eines Blechs oder Bandes nach irgendeinem der Ansprüche 11 bis 13 für den Bau von Industriefahrzeugen.
  17. Verwendung eines Blechs oder Bandes nach irgendeinem der Ansprüche 11 bis 13 beim Bau von Lager-, Transport- oder Handhabungsausrüstungen für Granulatprodukte, wie Kübel, Behälter oder Förderer.
  18. Verwendung eines Blechs oder Bandes nach irgendeinem der Ansprüche 11 bis 13 für die Herstellung von Automobilteilen.
  19. Verwendung eines Blechs oder Bandes nach irgendeinem der Ansprüche 11 bis 13 als Strukturelement im Flugzeugbau.
  20. Verwendung nach Anspruch 19, bei der das Strukturelement ein Deckblech für den Flugzeugrumpf ist.
  21. Verwendung nach irgendeinem der Ansprüche 14 bis 20, bei der mindestens zwei der Strukturelemente zusammengeschweißt werden.
  22. Schweißkonstruktion hergestellt mit mindestens zwei Blechen oder Bändern nach irgendeinem der Ansprüche 11 bis 13, dadurch gekennzeichnet, dass ihre Dehngrenze Rp0,2 in der Schweißverbindung zwischen zwei der genannten Erzeugnisse mindestens 200 MPa beträgt.
  23. Schweißkonstruktion nach Anspruch 22, bei der die Dehngrenze Rp0,2 in der Schweißverbindung zwischen zwei der genannten Erzeugnisse mindestens 220 MPa beträgt.
  24. Schweißkonstruktion hergestellt mit mindestens zwei Blechen oder Bändern nach irgendeinem der Ansprüche 11 bis 13, dadurch gekennzeichnet, dass ihre Bruchfestigkeit Rm in der Schweißverbindung zwischen zwei der genannten Erzeugnisse mindestens 250 MPa beträgt.
  25. Schweißkonstruktion nach Anspruch 24, bei der die Bruchfestigkeit Rm in der Schweißverbindung zwischen zwei der genannten Erzeugnisse mindestens 300 MPa beträgt.
  26. Schweißkonstruktion nach einem der Ansprüche 22 bis 25, bei der die Härte in der wärmebelasteten Zone größer oder gleich 100 HV, bevorzugt größer oder gleich 110 HV und besonders bevorzugt größer oder gleich 115 HV ist.
  27. Schweißkonstruktion nach Anspruch 26, bei der die Härte in der wärmebelasteten Zone mindestens ebenso groß ist wie die Härte desjenigen Basisblechs, das die größte Härte aufweist.
EP03767916A 2002-11-06 2003-11-06 Vereinfachtes verfahren zur herstellung von gewalzten produkten aus al-zn-mg-legierungen, und dadurch hergestellte produkte Expired - Lifetime EP1558778B1 (de)

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FR0213859 2002-11-06
FR0213859A FR2846669B1 (fr) 2002-11-06 2002-11-06 PROCEDE DE FABRICATION SIMPLIFIE DE PRODUITS LAMINES EN ALLIAGES A1-Zn-Mg, ET PRODUITS OBTENUS PAR CE PROCEDE
PCT/FR2003/003312 WO2004044256A1 (fr) 2002-11-06 2003-11-06 PROCEDE DE FABRICATION SIMPLIFIE DE PRODUITS LAMINES EN ALLIAGES Al-Zn-Mg, ET PRODUITS OBTENUS PAR CE PROCEDE

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Families Citing this family (42)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20050034794A1 (en) * 2003-04-10 2005-02-17 Rinze Benedictus High strength Al-Zn alloy and method for producing such an alloy product
GB2426979B (en) 2003-04-10 2007-05-23 Corus Aluminium Walzprod Gmbh An Al-Zn-Mg-Cu alloy with improved damage tolerance-strength combination properties
US7260972B2 (en) * 2004-03-10 2007-08-28 General Motors Corporation Method for production of stamped sheet metal panels
US20050238528A1 (en) * 2004-04-22 2005-10-27 Lin Jen C Heat treatable Al-Zn-Mg-Cu alloy for aerospace and automotive castings
US20060000094A1 (en) * 2004-07-01 2006-01-05 Garesche Carl E Forged aluminum vehicle wheel and associated method of manufacture and alloy
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
DE502005001724D1 (de) 2005-01-19 2007-11-29 Fuchs Kg Otto Abschreckunempfindliche Aluminiumlegierung sowie Verfahren zum Herstellen eines Halbzeuges aus dieser Legierung
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
WO2007009616A1 (en) * 2005-07-21 2007-01-25 Aleris Aluminum Koblenz Gmbh A wrought aluminum aa7000-series alloy product and method of producing said product
EP2038447B1 (de) 2006-07-07 2017-07-19 Aleris Aluminum Koblenz GmbH Verfahren zur herstellung von produkten aus aluminium-legierungen vom 2000-typ
FR2907796B1 (fr) * 2006-07-07 2011-06-10 Aleris Aluminum Koblenz Gmbh Produits en alliage d'aluminium de la serie aa7000 et leur procede de fabrication
JP5819294B2 (ja) * 2010-06-11 2015-11-24 昭和電工株式会社 Ａｌ合金接合体の製造方法
WO2012016027A1 (en) * 2010-07-30 2012-02-02 Alcoa Inc. Multi-alloy assembly having corrosion resistance and method of making the same
CN103119184B (zh) 2010-09-08 2015-08-05 美铝公司 改进的6xxx铝合金及其生产方法
EP2479305A1 (de) * 2011-01-21 2012-07-25 Aleris Aluminum Duffel BVBA Verfahren zur Herstellung eines Automobilstrukturteils aus einer gewalzten Al-Zn-Legierung
RU2468107C1 (ru) * 2011-04-20 2012-11-27 Открытое акционерное общество "Всероссийский институт легких сплавов" (ОАО "ВИЛС") Высокопрочный деформируемый сплав на основе алюминия с пониженной плотностью и способ его обработки
JP5023232B1 (ja) 2011-06-23 2012-09-12 住友軽金属工業株式会社 高強度アルミニウム合金材およびその製造方法
JP5285170B2 (ja) 2011-11-07 2013-09-11 住友軽金属工業株式会社 高強度アルミニウム合金材及びその製造方法
RU2489217C1 (ru) * 2011-12-27 2013-08-10 Открытое акционерное общество "Всероссийский институт легких сплавов" (ОАО "ВИЛС") Способ производства листов из термически упрочняемых алюминиевых сплавов, легированных скандием и цирконием
WO2013172910A2 (en) 2012-03-07 2013-11-21 Alcoa Inc. Improved 2xxx aluminum alloys, and methods for producing the same
JP6223669B2 (ja) * 2012-09-20 2017-11-01 株式会社神戸製鋼所 自動車部材用アルミニウム合金板
JP6223670B2 (ja) * 2012-09-20 2017-11-01 株式会社神戸製鋼所 自動車部材用アルミニウム合金板
US9587298B2 (en) 2013-02-19 2017-03-07 Arconic Inc. Heat treatable aluminum alloys having magnesium and zinc and methods for producing the same
US9315885B2 (en) * 2013-03-09 2016-04-19 Alcoa Inc. Heat treatable aluminum alloys having magnesium and zinc and methods for producing the same
JP6344923B2 (ja) 2014-01-29 2018-06-20 株式会社Uacj 高強度アルミニウム合金及びその製造方法
RU2569275C1 (ru) * 2014-11-10 2015-11-20 Федеральное государственное унитарное предприятие "Всероссийский научно-исследовательский институт авиационных материалов" (ФГУП "ВИАМ") Плита из высокопрочного алюминиевого сплава и способ ее изготовления
CN104831134A (zh) * 2015-04-30 2015-08-12 广西南南铝加工有限公司 一种中强高韧的Al-Zn-Mg合金
KR102055051B1 (ko) 2015-05-08 2019-12-11 노벨리스 인크. 알루미늄 합금 물품의 충격 열처리
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
KR102227325B1 (ko) 2016-10-17 2021-03-15 노벨리스 인크. 맞춤-조정된 성질을 갖는 금속 시트
US11072844B2 (en) 2016-10-24 2021-07-27 Shape Corp. Multi-stage aluminum alloy forming and thermal processing method for the production of vehicle components
KR102457529B1 (ko) * 2017-03-07 2022-10-21 엘지전자 주식회사 알루미늄 합금
CN109457147B (zh) * 2018-12-28 2020-10-20 辽宁忠旺集团有限公司 一种铝制打包带及其生产工艺
CN111411272B (zh) * 2020-03-23 2021-10-01 西安交通大学 用于电弧增材制造的Al-Zn-Mg系铝合金焊丝及其制备方法
JPWO2021193842A1 (de) * 2020-03-26 2021-09-30
JPWO2021193841A1 (de) * 2020-03-26 2021-09-30
JP7140892B1 (ja) 2021-06-28 2022-09-21 株式会社神戸製鋼所 アルミニウム合金押出材およびその製造方法
CN113564434B (zh) * 2021-08-12 2022-03-22 四川福蓉科技股份公司 一种7系铝合金及其制备方法
CN114990396B (zh) * 2022-07-11 2023-02-24 上海交通大学 一种超高强7000系铝合金材料及其制备方法和应用
CN116219238B (zh) * 2022-12-26 2024-09-24 江苏中天科技股份有限公司 铝合金导体线材及其制备方法与应用
CN116219239B (zh) * 2023-01-04 2024-10-18 福建煜雄科技有限公司 一种抗疲劳复合金属材料及其制备方法

Family Cites Families (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1483324C2 (de) 1965-12-02 1975-04-24 Vereinigte Aluminium-Werke Ag, 5300 Bonn Verwendung von AIZnMg-Leglerungen mit geringer Kerbempfindlichkeit
US3694272A (en) * 1970-12-24 1972-09-26 Kaiser Aluminium Chem Corp Method for forming aluminum sheet
GB1419491A (en) 1971-11-01 1975-12-31 British Aluminium Co Ltd Aluminium alloy
JPS5221966B2 (de) * 1971-12-29 1977-06-14
US3945861A (en) * 1975-04-21 1976-03-23 Aluminum Company Of America High strength automobile bumper alloy
JPS57161045A (en) * 1981-03-31 1982-10-04 Sumitomo Light Metal Ind Ltd Fine-grain high-strength aluminum alloy material and its manufacture
JPS619561A (ja) * 1984-06-25 1986-01-17 Mitsubishi Alum Co Ltd 熱間成形性の優れたＡｌ合金板の製造法
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
US5061327A (en) * 1990-04-02 1991-10-29 Aluminum Company Of America Method of producing unrecrystallized aluminum products by heat treating and further working
EP0544758A1 (de) * 1990-08-22 1993-06-09 Comalco Aluminium, Ltd. Aluminium-legierung geeignet zur dosenherstellung
GB9200622D0 (en) * 1992-01-13 1992-03-11 Duley Walter W Improved means of co2 laser welding of a1 7075
US5655593A (en) * 1995-09-18 1997-08-12 Kaiser Aluminum & Chemical Corp. Method of manufacturing aluminum alloy sheet
JP3735407B2 (ja) * 1996-04-02 2006-01-18 アイシン軽金属株式会社 高強度アルミニウム合金
JPH116044A (ja) 1997-06-13 1999-01-12 Aisin Keikinzoku Kk 高強度・高靱性アルミニウム合金
ATE217912T1 (de) * 1997-08-04 2002-06-15 Corus Aluminium Walzprod Gmbh Hochverformbare, korrosionsbeständige al- legierung
JPH11302763A (ja) * 1998-04-23 1999-11-02 Aisin Keikinzoku Co Ltd 耐応力腐食割れ性に優れる高強度アルミニウム合金
JP3926934B2 (ja) * 1998-10-15 2007-06-06 株式会社神戸製鋼所 アルミニウム合金板
JP4818509B2 (ja) * 2000-12-04 2011-11-16 新日本製鐵株式会社 塗装焼付け硬化およびプレス成形用アルミニウム合金板およびその製造方法

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EP1558778A1 (de) 2005-08-03
CA2504931A1 (fr) 2004-05-27
FR2846669B1 (fr) 2005-07-22
RU2005117168A (ru) 2006-01-20
ES2314255T3 (es) 2009-03-16
US7780802B2 (en) 2010-08-24
RU2326182C2 (ru) 2008-06-10
DE60324581D1 (de) 2008-12-18
US20060016523A1 (en) 2006-01-26
JP2006505695A (ja) 2006-02-16
WO2004044256A1 (fr) 2004-05-27
CA2504931C (fr) 2011-10-04
FR2846669A1 (fr) 2004-05-07
ATE413477T1 (de) 2008-11-15
AU2003292348A1 (en) 2004-06-03

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