EP0368005A1 - Verfahren zur Herstellung eines nichtkristallisierten, flachgewalzten, dünnen, wärmebehandelten Produktes auf Aluminiumbasis - Google Patents

Verfahren zur Herstellung eines nichtkristallisierten, flachgewalzten, dünnen, wärmebehandelten Produktes auf Aluminiumbasis Download PDF

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Publication number
EP0368005A1
EP0368005A1 EP89118810A EP89118810A EP0368005A1 EP 0368005 A1 EP0368005 A1 EP 0368005A1 EP 89118810 A EP89118810 A EP 89118810A EP 89118810 A EP89118810 A EP 89118810A EP 0368005 A1 EP0368005 A1 EP 0368005A1
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product
max
temperature
unrecrystallized
wrought
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EP89118810A
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French (fr)
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EP0368005B1 (de
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Alex Cho
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Howmet Aerospace Inc
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Aluminum Company of America
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Priority claimed from US07/256,521 external-priority patent/US4988394A/en
Priority claimed from US07/256,520 external-priority patent/US4946517A/en
Priority claimed from US07/256,840 external-priority patent/US4927470A/en
Application filed by Aluminum Company of America filed Critical Aluminum Company of America
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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
    • 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
    • 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
    • C22F1/057—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 copper as the next major constituent

Definitions

  • This invention relates to heat treatable alloys such as the AA2000, 6000 and 7000 series alloys and more specifically, it relates to thermal or thermal mechanical processing of such alloys to improve strength and fracture toughness in thin plate, for example.
  • alloys of the 7000 series have been used for high strength and toughness in aerospace applications. These alloys can be age hardened to very high strengths, for example, in the T6 temper condition. Further, the strengths of these alloys may be increased by increasing solute content. Increasing the strength of these alloys permits designers to reduce the weight of aircraft by reducing thickness of load carrying components such as upper wing skins. Such components must have (and even demand) relatively high fracture toughness as well as high strength to be useful.
  • load carrying components such as upper wing skins.
  • Such components must have (and even demand) relatively high fracture toughness as well as high strength to be useful.
  • U.S. Patent 4,092,181 discloses a method of imparting a fine grain recrystallized structure to aluminum alloys having precipitating constituents.
  • the method is provided for imparting a fine grain structure to aluminum alloys which have precipitating constituents.
  • the alloy is first heated to a solid solution temperature to dissolve the precipitating constituents in the alloy.
  • the alloy is then cooled, preferably by water quenching, to below the solution temperature and then overaged to form precipitates by heating it above the precipita­tion hardening temperature for the alloy but below its solution treating temperature. Strain energy is introduced into the alloy by plastically deforming it at or below the overaging temperature used.
  • the alloy is then subsequently held at a recrystallization temperature so that the new grains are nucleated by the overaged precipitates and the development of these grains results in a fine recrystallized grain structure.
  • This structure is useful for imparting superplastic properties but will provide lower toughness than an unrecrystallized structure.
  • the present invention provides improved thermal or thermal mechanical processing techniques which permit tle fabrication of flat rolled products, particularly thin gauge plate and sheet 7000 series aluminum alloys having a substantially unrecrystallized structure which imparts to the plate improved combinations of strength and fracture toughness.
  • an unrecrystallized thin gauge flat rolled product suitable for fabricating into aircraft structural members
  • the unrecrystal­lized thin gauge flat rolled product comprised of an aluminum base alloy selected from 2000, 6000 or 7000 series alloys.
  • the alloy can consist essentially of 1.0 to 12 wt.% Zn, 0.5 to 4.0 wt.% Mg, max. 3.0 wt.% Cu, max. 1.0 wt.% Mn, max. 0.5 wt.% each of Si, Fe, Cr, Ti, Zr, Sc and Hf, the balance aluminum and impurities.
  • a method of producing an unrecrystallized, thin gauge flat rolled product which includes hot working a body of the alloy to a thin gauge flat rolled product then subjecting the product to a ramp anneal wherein the annealing temperature is increased with time of anneal. This is followed by solution heat treating, quenching and aging to provide a substantially unrecrystallized product having improved levels of strength and fracture toughness.
  • an unrecrystallized aluminum base alloy, thin gauge flat rolled product which includes hot working a body of the alloy to a final gauge flat rolled product. This is followed by isothermal soaking the product, ramp annealing, solution heat treating, quenching and aging to provide a substantially unrecrystallized product having improved levels of strength and fracture toughness.
  • an unrecrystallized Al-Zn-Mg, thin gauge flat rolled product which includes hot working a body of the alloy to a first product.
  • the first product is then reheated, cooled and heat treated before rolling to a thin gauge flat rolled product, e.g., thin gauge plate or sheet.
  • solution heat treating, quenching and aging to provide a substantially unrecrystallized product having improved levels of strength and fracture toughness.
  • Aluminum based alloys which respond to thermal mechanical processing in accordance with the present invention include the Aluminum Association 7000 series. Such alloys include, for example, 7050, 7150, 7075, 7475, 7049 and 7039.
  • these aluminum based alloys contain 1.0 to 12.0 wt.% Zn, 0.5 to 4.0 wt.% Mg, max. 3.0 wt.% Cu, max. 1.0 wt.% Mn, max. 0.5 wt.% each of Si, Fe, Cr, Ti, Zr, Sc and Hf, the balance aluminum, incidental elements and impurities.
  • These alloys may be referred to as Al-Zn-Mg or Al-Zn-Cu-Mg type. Alloys which seem to respond more readily to thermal mechanical processing in accordance with the present invention include higher levels of zinc, preferably 7.0 to 12.0 wt.% Zn with a typical level being 8.0 to 11.0 wt.%.
  • Magnesium at these levels of zinc can range from 0.2 to 3.5, preferably 0.4 to 3.0 wt.%.
  • copper at the higher zinc levels can range from 0.5 to 3.0 wt.%, preferably 1.0 to 3.0 wt.%.
  • These alloying elements may be higher in certain cases, but the resulting alloys can have low fracture toughness. In certain cases, other ranges of alloying elements may be preferred.
  • Zn can be in the range of 7.0 to 9.0 wt.%, Mg 1.5 to 2.5 wt.%, Cu 1.9 to 2.7 wt.%, Zr, 0.08 to 0.14, with impurities such as Fe and Si being less than 0.3 wt.%.
  • the Aluminum Association composition limits encompassing 7050 and 7150 are: 5.7 to 6.9 wt.% Zn, 1.9 to 2.7 wt.% Mg, 1.9 to 2.6 wt.% Cu, 0.05 to 0.15 wt.% Zr, max. 0.12 wt.% Si, max. 0.15 wt.% Fe, max. 0.10 wt.% Mn, max. 0.06 wt.% Ti, max. 0.04 wt.% Cr, the balance aluminum and incidental elements and impurities.
  • AA7000 series aluminum alloys have been described in detail, it will be understood that the invention can be applied to other heat treatable alloys such as the AA2000 and 6000 series aluminum alloysas well as AA8000 alloys which include lithium, e.g., 8090 and 8091.
  • typical AA2000 series alloys which may be included are AA2024, 2124, 2324, 2219, 2519, 2014, 2618, 2034, 2090 and 2091, and typical of AA6000 series alloys are 6061 and 6013.
  • Products formed from these alloys have oxygen content of less than 0.1 wt.%.
  • the products, e.g., flat rolled products are substantially free of the as-cast structure.
  • the alloy be prepared according to specific method steps in order to provide the most desirable characteristics of both strength and fracture toughness.
  • the alloy as described herein can be provided as an ingot or billet for fabrication into a suitable wrought product by casting techniques currently employed in the art for cast products, with continuous casting being preferred.
  • the ingot or billet may be preliminarily worked or shaped to provide suitable stock for subsequent working operations.
  • the alloy stock Prior to the principal working operation, the alloy stock is preferably subjected to homogenization, and preferably at metal temperatures in the range of 850 to 1050°F for a period of time of at least one hour to dissolve soluble elements and to homogenize the internal structure of the metal.
  • a preferred time period is about 20 hours or more in the homogenization temperature range. Normally, the heat up and homogenization treatment does not have to extend for more than 40 hours; however, longer times are not normally detrimental. A time of 20 to 40 hours at the homogenization temperature has been found quite suitable.
  • the ingot may be rolled to a final gauge product. Then, the product is subjected to an annealing treatment wherein annealing temperature is increased with time of anneal and referred to herein as a ramp anneal.
  • annealing temperature is increased with time of anneal and referred to herein as a ramp anneal.
  • the starting temperature can be as high as 750°F and then increased with anneal time to temperatures higher than 750°F, e.g. 850°F. With respect to higher starting temperatures, a typical starting temperature is 730°F and the temperature can then be increased with time to about 800°F.
  • starting temperatures do not usually exceed 550°F, normally 400°F, with a typical starting temperature being in the range of 350 to 450°F and an ending temperature being in the range of 650 to 850°F.
  • Typical ending temperatures are in the range of 750 to 850°F, depending on the alloy composition.
  • the temperature can be increased at a rate of 2 to 100°/hr, and preferably at a rate of 5 to 80°/hr.
  • the time from the beginning to the end of the ramp anneal can range from 3 to about 10 hours, with typical times being in the range of 2 to 8 hours.
  • the ramp anneal can include a series of increases in temperature with a holding time at temperature plateau or series of plateaus.
  • the ingot may be hot rolled directly to final gauge plate or sheet before being subjected to an isothermal soak and then ramp annealed in accordance with the present invention.
  • the product is subjected to a warm temperature or isothermal soak treatment.
  • the isothermal soak can be carried out at a temperature as low as 250°F but normally higher than 275°F and typically in the range of 300 to 500°F.
  • the soak can be for a time of a few hours, e.g., 3 hours, particularly if the temperature is high and can extend for 24 hours or more.
  • the soak time extends for 4 to 20 hours.
  • the flat rolled product is subjected to a ramp anneal where the anneal temperature is increased with time of anneal and is carefully controlled until it reaches a higher ending temperature.
  • ending temperatures are in the range of 650 or 700 to 900°F.
  • the starting temperature can be anywhere from about 100°F or even ambient to 750°F in some instances.
  • the starting temperature will be in the range of 250 to 730°F with preferred starting temperatures being less than 300°F, but normally in the range of 300 to 500°F.
  • the temperature can be increased at a controlled rate, e.g., at a rate of 2 to 125°F/hr and preferably at a rate of 5 to 80°F/hr.
  • the ramp anneal can include a series of increases in temperature with a holding time at temperature plateau or series of plateaus. Further, it can include even increases in temperature followed by decreases in temperature until the final ending temperature is reached. Also, there may be even holding plateaus at any one or more temperature level. It will be understood that in some cases, as the anneal temperature gets higher, an independent solution heat treatment may not be necessary but, instead, is included as part of the ramp anneal, as shown in fig.
  • the product may be cooled and a separate solution heat treatment, quench and aging performed.
  • the time from the beginning of the ramp anneal to the ending temperature can be as short as two hours or even less to as long as 20 hours or more. Time periods in the range of 3 to 10 hours have been quite suitable with time periods of 4 to 8 hours being found to be useful.
  • the ramp anneal may be used in addition to precipitation heat treating intermediate the working steps, and such combination is contemplated within the purview of the invention.
  • an unrecrystallized thin gauge plate or sheet product may be produced in a third aspect of the present invention.
  • unrecrystallized is meant the absence of well-developed grains and the presence of a highly worked structure containing recovered subgrain and retaining as-worked crystallographic texture, i.e., at least 60% of the plate or sheet is free of well-developed grains or retains the as-worked texture.
  • the thermomechanical steps should be carefully controlled.
  • the slab is reheated typically to a temperature in the range of 650 to 900°F and preferably 650 or 700 to 800°F (depending upon composition), for purposes of dissolving or partially dissolving particles that precipitated during the preceding thermal mechanical operation.
  • Reheating can be carried out in a time as short as 1 ⁇ 4, or 1 ⁇ 2 hour at temperature, and can extend for 4 hours or more. However, the longer times are not normally necessary.
  • the slab is cooled at a rate sufficient to retain dissolved elements in solution.
  • the slab is cold water quenched or rapidly cooled.
  • the slab is subjected to an elevated temperature precipitation heat treatment to precipitate particles in a controlled manner.
  • the precipitation heat treatment can be carried out at a temperature in the range of 200 to 550°F, preferably 350 to 500°F, with typical temperatures being 400 to 500°F.
  • Precipitation heat treatment times at this temperature can range from 5 to 20 hours or longer, and times of from 9 to 15 hours can be quite suitable.
  • Thin gauge plate contemplates having a thickness of at least 0.125, typically 0.25 inch or more. The thickness can extend to 0.5 inch or more, for example, 0.75 or 1.0 or even 1.25 inch.
  • the slab may be cold rolled at these temperatures, it is preferred that the slab be rolled to final gauge, e.g., thin gauge plate or sheet, using warm rolling practices.
  • warm rolling is performed at a temperature of not greater than 550°F.
  • the temperature at which warm rolling begins is not less than 200°F.
  • the warm rolling can begin at the precipitation heat treatment temperature.
  • the warm rolling temperature should not exceed the precipitation heat treatment temperature. Such temperatures are in the range of about 350 to 500°F. This warm rolling practice contrasts with the prior art which teaches that rolling temperatures should be significantly higher, typically above about 750°F.
  • the plate or sheet product is subjected to a solution heat treatment and then cooled, for example, by cold water quenching.
  • the solution heat treatment is preferably accomplished at a temperature in the range of 800 to 1050°F and unrecrystal­lized grain structure is produced.
  • a temperature in the range of 800 to 1050°F and unrecrystal­lized grain structure is produced.
  • typical times at temperatures can be relatively short, e.g., 5 minutes or less can be adequate.
  • the time at temperature can be 1 ⁇ 4 to 5 hours, typically 2 hours.
  • the product should be rapidly quenched to prevent or minimize uncontrolled precipitation of strengthening phases.
  • the quenching rate be at least 100°F per second from solution temperature to a temperature of about 200°F or lower.
  • a preferred quenching rate is at least 200°F per second in the temperature range of 900°F or more to 200°F or less. After the metal has reached a temperature of about 200°F, it may then be air cooled.
  • the alloy product of the present invention After the alloy product of the present invention has been quenched, it may be subjected to a subsequent aging operation to provide the combination of fracture toughness and strength which are so highly desired in aircraft members. Artificial aging can be accomplished by subjecting the sheet or plate or shaped product to a temperature in the range of 150 to 400°F for a sufficient period of time to further increase the yield strength. Some compositions of the alloy product are capable of being artificially aged to a yield strength as high as 100 ksi. However, the useful strengths are in the range of 70 to 90 ksi and corresponding fracture toughnesses are in the range of 20 to 50 ksi/in.
  • artificial aging is accomplished by subjecting the alloy product to a temperature in the range of 275 to 375°F for a period of at least 30 minutes.
  • a suitable aging practice contemplates a treatment of about 8 to 24 hours at a temperature of about 325°F.
  • the alloy product in accordance with the present invention may be subjected to any of the typical overaging or underaging treatments well known in the art, including natural aging. However, it is presently believed that natural aging provides the least benefit.
  • multiple aging steps such as two or three aging steps, are contemplated and stretching or its equivalent working may be used prior to or even after part of such multiple aging steps.
  • the ingot is extruded to an intermediate cross-sectional area, e.g., to reduce the area 75%.
  • the partially extruded material is subjected to a reheating step, for example, under the same conditions as referred to herein with respect to slab.
  • it is cooled and subjected to an elevated precipitation treatment as referred to for slab, for example.
  • the partial extrusion is further worked or extruded to product form preferably utilizing warm temperatures, for example, under the same conditions referred to for slab being rolled to final gauge.
  • the extrusion may be solution heat treated, quenched and aged to produce an unrecrystallized aluminum alloy extrusion.
  • the forging operation may be carried out incorporating the procedures set forth for the flat rolled product to produce an unrecrystallized aluminum alloy forged product. It will be appreciated that the rolling, extruding or forging steps may be combined to produce an unrecrystallized product.
  • ramp annealing is suitable for use in many applications. That is, it may be used quite successfully regardless of the previous thermomechanical practices. For example, it has been used on thin gauge plate where the slab was reheated, quenched, heat treated and warm rolled to a plate product, described earlier herein, to produce a thoroughly or completely unrecrystallized product (see Example 3).
  • An aluminum alloy consisting essentially of, by weight percent, 10 Zn, 1.8 Mg, 1.5 Cu and 0.12 Zr, the balance essentially aluminum and impurities was cast into an ingot suitable for rolling.
  • the ingot was homogenized and hot rolled at about 800°F to a 1.5 inch thick slab.
  • the slab was cut into several pieces which were heated to temperatures of 750 to 880°F and then hot rolled starting at about 750°F to 0.3 inch thick plate. Samples were given a ramp anneal starting at a temperature of 730°F and ending at 800°F, with a heat-up rate of about 10°F/hr.
  • Samples of 0.3 inch plate having the composition and prepared as in Example 1 were subjected to a ramp anneal starting at a temperature of 400 and ending at a temperature of 800°F, the increase in temperature being performed in 4 hours, as shown in Figure 2. These samples were solution heat treated as in Example 1. Examination of the microstructure showed a basically unrecrystallized grain structure.
  • This sample (0.3 inch plate) had the same composition and treated as in Example 2 except that prior to hot rolling to 0.3 inch thick plate, the sample was reheated to 750°F for about 0.5 hours, cold water quenched and then precipitation heat treated at 400°F for 12 hours and hot rolled to 0.3 inch thick plate starting at a temperature of 400°F.
  • the microstructure of this sample revealed a completely unrecrystallized grain structure.
  • An aluminum alloy consisting essentially of, by weight percent, 10 Zn, 1.8 Mg, 1.5 Cu and 0.12 Zr, the balance essentially aluminum and impurities, was cast into an ingot suitable for rolling.
  • the ingot was homogenized and rolled to a 1.5 inch thick slab.
  • the slab was cut into several pieces which were subjected to anneals at temperatures of 750 to 880°F and then hot rolled to 0.3 inch plate. Thereafter, the 0.3 inch plate was isothermal soaked for 16 hours at 400°F and then subjected to a ramp anneal starting at 400°F and ending at 800°F, increase in temperature being made in 4 hours.
  • the 0.3 inch plate was then solution heat treated at 880°F for 1 hour followed by a cold water quench. Examination of the microstructure showed unrecrystallized grain structures which demonstrates the effectiveness of isothermal soaking and ramp annealing in preventing recrystallization.
  • the ingot was homogenized and then hot rolled at about 800°F to a 1.5 inch thick slab. Thereafter, the slab was annealed for 30 minutes at 750°F and cold water quenched. The slab was then precipitation heat treated for 12 hours at 400°F. Thereafter, the slab was rolled at about 400°F to 0.3 inch thick plate and then solution heat treated at 880°F for 1 hour and cold water quenched. Examination revealed that the microstructure was substantially an unrecrystallized microstructure.
  • thermomechanical processing in accordance with the subject invention can produce an unrecrystallized thin gauge plate or sheet product in the Al-Zn-Mg or Al-Zn-Mg-Cu type aluminum alloys.

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EP89118810A 1988-10-12 1989-10-10 Verfahren zur Herstellung eines nichtkristallisierten, flachgewalzten, dünnen, wärmebehandelten Produktes auf Aluminiumbasis Revoked EP0368005B1 (de)

Applications Claiming Priority (6)

Application Number Priority Date Filing Date Title
US07/256,521 US4988394A (en) 1988-10-12 1988-10-12 Method of producing unrecrystallized thin gauge aluminum products by heat treating and further working
US07/256,520 US4946517A (en) 1988-10-12 1988-10-12 Unrecrystallized aluminum plate product by ramp annealing
US07/256,840 US4927470A (en) 1988-10-12 1988-10-12 Thin gauge aluminum plate product by isothermal treatment and ramp anneal
US256840 1988-10-12
US256520 1988-10-12
US256521 1988-10-12

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Publication Number Publication Date
EP0368005A1 true EP0368005A1 (de) 1990-05-16
EP0368005B1 EP0368005B1 (de) 1996-09-11

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EP89118810A Revoked EP0368005B1 (de) 1988-10-12 1989-10-10 Verfahren zur Herstellung eines nichtkristallisierten, flachgewalzten, dünnen, wärmebehandelten Produktes auf Aluminiumbasis

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EP (1) EP0368005B1 (de)
JP (1) JPH02194153A (de)
DE (1) DE68927149T2 (de)

Cited By (17)

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EP0460809A1 (de) * 1990-06-08 1991-12-11 The Secretary Of State For Defence In Her Britannic Majesty's Government Of The United Kingdom Of Great Britain And Verfahren zur Behandlung von Metallmatrixverbundwerkstoffen
EP0462055A1 (de) * 1990-06-11 1991-12-18 Alusuisse-Lonza Services Ag Vormaterial aus einer superplastischen AlZnMg-Legierung
EP0760727A1 (de) * 1994-05-25 1997-03-12 Ashurst Coporation Aluminium-scandium legierungen und verwendungen
EP0829552A1 (de) * 1996-09-11 1998-03-18 Aluminum Company Of America Aluminiumlegierung für Verkehrsflugzeugflügel
EP0377779B1 (de) * 1989-01-13 1998-05-20 Aluminum Company Of America Erzeugnis aus einer Aluminium-Legierung mit verbesserten Kombinationen der Festigkeit, der Zähigkeit und der Korrosionsbeständigkeit
US5932037A (en) * 1993-04-15 1999-08-03 Luxfer Group Limited Method of making hollow bodies
WO2005090628A1 (de) * 2004-03-20 2005-09-29 Hydro Aluminium Deutschland Gmbh Al/si-gusslegierung mit zn sowie mg und verfahren zur herstellung eines gussteils aus einer solchen legierung
AT413035B (de) * 2003-11-10 2005-10-15 Arc Leichtmetallkompetenzzentrum Ranshofen Gmbh Aluminiumlegierung
WO2006037648A1 (en) * 2004-10-05 2006-04-13 Aleris Aluminum Koblenz Gmbh HIGH STRENGTH, HIGH TOUGHNESS Al-Zn ALLOY PRODUCT AND METHOD FOR PRODUCING SUCH PRODUCT
DE10328614B4 (de) * 2002-06-26 2008-07-31 Kabushiki Kaisha Kobe Seiko Sho (Kobe Steel, Ltd.), Kobe Hochduktiles Aluminiumlegierungsblech
WO2008120237A1 (en) * 2007-03-30 2008-10-09 Director General, Defence Research & Development Organisation Alloy composition and preparation thereof
US7666267B2 (en) 2003-04-10 2010-02-23 Aleris Aluminum Koblenz Gmbh Al-Zn-Mg-Cu alloy with improved damage tolerance-strength combination properties
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
US8133331B2 (en) 2005-02-01 2012-03-13 Surface Treatment Technologies, Inc. Aluminum-zinc-magnesium-scandium alloys and methods of fabricating same
CN110218921A (zh) * 2019-06-21 2019-09-10 天津忠旺铝业有限公司 一种t4态2024铝合金薄板的加工方法
US10472707B2 (en) 2003-04-10 2019-11-12 Aleris Rolled Products Germany Gmbh Al—Zn—Mg—Cu alloy with improved damage tolerance-strength combination properties
CN114182183A (zh) * 2021-12-09 2022-03-15 苏州创泰合金材料有限公司 一种铝合金热处理工艺

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DE502005001724D1 (de) 2005-01-19 2007-11-29 Fuchs Kg Otto Abschreckunempfindliche Aluminiumlegierung sowie Verfahren zum Herstellen eines Halbzeuges aus dieser Legierung
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
RU2443797C2 (ru) 2006-07-07 2012-02-27 Алерис Алюминум Кобленц Гмбх Продукты из алюминиевого сплава серии аа7000 и способ их изготовления
DE102008056511B4 (de) * 2008-11-08 2011-01-20 Audi Ag Verfahren zur Herstellung dünnwandiger Metallbauteile aus einer AI-SiMg-Legierung, insbesondere von Bauteilen eines Kraftfahrzeugs
JP2017052989A (ja) * 2015-09-08 2017-03-16 株式会社Uacj 構造用アルミニウム合金板及びその製造方法

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EP0377779B1 (de) * 1989-01-13 1998-05-20 Aluminum Company Of America Erzeugnis aus einer Aluminium-Legierung mit verbesserten Kombinationen der Festigkeit, der Zähigkeit und der Korrosionsbeständigkeit
EP0460809A1 (de) * 1990-06-08 1991-12-11 The Secretary Of State For Defence In Her Britannic Majesty's Government Of The United Kingdom Of Great Britain And Verfahren zur Behandlung von Metallmatrixverbundwerkstoffen
EP0462055A1 (de) * 1990-06-11 1991-12-18 Alusuisse-Lonza Services Ag Vormaterial aus einer superplastischen AlZnMg-Legierung
US5932037A (en) * 1993-04-15 1999-08-03 Luxfer Group Limited Method of making hollow bodies
EP0760727A1 (de) * 1994-05-25 1997-03-12 Ashurst Coporation Aluminium-scandium legierungen und verwendungen
EP0829552A1 (de) * 1996-09-11 1998-03-18 Aluminum Company Of America Aluminiumlegierung für Verkehrsflugzeugflügel
DE10328614B4 (de) * 2002-06-26 2008-07-31 Kabushiki Kaisha Kobe Seiko Sho (Kobe Steel, Ltd.), Kobe Hochduktiles Aluminiumlegierungsblech
US7666267B2 (en) 2003-04-10 2010-02-23 Aleris Aluminum Koblenz Gmbh Al-Zn-Mg-Cu alloy with improved damage tolerance-strength combination properties
US10472707B2 (en) 2003-04-10 2019-11-12 Aleris Rolled Products Germany Gmbh Al—Zn—Mg—Cu alloy with improved damage tolerance-strength combination properties
AT413035B (de) * 2003-11-10 2005-10-15 Arc Leichtmetallkompetenzzentrum Ranshofen Gmbh Aluminiumlegierung
WO2005090628A1 (de) * 2004-03-20 2005-09-29 Hydro Aluminium Deutschland Gmbh Al/si-gusslegierung mit zn sowie mg und verfahren zur herstellung eines gussteils aus einer solchen legierung
DE102004013777B4 (de) * 2004-03-20 2005-12-29 Hydro Aluminium Deutschland Gmbh Verfahren zur Herstellung eines Gussteils aus einer AL/Si-Gusslegierung
DE102004013777A1 (de) * 2004-03-20 2005-10-06 Hydro Aluminium Deutschland Gmbh Al/Si-Gusslegierung und Verfahren zur Herstellung eines Gussteils aus einer solchen Legierung
WO2006037648A1 (en) * 2004-10-05 2006-04-13 Aleris Aluminum Koblenz Gmbh HIGH STRENGTH, HIGH TOUGHNESS Al-Zn ALLOY PRODUCT AND METHOD FOR PRODUCING SUCH 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
CN101068943B (zh) * 2004-10-05 2011-11-23 阿勒里斯铝业科布伦茨有限公司 高强度、高韧性Al-Zn合金产品和生产该产品的方法
US8133331B2 (en) 2005-02-01 2012-03-13 Surface Treatment Technologies, Inc. Aluminum-zinc-magnesium-scandium alloys and methods of fabricating same
CN101835915B (zh) * 2007-03-30 2012-05-23 总理事，国防研发机构 合金组合物及其制备
WO2008120237A1 (en) * 2007-03-30 2008-10-09 Director General, Defence Research & Development Organisation Alloy composition and preparation thereof
CN110218921A (zh) * 2019-06-21 2019-09-10 天津忠旺铝业有限公司 一种t4态2024铝合金薄板的加工方法
CN114182183A (zh) * 2021-12-09 2022-03-15 苏州创泰合金材料有限公司 一种铝合金热处理工艺

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JPH02194153A (ja) 1990-07-31

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