EP0368005B1 - 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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EP0368005B1
EP0368005B1 EP89118810A EP89118810A EP0368005B1 EP 0368005 B1 EP0368005 B1 EP 0368005B1 EP 89118810 A EP89118810 A EP 89118810A EP 89118810 A EP89118810 A EP 89118810A EP 0368005 B1 EP0368005 B1 EP 0368005B1
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Prior art keywords
product
temperature
wrought
anneal
unrecrystallized
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French (fr)
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EP0368005A1 (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 US07/256,840 external-priority patent/US4927470A/en
Priority claimed from US07/256,520 external-priority patent/US4946517A/en
Priority claimed from US07/256,521 external-priority patent/US4988394A/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 treating 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 desiqners 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.
  • Several sources indicate that plate having an unrecrystallized structure develops higher toughness than plate having a recrystallized structure.
  • 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.
  • EP-A 0 266 741 discloses a method of producing unrecrystallized wrought aluminum-lithium products having improved levels of strength and fracture toughness comprising the steps of providing a body of a lithium containing aluminum base alloy; heating and hot rolling the body to a wrought product.
  • the product is cold worked or cold rolled to a second wrought product and then reheated by a ramp anneal and hot rolled while avoiding substantial recrystallization thereof, solution heat treating, quenching and aging the product to provide a substantially unrecrystallized product.
  • WO-A- 80/0071 discloses unrecrystallized 7000 series aluminum alloys made by hot working a body of said alloy to provide a wrought product, with recrystallization being held to a minimum.
  • the wrought product is solution heat treated, quenched and aged at elevated temperature, there being no disclosure of a ramped anneal.
  • the present invention provides improved thermal or thermal mechanical processing techniques which permit the 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.
  • Fiqure 1 is a diagram of a ramp anneal in accordance with the invention.
  • Figure 2 is a diagram of a ramp anneal in accordance with the invention.
  • Figure 3 is a schematic representing steps in the process for producing thin gauge unrecrystallized plate in accordance with the invention.
  • Figure 4 is a schematic representing steps in the process for producing thin gauge unrecrystallized plate in accordance with the invention.
  • 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 which do not comprise intentionally added lithium such as the AA2000 and 6000 series aluminum alloys.
  • typical AA2000 series alloys which may be included are AA2024, 2124, 2324, 2219, 2519, 2014, 2618, 2034, and typical of AA6000 series alloys are 6061 and 6013.
  • Products formed from these alloys have oxygen content of less than 0.1 wt.%. Further, 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 454 to 566°C (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.
  • the starting temperature can be as high as 399°C (750°F) and then increased with anneal time to temperatures higher than 399°C (750° F), e.g. 454° C (850°F). With respect to higher starting temperatures, a typical starting temperature is 388°C (730°F) and the temperature can then be increased with time to about 427°C (800°F).
  • starting temperatures do not usually exceed 288°C (550°F), normally 204°C (400°F), with a typical starting temperature being in the range of 177 to 232°C (350 to 450°F) and an ending temperature being in the range of 343 to 454°C (650 to 850°F).
  • Typical ending temperatures are in the range of 399 to 454°C (750 to 850°F), depending on the alloy composition.
  • the temperature can be increased at a rate of 1.1° C to 55.6° C/hr (2 to 100° F/hr), and preferably at a rate of 2.8 to 44.4°C/hr (5 to 80°F/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. 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 Figures 1 and 2, or the product may be cooled and a separate solution heat treatment, quench and aging performed.
  • 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 121° C (250°F) but normally higher than 135°C (275°F) and typically in the range of 149 to 260°C (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. Typically, 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.
  • such ending temperatures are in the range of 343 or 371 to 482° C (650 or 700 to 900°F).
  • the starting temperature can be anywhere from about 38° C (100°F) or even ambient to 399°C (750°F) in some instances.
  • the starting temperature will be in the range of 121 to 388° C (250 to 730° F) with preferred starting temperatures being less than 149°C (300°F), but normally in the range of 149 to 260° C (300 to 500°F).
  • the temperature can be increased at a controlled rate, e.g., at a rate of 1.1 to 69.4° C/hr (2 to 125°F/hr) and preferably at a rate of 2.8 to 44.4 °C/hr (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.
  • the anneal temperature 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. 3, or 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 343 to 482° C (650 to 900°F) and preferably 343 or 371 to 427°C (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 ⁇ 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. Thereafter, 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 93 to 288° C of (200 to 550°F), preferably, 177 to 260° C (350 to 500°F), with typical temperatures being 204 to 260 °C (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.
  • the slab is worked or rolled to thin gauge plate or to sheet stock.
  • Thin gauge plate contemplates having a thickness of at least 0.318 cm (0.25 inch), typically 0,64 cm (0.25 inch) or more.
  • the thickness can extend to 1.3 cm (0.5 inch) or more, for example, 1.9 or 2.5 cm (0.75 or 1.0 inch) or even 3.18 cm (1.25 inch).
  • warm rolling is performed at a temperature of not greater than 288°C (550°F). Further, preferably, the temperature at which warm rolling begins is not less than 93°C (200°F). Typically, the warm rolling can begin at the precipitation heat treatment not temperature. Preferably, the warm rolling temperature should not exceed the precipitation heat treatment temperature. Such temperatures are in the range of about 177 to 260° C (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 399°C (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 the temperature in the range of 427° to 566° C (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 55.6° C (100°F) per second from solution temperature to a temperature of about 93°C (200°F) or lower.
  • a preferred quenching rate is at least 111.2° C (200°F) per second in the temperature range of 482°C (900°F) or more to 93° C (200° F) or less. After the metal has reached a temperature of about 93°C (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 690 MPa (100 ksi). However, the useful strengths are in the range of 483 to 621 MPa (70 to 90 ksi) and corresponding fracture toughnesses are in the range of 18 to 46 MPa m (20 to 50 ksi in ).
  • artificial aging is accomplished by subjecting the alloy product to a temperature in the range of 135 to 191°C (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 163°C (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 process can be applied to extrusions and forgings having alloy compositions referred to herein or responsive to these treatments.
  • the process In contrast to rolling, for extrusion purposes, it is not difficult to keep the ingot hot, but it is uneconomical to do so because of the slow extruding rates. Consequently, extrusions typically have a recrystallized structure.
  • the process would include two or more extruding 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. Because the steps to form forgings are often repeated, 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 427° C (800°F) to a 3.8 cm, (1.5 inch) thick slab.
  • the slab was cut into several pieces which were heated to temperatures of 399 to 471°C (750 to 880°F) and then hot rolled starting at about 399°C (750°F) to 0.76 cm (0.3 inch) thick plate.
  • Samples were given a ramp anneal starting at a temperature of 388°C (730°F) and ending at 427° C (800°F), with a heat-up rate of about 5.6°C/hr (10°F/hr). After annealing, these samples, along with unannealed samples, were heated to 471° C (880°F) and solution heat treated at this temperature for 1 hour and then cold water quenched, as shown in Figure 1. Examination of the microstructure revealed that the degree of recrystallization of the ramp annealed samples was significantly reduced compared to the microstructure of samples which were not annealed in this manner.
  • Samples of 0.76 cm (0.3 inch) plate having the composition and prepared as in Example 1 were subjected to a ramp anneal starting at a temperature of 204° C (400°F) and ending at a temperature of 427°C (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 0.76 cm (0.3 inch) plate, had the same composition and was treated as in Example 2 except that prior to hot rolling to 0.76 cm (0.3 inch) thick plate, the sample was reheated 399°C to (750°F) for about 0.5 hours, cold water quenched and then precipitation heat treated at 204°C at (400°F) for 12 hours and hot rolled to 0.76 cm (0.3 inch) thick plate starting at a temperature of 204°C (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 3.8 cm (1.5 inch) thick slab.
  • the slab was cut into several pieces which were subjected to anneals at temperatures of 399 to 471°C (750 to 880°F) and then hot rolled to 0.76 cm (0.3 inch) plate.
  • the 0.76 cm (0.3 inch) plate was isothermal soaked for 16 hours at 204°C (400°F) and then subjected to a ramp anneal starting 204°C at (400°F) and ending at 427°C (800°F), increase in temperature being made in 4 hours.
  • the 0.76 (0.3 inch) plate was then solution heat treated at 471° C (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 427°C (800°F) to a 3.8 cm a (1.5 inch) thick slab. Thereafter, the slab was annealed for 30 minutes at 399° C (750°F) and cold water quenched. The slab was then precipitation heat treated for 12 hours at 204° C (400°F). Thereafter, the slab was rolled at about 204°C (400°F) to 0.76 cm (0.3 inch) thick plate and then solution heat treated at 471° C (880°F) for 1 hour and cold water quenched.
  • 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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Claims (8)

  1. Verfahren zum Erzeugen eines nichtrekristallisierten, wärmebehandelten, dünnen, flachgewalzten Produktes auf Aluminiumbasis mit verbesserten Werten der Festigkeit und Bruchzähigkeit, welches Verfahren die Schritte umfaßt:
    (a) Bereitstellen eines Körpers einer wärmebehandlungsfähigen Legierung auf Aluminiumbasis vom Typ der Reihen 7.000, 6.000 oder 2.000, die kein zugesetztes Lithium enthält;
    (b) Bearbeiten des Körpers zu einem Knetprodukt;
    (c) das Produkt einer Rampenglühbehandlung unterziehen; und
    (d) Lösungsglühen, Abschrecken und Altern des auf Fertigdicke flachgewalzten Produktes, um ein weitgehend nichtrekristallisiertes Produkt mit verbesserten Werten der Festigkeit und Bruchzähigkeit zu schaffen.
  2. Verfahren nach Anspruch 1, bei welchem die Glühtemperatur ausgewählt wird wie folgt:
    (1) das Rampenerhitzen beim Glühen beginnt bei einer Temperatur von nicht mehr als 399 °C (750 °F);
    (2) das Rampenerhitzen beim Glühen beginnt bei einer Temperatur von nicht mehr als 204 °C (400 °F);
    (3) das Rampenerhitzen beim Glühen endet bei einer Temperatur im Bereich von 343 ° ... 454 °C (650 ° ... 850 °F); oder
    (4) das Rampenerhitzen beim Glühen beginnt bei einer Temperatur im Bereich von 177 ° ... 232 °C (350 ° ... 450 °F) und wird auf eine Temperatur im Bereich von 399 ° ... 450 °C (750 °F ... 850 °F) über eine Dauer von etwa 2 ... 8 Stunden erhöht, und/oder die Temperatur des Rampenerhitzens beim Glühen wird mit einer Geschwindigkeit von 1,1 °C/h ... 55,6 °C/h (2 °CF/h ... 100 °F/h) erhöht.
  3. Verfahren nach Anspruch 1, bei welchem das Produkt vor dem Rampenglühen einem isothermen Durchwärmen unterzogen wird.
  4. Verfahren nach Anspruch 1, bei welchem das Bearbeiten die folgenden Schritte umfaßt:
    (1) Warm(um)formen des Körpers zu einer ersten Knetlegierung;
    (2) Wiedererwärmen des ersten Knetproduktes;
    (3) Kühlen des ersten Knetproduktes;
    (4) Wärmebehandeln des ersten Knetproduktes;
    (5) weiteres Warmformen des ersten Knetproduktes, um ein zweites Knetprodukt zu erzeugen.
  5. Verfahren zum Erzeugen eines nichtrekristallisierten Knetlegierungproduktes auf Aluminiumbasis mit verbesserten Werten der Festigkeit und Bruchzähigkeit, welches Verfahren die Schritte umfaßt:
    (a) Bereitstellen eines Körpers einer wärmebehandlungsfähigen Legierung auf Aluminiumbasis vom Typ der Reihen 7.000, 6.000 oder 2.000, die kein zugesetztes Lithium enthält;
    (b) Bearbeiten des Körpers zu einem Knetprodukt;
    (c) das Produkt einem isothermen Durchwärmen unterziehen;
    (d) sodann das Produkt einer Rampenglühbehandlung unterziehen, bei der die Glühtemperatur während der Glühdauer erhöht wird; und
    (e) Lösungsglühen, Abschrecken und Altern des Produktes, um ein weitgehend nichtrekristallisiertes Knetprodukt mit verbesserten Werten der Festigkeit und Bruchzähigkeit zu schaffen.
  6. Verfahren nach Anspruch 5, bei welchem die Glühtemperatur ausgewählt wird wie folgt:
    (1) die Abschlußtemperatur beträgt 343 °C ... 482 °C (650 °F ... 900 °F) oder
    (2) die Ausgangstemperatur ist kleiner als 149 °C (300 °F) und die Abschlußtemperatur 371 °... 482 °C (700 ° ... 900 °F), und /oder die Temperatur wird bei 1,1 ... 69,4 °C pro Stunde (2 ° ... 125 °F pro Stunde) erhöht.
  7. Verfahren nach Anspruch 5, bei welchem das isotherme Durchwärmen bei einer Temperatur im Bereich von 149 ° ... 260 °C (300 ° ... 500 °F erfolgt und /oder die Dauer des Durchwärmens ausgewählt wird aus:
    (1) mindestens 3 Stunden;
    (2) mindestens 4 Stunden;
    (3) einer Dauer im Bereich von 4 ... 24 Stunden.
  8. Verfahren zum Erzeugen eines nichtrekristallisierten wärmebehandelten Knetproduktes auf Aluminiumbasis mit verbesserten Werten der Festigkeit und Bruchzähigkeit, welches Verfahren die Schritte umfaßt:
    (a) Bereitstellen eines Körpers einer wärmebehandlungsfähigen Legierung auf Aluminiumbasis vom Typ der Reihen 7.000, 6.000 oder 2.000, die kein zugesetztes Lithium enthält;
    (b) Warm(um)formen des Körpers zu einem ersten Knetprodukt;
    (c) Wiedererwärmen des ersten Knetproduktes;
    (d) Kühlen des ersten Knetproduktes;
    (e) Wärmebehandeln des ersten Knetproduktes;
    (f) weiteres Warmformen des ersten Knetproduktes, um ein zweites Knetprodukt zu erzeugen; und
    (g) Lösungsglühen, Abschrecken und Altern des zweiten Knetproduktes, um ein weitgehend nichtrekristallisiertes Produkt mit verbesserten Werten der Festigkeit und Bruchzähigkeit zu schaffen.
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
US256840 1988-10-12
US07/256,840 US4927470A (en) 1988-10-12 1988-10-12 Thin gauge aluminum plate product by isothermal treatment and ramp anneal
US07/256,520 US4946517A (en) 1988-10-12 1988-10-12 Unrecrystallized aluminum plate product by ramp annealing
US256521 1988-10-12
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
US256520 2002-09-27

Publications (2)

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

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

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DE102008056511A1 (de) * 2008-11-08 2010-05-20 Audi Ag Verfahren zur Herstellung dünnwandiger Metallbauteile aus einer AI-SiMg-Legierung, insbesondere von Bauteilen eines Kraftfahrzeugs
US8002913B2 (en) 2006-07-07 2011-08-23 Aleris Aluminum Koblenz Gmbh AA7000-series aluminum alloy products and a method of manufacturing thereof
US8608876B2 (en) 2006-07-07 2013-12-17 Aleris Aluminum Koblenz Gmbh AA7000-series aluminum alloy products and a method of manufacturing thereof
US10301710B2 (en) 2005-01-19 2019-05-28 Otto Fuchs Kg Aluminum alloy that is not sensitive to quenching, as well as method for the production of a semi-finished product

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EP0462055A1 (de) * 1990-06-11 1991-12-18 Alusuisse-Lonza Services Ag Vormaterial aus einer superplastischen AlZnMg-Legierung
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JP3869323B2 (ja) * 2002-06-26 2007-01-17 株式会社神戸製鋼所 延性に優れたＡｌ合金板
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BRPI0409267B1 (pt) 2003-04-10 2017-04-25 Corus Aluminium Walzprodukte Gmbh produto de liga de alumínio com alta resistência mecânica e tenacidade à fratura e uma boa resistência à corrosão, componente estrutural de liga de alumínio e chapa de molde
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US10301710B2 (en) 2005-01-19 2019-05-28 Otto Fuchs Kg Aluminum alloy that is not sensitive to quenching, as well as method for the production of a semi-finished product
US8002913B2 (en) 2006-07-07 2011-08-23 Aleris Aluminum Koblenz Gmbh AA7000-series aluminum alloy products and a method of manufacturing thereof
US8088234B2 (en) 2006-07-07 2012-01-03 Aleris Aluminum Koblenz Gmbh AA2000-series aluminum alloy products and a method of manufacturing thereof
US8608876B2 (en) 2006-07-07 2013-12-17 Aleris Aluminum Koblenz Gmbh AA7000-series aluminum alloy products and a method of manufacturing thereof
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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

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DE68927149T2 (de) 1997-04-03
EP0368005A1 (de) 1990-05-16
DE68927149D1 (de) 1996-10-17

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