EP1838891B1 - Grobblech aus al-zn-cu-mg legierung mit niedrigen internen drücken - Google Patents

Grobblech aus al-zn-cu-mg legierung mit niedrigen internen drücken Download PDF

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EP1838891B1
EP1838891B1 EP05825980.5A EP05825980A EP1838891B1 EP 1838891 B1 EP1838891 B1 EP 1838891B1 EP 05825980 A EP05825980 A EP 05825980A EP 1838891 B1 EP1838891 B1 EP 1838891B1
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thickness
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plates
alloy
elastic energy
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EP1838891A1 (de
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Sjoerd Van Der Veen
Fabrice Heymes
Julien Boselli
Philippe Lequeu
Philippe Lassince
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Constellium Issoire 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

Definitions

  • This invention relates to a method for reducing the level of residual stresses throughout the thickness of 7xxx series aluminum alloy plates which are subjected to traction with permanent elongation.
  • Alloy plates of the 7xxx series (Al-Zn-Mg type alloys with or without copper) must be quenched quickly after being put in solution in order to be able to present, after income, high mechanical characteristics throughout their thickness.
  • the presence at the time of quenching of strong thermal gradients near the surface of the strong plate leads to inhomogeneous plastic deformation. Therefore, when the sheet is completely cooled, it contains residual stresses (internal stresses). Specifically, there are compressive stresses near the surface, and tensile stresses in the center.
  • the strength of these constraints depends on the alloy and the structure of the material, as well as the solution and quenching process; the order of magnitude is 200 MPa.
  • Licences US 6,159,315 and US 6,406,567 discloses a method for relaxing the residual stresses of the hot plates after solution and quenching, which comprises a first step of L-shaped cold drawing, followed by a cold compression step in the TC direction.
  • Plastic deformation typically reduces the residual stresses by a factor of about 10. This is illustrated in FIG. figure 2 .
  • the residual stresses in thick semi-products considered to be identical can vary greatly. This may be related to the variation of their chemical composition, but also and especially to the variation of the parameters of the manufacturing processes, such as casting, rolling, quenching, traction and income; the influence of these process parameters on the level of residual stresses in the finished product is not always well understood.
  • Some process modifications actually lead to a reduction in the level of residual stresses (such as the choice of a slower quenching or a higher tempering temperature), but they also modify the tradeoff between certain properties which are important for structural applications, such as, typically, mechanical strength, damage tolerance and corrosion resistance.
  • Licences EP 0 731 185 and US 6,077,363 describe a method to reduce residual stresses in 2024 alloy plate.
  • Such a sheet shows a better homogeneity of the mechanical characteristics as a function of the thickness, as well as a reduced level of residual stresses after traction.
  • the sheets were pre-expanded to change from a plate width of 1100 mm to 2500 mm to a hot rolling up to 38 mm with an outlet temperature of 378 ° C solution at 475 ° C, a quenched with cold water, and a controlled pull at 2.8% permanent elongation after a delay of 1 h after quenching.
  • Residual stresses in thick plates can be determined by the method of successive machining described in the publication of Heymes, Commet et al., Referenced above. A method based on this publication is described in detail below.
  • the aim of the present invention is to present a method for obtaining thick aluminum alloy plates of the 7xxx series which, in the tractionned state, in the matured state or in any state of artificial aging, exhibits a lower residual stress level, without degrading mechanical strength and damage tolerance. More particularly, it is desired to have plates that do not deform during machining, which is observed when the total elastic energy stored in the sheet, W, is less than 2 kJ / m 3 and preferably less than 1 kJ / m 3 .
  • the subject of the invention is a method for manufacturing thick plates made of Al-Zn-Cu-Mg type alloy comprising between 4 and 12% of zinc, less than 4% of magnesium and less than 4% of copper, minor elements ⁇ 0.5% each, the rest aluminum, said process comprising hot rolling, dissolution, quenching, traction controlled with a permanent elongation greater than 0.5%, as well as aging, characterized in that delay D between the end of quenching and the beginning of the controlled pull is less than 2 hours, and preferably less than 1 hour.
  • Yet another subject of the invention is a control batch or a heat treatment batch of Al-Zn-Cu-Mg alloy thick plates comprising between 4 and 12% of zinc, less than 4% of magnesium and less of 4% copper, minor elements ⁇ 0.5% each, the rest aluminum, in the dissolved state, quenched, triturated and aged, characterized in that the total elastic energy W (expressed in kJ / m 3 ) plate shows a standard deviation less than or equal to 0 , 20 + 0 , 0030 ⁇ P p ⁇ 0 , 2 The MPa - 400 around an average value .
  • Al-Zn-Cu-Mg alloy refers to an aluminum-based alloy that contains the elements of zinc, copper and magnesium alloy; such an alloy may contain in addition to other alloying elements as well as other elements, the presence of which may be intentional or not, for example impurities.
  • the metallurgical states are defined in the European standard EN 515.
  • the chemical composition of standardized aluminum alloys is defined for example in the standard EN 573-3.
  • the static mechanical characteristics ie the breaking strength R m , the yield stress R p0,2 , and the elongation at break A, are determined by a tensile test according to EN 10002-1 standard, the location and direction of specimen collection being defined in EN 485-1.
  • K IC toughness was measured according to ASTM E 399.
  • a "thick sheet” designates a sheet whose thickness is greater than 6 mm.
  • the term "inspection lot” is defined in EN 12258-1; it means an expedition or part of an expedition, subject to control, and which includes products of the same quality or alloy, of the same shape, metallurgical condition, size, geometry, thickness or cross-section, and which have been produced by the same processes.
  • heat treatment batch means a quantity of products of the same quality or alloy, of the same shape, thickness or cross-section, and which have been produced in the same way, including the heat treatment or solution solution followed quenching was carried out in a single charge; several batches can be dissolved in the same heat treatment batch.
  • aging includes natural aging at room temperature (also called “ripening”), as well as any artificial aging (also known as “income”).
  • machining includes any material removal process such as turning, machining, milling, drilling, reaming, tapping, EDM, grinding, polishing, chemical machining.
  • structural element refers to an element used in mechanical engineering for which the static and / or dynamic mechanical characteristics are of particular importance for the performance and integrity of the structure, and for which a calculation of the structure is usually prescribed or performed. It is typically 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 composed in particular of stabilizers Horizontal and vertical (horizontal or vertical stabilizers), as well as floor beams, seat rails and doors.
  • fuselage such as fuselage skin (fuselage skin in English
  • stiffeners or stringers such as the wing skin
  • the stiffeners stringers or stiffeners
  • ribs ribs
  • spars spars
  • empennage composed in particular of stabilizers Horizontal and vertical (horizontal or vertical stabilizers), as well as floor beams, seat rails and doors.
  • monolithic structure element refers to a structural element that has been obtained, most often by machining, from a single piece of laminated, extruded, forged or molded semi-finished product, such as riveting, welding, gluing, with another piece.
  • the directions L (Long direction), TL (cross-long direction) and TC (short-path direction) in a rolled product refer to the rolling direction corresponding to the direction L. These three directions are defined on the figure 1 .
  • the residual stresses were determined using the method based on the successive removal of layers described in the publication " Development of New Alloy for Distortion Free Machined Aluminum Aircraft Components ", F. Heymes, B.Commet, B.Dubost, P.Lassince, P.Lequeu, GM.Raynaud, in 1st International Non-Ferrous Processing & Technology Conference, 10- March 12, 1997 - Adams's Mark Hotel, St. Louis, Missouri .
  • This method is especially applicable to tractionned heavy plates, in which the state of stress can be considered as biaxial; the two main components being located in the directions L and TL, and there is therefore no component in the direction TC.
  • This method is based on the determination of the residual stresses in the directions L and TL on rectangular bars, cut in full thickness of the sheet in the direction parallel to the indicated directions. These bars are machined in the TC step by step direction. After each step, the stress and / or deflection are measured and the thickness of the bar is measured.
  • a particularly preferred method is to set a strain gauge at mid-length of the bar, on the surface opposite to that which is machined. This makes it possible to calculate the residual stress profiles in the L and TL directions. The bar should be long enough to avoid edge effects.
  • Table 1 Dimensions [mm] used for the method of successive layer removal Thickness of the sheet (h) Width (w) Length (1) 20 ⁇ h ⁇ 100 24 ⁇ 1 5h ⁇ 1 h> 100 30 ⁇ 1 5h ⁇ 1
  • Unidirectional strain gauges with compensation for thermal expansion are glued to the lower surface of the bar (see figure 3 ), following the manufacturer's instructions. Then they are covered with an insulating lacquer. The value read on each of these gauges is taken as zero.
  • the machining depth must not be less than 1 mm, in order to obtain a good quality of cut; for very thick sheets, it can reach 10 mm.
  • Chemical machining can also be used to remove a very small thickness of metal.
  • the machining pitch should be the same for both samples (i.e. in the L direction and in the TL direction).
  • the bar is detached from the vice, and the temperature is allowed to stabilize before measuring the deformation.
  • the thickness h (i) and the strain ⁇ (i) are noted .
  • the scheme of the figure 4 shows how we collect this data.
  • the problem is solved by a modification of the manufacturing process so that the ripening (natural aging) between the end of the quenching and the beginning of the controlled pull is minimized so that the energy total elasticity (W) in the return state remains below a certain limit value.
  • This limit value represents a maximum value to keep the machining deformity at a level that is still acceptable; for most applications, this limit value is 2 kJ / m 3 for a sheet having a thickness of between 60 mm and 100 mm, and preferably of 1.5 kJ / m 3 . For particularly complex parts, it must be 1 kJ / m 3 .
  • the figure 5 shows the diagram of the heat treatment process that a sheet undergoes after rolling.
  • the dissolution can be carried out in a single stage, in several stages, or in ramp with or without definite stage. The same is true of income.
  • the critical phase in the context of the present invention is the delay D between the end of the quenching and the beginning of the controlled pull.
  • the inventors have found that a long delay D leads to a greater heterogeneity of the mechanical characteristics between areas near the surface and areas near the mid-thickness of the material. This heterogeneity can be mainly attributed to differences in cooling rate in the thickness of the sheet.
  • the figure 6 shows the evolution of the yield strength L, determined close to the surface and at mid-thickness, as a function of the curing time for very high alloy plates AA7010 and AA7050 and for different nominal quenching rates. These quenching speeds were obtained on tensile test pieces but they are representative of the differences in quenching velocity observed between the surface and the core of a thick sheet. It can be seen that the difference between the levels of mechanical strength increases over time.
  • the inventors have found that the variation of the residual stresses across the thickness of the alloy sheets 7xxx depends on (i) the variation of the cooling rates and the plastic deformation during quenching, (ii) the heterogeneities of the microstructure granular structure and texture that are generated during rolling, and (iii) local variations in chemical composition that result from the casting process (including solidification and homogenization). Between the end of the quenching and the beginning of the traction, a maturation is observed throughout the thickness of the sheet, but the speed of this maturation depends on the thickness: the limit of elasticity increases faster close to a surface only half thickness.
  • the inventors have found by a calculation based on a finite element model that an increase in the heterogeneity of the mechanical characteristics (i.e. the elastic limit or the coefficients of work hardening) leads to an increase in the residual stresses after pulling.
  • the figure 7 shows the effect of increasing the variation of elastic limit values on the residual stress profiles after quenching.
  • the method according to the invention does not give an improved result in the case of other alloys with structural hardening, such as the 2xxx and 6xxx series alloys.
  • the stored energy is very high, and the improvement obtained with the process according to the invention. invention does not appear to be significant.
  • These alloys also have difficulty responding to solution treatment.
  • R p0,2 (L) denotes the yield strength of the finished sheet measured according to EN 10002-1 and EN 485-1.
  • the influence of the thickness on the level of residual stresses and the total elastic energy is here expressed in terms of the limited elasticity, measured as recommended by the EN 485-1 standard.
  • the method according to the invention can advantageously be applied to the manufacture of a plurality of sheets whose thickness is between about 10 mm and about 250 mm, and even more advantageously to sheets whose thickness is greater than 25 mm. , but these values are not limiting.
  • the method according to the invention also makes it possible to reduce the dispersion between the values of W for a plurality of sheets belonging to the same control lot or batch of heat treatment, so that all the plates have a standard deviation of the total elastic energy W of the various sheets around a mean value less than or equal to 0 , 20 + 0 , 0086 ⁇ P p ⁇ 0 , 2
  • the MPa - 400 and preferably less than or equal to 0 , 20 + 0 , 0030 ⁇ P p ⁇ 0 , 2
  • the MPa - 400 denotes the average of the measurements of R p0,2 (L) carried out according to the standard for each of the finished sheets of the batch, according to the standards EN10002-1 and EN485-1.
  • the standard deviation between the measurements of the total elastic energy W of the different sheets of a batch can depend on the number of sheets contained in the batch. In particular, a standard deviation obtained on two measurements is weakly significant and can randomly be very high or very low. From 3 sheets, the standard deviation of the measurements can be considered but, in a preferred manner, the control or heat treatment batches used in the context of the present invention contain at least 5 sheets.
  • the use of the method according to the invention enables the manufacturer to guarantee that such a control batch or such a batch of heat treatment comprises sheets whose average total elastic energy is less than 3 kJ / m 3 .
  • this average value is less than 2 kJ / m 3 , and a value less than 1 kJ / m 3 is preferred, which requires excellent control of the critical processes and very rigorous management of the product streams at the stages of production. dissolution, quenching and traction.
  • the implementation of the method according to the invention may require an adaptation of the metal flows inside the plant, because if the producer wants to produce plates with a delay D less than a few hours, it is necessary to synchronize the tempering furnace with the traction bench.
  • the maturation is carried out at low temperature, that is to say at a temperature below 10 ° C. and preferably at a temperature below 5 ° C., which makes it possible to obtain similar results in terms of total elastic energy W for delays D between 2h and 3h.
  • the invention is particularly advantageous for thick plates of AA7010, 7050, 7056, 7449, 7075, 7475, 7150, 7175 alloys.
  • the advantage of the process according to the invention is the overall reduction of the stress level in the heavy plates. This generally reduces the deformation during machining.
  • Another advantage of the process according to the invention is that the control of the time which elapses between the end of the quenching and the beginning of the traction also makes it possible to reduce the dispersion of the stress level which is observed between different sheets nominally. identical, even within the same manufacturing batch or batch of heat treatment. This allows a better standardization of the machining processes for a given series of products, and reduces the number of incidents during the manufacture of machined parts in the machine shop.
  • Three AA7010 alloy rolling plates were cast by semi-continuous casting. After homogenization, they were hot-rolled to a thickness of 100 mm. At the outlet of the hot rolling mill, they were subjected to quenching followed by a controlled pull, and finally to a treatment of income.
  • the metallurgical state of the three products A1, A2 and A3 thus obtained was the T7651 state. For these three products, all manufacturing parameters were nominally identical and well controlled. The only difference was the waiting time D between the end of quenching and the beginning of tensile stress relief.
  • Table 2 shows the stored elastic energy of the various sheets obtained, determined in the final state. When reducing the waiting time D between the end of the quenching and the beginning of tensile stress relief, a reduction in the overall stress level as measured by W L , W LT and W is observed. Table 2 Stored elastic energy (in the final state) as a function of the ripening time for three alloy plates 7010 and 7050.
  • Table 3 Static mechanical characteristics (L direction) in the final state as a function of the maturation time D for alloy plates 7010 and 7050 sheet metal Alloy / state Maturation time D [h] Location R m (L) [MPa] R p0.2 (L) [MPa] A (L) [%] A1 7010 T7651 1.17 1 ⁇ 4 thickness 524 479 14.0 1 ⁇ 2 thickness 519 468 12.7 3 ⁇ 4 thickness 533 471 11.0 A2 7010 T7651 9 1 ⁇ 4 thickness 529 480 14.4 1 ⁇ 2 thickness 523 477 11.5 3 ⁇ 4 thickness 539 480 9.6 A3 7010 T7651 48.92 1 ⁇ 4 thickness 521 472 12.6 1 ⁇ 2 thickness 516 466 9.2 3 ⁇ 4 thickness 528 472 8.2 B1 7050 T7451 1.25 1 ⁇ 4 thickness 536 482 13.0 1 ⁇ 2 thickness 519 465 10.4 3 ⁇ 4 thickness 531 470 9.6 B2 7050 T7451 8.83 1 ⁇ 4 thickness 534 479 14.2 1 ⁇
  • K IC toughness was also measured in LT and TL directions at 1 ⁇ 4 thickness. The results, shown in Table 6, show that maturation has no significant influence on toughness.
  • Table 6 Tenacity (in the final state) in the final state as a function of the aging time D for heavy plates in alloys 7010 and 7050 sheet metal Alloy / state Maturation time D [h]
  • K IC (TL) MPa ⁇ m)
  • Table 7 shows the stored elastic energy of the various sheets obtained, determined in the final state (ie after controlled pulling).
  • a reduction in the overall stress level W L , W LT and W is observed.
  • Table 7 Elastic energy stored according to ripening time D for flat plate alloy 7475 W51 sheet metal Alloy / state Maturation time D [h] W [kJ / m 3 ] W L [kJ / m 3 ] W LT [kJ / m 3 ] C1 7475 W51 1.75 2.24 1.6 0.64 C2 7475 W51 22.5 4.51 3.61 0.9 C3 7475 W51 48 5.18 3.97 1.21
  • Two AA7449 alloy rolling plates were converted by homogenization, hot rolling to a thickness between 16.5 and 21.5 mm, quenching and controlled pulling, followed by tempering.
  • the metallurgical state of the two products D1 and D2 thus obtained was the T651 state.
  • all manufacturing parameters were nominally identical and well controlled, and the only difference was the waiting time D between the end of quenching and the beginning of tensile stress relief.
  • Table 8 shows the stored elastic energy of the various sheets obtained, determined in the final state (ie after controlled pulling).
  • Table 8 Stored elastic energy (in the final state) as a function of the aging time D for alloy plates 7449 T651 sheet metal Alloy / state Thickness [mm] Maturation time D [h] W [kJ / m 3 ] W L [kJ / m 3 ] W LT [kJ / m 3 ] D1 7449 T651 16.5 10.5 6.3 5.56 0.74 D2 7449 T651 21.5 3 4.17 3.66 0.51
  • the stored energy is maximum.
  • the method according to the invention leads, for a given thickness, firstly to a reduction in the overall level of residual stresses (that is to say of the stored energy W totat ) of approximately 50%, and of on the other hand, a significant reduction in the statistical dispersion of this value.
  • the effect of the invention on the overall level of residual stresses is particularly remarkable for thicknesses of between 40 and 150 mm and even more clearly for thicknesses of between 50 and 100 or even 80 mm.

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Claims (14)

  1. Verfahren zur Herstellung dicker Bleche mit einer Dicke größer als 40 mm aus einer Legierung vom Typ Al-Zn-Cu-Mg enthaltend 4 bis 12% Zink, weniger als 4% Magnesium und weniger als 4% Kupfer, Nebenelemente jeweils ≤ 0,5%, Rest Aluminium, wobei das Verfahren die Schritte Warmwalzen, Lösungsglühen, Abschrecken, kontrolliertes Ziehen mit einer bleibenden Dehnung von mehr als 0,5% sowie Auslagern umfasst,
    dadurch gekennzeichnet, dass die Zeitdauer D zwischen dem Ende des Abschreckens und dem Beginn des kontrollierten Ziehens kleiner als 1 Stunde ist.
  2. Verfahren nach Anspruch 1, bei dem die Zeitdauer D kleiner als 30 Minuten ist.
  3. Verfahren nach Anspruch 1 oder 2, bei dem die Legierung ausgewählt ist aus der Gruppe bestehend aus den Legierungen AA7010, 7050, 7056, 7449, 7075, 7475, 7150, 7175.
  4. Verfahren nach irgendeinem der Ansprüche 1 bis 3, bei dem das Blech eine Dicke im Bereich von 40 bis 80 mm hat.
  5. Verfahren nach irgendeinem der Ansprüche 1 bis 3, bei dem das Blech eine Dicke im Bereich von 40 bis 150 mm hat.
  6. Dickes Blech von mindestens 60 mm Dicke aus einer Legierung vom Typ Al-Zn-Cu-Mg enthaltend 4 bis 12% Zink, weniger als 4% Magnesium und weniger als 4% Kupfer, Nebenelemente jeweils ≤ 0,5%, Rest Aluminium, welches Blech warmgewalzt, lösungsgeglüht, abgeschreckt, mit einer bleibenden Dehnung von mehr als 0,5% gezogen und ausgelagert wurde, dadurch gekennzeichnet, dass seine elastische Gesamtenergie kleiner oder gleich W kJ / m 3 = 0 , 54 + 0 , 013 ⁢ R p ⁢ 0 , 2 L MPa - 400
    Figure imgb0014
     ist, und dass seine elastische Gesamtenergie kleiner als 1,5 kJ/m3 ist.
  7. Blech nach Anspruch 6, dadurch gekennzeichnet, dass seine Dicke größer als 100 mm und seine elastische Gesamtenergie kleiner als 1,0 kJ/m3 ist.
  8. Prüfungslos oder Wärmebehandlungslos von dicken Blechen mit einer Nenndicke von 40 bis 100 mm aus einer Legierung vom Typ Al-Zn-Cu-Mg enthaltend 4 bis 12% Zink, weniger als 4% Magnesium und weniger als 4% Kupfer, Nebenelemente jeweils ≤ 0,5%, Rest Aluminium, im lösungsgeglühten, abgeschreckten, gezogenen und ausgelagerten Zustand, dadurch gekennzeichnet, dass die elastische Gesamtenergie W der Bleche, ausgedrückt in kJ/m3, eine Standardabweichung kleiner oder gleich 0 , 20 + 0 , 0030 ⁢ P p ⁢ 0 , 2 L MPa - 400
    Figure imgb0015
     um einen Mittelwert aufweist.
  9. Prüfungslos oder Wärmebehandlungslos von dicken Blechen nach Anspruch 8, dadurch gekennzeichnet, dass der Mittelwert der elastischen Gesamtenergie kleiner als W [kJ/m3] = 0,54 + 0,013 (Rp0,2(L)[MPa] - 400) ist.
  10. Prüfungslos oder Wärmebehandlungslos von dicken Blechen nach Anspruch 9, dadurch gekennzeichnet, dass der Mittelwert der elastischen Gesamtenergie kleiner als 3 kJ/m3 ist.
  11. Prüfungslos oder Wärmebehandlungslos nach Anspruch 9, dadurch gekennzeichnet, dass der Mittelwert der elastischen Gesamtenergie kleiner als 2 kJ/m3 und vorzugsweise kleiner als 1 kJ/m3 ist.
  12. Prüfungslos oder Wärmebehandlungslos nach irgendeinem der Ansprüche 9 bis 11, dadurch gekennzeichnet, dass die Bleche aus einer Legierung gefertigt sind, die ausgewählt ist aus der Gruppe bestehend aus AA7010, 7050, 7056, 7449, 7075, 7475, 7150, 7175.
  13. Prüfungslos oder Wärmebehandlungslos nach irgendeinem der Ansprüche 9 bis 12, dadurch gekennzeichnet, dass es aus mindestens 3 Blechen und vorzugsweise mindestens 5 Blechen besteht.
  14. Verwendung von Blechen nach irgendeinem der Ansprüche 6 bis 7 oder eines Prüfungsloses oder Wärmebehandlungsloses von Blechen nach irgendeinem der Ansprüche 8 bis 14 für die Herstellung von Werkstücken.
EP05825980.5A 2004-12-13 2005-12-09 Grobblech aus al-zn-cu-mg legierung mit niedrigen internen drücken Revoked EP1838891B1 (de)

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FR0413204A FR2879217B1 (fr) 2004-12-13 2004-12-13 Toles fortes en alliage ai-zn-cu-mg a faibles contraintes internes
PCT/FR2005/003090 WO2006064113A1 (fr) 2004-12-13 2005-12-09 TOLES FORTES EN ALLIAGE Al-Zn-Cu-Mg A FAIBLES CONTRAINTES INTERNES

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EP1838891B1 true EP1838891B1 (de) 2015-12-09

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WO (1) WO2006064113A1 (de)

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US10835942B2 (en) 2016-08-26 2020-11-17 Shape Corp. Warm forming process and apparatus for transverse bending of an extruded aluminum beam to warm form a vehicle structural component
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

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2879217B1 (fr) 2004-12-13 2007-01-19 Pechiney Rhenalu Sa Toles fortes en alliage ai-zn-cu-mg a faibles contraintes internes
US8083871B2 (en) 2005-10-28 2011-12-27 Automotive Casting Technology, Inc. High crashworthiness Al-Si-Mg alloy and methods for producing automotive casting
US8673209B2 (en) * 2007-05-14 2014-03-18 Alcoa Inc. Aluminum alloy products having improved property combinations and method for artificially aging same
WO2010081889A1 (en) * 2009-01-16 2010-07-22 Aleris Aluminum Koblenz Gmbh Method for the manufacture of an aluminium alloy plate product having low levels of residual stress
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US10835942B2 (en) 2016-08-26 2020-11-17 Shape Corp. Warm forming process and apparatus for transverse bending of an extruded aluminum beam to warm form a vehicle structural component
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

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US20060151075A1 (en) 2006-07-13
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CN101076613A (zh) 2007-11-21
FR2879217B1 (fr) 2007-01-19

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