EP3807434B1 - Procédé de fabrication d'un produit plat en alliage d'aluminium de série 7xxx présentant une meilleure résistance à la rupture par fatigue - Google Patents

Procédé de fabrication d'un produit plat en alliage d'aluminium de série 7xxx présentant une meilleure résistance à la rupture par fatigue Download PDF

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EP3807434B1
EP3807434B1 EP19729715.3A EP19729715A EP3807434B1 EP 3807434 B1 EP3807434 B1 EP 3807434B1 EP 19729715 A EP19729715 A EP 19729715A EP 3807434 B1 EP3807434 B1 EP 3807434B1
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Prior art keywords
plate product
hot rolling
aluminium alloy
thickness
plate
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German (de)
English (en)
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EP3807434A1 (fr
Inventor
Sabine Maria Spangel
Philippe Meyer
Achim BÜRGER
Matthias RÜBNER
Simon LACHNITT
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Novelis Koblenz GmbH
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Novelis Koblenz GmbH
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    • C—CHEMISTRY; METALLURGY
    • C21—METALLURGY OF IRON
    • C21D—MODIFYING THE PHYSICAL STRUCTURE OF FERROUS METALS; GENERAL DEVICES FOR HEAT TREATMENT OF FERROUS OR NON-FERROUS METALS OR ALLOYS; MAKING METAL MALLEABLE, e.g. BY DECARBURISATION OR TEMPERING
    • C21D8/00—Modifying the physical properties by deformation combined with, or followed by, heat treatment
    • C21D8/02—Modifying the physical properties by deformation combined with, or followed by, heat treatment during manufacturing of plates or strips
    • C21D8/0221—Modifying the physical properties by deformation combined with, or followed by, heat treatment during manufacturing of plates or strips characterised by the working steps
    • C21D8/0226—Hot rolling
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22D—CASTING OF METALS; CASTING OF OTHER SUBSTANCES BY THE SAME PROCESSES OR DEVICES
    • B22D7/00—Casting ingots, e.g. from ferrous metals
    • B22D7/005—Casting ingots, e.g. from ferrous metals from non-ferrous metals
    • C—CHEMISTRY; METALLURGY
    • C21—METALLURGY OF IRON
    • C21D—MODIFYING THE PHYSICAL STRUCTURE OF FERROUS METALS; GENERAL DEVICES FOR HEAT TREATMENT OF FERROUS OR NON-FERROUS METALS OR ALLOYS; MAKING METAL MALLEABLE, e.g. BY DECARBURISATION OR TEMPERING
    • C21D9/00—Heat treatment, e.g. annealing, hardening, quenching or tempering, adapted for particular articles; Furnaces therefor
    • C21D9/46—Heat treatment, e.g. annealing, hardening, quenching or tempering, adapted for particular articles; Furnaces therefor for sheet metals
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C21/00—Alloys based on aluminium
    • C22C21/10—Alloys based on aluminium with zinc as the next major constituent
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22F—CHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS AND NON-FERROUS ALLOYS
    • C22F1/00—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
    • C22F1/04—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon
    • C22F1/053—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon of alloys with zinc as the next major constituent

Definitions

  • the invention relates to a method of manufacturing a 7xxx-series aluminium alloy plate product having improved fatigue failure resistance.
  • the plate product can be ideally applied in aerospace structural applications, such as wing skin panels and members, and other high strength end users.
  • AI-Zn-Mg-(Cu) type alloys or AA7xxx-series alloys have been used for aircraft constructions for more than 50 years, and particularly for wing members, for example, inter alia, AA7055-series alloys have been used.
  • These aluminium alloys possess a required balance of strength, fracture toughness and corrosion resistance, and are especially well suited for structural aerospace applications such as wing upper skin panels. This is disclosed for example in US patent no. 5,221,377 .
  • This US patent discloses that in order to obtain these high mechanical characteristics, it is necessary to subject the alloys to a three-stage artificial ageing process. However, this US patent does not deal with the property of fatigue failure resistance of the AA7055 alloys.
  • US patent no. 7,097,719 discloses that the fatigue failure resistance of AA7055-series alloys can be improved by using an optimized alloy composition, later registered as the AA7255 alloy.
  • the AA7255 alloys have much more stringent upper-limits for the Si- and Fe-levels than the AA7055 alloy.
  • this US patent discloses that products made from the AA7255 alloy having lower Si and Fe levels than AA7055 (i.e. Si and Fe concentrations below 0.06 wt.%, preferably below 0.04 wt.%) exhibit better fatigue failure resistance.
  • the US patent discloses in the Examples that alloys having less than 0.029 wt.% Si and less than 0.039 wt.% Fe (while maintaining Cu, Mg, Zn and Zr within the ranges of standard AA7055) achieved improvements in fatigue life with respect to standard AA7055 products when having higher Si- and Fe-levels. Accordingly, the fatigue life of an AA7255 aluminium alloy product with respect to a standard AA7055 product can be improved. Such an improvement delays the inspection intervals in an aircraft structure. However, keeping the content of impurities Si and Fe at such a very low level increases the costs for the aluminium alloy produced, as materials with a very high purity grade are to be sourced.
  • fatigue performance in particular fatigue failure resistance
  • AA7xxx-series alloys including the AA7055-series alloys.
  • an aluminium alloy rolled plate product having a final thickness or final gauge of less than 75 mm, preferably less than 50 mm, ideally suitable for use as an aerospace plate product, with improved fatigue failure resistance
  • the method comprising the steps, in that order, of: (a) casting an ingot of an aluminium alloy of the 7xxx-series, the aluminium alloy comprising (in wt.%): Zn 5 to 9, Mg 1 to 3, Cu 0 to 3, Fe up to 0.20, Si up to 0.15, Zr up to 0.5, preferably 0.03 to 0.20, and optionally one or more elements selected from the group consisting of: Ti up to 0.3% Cr up to 0.4% Sc up to 0.5% Hf up to 0.3% Mn up to 0.4% V up to 0.4% Ag up to 0.5%, balance aluminium and impurities; (b) homogenizing and/or preheating the cast ingot; (c) hot rolling the ingot into a plate product by rolling the ingot
  • the method according to this invention can be applied to a wide range of 7xxx-series aluminium alloys consisting of the following composition, in wt.%, Zn 5% to 9%, preferably 5.5% to 8.5%, more preferably 7% to 8.5%, Mg 1% to 3%, Cu 0% to 3%, preferably 0.3% to 3%, Si up to 0.15%, preferably up to 0.10%, Fe up to 0.20%, preferably up to 0.15%, Zr up to 0.5%, preferably 0.03% to 0.20%, and optionally one or more elements selected from the group consisting of: Ti up to 0.3% Cr up to 0.4% Sc up to 0.5% Hf up to 0.3% Mn up to 0.4% V up to 0.4% Ag up to 0.5%, and balance being aluminium and impurities. Typically, such impurities are present each ⁇ 0.05%, total ⁇ 0.15%.
  • the aluminium alloy has a chemical composition within the ranges of AA7010, AA7040, AA7140, AA7449, AA7050, AA7150, AA7055, AA7255, AA7081, AA7181, AA7085, AA7185, AA7090, AA7099, AA7199, and modifications thereof.
  • the aluminium alloy has a chemical composition within the ranges of AA7055.
  • aluminium alloy designations and temper designations refer to the Aluminium Association designations in Aluminium Standards and Data and the Registration Records, as published by the Aluminium Association in 2016, and are well known to the person skilled in the art.
  • ⁇ and "up to” and “up to about”, as employed herein, explicitly include, but are not limited to, the possibility of zero weight-percent of the particular alloying component to which it refers.
  • up to 0.4% Cr may include an alloy having no Cr.
  • no cold rolling step is carried out when rolling the plate product to final gauge (thickness) to avoid at least partial recrystallization during a subsequent solution heat treatment step resulting in adversely affecting the balance of engineering properties in the final plate product.
  • the final thickness of the rolled plate product is less than 75 mm, preferably 50 mm, preferably less than 45 mm, more preferably less than 40 mm, and most preferably less than 35 mm. In useful embodiments, the final thickness of the plate product is more than 10 mm, preferably more than 12.5 mm, more preferably more than 15 mm and most preferably more than 19 mm.
  • the aluminium alloy can be provided as a rolling ingot or slab by casting techniques regular in the art for casting products, e.g. DC-casting, EMC-casting, EMS-casting, and preferably having a thickness in a range of 300 mm or more, for example 400 mm, 500 mm or 600 mm.
  • slabs resulting from continuous casting e.g. belt casters or roll casters, also may be used, which in particular may be advantageous when producing thinner gauge end products.
  • Grain refiners such as those containing titanium and boron, or titanium and carbon, may also be used as is well-known in the art.
  • the ingot is commonly scalped to remove segregation zones near the cast surface of the ingot.
  • the rolling ingot is homogenized and/or preheated.
  • a homogenisation heat treatment has the following objectives: (i) to dissolve as much as possible coarse soluble phases formed during solidification, and (ii) to reduce concentration gradients to facilitate the dissolution step.
  • a preheat treatment achieves also some of these objectives.
  • a pre-heat refers to the heating of an ingot to a set temperature and soaking at this temperature for a set time followed by the start of the hot rolling at about that temperature.
  • Homogenisation refers to a heating and cooling cycle applied to a rolling ingot in which the final temperature after homogenisation is ambient temperature.
  • a typical preheat treatment for AA7xxx-series alloys used in the method according to this invention would be a temperature of 400°C to 460°C with a soaking time in the range of 2 to 50 hours, more typically for 2 to 20 hours.
  • the soluble eutectic phases such as the S-phase, T-phase, and M-phase in the alloy stock are dissolved using regular industry practice. This is typically carried out by heating the stock to a temperature of less than 500°C, typically in a range of 450°C to 490°C, as S-phase eutectic phase (Al 2 MgCu-phase) have a melting temperature of about 489°C in AA7xxx-series alloys and the M-phase (MgZn 2 -phase) has a melting point of about 478°C.
  • S-phase eutectic phase Al 2 MgCu-phase
  • M-phase MgZn 2 -phase
  • this can be achieved by a homogenisation treatment in said temperature range and allowed to cool to the hot rolling temperature, or after homogenisation the stock is subsequently cooled and reheated before hot rolling.
  • the regular homogenisation process can also be done in a two or more steps if desired, and which are typically carried out in a temperature range of 430°C to 490°C for AA7xxx-series alloys. For example in a two-step process, there is a first step between 455°C and 465°C, and a second step between 470°C and 485°C, to optimise the dissolving process of the various phases depending on the exact alloy composition.
  • the soaking time at the homogenisation temperature is alloy dependent as is well known to the skilled person, and is commonly in the range of 1 to 50 hours.
  • the heat-up rates that can be applied are those which are regular in the art.
  • Hot rolling of the ingot is carried out with multiple hot rolling passes, usually in a hot rolling mill.
  • the number of hot rolling passes is typically between 15 and 35, preferably between 20 and 29.
  • the method applies at least one high reduction hot rolling pass with a thickness reduction of at least 25%, preferably of at least 30% and most preferred of at least 35%.
  • the thickness reduction in this high reduction pass is less than 70%, preferably less than 60%, more preferred less than 50%.
  • the "thickness reduction" of a rolling pass also referred to as reduction ratio, is preferably the percentage by which the thickness of the plate is reduced in the individual rolling pass.
  • Such an at least one high reduction hot rolling pass is not carried out in conventional industrial hot rolling practices when producing 7xxx-series plate products. Therefore, the hot rolling passes between 80 mm and 220 mm according to a non-limitative example of the invention could be described as follows (looking at the plate intermediate thickness): 203 mm - 190 mm - 177 mm - 167 mm - 117 mm - 102 mm - 92 mm.
  • the high reduction hot rolling pass from 167 mm to 117 mm corresponds to a thickness reduction of 30%.
  • the thickness reduction of each hot rolling pass is typically between 9% and 18% when at the intermediate thickness between 80 mm and 220 mm.
  • the hot rolling passes between 80 mm and 220 mm could be described as follows (looking at the plate intermediate thickness): 203 mm - 188 mm - 166 mm - 144 mm - 124 mm - 104 mm - 92 mm.
  • the method according to the invention defines a hot rolling step wherein at least one high reduction hot rolling pass is carried out.
  • This high reduction pass is defined by a thickness reduction of at least 25%, preferably of at least 30% and more preferred of at least 35%.
  • each hot rolling pass before and after the high reduction hot rolling pass could have a thickness reduction between 8% and 18%. Since the thickness reduction varies depending on the thickness of the plate, e.g. thick plates having more than 300 mm or thin plates having less than 30 mm, it is a feature of the claimed method that the high reduction step is carried out when the intermediate thickness of the plate product has reached between 220 mm and 80 mm, preferably 200 mm to 100 mm, most preferred between 200 mm and 120 mm. This thickness is chosen to ensure that the high deformation/shear is consistent throughout the entire plate product thickness.
  • one high reduction hot rolling pass is carried out.
  • two high reduction hot rolling passes are carried out. If one high reduction hot rolling pass is applied, this high reduction hot rolling pass is preferably one of the last seven or eight passes of the multiple hot rolling passes.
  • the rolling ingot is pre-heated to a temperature regular in the art and known to the skilled person, of e.g. 390°C to 480°C, preferably 400°C to 460°C, more preferred 400°C to 430°C, such as 410°C. Accordingly, it is possible to maintain an entry temperature of the hot rolling mill of more than 380°C, preferably of more than 390°C.
  • the maximum temperature for the hot rolling passes is not more than 450°C because it has been observed that coarsening of the S-phase could occur above this temperature and there is a risk of incipient melting.
  • the deformation rate during the at least one high reduction pass in a useful embodiment of the method is preferably lower than ⁇ 1 s-1, preferably ⁇ 0.8 s-1. This intense shearing is believed to cause a break-up of the constituent particles, e.g. Fe-rich intermetallics.
  • the deformation rate is the change of strain (deformation) of a material with respect to time. It is sometimes also referred to as "strain rate".
  • strain rate The formula shows that not only the entry thickness and the exit thickness of the aluminium alloy plate, but also the rolling speed of the working rolls has an influence on the deformation rate.
  • the deformation rate of each rolling pass is typically equal to or more than 2 s -1 .
  • the deformation rate is reduced to ⁇ 1 s -1 , preferably to ⁇ 0.8 s -1 .
  • the aluminium alloy plate product manufactured by the present invention can be, if desired, solution heat treated (SHT), cooled, preferably by means of quenching, stretched and artificially aged after the hot rolling to final gauge step.
  • solution heat treating SHT
  • the plate product should be heated, similar as for the homogenization heat treatment prior to the hot rolling, to a temperature of typically in the range of 430°C to 490°C, to bring all or substantially all portions of the soluble zinc, magnesium and copper into solution.
  • the plate product After a set soaking time at the elevated temperature, the plate product should be rapidly cooled or quenched to complete the solution heat treating procedure.
  • Such quenching is preferably carried out by water-quenching, e.g. via water immersion or water jets.
  • the plate products may further be cold worked by means of stretching in the range of 0.5% to 8 % of its original length to relieve residual stresses therein and to improve the flatness of the product.
  • the stretching is in the range of 0.5% to 5%, more preferably of 1% to 3%.
  • the plate products obtained by the present invention are artificially aged. All ageing practices known in the art and those which may be subsequently developed can be applied to the AA7000-series alloy products obtained by the method according to this invention to develop the required strength and other engineering properties.
  • the plate product is artificially aged to a T7 temper, preferably to a T79 or T77 temper.
  • the artificial ageing step can be carried out in one step or multiple-ageing steps. Preferably, a two-step ageing procedure is carried out.
  • a desired structural shape is then machined from these heat-treated plate sections, more often generally after artificial ageing, for example, an integral wing spar.
  • the aluminium alloy product shows improved fatigue failure resistance without the need to maintain its iron and silicon contents at an extremely low level. According to the prior art, it is generally believed that Fe and Si are both harmful to the fatigue failure resistance. However, the aluminium alloy plate products manufactured by the method of the present invention are much more tolerant to the presence of Fe and Si while still delivering the required balance of properties including a high fatigue failure resistance.
  • the alloy may contain more than 0.05 %, preferably more than 0.06 %, Fe. In an embodiment it may contain more than 0.05 %, preferably more than 0.06 % Si.
  • each of the Fe- and Si-content is equal to or higher than 0.07 wt.%.
  • the Si-content is between 0.06% and 0.10 % and the Fe-content is within 0.06% to 0.15 %. Accordingly, for example a commercially available AA7055 aluminium alloy can be used in the claimed method.
  • the Fe and Si levels are kept at very low levels in order to achieve a further improvement in the properties.
  • the Fe content may be kept at less than 0.05%, preferably less than 0.03%
  • the Si content may be less than 0.05%, preferably less than 0.03%.
  • the AA7000-series alloy plate product when manufactured according to this invention can be used as an aerospace structural component, amongst others as fuselage frame member, upper wing plate, lower wing plate, thick plate for machined parts, thin sheet for stringers, spar member, rib member, floor beam member, and bulkhead member.
  • the aluminium alloy plate product can be used as a wing panel or member, more in particular as an upper wing panel or member.
  • the plate product manufactured according to the invention provides improved properties compared to a plate product manufactured according to conventional standard methods for this type of aluminium alloys having otherwise the same dimensions and processed to the same temper.
  • Rolling ingots have been DC-cast of the aluminum alloy AA7055, with a composition as given in Table 1 Table 1 Si Fe Cu Mg Zn Zr Lot A,B,C,D,E 0.07 0.07 2.35 1.94 8.05 0.12
  • the rolling ingots had a thickness of about 400 mm. Homogenization of the ingots was carried out in a two-step homogenization procedure at 465°C (first step) and 475°C (second step) followed by cooling to ambient temperature. After scalping, the ingots were pre-heated to 410°C for hot rolling. Hot rolling was carried out on a hot rolling mill having a work roll radius of about 575mm. Lots A and B were processed in accordance with the invention, i.e. both lots receive a high reduction pass during the hot rolling process. During the high reduction rolling pass, lot A received a thickness reduction of about 30% (167 mm to 117 mm) and lot B received a thickness reduction of about 28% (165 mm to 118 mm).
  • the rolling speed during this high reduction pass was about 25 m/min giving a deformation rate of about 0.53 s -1 .
  • Lots C, D, and E were processed according to a conventional hot rolling method (a thickness reduction between 9% to 18% for each hot rolling pass between 220 mm and 80 mm thickness).
  • the rolling speed during the standard hot rolling passes was about 105 m/min giving a deformation rate of between 1.61 s -1 (entry thickness 188 mm) and 2.27 s -1 (entry thickness 123 mm).
  • Plate A received 27 hot rolling passes, wherein the high reduction pass was pass number 19.
  • Plate B received 25 hot rolling passes, wherein the high reduction pass was pass number 17.
  • the plates A, C, and E had a final thickness of 19 mm after the hot rolling process, and the plates B and D had a final thickness of 25.4 mm after the hot rolling process.
  • all the plates in final thickness were solution heat treated at a temperature of about 470°C, quenched and stretched for about 2%.
  • An artificial ageing step was applied, bringing the plate products in a T7951 condition.
  • Fatigue testing was performed according to DIN EN 6072 by using a single open hole test coupon having a net stress concentration factor Kt of 2.3.
  • the test coupons were 150 mm long by 30 mm wide, by 3 mm thick with a single hole 10 mm in diameter. The hole was countersunk to a depth of 0.3 mm on each side.
  • the test frequency was 25 Hz and the tests were performed in high humidity air (RH ⁇ 90%). The individual results of these tests are shown in Table 2 and Figs. 1 and 2 .
  • the lines in Figure 2 are an interpolation between the calculated log average data points.
  • Fig. 1 illustrates that by using the method of this invention, it is possible to significantly improve the fatigue life and thus the fatigue failure resistance with respect to AA7055 alloy plates prepared by conventional methods.
  • plate A has a lifetime of 470421 cycles representing a 3.2 times improvement in life time compared to an AA7055 alloy, i.e. alloys C and E which have a life time of 142655 cycles.
  • alloys C and E which have a life time of 142655 cycles.
  • a life time of 200000 cycles see the log average curve in Fig.
  • Fig. 2 shows the logarithmic average of lots A and B manufactured according to the method of this invention compared to the logarithmic average of lots C, D, and E manufactured according to a conventional method of the same alloys as given in Fig. 1 , with lines showing the interpolation between the calculated log average data points. From this figure, it is evident that the method of this invention leads to an improvement of the fatigue live over conventional methods by using the same alloy composition.

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Claims (11)

  1. Procédé de fabrication d'un produit de plaque en alliage d'aluminium de la série 7xxx ayant une résistance améliorée à la rupture par fatigue, le procédé comprenant les étapes suivantes :
    (a) couler un lingot d'un alliage d'aluminium de la série 7xxx, l'alliage d'aluminium comprenant (en % en poids) : Zn 5 à 9, de préférence 5,5 % à 8,5 %, Mg 1 à 3, Cu 0 à 3, de préférence 0,3 % à 3 %, Fe jusqu'à 0,20, de préférence jusqu'à 0,15 %, Si jusqu'à 0,15, de préférence jusqu'à 0,10 %, Zr jusqu'à 0,5, de préférence de 0,03 à 0,20 %,
    et éventuellement un ou plusieurs éléments choisis dans le groupe constitué par : Ti jusqu'à 0,3 % Cr jusqu'à 0,4 % Sc jusqu'à 0,5 % Hf jusqu'à 0,3 % Mn jusqu'à 0,4 % V jusqu'à 0,4 % Ag jusqu'à 0,5 %,
    le reste étant de l'aluminium et des impuretés ;
    (b) homogénéisation et/ou préchauffage du lingot coulé ;
    (c) laminer à chaud le lingot en un produit de plaque en laminant le lingot avec de multiples passes de laminage, caractérisé en ce que, lorsqu'à une épaisseur intermédiaire de la plaque entre 80 et 220 mm, au moins une passe de laminage à chaud à haute réduction est effectuée avec une réduction d'épaisseur d'au moins 25 % ; dans lequel le produit de plaque a une épaisseur finale inférieure à 75 mm, de préférence inférieure à 50 mm.
  2. Procédé selon la revendication 1, dans lequel le procédé comprend en outre les étapes suivantes
    (d) traitement thermique en solution du produit de plaque ;
    (e) refroidissement, de préférence au moyen d'une trempe, du produit de plaque traité thermiquement en solution ;
    (f) étirer éventuellement le produit de plaque traité thermiquement en solution et refroidi, et
    (g) vieillissement artificiel du produit de plaque traité thermiquement en solution et refroidi.
  3. Procédé selon la revendication 1 ou 2, dans lequel le procédé ne comprend pas d'étape de laminage à froid jusqu'au calibre final.
  4. Procédé selon l'une quelconque des revendications précédentes, dans lequel la passe de laminage à chaud à forte réduction est réalisée avec une réduction d'épaisseur d'au moins 30 %, de préférence d'au moins 35 %.
  5. Procédé selon l'une quelconque des revendications précédentes, dans lequel une vitesse de déformation lors de la passe de laminage à chaud à haute réduction est < 1 s-1, de préférence ≤ 0,8 s-1.
  6. Procédé selon l'une quelconque des revendications précédentes, dans lequel l'épaisseur intermédiaire de la plaque avant la passe de laminage à chaud à haute réduction est comprise entre 100 mm et 200 mm, de préférence entre120 mm et 200 mm.
  7. Procédé selon l'une quelconque des revendications précédentes, dans lequel la teneur en Si et/ou la teneur en Fe de l'alliage d'aluminium est supérieure ou égale à 0,05 % en poids.
  8. Procédé selon l'une quelconque des revendications précédentes, dans lequel l'alliage d'aluminium a une composition conforme à la norme AA7055.
  9. Procédé selon l'une quelconque des revendications précédentes, dans lequel l'épaisseur finale du produit de plaque est inférieure à 45 mm, de préférence inférieure à 40 mm, et plus préférentiellement inférieure à 35 mm et/ou, dans lequel l'épaisseur finale du produit de plaque est supérieure à 10 mm, de préférence supérieure à 12,5 mm, plus préférentiellement supérieure à 15 mm et plus préférentiellement supérieure à 19 mm.
  10. Procédé selon l'une quelconque des revendications précédentes, dans lequel, dans l'étape (c) du procédé, la température d'entrée du laminoir à chaud est supérieure à 380 °C, de préférence supérieure à 390 °C.
  11. Procédé selon l'une quelconque des revendications précédentes, dans lequel le produit de plaque est artificiellement vieilli jusqu'à un état T7, de préférence un état T79 ou T77.
EP19729715.3A 2018-06-12 2019-06-05 Procédé de fabrication d'un produit plat en alliage d'aluminium de série 7xxx présentant une meilleure résistance à la rupture par fatigue Active EP3807434B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
EP18177389 2018-06-12
PCT/EP2019/064719 WO2019238509A1 (fr) 2018-06-12 2019-06-05 Procédé de fabrication d'un produit en plaque d'alliage d'aluminium de série 7xxx ayant une résistance améliorée à la rupture par la fatigue

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EP3807434A1 EP3807434A1 (fr) 2021-04-21
EP3807434B1 true EP3807434B1 (fr) 2022-09-14

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US (1) US20210246523A1 (fr)
EP (1) EP3807434B1 (fr)
JP (1) JP7282106B2 (fr)
KR (1) KR102547038B1 (fr)
CN (1) CN112262223B (fr)
BR (1) BR112020023249A2 (fr)
CA (1) CA3100242C (fr)
ES (1) ES2929839T3 (fr)
PT (1) PT3807434T (fr)
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CN111118418B (zh) * 2019-12-27 2020-12-29 燕山大学 提高Al-Zn-Mg-Cu铝合金强韧性的时效处理方法、高强韧铝合金及其制备方法
CN113430431B (zh) * 2021-06-16 2022-08-05 山东南山铝业股份有限公司 一种航空用高损伤容限7系铝合金厚板及其制备方法
CN113528866B (zh) * 2021-06-16 2022-05-20 天津忠旺铝业有限公司 一种航空用高强耐腐蚀7xxx铝合金板材的制备方法
CN113667867A (zh) * 2021-07-30 2021-11-19 宁波吉胜铸业有限公司 一种高强连接件

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US20210246523A1 (en) 2021-08-12
CN112262223B (zh) 2023-02-14
CA3100242A1 (fr) 2019-12-19
BR112020023249A2 (pt) 2021-02-23
KR102547038B1 (ko) 2023-06-26
EP3807434A1 (fr) 2021-04-21
KR20210020992A (ko) 2021-02-24
ES2929839T3 (es) 2022-12-02
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WO2019238509A1 (fr) 2019-12-19
RU2757280C1 (ru) 2021-10-12

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