EP1809779B1 - Produkte aus hochfester aluminiumlegierung und herstellungsverfahren dafür - Google Patents

Produkte aus hochfester aluminiumlegierung und herstellungsverfahren dafür Download PDF

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EP1809779B1
EP1809779B1 EP05805764A EP05805764A EP1809779B1 EP 1809779 B1 EP1809779 B1 EP 1809779B1 EP 05805764 A EP05805764 A EP 05805764A EP 05805764 A EP05805764 A EP 05805764A EP 1809779 B1 EP1809779 B1 EP 1809779B1
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alloy
ingot
cast form
process according
parameter
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French (fr)
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EP1809779A1 (de
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Bernard Bes
Philippe Jarry
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Constellium Issoire SAS
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Alcan Rhenalu SAS
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    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C1/00—Making non-ferrous alloys
    • C22C1/06—Making non-ferrous alloys with the use of special agents for refining or deoxidising
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22B—PRODUCTION AND REFINING OF METALS; PRETREATMENT OF RAW MATERIALS
    • C22B21/00—Obtaining aluminium
    • C22B21/06—Obtaining aluminium refining
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22B—PRODUCTION AND REFINING OF METALS; PRETREATMENT OF RAW MATERIALS
    • C22B21/00—Obtaining aluminium
    • C22B21/06—Obtaining aluminium refining
    • C22B21/062—Obtaining aluminium refining using salt or fluxing agents
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C1/00—Making non-ferrous alloys
    • C22C1/02—Making non-ferrous alloys by melting
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C1/00—Making non-ferrous alloys
    • C22C1/02—Making non-ferrous alloys by melting
    • C22C1/026—Alloys based on aluminium
    • 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
    • C22C21/02—Alloys based on aluminium with silicon as the next major constituent
    • 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
    • C22C21/06—Alloys based on aluminium with magnesium as the next major constituent
    • C22C21/08—Alloys based on aluminium with magnesium as the next major constituent with silicon
    • 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
    • C22C21/12—Alloys based on aluminium with copper as the next major constituent
    • C22C21/14—Alloys based on aluminium with copper as the next major constituent with silicon
    • 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
    • C22C21/12—Alloys based on aluminium with copper as the next major constituent
    • C22C21/16—Alloys based on aluminium with copper as the next major constituent with magnesium
    • 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
    • C22C21/12—Alloys based on aluminium with copper as the next major constituent
    • C22C21/18—Alloys based on aluminium with copper as the next major constituent with zinc
    • 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

Definitions

  • the invention relates to a new manufacturing method for high tenacity and high fatigue resistant aluminum alloy rolled products, as well as products obtained by this process.
  • This process comprises a particular refining of the liquid metal.
  • These sheets can be used as aircraft fuselage liner.
  • Al-Si-Mg-Cu alloys can be used for fuselage structural members. These elements must have on the one hand a high mechanical strength, and on the other hand good toughness and good resistance to fatigue. Any new opportunity to improve one of these property groups without degrading others would be welcome.
  • the object of the present invention is to propose a new process for obtaining highly recrystallized wrought products, preferably laminated products, and in particular 6xxx series alloy thin metal sheets with high mechanical strength which also show excellent toughness and fatigue resistance.
  • Another object of the present invention is a rolling plate that can be obtained by the casting process.
  • Yet another object of the present invention is a sheet capable of being obtained from the process or from the rolling plate according to the invention.
  • the figure 1 shows the influence of refining and titanium content on the parameter p *.
  • the figure 2 shows the influence of refining and titanium content on the parameter s *.
  • the black triangle represents an alloy refined with TiB 2 , while the other alloys have been refined with AlTiC.
  • the designation of the alloys follows the rules of THE ALUMINUM ASSOCIATION.
  • 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 as well as in the publications of THE ALUMINUM ASSOCIATION. These rules, standards and publications are known to those skilled in the art.
  • alloy of the 6xxx series or "alloy of the Al-Mg-Si type” is understood to mean aluminum alloys (i) whose chemical composition falls into one of the standardized designations of an alloy of the 6xxx series, or (ii) that is derived from an alloy corresponding to such a standardized designation by the addition or deletion of one or more chemical elements other than silicon or magnesium, and / or by the exceedance (to the up or down) of the standardized concentration limit of one or more chemical elements (including silicon and magnesium), it being understood that in both cases (i) and (ii), the application of the Standardized designation should lead to storing this modified alloy in the 6xxx series.
  • 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.
  • the fatigue strength is determined by a test according to ASTM E 466, the fatigue crack growth rate (so-called da / dn test) according to ASTM E 647, and the critical stress intensity factor K C , Kco or K App according to ASTM E 561.
  • the term "spun product” includes so-called “stretched” products, that is products that are made by spinning followed by stretching.
  • structural element or “structural element” of a mechanical construction a mechanical part whose failure is likely to endanger the safety of said construction, its users, its users or others.
  • these structural elements include the elements that make up the fuselage (such as fuselage skin (fuselage skin in English), stiffeners or stringers, bulkheads, fuselage (circumferential frames)), the wings (such as the wing skin), the stiffeners (stringers or stiffeners), the ribs (ribs) and spars) and the empennage composed in particular of horizontal stabilizers 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, bulkheads, fuselage (circumferential frames)
  • the wings such as the wing skin
  • stiffeners stringers or stiffeners
  • ribs ribs
  • spars the empennage composed in particular of horizontal stabilizers and vertical (horizontal or vertical stabilizers), as
  • the present invention is applicable to wrought alloys AA6056 and AA 6156 It is based on the discovery that the refining of an aluminum alloy using a refining containing AlTiC-type phases added in the right proportion makes it possible to obtain a very particular microstructure of the cast raw form, and in particular a grain size greater than 500 ⁇ m and a regular distribution of intermetallic phases, observed by optical microscopy at a magnification Typically 50.
  • wrought products After hot transformation according to known processes, optionally followed by a cold conversion and a heat treatment, in particular for highly recrystallized products, wrought products are obtained which show, in a manner surprisingly, a significantly better toughness and a lower crack propagation rate than products made from raw forms obtained by known methods.
  • highly recrystallized product means a product for which the fraction of recrystallized grains measured between the quarter-thickness and the half-thickness of the finished products is greater than 70%.
  • the products from step (f) are strongly recrystallized. It is known for weakly recrystallized products that the casting microstructure can be reflected up to the properties of the transformed product (for example hot-rolled, cold-rolled and heat-treated), but in the present case the mechanism of this surprising phenomenon does not occur. has not yet been elucidated in terms of structural metallurgy.
  • the product produced by the process according to the invention differs from the products according to the state of the art by the presence of AlTiC type phases.
  • AlTiC type phases we mean any ternary Al-Ti-C phase as well as any Ti-C binary phase in an aluminum matrix; this term notably includes the AlTiC 2 and TiC phases. These phases are typically added in a refining yarn. Despite the small quantity of these phases, their effect on the microstructure of casting is very clear. Since wire refining containing AlTiC-type phases can substitute for the boron-containing wire refining (such as AT5B) commonly used, the raw form produced by the process according to the invention may contain less than 0, 0001% boron.
  • the casting microstructure obtained by the process according to the invention is characterized by two parameters, p * (dimension [ ⁇ m]) and s * (dimension [ ⁇ m -1 ]). These parameters characterize more particularly the smoothness and the uniformity of the microsegrégation.
  • the parameter p * characterizes the average distance between precipitates in the solidification structures, and therefore the average size of the zones without precipitates.
  • the parameter s * characterizes the uniformity of the distribution of these distances.
  • the precise definition of these two parameters as well as the method for their determination are specified in the article "Quantification of Spatial Distribution of As-Cast Microstructural Features" by Ph. Jarry, M. Boehm, and S. Antoine, published in Proceedings of the Light Metals 2001 Conference, Ed.
  • Digital image analysis is an iterative closing of the image with a step up.
  • the step i which closes the image C i is defined by i successive dilations of the image of the same object (a dilation consisting of the replacement of each pixel of an image by the maximum value of its neighbors) followed by i successive erosions of the image of the same object (an erosion consisting of the replacement of each pixel of an image by the minimal value of its neighbors) of the image d (note that erosion and expansion operations are not commutative).
  • the surface ratio A which represents the surface fraction of the objects, is plotted as a function of the number of closing steps i .
  • A denotes the surface fraction of objects after transformation
  • a min denotes the initial surface fraction of intermetallic particles after thresholding
  • a max denotes their surface fraction corresponding to the conventional filling at which the algorithm is stopped (in practice 90%) in order to avoid problems of slow convergence at the end of filling
  • i is the number of calculation steps
  • ⁇ is an adjustment coefficient of the slope of the sigmoid.
  • the parameter p * represents the average distance between particles present in the matrix.
  • a rolling plate is manufactured according to the method of the invention, so as to obtain a value of s * greater than 0.92 ⁇ m -1 , and preferably greater than 0.94. -1 .mu.m and simultaneously obtain a value of p * of less than 107 .mu.m.
  • the raw form obtained at the end of the casting such as a spinning billet, a forge billet or a rolling plate, is transformed hot and optionally cold to its final thickness.
  • the product of final thickness is then subjected to a solution and quenching heat treatment, followed by controlled tensile stress relieving with a permanent elongation of between 0.5 and 5%, and optionally followed by an income. If the permanent elongation obtained during tensioning by controlled tensing is less than 0.5%, the product does not reach sufficient flatness. If the permanent elongation achieved during controlled tensile stress relieving is greater than 5%, the damage tolerance properties may be affected.
  • the process according to the invention is particularly well suited for producing wrought products made of alloy AA6056, AA6156 or similar alloys.
  • alloy AA6056, AA6156 or similar alloys it is preferred to limit the iron content to 0.15%, and even 0.13%, in order to reduce the tendency to microsegregate during casting.
  • An advantageous embodiment for heat-treated alloys comprises converting the hot-rolling sheet into a sheet having a thickness of between 3 and 12 mm, and heat treating to the T6 state.
  • this process leads to a sheet with a tolerance to damage K R , determined in TL direction for a crack extension ⁇ a eff of 20 mm from a curve R measured according to ASTM E561, from minus 115 MPa ⁇ m, and preferably at least 116 MPa ⁇ m.
  • a sheet of AA6056 or AA6156 alloys manufactured by the method according to the invention also has in the T6 temper in a thickness between 3 and 12 mm a damage tolerance K R determined in the TL direction to an extension of cracks .DELTA.a eff 60 mm obtained from a curve R measured according to ASTM E561, of at least 175 Pa ⁇ m.
  • the improvement of the parameter K R which results from the method according to the present invention may make it possible to increase the guaranteed minimum value of this parameter for a given constraint, knowing that this parameter, like all the parameters which characterize a product metallurgical, always shows a certain statistical dispersion.
  • An AA6056 alloy was cast into two industrial-size rolling plates, in particular 446 mm thick, at a speed of 55 mm / min and at a temperature of 680 ° C.
  • Table 1 gives the refining method (AlT3C0,15 or AT5B wire.)
  • the designation A1T3C0,15 corresponds to a composition Al-3% Ti-0,15% C.
  • the designation AT5B corresponds to an Al-5% Ti composition.
  • -1% B this product is also known under the commercial designation "AlTiB 5: 1", the Ti content (in ppm mass), the inoculation rate and mean values for the parameters s * and p * as defined above.
  • the parameters s * and p * were determined on samples cut at about 140 mm from the skin and at the third width of the rolling plates.
  • Table 1 Reference Ti [ppm] Inoculation rate refining s * p * [Kg / t] 4032A 180 0.7 AT5B 0.88 110 4032B 180 0.5 AlT3C0,15 0.99 101
  • plated plates having a final thickness of 5 mm in the T6 state were produced using the same transformation range comprising homogenization, hot rolling, dissolution, quenching. , controlled traction stress relief and income.
  • the permanent elongation obtained during controlled tensile stress relaxation was 1.5%.
  • the fraction of recrystallized grains measured between the quarter-thickness and the mid-thickness of the finished products was close to 100%.
  • the static mechanical characteristics and the damage tolerance of these sheets have been determined.
  • the results are collated in Table 2.
  • the parameter K R (20) refers to a crack extension value ⁇ a eff of 20 mm.
  • figure 1 gives a comparison of the fineness of the casting microstructures (parameter p *) as a function of the Ti content and the type of refining agent.
  • figure 2 gives a comparison of the regularity of the casting microstructures (parameter s *).
  • Table 4 summarizes the total Ti content in the alloys of Examples 1 and 2, as well as the size of the foundry grains.
  • Table 4 Reference refining Ti [ppm] Fe [%] Grain size Type Kg / t Average [ ⁇ m] Standard deviation IC 4031A AlTiC 0.5 50 0.09 902 214 153 4031B AlTiC 1 50 0.09 655 101 72 4032A AT5B 0.7 180 0.08 388 38 27 4032B AlTiC 0.5 180 0.08 713 112 80 4033A AlTiC 0.5 430 0.07 757 143 102 4033B AlTiC 2 430 0.07 664 200 143 4034A AlTiC 0.5 630 0.2 833 201 144 4034B AlTiC 2 630 0.2 644 113 81 4035A AlTiC 0.5 80 0.2 771 171 122 4035B AlTiC 0.5 80 0.2 822 118 84

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  • Manufacturing & Machinery (AREA)
  • Physics & Mathematics (AREA)
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Claims (14)

  1. Verfahren zur Herstellung hochfester und ermüdungsfester Aluminiumlegierungsprodukte, das folgende Schritte umfasst:
    (a) es wird ein Aluminiumlegierungsbad hergestellt,
    (b) in das Bad wird ein Feinungsmittel eingebracht,
    (c) es wird eine Rohform gegossen, wie z.B. ein Pressbarren, ein Schmiedebarren oder ein Walzbarren,
    (d) die Rohform wird warm umgeformt, eventuell nach erfolgtem Fräsen, um ein Vormaterial oder ein Produkt mit Enddicke herzustellen,
    (e) das Vormaterial wird optional auf seine Enddicke kalt umgeformt,
    (f) das Produkt aus dem Schritt (d) oder (e) wird einer Wärmebehandlung bestehend aus Lösungsglühen und Abschrecken unterzogen, an die sich eine Entspannung durch kontrolliertes Recken mit einer bleibenden Dehnung zwischen 0,5 und 5 % und eventuell eine Warmauslagerung anschließen,
    dadurch gekennzeichnet, dass das Feinungsmittel Teilchen aus AlTiC-Phasen enthält, dass die Menge an Feinungsmittel so gewählt wird, dass die mittlere Gusskorngröße der Rohform größer als 500 µm ist und dass die Legierung eine Legierung AA6056 oder eine Legierung AA6156 ist.
  2. Verfahren nach Anspruch 1, dadurch gekennzeichnet, dass die Menge an Feinungsmittel so gewählt wird, dass die im Lichtmikroskop mit 50-facher Vergrößerung beobachtete Verteilung der intermetallischen Phasen der Rohform regelmäßig ist.
  3. Verfahren nach Anspruch 1 oder 2, dadurch gekennzeichnet, dass der rekristallisiere Anteil gemessen zwischen einem Viertel der Dicke und der halben Dicke der Produkte aus dem Schritt (f) größer als 70 % ist.
  4. Verfahren nach einem der Ansprüche 1 bis 3, dadurch gekennzeichnet, dass die Rohform weniger als 0,0001 % Bor enthält.
  5. Verfahren nach irgendeinem der Ansprüche 1 bis 4, wobei der Gehalt an Eisen 0,15 % und vorzugsweise 0,13 % nicht übersteigt.
  6. Verfahren nach irgendeinem der Ansprüche 1 bis 5, wobei die Rohform ein Walzbarren ist.
  7. Verfahren nach Anspruch 6, wobei nach erfolgtem Fräsen oder eventuell nach einer ersten Warmwalzstufe eine Plattierung auf eine oder beide Seiten des Walzbarrens aufgebracht wird.
  8. Walzbarren aus Legierung AA6056 oder AA6156 mit einer mittleren Gusskorngröße größer als 500 µm, der durch ein Verfahren gewonnen werden kann, welches die Schritte (a) bis (c) des Verfahrens nach irgendeinem der Ansprüche 1 oder 4 bis 7 umfasst, gekennzeichnet durch einen Parameter s* größer als 0,92 µm-1, vorzugsweise größer als 0,94 µm-1, und durch einen Parameter p* kleiner als 107 µm,
    wobei der Parameter p* definiert ist durch die Gleichung A = A min + A max - A min 1 + exp α ⁢ p * - i ) ,
    Figure imgb0007
    und wobei der Parameter s* definiert ist durch die Gleichung s * = α × A max - A min 4 ,
    Figure imgb0008
    worin
    A den Oberflächenanteil von Gegenständen nach erfolgter Umformung bezeichnet,
    Amin den anfänglichen Oberflächenanteil intermetallischer Teilchen nach erfolgter Schwellenwertbestimmung bezeichnet,
    Amax ihren Oberflächenanteil entsprechend der konventionellen Füllung bezeichnet, bei welcher der Algorithmus gestoppt wird, um die Probleme der langsamen Konvergenz am Ende des Füllvorgangs zu vermeiden,
    i die Zahl der Rechenschritte ist,
    und α ein Koeffizient zum Abgleich der Steilheit der Sigmoidkurve ist.
  9. Walzbarren nach Anspruch 8, dadurch gekennzeichnet, dass er weniger als 0,0001 % Bor enthält.
  10. Walzblech, welches aus einem Walzbarren nach irgendeinem der Ansprüche 8 bis 9 gewonnen werden kann.
  11. Walzblech aus Legierung AA6056 oder AA6156 nach Anspruch 10, dadurch gekennzeichnet, dass es im Zustand T6 in einer Dicke im Bereich zwischen 3 und 12 mm eine Schadentoleranz KR, ermittelt aus einer nach ASTM E 561 gemessenen R-Kurve in Quer-Längsrichtung bei einer Rissausdehnung Δaeff von 20 mm, von mindestens 115 MPa√m und vorzugsweise von mindestens 116 MPa√m besitzt.
  12. Blech aus Legierung AA6056 oder AA6156 nach irgendeinem der Ansprüche 10 bis 11, dadurch gekennzeichnet, dass es im Zustand T6 in einer Dicke im Bereich zwischen 3 und 12 mm eine Schadentoleranz KR, ermittelt aus einer nach ASTM E 561 gemessenen R-Kurve in Quer-Längsrichtung bei einer Rissausdehnung Δaeff von 60 mm, von mindestens 175 MPa√m besitzt.
  13. Blech aus Legierung AA6056 oder AA6156 nach irgendeinem der Ansprüche 10 bis 12, dadurch gekennzeichnet, dass seine Rissausbreitungsgeschwindigkeit da/dn in Längs-Querrichtung, gemessen nach ASTM E 561 in Längs-Querrichtung an einer Platte der Breite w = 400 bei Δk = 50 MPa√m und R = 0.1, kleiner als 2 10-2 mm / Zyklus ist.
  14. Blech aus Legierung AA6056 oder AA6156 nach irgendeinem der Ansprüche 10 bis 13, dadurch gekennzeichnet, dass es auf einer oder beiden Seiten plattiert ist.
EP05805764A 2004-09-24 2005-09-19 Produkte aus hochfester aluminiumlegierung und herstellungsverfahren dafür Expired - Lifetime EP1809779B1 (de)

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FR0410138A FR2875815B1 (fr) 2004-09-24 2004-09-24 Produits en alliage d'aluminium a haute tenacite et procede d'elaboration
PCT/FR2005/002310 WO2006035133A1 (fr) 2004-09-24 2005-09-19 Produits en alliage d ' aluminium a haute tenacite et procede d ' elaboration

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AT (1) ATE463588T1 (de)
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CN101590591B (zh) * 2008-05-30 2011-08-03 杰出材料科技股份有限公司 容易焊接的高强度铝合金型材的制作方法
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US20060065331A1 (en) 2006-03-30
ES2344213T3 (es) 2010-08-20
EP1809779A1 (de) 2007-07-25
WO2006035133A1 (fr) 2006-04-06
FR2875815B1 (fr) 2006-12-01
ATE463588T1 (de) 2010-04-15
US20100006186A1 (en) 2010-01-14
CN101027419A (zh) 2007-08-29
US7615125B2 (en) 2009-11-10
CN101027419B (zh) 2010-06-16
FR2875815A1 (fr) 2006-03-31

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