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EP1359232B1 - Procédé servant a améliorer la ténacité d'alliages d'aluminium et de lithium - Google Patents

Procédé servant a améliorer la ténacité d'alliages d'aluminium et de lithium Download PDF

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Publication number
EP1359232B1
EP1359232B1 EP03015053A EP03015053A EP1359232B1 EP 1359232 B1 EP1359232 B1 EP 1359232B1 EP 03015053 A EP03015053 A EP 03015053A EP 03015053 A EP03015053 A EP 03015053A EP 1359232 B1 EP1359232 B1 EP 1359232B1
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Prior art keywords
fracture toughness
lithium
aluminum
ksi
weight percent
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German (de)
English (en)
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EP1359232B2 (fr
EP1359232A2 (fr
EP1359232A3 (fr
EP1359232B9 (fr
Inventor
Alex Cho
Michael Skillingberg
Richard Greene
Michael Niedzinski
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Constellium Rolled Products Ravenswood LLC
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Alcan Rolled Products Ravenswood LLC
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Priority to DE69836569.0T priority Critical patent/DE69836569T3/de
Publication of EP1359232A2 publication Critical patent/EP1359232A2/fr
Publication of EP1359232A3 publication Critical patent/EP1359232A3/fr
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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
    • C22C21/12—Alloys based on aluminium with copper 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

  • the present invention is directed to a method of improving the fracture toughness in the short longitudinal direction in aluminum-lithium alloys and a product there from and, in particular, to a method which controls the levels of copper, manganese, lithium, and zirconium in the alloys to obtain the improved fracture toughness.
  • Aluminum-lithium alloys exhibit improvements in stiffness and strength while reducing density. Consequently, these types or alloys have utility as structural materials in airplane and aerospace applications. Examples of known aluminum-lithium alloys include AA2097 and AA2197. The chemical compositions of these alloys are shown in Table 1 below.
  • Toughness values in this direction tend to be significantly lower than toughness values in other directions such as the longitudinal (L-T) direction or the long transverse (T-L) direction.
  • the present invention provides both a method and a product therefrom which significantly increases the fracture toughness of aluminum-lithium alloys in the short longitudinal (S-L) direction, thereby improving their suitability for more commercial applications.
  • a first object of the invention is to improve the fracture toughness in the short longitudinal (S-L) direction of aluminum-lithium alloys.
  • Another object of the invention is to provide a method of making an aluminum-lithium alloy having improved short longitudinal direction fracture toughness.
  • a still further object of the present invention is to utilize an aluminum-lithium alloy having controlled amounts of copper, lithium, manganese, zinc and zirconium to achieve fracture toughness improvements.
  • Yet another object of the present invention is to provide an aluminum-lithium alloy product having both improved fracture toughness in the short longitudinal (S-L) direction and acceptable strength in the short transverse direction.
  • the present invention provides a method for improving the fracture toughness in the short longitudinal (S-L) direction in an aluminum-lithium alloy article comprising the steps of providing an aluminum alloy consisting essentially of, in weight percent all subsequent alloying levels are weight percent unless otherwise indicated): 2.7 to 3.0% copper, 0.8% to less than 1.3% lithium, 0.05 to 0.8% manganese, 0.04 to 0.18% zirconium, with the balance aluminum and inevitable impurities.
  • the aluminum alloy can also include grain refining elements such as at least one of boron, titanium, vanadium, manganese, hafnium, scandium and chromium.
  • the aluminum alloy has only impurity levels of zinc so that it is essentially zinc-free, e.g., less than 0.05 weight percent zinc, more preferably less than or equal to 0.02%.
  • the lithium content is preferably controlled between about 1.2 to 1.28 weight percent to provide a low density product with good fracture toughness in the short longitudinal direction.
  • Manganese is preferably between 0.30 and 0.32 weight percent, with zirconium being about 0.10 weight percent. It should be appreciated that the amounts of alloying elements, other than the amounts of lithium and copper, can be within the ranges described in the preceding paragraph.
  • the lithium content ranges from about 0.8% to less than 1.2 and the copper content is between about 2.8 and 3%.
  • This composition should provide even higher combined properties of fracture toughness and strength, with slightly higher density.
  • additional theta' precipitate particles (Al2Cu) would precipitate in addition to T1 precipitate particles (Al2CuLi) at the grain boundaries. This would increase the combined properties of strength and fracture toughness in the short longitudinal direction.
  • Magnesium can be added if desired, in an amount up to 0.25 weight percent. Small amounts of magnesium may be beneficial in terms of strength and lowering of density. However, excessive amounts may create susceptibility to stress corrosion cracking and do not provide further benefits in terms of strength and density reduction.
  • the aluminum alloy is cast into an ingot and homogenized for a select period of time.
  • the homogenized ingot is then hot worked into a shape such as a plate and solution heat treated for a select period of time.
  • the solution heat treated shape is then quenched, preferably in water, cold worked, preferably by stretching, and aged for a select period of time. With this processing, the cold worked (stretched) and aged shape exhibits equivalent strengths but higher fracture toughness in the short longitudinal (S-L) direction than similar aluminum alloys having lithium contents greater than 1.38.
  • the homogenization and solution heat treating temperatures range between about 940°F (505°C) to 975°F (524°C), and solution heat treating temperatures will range between about 975°F (524°C) to 1000°F (538°C).
  • the preferred temperature often depends on the particular alloy composition as will be understood by one skilled in the art.
  • Homogenization times can be about 8 to 48 hours, preferably about 24 to about 36 hours.
  • Solution heat treating times can range from about 1 to 10 hours, preferably about 1 hour to 6 hours, more preferably about 2 hours, once the metal reaches a desired temperature.
  • the plate may be artificially aged without any cold work. However, it is preferred to provide between about 4 and 8 cold work, preferably by stretching.
  • the plate is preferably artificially aged between about 300 and 350°F (149 to 177°C) for between about 4 and about 48 hours, preferably between about 12 and about 36 hours, with the aging time being a function of the aging temperature.
  • an aluminum-lithium alloy article is made having vastly improved fracture toughness in the short longitudinal (S-L) direction.
  • the fracture toughness value in the short longitudinal (S-L) direction is at least about 689 of the fracture toughness in the long transverse (T-L) direction.
  • the inventive aluminum-lithium alloy articles While exhibiting improved fracture toughness in the short longitudinal (S-L) direction, the inventive aluminum-lithium alloy articles have tensile yield strengths exceeding about 54 KSI.
  • the present invention solves a significant problem in the field of aluminum-lithium materials for structural applications such as those found in the aerospace and airplane industry. That is, by controlling the compositional amounts of copper, lithium, manganese and zirconium in these types of alloys, acceptable fracture toughness in the short longitudinal (S-L) direction with acceptable strength in the short transverse (ST) direction is obtained. This unexpected improvement in fracture toughness in the S-L direction permits the use of these types of alloys in a wide variety of structural applications requiring low weight, high strength and stiffness, and good fracture toughness.
  • the alloy elements of copper, lithium, manganese and zirconium are controlled in the following ranges to achieve the improvements in fracture toughness: about 2.7 to 3.0 weight percent copper, about 0.8 to less than about 1.2 or 1.3 weight percent lithium, about 0.05 to 0.8 weight percent manganese, about 0.04 to 0.16 weight percent zirconium, with the balance aluminum and inevitable impurities.
  • One or more grain refining elements can also be added to the aluminum-lithium composition described above.
  • the grain refining elements can be selected from the group consisting of titanium in an amount up to 0.2 weight percent, boron in an amount of up to 0.2 weight percent, vanadium in an amount of up to 0.2 weight percent, hafnium in an amount up to 0.2 weight percent, scandium in an amount up to 0.5 weight percent, and chromium in an amount up to 0.3 weight percent.
  • the aluminum is free of zinc.
  • zinc is present only as an impurity and at levels less than 0.05 weight percent. It is believed that zinc in levels greater than such impurity level adversely affects the mechanical properties of these types of aluminum-lithium alloys.
  • the copper content should be kept higher than 2.7 weight percent to achieve high strength but less than 3.0 weight percent to avoid undissolved particles during solution heat treatment.
  • the lithium content should be kept higher than 0.8 weight percent to achieve good strength and low density but less than 1.3 weight percent to avoid a loss of fracture toughness in the short longitudinal (S-L) direction.
  • the manganese content should be kept below 0.8 weight percent to avoid large non-dissolvable particles which would be detrimental to fracture toughness.
  • the manganese should be higher than 0.05 weight percent to control grain size and homogenous slip behavior during plastic deformation processing.
  • the lithium content should be controlled between 1.2 and to less than 1.3 weight percent. Still more preferably, in one embodiment, the lithium content is controlled to less than 1.2 weight percent.
  • the manganese is more preferably between 0.3 and 0.32 weight percent with the copper level ranging between about 2.7 and 3.0 weight percent.
  • Magnesium can be added if desired, in an amount preferably up to 0.25 weight percent. Small amount of magnesium may be beneficial in terms of strength and lowering of density. However, excessive amounts may create susceptibility to stress corrosion cracking and do not provide further benefits in terms of strength and density reduction.
  • the alloy is processed by the steps of casting, homogenizing, hot working (for instance, by rolling, forging, extruding and combinations thereof), solution heat treating, quenching, cold working (for instance by stretching) and aging to form an aluminum-lithium article having the improvements in fracture toughness in the S-L direction.
  • the aluminum-lithium alloy described above is cast into an ingot, billet or other shape to provide suitable stock for the subsequent processing operations.
  • the shape can be stress-relieved as is known in the art prior to homogenization.
  • the cast shape is then homogenized at temperatures in the range of 940°F to 975°F, 505°C to 524°C, for a sufficient period of time to dissolve the soluble elements and homogenize the internal structure of the metal.
  • a preferred homogenization residence time is in the range of 1 to 36 hours, while longer times do not normally adversely affect the article.
  • the homogenization can be conducted at one temperature or in multiple steps utilizing several temperatures.
  • the cast shape is then hot worked to produce stock such as sheet, plate, extrusions, or other stock material depending on the desired end use of the aluminum-lithium alloy article.
  • stock such as sheet, plate, extrusions, or other stock material depending on the desired end use of the aluminum-lithium alloy article.
  • an ingot having a rectangularly shaped cross section could be hot worked into a plate form. Since this hot working step is conventional in the art, a further description thereof is not deemed necessary for understanding of the invention.
  • the hot worked shape is then solution heat treated and quenched.
  • the hot worked shape is solution heat treated between 975° to 1000°F (524° to 538°C) at a time from less than an hour to up to several hours.
  • This solution heat treated shape is preferably rapidly quenched, e.g. quenched in ambient temperature water, to prevent or minimize uncontrolled precipitation of strengthening phases in the alloy.
  • the rapid quenching can also include a subsequent air cooling step, if desired.
  • the quenched shape is then preferably stretched up to 8% and artificially aged in the temperature range of 150° to 400°F (66° to 204°C) for sufficient time to further increase the yield strength, e.g., up to 100 hours, depending on the temperature, for instance, 24 hours at 300°F (149°C).
  • the stretched and aged shape is then ready for use in any application, particularly an aerospace or airplane application.
  • the shape may be formed into an article and then aged.
  • An aluminum alloy consisting of, in weight percent, 2.84 Cu-1.36 Li-.32 Mn.-.1 Zr, the balance aluminum and impurities, was cast into an ingot with a cross section of 16" (406.4 mm) and 45" (1143 mm) wide.
  • the ingot was homogenized at 950°F (510°C) for 36 hours, then hot worked to 4" (101.6 mm) thick plate.
  • the plate was then solution heat treated in a heat treating furnace at a temperature of 990°F (532°C) for 2 hours and then quenched in water.
  • the plate was then stretched by 6% in the longitudinal direction at room temperature. For artificial aging, the stretched samples were aged in an oven at 320°F (160°C)for 24 hours.
  • An aluminum alloy consisting of, in weight percent, 2.71 Cu-1.37 Li-.32 Mn.-.1 Zr, the balance aluminum and impurities, was cast into an ingot with a cross section of 16" (406.4 mm) and 45" (1143 mm) wide.
  • the ingot was homogenized at 950°F (510°C) for 36 hours, then hot worked to 4" (101.6 mm) thick plate.
  • the plate was then solution heat treated in a heat treating furnace at a temperature of 990°F (532°C) for 2 hours and then quenched in water.
  • the plate was then stretched by 6% in the longitudinal direction at room temperature. For artificial aging, the stretched samples were aged in an oven at 320°F (160°C)for 24 hours.
  • An aluminum alloy consisting of, in weight percent, 2.77 Cu-1.33 Li-.32 Mn.-. 11 Zr, the balance aluminum and impurities, was cast into an ingot with a cross section of 16" (406.4 mm) and 45" (1143 mm) wide.
  • the ingot was homogenized at 950°F (510°C) for 36 hours, then hot worked to 4" (101.6 mm) thick plate.
  • the plate was then solution heat treated in a heat treating furnace at a temperature of 990°F (532°C) for 2 hours and then quenched in water.
  • the plate was then stretched by 6% in the longitudinal direction at room temperature. For artificial aging, the stretched samples were aged in an oven at 320°F (160°C)for 24 hours.
  • An aluminum alloy consisting of, in weight percent, 2.89 Cu-1.36 Li-.32 Mn.-0.1 Zr, the balance aluminum and impurities, was cast into an ingot with a cross section of 16" (406.4 mm) and 45" (1143 mm) wide.
  • the ingot was homogenized at 950°F (5100C) for 36 hours, then hot worked to 4" (101.6 mm) thick plate.
  • the plate was then solution heat treated in a heat treating furnace at a temperature of 990°F (532°C) for 2 hours and then quenched in water.
  • the plate was then stretched by 6% in the longitudinal direction at room temperature. For artificial aging, the stretched samples were aged in an oven at 320°F (160°C)for 24 hours.
  • An aluminum alloy consisting of, in weight percent, 2.78 Cu-1.21 Li-.31 Mn.-0.1 Zr, the balance aluminum and impurities, was cast into an ingot with a cross section of 16" (406.4 mm) and 45" (1143 mm) wide.
  • the ingot was homogenized at 950°F (510°C) for 36 hours, then hot worked to 4" (101.6 mm) thick plate.
  • the plate was then solution heat treated in a heat treating furnace at a temperature of 990°F (532°C) for 2 hours and then quenched in water.
  • the plate was then stretched by 8% in the longitudinal direction at room temperature. For artificial aging, the stretched samples were aged in an oven at 320°F (160°C)for 24 hours.
  • An aluminum alloy consisting of, in weight percent, 2.86 Cu-1.28 Li-.3 Mn.-0.1 Zr, the balance aluminum and impurities, was cast into an ingot with a cross section of 16" (406.4 mm) and 45" (1143 mm) wide.
  • the ingot was homogenized at 950°F (510°C) for 36 hours, then hot worked to 4" (101.6 mm) thick plate.
  • the plate was then solution heat treated in a heat treating furnace at a temperature of 990°F (532°C) for 2 hours and then quenched in water.
  • the plate was then stretched by 6% in the longitudinal direction at room temperature. For artificial aging, the stretched samples were aged in an oven at 320°F (160°C) for 24 hours.
  • An aluminum alloy consisting of, in weight percent, 2.73 Cu-1.28 Li-.3 Mn.-0.1 Zr, the balance aluminum and impurities, was cast into an ingot with a cross section of 16" (406.4 mm) and 45" (1143 mm) wide.
  • the ingot was homogenized at 950%F (510°C) for 36 hours, then hot worked to 4" (101.6 mm) thick plate.
  • the plate was then solution heat treated in a heat treating furnace at a temperature of 990°F (532°C) for 2 hours and then quenched in water.
  • the plate was then stretched by 6% in the longitudinal direction at room temperature. For artificial aging, the stretched samples were aged in an oven at 320°F (160°C)for 24 hours.
  • An aluminum alloy consisting of, in weight percent, 2.83 Cu-1.26 Li-.32 Mn.-0.11 Zr, the balance aluminum and impurities, was cast into an ingot with a cross section of 16" (406.4 mm) and 45" (1143 mm) wide.
  • the ingot was homogenized at 950°F (510°C) for 36 hours, then hot worked to 4" (101.6 mm) thick plate.
  • the plate was then solution heat treated in a heat treating furnace at a temperature of 990°F (532°C) for 2 hours and then quenched in water.
  • the plate was then stretched by 6% in the longitudinal direction at room temperature. For artificial aging, the stretched samples were aged in an oven at 320°F (160°C)for 24 hours.
  • Figure 1 correlates the fracture toughness values in Tables 2-9 in the S-L direction with tensile yield strengths in the S-T direction.
  • Figure 1 shows that no compromise is made in the tensile yield strengths between the prior art examples and the examples of the invention. More specifically, the prior art tensile yield strength values range from just above 54 KSI to almost 60 KSI. In comparison, the tensile yield strengths of the examples according to the invention range from just below 55 KSI to just above 57 KSI.
  • Figure 1 demonstrates that the articles made of the present invention provide significantly improved fracture toughness in the S-L direction while maintaining acceptable strength levels in the S-T direction.
  • Figure 2 illustrates the unexpected improvements in fracture toughness in the S-L direction over the prior art.
  • the values depicted in Figure 2 demonstrate that the fracture toughness in the S-L direction for Examples 5-8 is vastly superior to that shown for Examples 1-4.
  • This improvement, which relates to lithium content, is quite unexpected in view of the prior art.
  • Figure 3 emphasizes the fact that the improvements in fracture toughness are related to the lithium content of the alloys.
  • Figure 3 demonstrates that the fracture toughness does not vary widely with respect to copper content.
  • the fracture toughness appears to remain relatively the same with increasing or decreasing amounts of copper.
  • the fracture toughness of Examples 1-4 does not vary widely with increasing or decreasing copper content.
  • the lithium content can be as low as 0.8 weight percent while still giving improvements in fracture toughness and maintaining the acceptable strength in the short transverse direction. It is further believed that the same results are obtainable when practicing the inventive processing in accordance with the broad processing variable ranges disclosed above.

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Claims (9)

  1. Procédé de fabrication d'un produti en alliage aluminium-lithium comprenant les étapes de :
    a) production d'un alliage d'aluminium comprenant, en pourcent en poids :
    de 2,7 à 3,0 % de cuivre,
    de 0,8 à moins de 1,3 % de lithium,
    de 0,05 à 0,8 % de manganèse,
    jusqu'à 0,25 % de magnésium,
    de 0,04 à 0,18 % de zirconium,
    optionnellement un ou plusieurs éléments d'affinage de grains choisis dans le groupe constitué de jusqu'à 0,2 % de titane, jusqu'à 0,2 % de bore, jusqu'à 0,2 % de vanadium, jusqu'à 0,2 % d'hafnium, jusqu'à 0,5 % de scandium et jusqu'à 0,3 % de chrome,
    l'aluminium restant et des impuretés inévitables ;
    b) coulée de l'alliage d'aluminium en un lingot ;
    c) homogénéisation du lingot à une température comprise entre 940°F et 975°F (de 505°C à 524°C) ;
    d) transformation à chaud du lingot homogénéisé en une ébauche transformée à chaud ;
    e) traitement thermique de mise en solution de l'ébauche transformée à chaud à une température comprise entre 975° et 1000°F (de 524 à 538°C) ;
    f) trempe de l'ébauche mise en solution ; et
    g) transformation à froid et vieillissement de l'ébauche trempée.
  2. Procédé selon la revendication 1 dans lequel l'ébauche est déformée par traction contrôlée entre 4 et 8 % et ensuite revenue entre 150 et 400°F (de 66 à 204°C), et de préférence entre environ 300 et 350°F (de 149 à 177°C).
  3. Procédé selon la revendication 1 ou la revendication 2 dans lequel la teneur en lithium est inférieure à 1,2 % en poids.
  4. Procédé selon la revendication 1, dans lequel la teneur en lithium varie entre 1,2 et 1,28 %.
  5. Procédé selon la revendication 1 dans lequel la teneur en lithium est inférieure à 1,2 % en poids et la teneur en cuivre est supérieure à 2,8 % en poids.
  6. Procédé selon la revendication 4 dans lequel la teneur en zirconium est entre 0,04 et 0,16 %.
  7. Procédé selon l'une quelconque des revendications 1 à 6 dans lequel l'alliage d'aluminium est essentiellement exempt de zinc.
  8. Procédé selon l'une quelconque des revendications 1 à 7, dans lequel ledit produit en aluminium-lithium est une tôle.
  9. Procédé selon la revendication 1 dans lequel la résistance à la rupture de la plaque dans la direction longitudinale courte (S-L) est au moins environ 68,5 % de la résistance à la rupture de la plaque dans la direction transversale longue (T-L).
EP03015053.6A 1997-01-31 1998-01-30 Procédé servant a améliorer la ténacité d'alliages d'aluminium et de lithium Expired - Lifetime EP1359232B9 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
DE69836569.0T DE69836569T3 (de) 1997-01-31 1998-01-30 Verfahren zur Erhöhung der Bruchzähigkeit in Aluminium-Lithium-Legierungen

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US3632997P 1997-01-31 1997-01-31
US36329 1997-01-31
EP98903777A EP0981653B1 (fr) 1997-01-31 1998-01-30 Procede servant a ameliorer la tenacite d'alliages d'aluminium et de lithium

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EP1359232A2 EP1359232A2 (fr) 2003-11-05
EP1359232A3 EP1359232A3 (fr) 2004-01-02
EP1359232B1 true EP1359232B1 (fr) 2006-11-29
EP1359232B2 EP1359232B2 (fr) 2014-03-12
EP1359232B9 EP1359232B9 (fr) 2014-09-10

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EP (2) EP1359232B9 (fr)
AT (2) ATE250675T1 (fr)
DE (2) DE69818448T2 (fr)
ES (1) ES2278093T5 (fr)
WO (1) WO1998033947A1 (fr)

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CN101903546B (zh) * 2007-12-21 2013-01-02 法国肯联铝业 用于航空应用的由铝-锂合金制成的轧制产品

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EP1359232B2 (fr) 2014-03-12
EP0981653A4 (fr) 2000-05-17
DE69836569D1 (de) 2007-01-11
DE69818448T2 (de) 2004-07-29
DE69836569T2 (de) 2008-01-03
ES2278093T3 (es) 2007-08-01
ATE250675T1 (de) 2003-10-15
DE69836569T3 (de) 2014-07-31
EP1359232A2 (fr) 2003-11-05
EP1359232A3 (fr) 2004-01-02
ES2278093T5 (es) 2014-07-16
ATE346963T1 (de) 2006-12-15
EP1359232B9 (fr) 2014-09-10
EP0981653A1 (fr) 2000-03-01
DE69818448D1 (de) 2003-10-30
WO1998033947A1 (fr) 1998-08-06
EP0981653B1 (fr) 2003-09-24

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