EP0266741B1 - Alliages à base d'aluminium-lithium et procédé de production - Google Patents

Alliages à base d'aluminium-lithium et procédé de production Download PDF

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EP0266741B1
EP0266741B1 EP19870116166 EP87116166A EP0266741B1 EP 0266741 B1 EP0266741 B1 EP 0266741B1 EP 19870116166 EP19870116166 EP 19870116166 EP 87116166 A EP87116166 A EP 87116166A EP 0266741 B1 EP0266741 B1 EP 0266741B1
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product
temperature
strength
toughness
hot rolling
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EP0266741A1 (fr
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Alex Cho
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Howmet Aerospace Inc
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Aluminum Company of America
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    • 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
    • C22F1/047—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 magnesium 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
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22F—CHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS AND NON-FERROUS ALLOYS
    • C22F1/00—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
    • C22F1/04—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon
    • C22F1/053—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon of alloys with zinc as the next major constituent
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22F—CHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS AND NON-FERROUS ALLOYS
    • C22F1/00—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
    • C22F1/04—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon
    • C22F1/057—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon of alloys with copper as the next major constituent

Definitions

  • This invention relates to aluminum base alloy products, and more particularly, it relates to improved lithium containing aluminum base alloy products and a method of producing the same.
  • More desirable alloys would permit increased strength with only minimal or no decrease in toughness or would permit processing steps wherein the toughness was controlled as the strength was increased in order to provide a more desirable combination of strength and toughness. Additionally, in more desirable alloys, the combination of strength and toughness would be attainable in an aluminum-lithium alloy having density reductions in the order of 5 to 15%. Such alloys would find widespread use in the aerospace industry where low weight and high strength and toughness translate to high fuel savings. Thus, it will be appreciated that obtaining qualities such as high strength at little or no sacrifice in toughness, or where toughness can be controlled as the strength is increased would result in a remarkably unique aluminum-lithium alloy product.
  • the present invention solves problems which limited the use of these alloys and provides an improved lithium containing aluminum base alloy product which can be processed to provide improved strength characteristics while retaining high toughness properties.
  • EP-A-0157600 discloses a step of stretching at a specified point, before aging, and discloses steps relating to heat treatment and working.
  • the present invention solves problems which limited the use of these alloys and provides an improved lithium containing aluminum base alloy product which can be processed to provide improved strength characteristics while retaining high toughness properties.
  • the product comprises 0.5 to 4.0 wt. % Li, 0 to 5.0 wt. % Mg, up to 5.0 wt. % Cu, 0.03 to 0.25 wt. % Zr, 0 to 2.0 wt. % Mn, 0 to 7.0 wt. % Zn, 0.5 wt. % max. Fe, 0.5 wt. % max. Si, the balance aluminum and incidental impurities.
  • the method of making the product comprising the steps of providing a body of a lithium containing aluminum base alloy and heating the body for hot working operations, e.g., hot rolling to a first intermediate sheet product.
  • the sheet product After cold rolling to a second intermediate gauge, the sheet product is reheated and hot rolled to a final sheet product while avoiding substantial recrystallization thereof, the hot rolling adapted to relieve stored energy capable of initiating recrystallization during a subsequent heat treating step.
  • the final sheet product is solution heat treated, quenched and aged to provide a substantially unrecrystallized product having improved levels of strength and fracture toughness.
  • Figures 1 - 7 illustrate concepts useful for understanding the invention.
  • the expression "Ksi" means 1000 pounds per square inch.
  • Figure 1 shows that the relationship between toughness and yield strength for a worked alloy product is increased by stretching.
  • Figure 2 shows that the relationship between toughness and yield strength is increased for a second worked alloy upon stretching.
  • Figure 3 shows the relationship between toughness and yield strength of a third alloy product after stretching.
  • Figure 4 shows that the relationship between toughness and yield strength is increase for another alloy product after stretching.
  • Figure 5 shows that the relationship between toughness (notch-tensile strength divided by yield strength) and yield strength decreases with increase amounts of stretching for AA7050.
  • Figure 6 shows that stretching AA2024 beyond 2% does not significantly increase the toughness-strength relationship for this alloy.
  • Figure 7 illustrates different toughness yield strength relationships where shifts in the upward direction and to the right represent improved combinations of these properties.
  • Figure 8 shows a plot of elongation versus tensile yield stress of aluminum-lithium alloy processed in accordance with the invention and processed conventionally.
  • Figure 9 shows tear test results of an aluminum-lithium alloy processed in accordance with the invention and processed conventionally.
  • Figure 10 shows a metallurgical structure of an aluminum-lithium alloy processed in accordance with conventional practices.
  • Figure 11 shows an unrecrystallized metallurgical structure of an aluminum-lithium alloy processed in accordance with the invention.
  • Figure 12 shows a metallurgical structure of an aluminum-lithium alloy processed in accordance with conventional practices.
  • Figure 13 shows an unrecrystallized metallurgical structure of an aluminum-lithium alloy processed in accordance with the invention.
  • the alloy of the present invention can contain 0.5 to 4.0 wt. % Li, 0 to 5.0 wt. % Mg, up to 5.0 wt. % Cu, 0 to 1.0 wt.% Zr, 0 to 2.0 wt.% Mn, 0 to 7.0 wt.% Zn, 0.5 wt.% max. Fe, 0.5 wt.% max. Si, the balance aluminum and incidental impurities.
  • the impurities are preferably limited to about 0.05 wt.% each, and the combination of impurities preferably should not exceed 0.15 wt.%. Within these limits, it is preferred that the sum total of all impurities does not exceed 0.35 wt.%.
  • a preferred alloy in accordance with the present invention can contain 1.0 to 4.0 wt.% Li, 0.1 to 5.0 wt.% Cu, 0 to 5.0 wt.% Mg, 0 to 1.0 wt.% Zr, 0 to 2 wt.% Mn, the balance aluminum and impurities as specified above.
  • a typical alloy composition would contain 2.0 to 3.0 wt.% Li, 0.5 to 4.0 wt.% Cu, 0 to 3.0 wt.% Mg, 0 to 0.2 wt.% Zr, 0 to 1.0 wt.% Mn and max. 0.1 wt.% of each of Fe and Si.
  • lithium is very important not only because it permits a significant decrease in density but also because it improves tensile and yield strengths markedly as well as improving elastic modulus. Additionally, the presence of lithium improves fatigue resistance. Most significantly though, the presence of lithium in combination with other controlled amounts of alloying elements permits aluminum alloy products which can be worked to provide unique combinations of strength and fracture toughness while maintaining meaningful reductions in density. It will be appreciated that less than 0.5 wt.% Li does not provide for significant reductions in the density of the alloy and 4 wt.% Li is close to the solubility limit of lithium, depending to a significant extent on the other alloying elements. It is not presently expected that higher levels of lithium would improve the combination of toughness and strength of the alloy product.
  • copper With respect to copper, particularly in the ranges set forth hereinabove for use in accordance with the present invention, its presence enhances the properties of the alloy product by reducing the loss in fracture toughness at higher strength levels. That is, as compared to lithium, for example, in the present invention copper has the capability of providing higher combinations of toughness and strength. For example, if more additions of lithium were used to increase strength without copper, the decrease in toughness would be greater than if copper additions were used to increase strength. Thus, in the present invention when selecting an alloy, it is important in making the selection to balance both the toughness and strength desired, since both elements work together to provide toughness and strength uniquely in accordance with the present invention. It is important that the ranges referred to hereinabove, be adhered to, particularly with respect to the upper limits of copper, since excessive amounts can lead to the undesirable formation of intermetallics which can interfere with fracture toughness.
  • Magnesium is added or provided in this class of aluminum alloys mainly for purposes of increasing strength although it does decrease density slightly and is advantageous from that standpoint. It is important to adhere to the upper limits set forth for magnesium because excess magnesium can also lead to interference with fracture toughness, particularly through the formation of undesirable phases at grain boundaries.
  • the amount of manganese should also be closely controlled. Manganese is added to contribute to grain structure control, particularly in the final product. Manganese is also a dispersoid-forming element and is precipitated in small particle form by thermal treatments and has as one of its benefits a strengthening effect. Dispersoids such as Al2Cu2Mn3 and Al12Mg2Mn can be formed by manganese. Chromium can also be used for grain structure control but on a less preferred basis. Zirconium is the preferred material for grain structure control. The use of zinc results in increased levels of strength, particularly in combination with magnesium. However, excessive amounts of zinc can impair toughness through the formation of intermetallic phases.
  • Toughness or fracture toughness as used herein refers to the resistance of a body, e.g. sheet or plate, to the unstable growth of cracks or other flaws.
  • Improved combinations of strength and toughness is a shift in the normal inverse relationship between strength and toughness towards higher toughness values at given levels of strength or towards higher strength values at given levels of toughness.
  • going from point A to point D represents the loss in toughness usually associated with increasing the strength of an alloy.
  • going from point A to point B results in an increase in strength at the same toughness level.
  • point B is an improved combination of strength and toughness.
  • in going from point A to point C results in an increase in strength while toughness is decreased, but the combination of strength and toughness is improved relative to point A.
  • point C at point C, toughness is improved and strength remains about the same, and the combination of strength and toughness is considered to be improved.
  • toughness is improved and strength has decreased yet the combination of strength and toughness are again considered to be improved.
  • the alloy be prepared according to specific method steps in order to provide the most desirable characteristics of both strength and fracture toughness.
  • the alloy as described herein can be provided as an ingot or billet for fabrication into a suitable wrought product by casting techniques currently employed in the art for cast products with continuous casting being preferred.
  • the alloy may also be provided in billet form consolidated from fine particulate such as powdered aluminum alloy having the compositions in the ranges set forth hereinabove.
  • the powder or particulate material can be producted by processes such as atomization, mechanical alloying and melt spinning.
  • the ingot or billet may be priliminarily worked or shaped to provide suitable stock for subsequent working operations.
  • the alloy stock Prior to the principal working operation, the alloy stock is preferably subjected to homogenization, and preferably at metal temperatures in the range of 482 to 566°C (900 to 1050°F) for a period of time of at least one hour to dissolve soluble elements such as Li and Cu, and to homogenize the internal structure of the metal.
  • a preferred time is about 20 hours or more in the homogenization temperature range.
  • the heat up and homogenizing treatment does not have to extend for more than 40 hours; however, long times are not normally detrimental.
  • a time of 20 to 40 hours at the homogenization temperature has been found quite suitable.
  • this homogenization treatment is important in that it is believed to precipitate the Mn and Zr-bearing dispersoids which help to control final grain structure.
  • the metal can be rolled or extruded or otherwise subjected to working operations to produce stock such as sheet, plate or extrusions or other stock suitable for shaping into the end product.
  • thermomechanical steps must be carefully controlled. That is, after the ingot has been homogenized, it may be hot worked or hot rolled. Hot rolling may be performed at a temperature in the range of 427 to 560°C (800 to 1040°F) with a typical temperature being in the range of 510 to 538°C (950 to 1000°F) Hot rolling can reduce the thickness of the ingot to one quarter of its original thickness to provide a first intermediate gauge Thereafter, it may be cold rolled to provide a further gauge reduction. Preferably, such cold rolling produces a gauge thickness near final gauge thickness.
  • the cold rolled sheet is first subjected to a reheat step and then subjected to a light hot rolling pass where preferably not more than 50% reduction is made. Typically, not more than 30% for example 15 to 20%, reduction is required to condition the sheet so as to obtain an unrecrystallized structure after solution heat treating.
  • a light hot rolling pass where preferably not more than 50% reduction is made.
  • not more than 30% for example 15 to 20%, reduction is required to condition the sheet so as to obtain an unrecrystallized structure after solution heat treating.
  • dynamic recovery is meant a dislocation rearrangement process which results in destroying dislocation substructures or permits the recovery of dislocation structures produced during prior rolling steps. This process of deformation processing acts to substantially avoid recrystallization during solution heat treating.
  • the reheat temperature and the hot rolling be controlled so as to prevent recrystallization during these steps. That is, the sheet product is given a light rolling pass at a temperature slightly below recrystallization temperature prior to solution heat treating.
  • the hot rolling pass is performed at a temperature of not greater than about 493°C (920°F) and preferably not greater than 454°C (850°F) with a typical temperature being 427°C (800°F)
  • the time at these temperature should be minimized so as to avoid recrystallization, e.g. typically not more than 2 hours at the higher temperatures.
  • the reheating and light hot rolling can be performed continuously, e.g., with a web of the sheet being continuously passed through a furnace to reach temperature.
  • the sheet can be reheated to temperature in coils for light hot rolling.
  • the cold rolled product (normally rolled to final gauge) is subjected to a controlled reheat treatment. This treatment is carried out for a time and temperature at which recrystallization does not occur.
  • the reheat treatment is provided to relieve stored energy capable of causing recrystallization during subsequent solution heat treatments.
  • a reheat treatment in accordance with the invention which results in an unrecrystallized product after solution heat treating can be achieved when the cold rolled or worked product is subjected to a temperature of 427°C (800°F) for 12 hours.
  • the time at temperatures for the reheat process is important.
  • the initial temperature for the reheat treatment should not be less than 399°C (750°F) and the highest temperature should not exceed 493°C (920°F)
  • the initial temperature is about 427°C (800°F) and the temperature increased gradually from 28 to 57°C (50 to 100°F) until the maximum temperature is reached, sometimes referred to as a ramp anneal.
  • the ramped anneal rate can range from 1.7 to 5.7°C (3 to 10°F) per hour from the low to the high temperature with a typical rate being about 3.4°C (6°F) per hour.
  • the temperature should be raised about 28°C (50°F) over a period of a least 2 to 8 hours. Thereafter, the sheet should be held at 454°C (850°F) for about 1 to 3 hours, typically 2 hours before being cooled to room temperature. If the cooling rate in the furnace is controlled, this can improve the effectiveness of the process.
  • the return to room temperature should be over a period of 6 to 10 hours, typically 8 hours, to guard against small amounts of recrystallisation, particularly at low lithium levels.
  • the temperature can be raised from as much as 83°C (150°F) from a starting reheat temperature of 399°C (750°F)
  • the ramp anneal rate can be as low as 2.8°C (5°F) per hour and as high as 14°C (25°F) per hour with a typical rate being 5.7 to 8°C (10 to 15°F) per hour.
  • the extrusion or forgings may be held at that temperature for 1 to 4 hours to ensure relief of stored energy but not long enough to cause recrystallization.
  • the temperature may be lowered at a controlled rate to room temperature.
  • Products such as rivet wire or plate (AA2090) can be reheated in the same manner except the time for reheat, starting at a reheat temperature of 399 to 427°C (750 to 800°F), should be 12 hours for rivet wire to reach 482°C (900°F) and 24 hours for AA2090 plate to reach 482°C (900°F), for example.
  • the longer times or slower ramp anneal rates are required for products having lower amounts of elements which resist recrystallization, e.g., Zr.
  • ramped anneal is meant to include gradual and stepped increases in temperature.
  • the sheet product is solution heat treated typically at a temperature in the range of 516 to 560°C (960 to 1040°F) for a period in the range of 980 to 1020 hours.
  • the product should be rapidly quenched to prevent or minimize uncontrolled precipitation of strengthening phases referred to herein later.
  • the quenching rate be at least 57°C (100°F) per second from solution temperature to a temperature of about 113°C (200°F) or lower.
  • a preferred quenching rate is at least 113°C (200°F) per second in the temperature range of 482°C (900°F) or more to 93°C (200°F) or less.
  • After the metal has reached a temperature of about 93°C (200°F), it may then be air cooled.
  • the alloy of the invention is slab cast or roll cast, for example, it may be possible to omit some or all of the steps referred to hereinabove, and such is contemplated within the purview of the invention.
  • the improved sheet, plate or extrusion and other wrought products can have a range of yield strength from about 174.4 to 344.7 MPa (25 to 50 ksi) and a level of fracture toughness in the range of about 344.7 to 1034.2 MPa (50 to 150 ksi) in.
  • yield strength from about 174.4 to 344.7 MPa (25 to 50 ksi)
  • level of fracture toughness in the range of about 344.7 to 1034.2 MPa (50 to 150 ksi) in.
  • fracture toughness can drop considerably.
  • the solution heat treated and quenched alloy product may be stretched, preferably at room: temperature, an amount greater than 3% of its original length or otherwise worked or deformed to impart to the product a working effect equivalent to stretching greater than 3% of its original length.
  • the working effect referred to is meant to include rolling and forging as well as other working operations.
  • the strength of sheet or plate, for example, of the subject alloy can be increased substantially by stretching prior to artificial aging, and such stretching causes little or no decrease in fracture toughness. It will be appreciated that in comparable high strength alloys, stretching can produce a significant drop in fracture toughness.
  • Stretching AA7050 reduces both toughness and strength, as shown in Figure 5, taken from the reference by J. T. Staley, mentioned previously. Similar toughness strength data for AA2024 are shown in Figure 6. For AA2024, stretching 2% increases the combination of toughness and strength over that obtained without stretching; however, further stretching does not provide any substantial increases in toughness. Therefore, when considering the toughness-strength relationship, it is of little benefit to stretch AA2024 more than 2%, and it is detrimental to stretch AA7050. In contrast, when stretching or its equivalent is combined with artificial aging, an alloy product in accordance with the present invention can be obtained having significantly increased combinations of fracture toughness and strength.
  • this practive inhibits nucleation of both metastable and equilibrium phases such as Al3Li, AlLi, Al2CuLi and Al5CuLi3 at grain sub-grain boundaries. Also, it is believed that the combination of enhanced uniform precipitation throughout each grain and decreased grain boundary precipitation results in the observed higher combination of strength and fracture toughness in aluminum-lithium alloys worked or deformed as by stretching, for example, prior to final aging.
  • stretching or equivalent working is greater than 3% and less than 14%. Further, it is preferred that stretching be in the range of about a 4 to 12% increase over the original length with typical increases being in the range of 5 to 8%.
  • the alloy product of the present invention may be artificially aged to provide the combination of fracture toughness and strength which are so highly desired in aircraft members. This can be accomplished by subjecting the sheet or plate or plate or shaped product to a temperature in the range of 66 to 204°C (150 to 400°F) for a sufficient period of time to further increase the yield strength.
  • compositions of the alloy product are capable of being artificially aged to a yield strength as high as 655 MPa (95 ksi)
  • the useful strength are in the range of 344.7 to 586.1 MPa (50 to 85 ksi) and corresponding fracture toughnesses are in the range of 172.4 to 517.1 MPa (25 to 75 ksi in.)
  • artificial aging is accomplished by subjecting the alloy product to a temperature in the range of 135 to 191°C (275 to 375°F) for a period of at least 30 minutes.
  • a suitable aging practice contemplate a treatment of about 8 to 24 hours at a temperature of about 163°C (325°F)
  • the alloy product in accordance with the present invention may be subjected to any of the typical underaging treatments well known in the art, including natural aging. However, it is presently believed that natural aging provides the least benefit. Also, while reference has been made herein to single aging steps, multiple aging steps, such as two or three aging steps, are contemplated and stretching or its equivalent working may be used prior to or even after part of such multiple aging steps.
  • Examples I-VI are present for Comparative purposes, Examples VII-IX illustrate the invention.
  • An aluminum alloy consisting of 1.73 wt.% Li, 2.63 wt.% Cu, 0.12 wt.% Zr, the balance essentially aluminum and impurities, was cast into an ingot suitable for rolling.
  • the ingot was homogenized in a furnace at a temperature of 538°C (1000°F) for 24 hours and then hot rolled into a plate product about 2.5 centimeters (one inch) thick.
  • the plate was then solution heat treated in a heat treating furnace at a temperature of 552°C (1025°F) for one hour and then quenched by immersion in 21°C (70°F) water, the temperature of the plate immediately before immersion being 552°C (1025°F) Thereafter, a sample of the plate was stretched 2% greater than its original length, and a second sample was stretched 6% greater than its original length, both at about room temperature. For purposes of artificially aging, the stretched samples were treated at either 163°C (325°F) or 191°C (375°F) for times as shown in Table I.
  • the yield strength values for the samples referred to are based on specimens taken in the longitudinal direction, the direction parallel to the direction of rolling.
  • Toughness was determined by ASTM Standard Practice E561-81 for R-curve determination. The results of these tests are set forth in Table I. In addition, the results are shown in Figure 1 where toughness is plotted against yield strength. It will be noted from Figure 1 that 6% stretch displaces the strength-toughness relationship upwards and to the right relative to the 2% stretch. Thus, it will be seen that stretching beyond 2% substantially improved toughness and strength in this lithium containing alloy. In contrast, stretching decreases both strength and toughness in the long transverse direction for alloy 7050 ( Figure 5). Also, in Figure 6, stretching beyond 2% provides added little benefit to the toughness-strength relationship in AA2024. Table I 2% Stretch 6% Stretch Aging hrs.
  • Example II An aluminum alloy consisting of, by weight, 2.0% Li, 2.7% Cu, 0.65% Mg and 0.12% Zr, the balance essentially aluminum and impurities, was cast into an ingot suitable for rolling.
  • the ingot was homogenized at 527°C (980°F) for 36 hours, hot rolled to 2.5 centimeter (1.0 inch) plate as in Example I, and solution heat treated for one hour at 527°C (980°F) Additionally, the specimens were also quenched, stretched, aged and tested for toughness and strength as in Example I.
  • Table II The results are provided in Table II, and the relationship between toughness and yield strength is set forth in Figure 2. As in Example I, stretching this alloy 6% displaces the toughness-strength relationship to substantially higher levels.
  • Example I An aluminum alloy consisting of, by weight, 2.78% Li, 0.49% Cu, 0.98% Mg, 0.50 Mn and 0.12% Zr, the balance essentially aluminum, was cast into an ingot suitable for rolling.
  • the ingot was homogenized as in Example I and hot rolled to plate of 64 millimeter (0.25 inch) thick. Thereafter, the plate was solution heat treated for one hour at 538°C (1000°F) and quenched in 21°C (70°F) water. Samples of the quenched plate were stretched 0%, 4% and 8% before aging for 24 hours at 163°C (325°F) or 191°C (375°F) Yield strength was determined as in Example I and toughness was determined by Kahn type tear tests.
  • Example III An aluminum alloy consisting of, by weight, 2.72% Li, 2.04% Mg, 0.53% Cu, 0.49 Mn and 0.13% Zr, the balance essentially aluminum and impurities, was cast into an ingot suitable for rolling. Thereafter, it was homogenized as in Example I and then hot rolled into plate 64 millimeters (0.25 inch) thick. After hot rolling, the plate was solution heat treated for one hour at 538°C (1000°F) and quenched in 21°C (70°F) water. Samples were taken at 0%, 4% and 8% stretch and aged as in Example I. Tests were performed as in Example III, and the results are presented in Table IV. Figure 4 shows the relationship of toughness and yield strength for this alloy as a function of the amount of stretching.
  • the dashed line is meant to suggest the toughness-strength relationship for this amount of stretch.
  • the increase in strength at equivalent toughness is significiantly greater than the previous alloys and was unexpected in view of the behavior of conventional alloys such as AA7050 and AA2024.
  • Table IV Stretch Aging Practice Tensile Yield Strength Tear Strength Tear Strength/ Yield Strength hrs.
  • An aluminum alloy consisting of, by weight, 2.25% Li, 2.98% Cu, .12% Zr, the balance being essentially aluminum and impurities, was cast into an ingot suitable for rolling.
  • the ingot was homogenized in a furnace at a temperature of 510°C (950°F) for 8 hours followed immediately by a temperature of 538°C (1000°F) for 24 hours and air cooled.
  • the ingot was then preheated in a furnace for 30 minutes at 524°C (975°F) and hot rolled to 4.45 centimeters (1.75 inch) thick plate.
  • the plate was solution heat treated for 2 hours at 549°C (1020°F) followed by a continuous water spray quench with a water temperature of 22°C (72°F)
  • the plate was stretched at room temperature in the rolling direction with 4.9% permanent set. Stretching was followed by an artificial aging treatment of 18 hours at 163°C (325°F)
  • Tensile properties were determined in the short transverse direction in accordance with ASTM B-557. These values are shown in Table V. The ultimate tensile strength and the yield tensile strength were equal, and the resulting elongations are zero. Table V Specimen No.
  • An aluminum alloy consisting of, by weight, 2.13% Li, 2.83% Cu, .13% Zr, the balance being essentially aluminum and impurities, was cast into an ingot suitable for rolling.
  • the ingot was homogenized in a furnace at a temperature of 510°C (950°F) for 8 hours followed immediately by a temperature of 538°C (1000°F) for 24 hours and air cooled.
  • the ingot was then preheated in a furnace for 30 minutes at 524°C (975°F) and hot rolled to 8.9 cm. (3.5") thick slab.
  • the slab was reheated for 4 hours at 538°C (1000°F) and hot rolled to 3.7 mm. (0.144") thick sheet.
  • the sheet was then annealed for 4 hours at 343°C (650°F) and cold rolled to 2.0 mm. (0.080") thick gauge sheet.
  • the sheet was solution heat treated for 1 hour at 538°C (1000°F) followed by a cold water quench with a water temperature of 22°C (72°F)
  • the sheet was stretched 4% at room temperature in the rolling direction. Stretching was followed by an artificial aging of 8 hours at 163°C (325°F) for under aged condition and 24 hours at 163°C (325°F) for peak aged condition. Examination of microstructure revealed heavily recrystallized microstructure with extremely coarse grain structures, as shown in Figure 10.
  • the tensile test result and tear test result are shown in Figures 8 and 9, showing properties at three strength levels, i.e., T3 temper (as stretched), underaged (stretched and aged for 8 hours at 163°C (325°F)) and peak aged (stretched and aged for 24 hours at 163°C (325°F)).
  • An aluminum alloy consisting of, by weight, 2.13% Li, 2.83% Cu, .13% Zr, the balance being essentially aluminum and impurities, was cast into an ingot suitable for rolling.
  • the ingot was homogenized in a furnace at a temperature of 510°C (950°F) for 8 hours followed immediately by a temperature of 538°C (1000°F) for 24 hours and air cooled.
  • the ingot was then preheated in a furnace for 30 minutes at 524°C (975°F) and hot rolled to 8.9 cm. (3.5") thick slab.
  • the slab was reheated for 4 hours at 538°C (1000°F) and hot rolled to 3.7 mm. (0.144") thick sheet.
  • the sheet was then annealed for 4 hours at 343°C (650°F) and cold rolled to 2.0 mm. (0.080") thick gauge sheet.
  • the cold rolled sheet was annealed for 12 hours at 427°C (800°F) to relieve a stored energy capable of commencing recrystallization during the subsequent heat treatment.
  • the sheet was solution heat treated for 1 hour at 543°C (1010°F) followed by a cold water quench with a water temperature of 22°C (72°F)
  • the sheet was stretched by 4% at room temperature in the rolling direction. Stretching was followed by an artificial aging of 8 hours at 163°C (325°F) for under aged condition and 24 hours at 163°C (325°F) for peak aged condition.
  • microstructure revealed an unrecrystallized microstructure, as shown in Figure 11.
  • the tensile test result and tear test result are shown in Figures 8 and 9, showing properties at three strength levels, i.e., T3 temper (as stretched), underaged (stretch and aged for 8 hours at 163°C (325°F)) and peak aged (stretched and aged for 24 hours at 163°C (325°F)
  • FIG. 11 is an optical micrograph of solution heat treatment material in accordance with the invention.
  • Figure 10 shows conventionally treated material. That is, Figure 10 shows cold rolled sheet which was solution heat treated. The X-ray analysis shows that the sheet was completely recrystallized.
  • An aluminum alloy consisting of, by weight, 1.97% Li, 2.83% Cu, .12% Zr, the balance being essentially aluminum and impurities, was cast into an ingot suitable for rolling.
  • the ingot was homogenized in a furnace at a temperature of 510°C (950°F) for 8 hours followed immediately by a temperature of 538°C (1000°F) for 24 hours and air cooled.
  • the ingot was then preheated in a furnace for 30 minutes at 524°C (975°F) and hot rolled to 8.9 centimeter (3.5 inch) thick slab.
  • the slab was reheated for 4 hours at 538°C (1000°F) and hot rolled to 3.7 millimeter (0.144 inch) thick sheet.
  • the sheet was then annealed for 2 hours at 343°C (650°F) and cold rolled to 1.6 millimeter (0.063 inch) thick gauge sheet.
  • the cold rolled sheet (1.6 millimeter (0.063 inch) gauge) was solution heat treated for 30 minutes at 549°C (1020°F) followed by a cold water quench with a water temperature of 22°C (72°F) Examination of microstructure revealed heavily recrystallized microstructure with extremely coarse grain structures as shown in Figure 10.
  • the 1.6 millimeter (0.063 inch) thick cold rolled sheet was heated to 427°C (800° F) then the temperature was slowly increased at a controlled heat-up rate to reach 454°C (850°F) in 8 hours, then soaked for 2 hours at 454°C (850°F) followed by a furnace cool to 22°C (72°F)
  • the annealed sheet samples were then heat treated at 549°C (1020°F) for 30 minutes and cold water quenched.
  • Microstructural examination by optical metallography revealed an unrecrystallized structure, shown as S.N. 585703-1 in Figure 13.
  • the ramped anneal practice was found to be a more efficient anneal practice in preventing recrystallisation than anneal practices utilizing a constant temperature.

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Claims (11)

  1. Procédé de production d'un produit corroyé non cristallisé à base d'aluminium-lithium présentant des niveaux améliorés de résistance mécanique et de ténacité à la rupture, le procédé comprenant tes étapes suivantes :
    (a) fourniture d'un corps d'un alliage à base d'aluminium contenant du lithium dans lequel ledit produit contient 0,5 à 4,0 % en poids de Li, 0 à 5,0 % de Mg, jusqu'à 5,0 % en poids de Cu, 0 à 2,0 % en poids de Mn, 0 à 7,0 % en poids de Zn, au maximum 0,5 % en poids de Fe, au maximum 0,5 % en poids de Si et l'un des éléments choisis dans le groupe formé par Zr, Cr, Ce et Sc, le complément étant constitué par de l'aluminium, des éléments et impuretés éventuels ;
    (b) chauffage du corps jusqu'à une température de façonnage à chaud ou de laminage à chaud ;
    (c) façonnage à chaud ou laminage à chaud du corps pour former un premier produit ;
    (d) façonnage à froid ou laminage à froid dudit premier produit pour former un second produit corroyé ;
    (e) réchauffage ou réchauffage et laminage à chaud dudit second produit corroyé tout en évitant une recristallisation sensible de celui-ci, le réchauffage et le laminage à chaud étant réalisés à une température comprise dans la gamme de 399 à 493°C (750 à 920°F), ou étant amorcés et parachevés dans ladite gamme, la température de parachèvement étant de préférence supérieure d'au moins 28 à 83°C (50 à 150°F) à la température d'amorçage ;
    (f) recuit de mise en solution, trempe et vieillissement dudit produit réchauffé.
  2. Procédé selon la revendication 1, dans lequel ledit réchauffage est conçu pour libérer l'énergie stockée.
  3. Procédé selon la revendication 2, dans lequel la température est augmentée à une vitesse de 1,7 à 14°C (3 à 25°F) par heure, ou à une vitesse de 2,8 à 8°C (5 à 15°F) par heure.
  4. Procédé selon la revendication 2 ou 3, dans lequel ledit réchauffage comprend le maintien dudit produit pendant au moins une demi-heure à la température de parachèvement.
  5. Procédé selon la revendication 1, pour produire un produit en tôle d'aluminium-lithium laminé a froid à faible calibre, non recristallisé, ayant des niveaux améliorés de résistance mécanique et de ténacité à la rupture, dans lequel dans l'étape (b) le chauffage est opéré jusqu'à une température de laminage à chaud, dans l'étape (c) le corps est laminé à chaud pour former un premier produit de calibre intermédiaire, dans l'étape (d) ledit premier produit est laminé à froid pour former un second produit en tôle intermédiaire, et dans l'étape (e) le second produit en tôle intermédiaire est réchauffé et laminé à chaud pour former un produit en tôle tout en évitant une recristallisation sensible de celui-ci.
  6. Procédé selon la revendication 5, dans lequel l'étape de réchauffage et de laminage à chaud est réalisée à une température qui ne dépasse pas 493°C (920°F).
  7. Procédé selon la revendication 5 ou 6, dans lequel dans l'étape (e) ledit laminage à chaud conduit à une réduction de calibre qui ne dépasse pas 50 %.
  8. Procédé selon la revendication 5 ou 6, dans lequel dans l'étape (e) ledit laminage à chaud conduit à une réduction de calibre qui ne dépasse pas 30 %.
  9. Procédé selon la revendication 5 ou 6, dans lequel dans l'étape (e) ledit laminage à chaud conduit à une réduction de calibre qui ne dépasse pas 15 à 20 %.
  10. Procédé selon l'une quelconque des revendications précédentes, dans lequel ledit produit contient 1,0 à 4,0 % en poids de Li, 0,5 à 4,0 % en poids de Cu, 0 à 3,0 % en poids de Mg, 0,03 à 0,15 % en poids de Zr et 0 à 1,0 % en poids de Mn.
  11. Procédé selon la revendication 10, dans lequel ledit produit contient 2,0 à 3,0 % en poids de Li, 0,5 à 4,0 % en poids de Cu, 0 à 3,0 % en poids de Mg, 0,05 à 0,12 % en poids de Zr et 0 à 1,0 % en poids de Mn.
EP19870116166 1986-11-04 1987-11-03 Alliages à base d'aluminium-lithium et procédé de production Expired EP0266741B1 (fr)

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JP (1) JPH01501325A (fr)
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DE68927149T2 (de) * 1988-10-12 1997-04-03 Aluminum Co Of America Verfahren zur Herstellung eines nichtkristallisierten, flachgewalzten, dünnen, wärmebehandelten Produktes auf Aluminiumbasis
GB9012810D0 (en) * 1990-06-08 1990-08-01 British Petroleum Co Plc Method of treatment of metal matrix composites
DE4113352C2 (de) * 1991-04-24 1996-05-23 Hoogovens Aluminium Gmbh Verfahren zur Herstellung von Aluminiumblechen
US20150376740A1 (en) * 2013-03-14 2015-12-31 Alcoa Inc. Aluminum-magnesium-lithium alloys, and methods for producing the same
EP3577246A1 (fr) * 2017-01-31 2019-12-11 Universal Alloy Corporation Extrusions d'alliage aluminium-cuivre-lithium de faible densité
FR3065012B1 (fr) * 2017-04-10 2022-03-18 Constellium Issoire Produits en alliage aluminium-cuivre-lithium a faible densite
CN117144213B (zh) * 2023-10-31 2024-01-23 湖南卓创精材科技股份有限公司 一种高综合性能的铝锂合金和制备方法

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US4094705A (en) * 1977-03-28 1978-06-13 Swiss Aluminium Ltd. Aluminum alloys possessing improved resistance weldability
FR2561260B1 (fr) * 1984-03-15 1992-07-17 Cegedur Alliages al-cu-li-mg a tres haute resistance mecanique specifique
US4648913A (en) * 1984-03-29 1987-03-10 Aluminum Company Of America Aluminum-lithium alloys and method

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DE3775522D1 (de) 1992-02-06
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WO1988003575A1 (fr) 1988-05-19
JPH01501325A (ja) 1989-05-11
CA1321126C (fr) 1993-08-10

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