EP4350020A1 - Aluminiumlegierung, aluminiumlegierungsdraht und verfahren zur herstellung eines aluminiumlegierungsdrahts - Google Patents

Aluminiumlegierung, aluminiumlegierungsdraht und verfahren zur herstellung eines aluminiumlegierungsdrahts Download PDF

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Publication number
EP4350020A1
EP4350020A1 EP22810942.7A EP22810942A EP4350020A1 EP 4350020 A1 EP4350020 A1 EP 4350020A1 EP 22810942 A EP22810942 A EP 22810942A EP 4350020 A1 EP4350020 A1 EP 4350020A1
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EP
European Patent Office
Prior art keywords
mass
aluminum alloy
amount
plane
working
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EP22810942.7A
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English (en)
French (fr)
Inventor
Ryota MATSUGI
Kazuya Tokuda
Tsukasa Matsuo
Hiroaki Takai
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Sumitomo Electric Industries Ltd
Sumitomo Electric Toyama Co Ltd
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Sumitomo Electric Industries Ltd
Sumitomo Electric Toyama Co Ltd
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Publication of EP4350020A1 publication Critical patent/EP4350020A1/de
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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
    • C22C21/02—Alloys based on aluminium with silicon as the next major constituent
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
    • B21C—MANUFACTURE OF METAL SHEETS, WIRE, RODS, TUBES OR PROFILES, OTHERWISE THAN BY ROLLING; AUXILIARY OPERATIONS USED IN CONNECTION WITH METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL
    • B21C1/00—Manufacture of metal sheets, metal wire, metal rods, metal tubes by drawing
    • B21C1/003—Drawing materials of special alloys so far as the composition of the alloy requires or permits special drawing methods or sequences
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
    • B21B—ROLLING OF METAL
    • B21B1/00—Metal-rolling methods or mills for making semi-finished products of solid or profiled cross-section; Sequence of operations in milling trains; Layout of rolling-mill plant, e.g. grouping of stands; Succession of passes or of sectional pass alternations
    • B21B1/16—Metal-rolling methods or mills for making semi-finished products of solid or profiled cross-section; Sequence of operations in milling trains; Layout of rolling-mill plant, e.g. grouping of stands; Succession of passes or of sectional pass alternations for rolling wire rods, bars, merchant bars, rounds wire or material of like small cross-section
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
    • B21C—MANUFACTURE OF METAL SHEETS, WIRE, RODS, TUBES OR PROFILES, OTHERWISE THAN BY ROLLING; AUXILIARY OPERATIONS USED IN CONNECTION WITH METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL
    • B21C1/00—Manufacture of metal sheets, metal wire, metal rods, metal tubes by drawing
    • B21C1/02—Drawing metal wire or like flexible metallic material by drawing machines or apparatus in which the drawing action is effected by drums
    • 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
    • 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
    • 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
    • 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
    • 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
    • C22F1/02—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working in inert or controlled atmosphere or vacuum
    • 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
    • C22F1/043—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 silicon 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
    • C22F1/047—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
    • C22F1/05—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 of the Al-Si-Mg type, i.e. containing silicon and magnesium in approximately equal proportions
    • 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 disclosure relates to an aluminum alloy, an aluminum alloy wire, and a method of manufacturing an aluminum alloy wire.
  • This application claims priority based on Japanese Patent Application No. 2021-089504 filed on May 27, 2021 , and the entire contents of the Japanese patent application are incorporated herein by reference.
  • PTL 1 discloses an aluminum alloy wire which is a wire composed of an aluminum alloy including silicon and magnesium and has high tensile strength after being subjected to solution treatment and aging treatment.
  • the aluminum alloy wire can be used as a raw material for an aluminum alloy member.
  • the aluminum alloy member is manufactured by performing predetermined plastic working on the aluminum alloy wire and then subjecting solution treatment and aging treatment on the aluminum alloy wire.
  • An aluminum alloy of the present disclosure has a composition including silicon in an amount of 0.6 mass% to 1.5 mass%, magnesium in an amount of 0.5 mass% to 1.3 mass%, copper in an amount of 0.1 mass% to 1.2 mass%, and manganese in an amount of 0.2 mass% to 1.15 mass%, with the balance consisting of aluminum and inevitable impurities.
  • An average of degrees of orientation of a 111 plane determined by X-ray diffraction of a whole area of a section in a state of having been subjected to solution treatment and aging treatment is 50% or more, and a variance of the degrees of orientation of the 111 plane is 45% or less.
  • the aluminum alloy wire of the present disclosure is composed of an aluminum alloy of the present disclosure.
  • a method of manufacturing an aluminum alloy wire of the present disclosure includes performing plastic working on a cast product of an aluminum alloy to manufacture a worked product, the aluminum alloy having a composition including silicon in an amount of 0.6 mass% to 1.5 mass%, magnesium in an amount of 0.5 mass% to 1.3 mass%, copper in an amount of 0.1 mass% to 1.2 mass%, and manganese in an amount of 0.2 mass% to 1.15 mass%, with the balance consisting of aluminum and inevitable impurities, performing first drawing on the worked product under cold conditions to manufacture a first drawn product, performing softening treatment on the first drawn product to manufacture a softened product, and performing second drawing on the softened product under cold conditions to manufacture a second drawn product.
  • a degree of working in the second drawing is 20% or more and is also higher than a degree of working in the first drawing.
  • an object of the present disclosure to provide an aluminum alloy having high-strength in a state of having been subjected to solution treatment and aging treatment. Another object of the present disclosure is to provide an aluminum alloy wire composed of the aluminum alloy described above. Another object of the present disclosure is to provide a method of manufacturing an aluminum alloy wire, with which the aluminum alloy wire can be manufactured.
  • the aluminum alloy of the present disclosure and the aluminum alloy wire of the present disclosure have high-strength in a state of having been subjected to solution treatment and aging treatment.
  • the aluminum alloy wire of the present disclosure can be manufactured with the method of manufacturing the aluminum alloy wire of the present disclosure.
  • An aluminum alloy according to an embodiment of the present disclosure has a composition including silicon in an amount of 0.6 mass% to 1.5 mass%, magnesium in an amount of 0.5 mass% to 1.3 mass%, copper in an amount of 0.1 mass% to 1.2 mass%, and manganese in an amount of 0.2 mass% to 1.15 mass%, with the balance consisting of aluminum and inevitable impurities.
  • an average of degrees of orientation of a 111 plane determined by X-ray diffraction of a whole area of a section in a state of having been subjected to solution treatment and aging treatment is 50% or more, and a variance of the degrees of orientation of the 111 plane is 45% or less.
  • the 111 plane in the present disclosure means a crystal plane denoted by (111) in crystallography.
  • the degree of orientation of the 111 plane in the present disclosure is determined using values obtained by normalizing each of the following three diffraction intensities obtained by X-ray diffraction of the whole area of the section.
  • the degree of orientation of the 111 plane in the present disclosure is the ratio of the normalized value of the diffraction intensity of the 111 plane to the sum of the three normalized values.
  • the three diffraction intensities are the diffraction intensity of the 111 plane, the diffraction intensity of the 200 plane, and the diffraction intensity of the 220 plane.
  • the 200 plane and the 220 plane mean crystal planes each denoted by (200) and (220) in crystallography, respectively.
  • the average of the degrees of orientation of the 111 plane in the present disclosure is a value obtained by averaging the above-described ratio at each measurement point of the whole area of the section.
  • the variance of the degrees of orientation of the 111 plane in the present disclosure is a value obtained from the above average. Methods for measuring the average and the variance of the degrees of orientation of the 111 plane in the present disclosure are described below.
  • the section of the aluminum alloy is, for example, the following section.
  • the section is a section cut along a plane perpendicular to the longitudinal direction of the aluminum alloy.
  • the heating temperature is a temperature selected from a range of 530°C to 580°C.
  • the heating time is a time selected from a range of 15 minutes to 120 minutes.
  • the heating temperature is a temperature selected from a range of 150°C to 180°C.
  • the heating time is a time selected from a range of 4 hours to 100 hours.
  • the aluminum alloy of the present disclosure has the above-described specific composition, the aluminum alloy has a high tensile strength due to precipitation hardening in a state of having been subjected to solution treatment and aging treatment.
  • the state in which the 111 plane of the crystal grains is oriented occurs not in a part of the section but over the whole area of the section.
  • the aluminum alloy of the present disclosure having such a section is hard to break, for example, when it is pulled in a direction perpendicular to the section as a pulling direction.
  • the aluminum alloy of the present disclosure has high tensile strength.
  • the aluminum alloy of the present disclosure has a higher tensile strength than the aluminum alloy described in PTL 1.
  • the aluminum alloy of the present disclosure has high-strength in the state of having been subjected to solution treatment and aging treatment.
  • the aluminum alloy of the present disclosure has well-balanced heat resistance, corrosion resistance, and strength in the state of having been subjected to solution treatment and aging treatment, similarly to an alloy called a 6000 series alloy by the International Alloy Designations.
  • the aluminum alloy of the present disclosure can be suitably used as an aluminum alloy member required to have higher strength in addition to heat resistance and corrosion resistance and as a raw material for the aluminum alloy member.
  • the aluminum alloy member is, for example, an automobile part or various structural members. Automotive parts and various structural members may take the form of wires, rods, pipes and the like.
  • the raw material is, for example, aluminum alloy wire, aluminum alloy plate or the like.
  • the aluminum alloy of the present disclosure may further include at least one element selected from the group consisting of iron, chromium, zinc, titanium, and zirconium.
  • a content ratio of iron is more than 0 mass% and 0.8 mass% or less.
  • a content ratio of chromium is more than 0 mass% and 0.35 mass% or less.
  • a content ratio of zinc is more than 0 mass% and 0.5 mass% or less.
  • a content ratio of titanium is more than 0 mass% and 0.2 mass% or less.
  • a content ratio of zirconium is more than 0 mass% and 0.2 mass% or less.
  • the aluminum alloy tends to have a higher tensile strength.
  • the aluminum alloy according to (2) above may have the composition including silicon in an amount of 1.0 mass% to 1.3 mass%, magnesium in an amount of 0.5 mass% to 1.2 mass%, iron in an amount of 0.3 mass% to 0.8 mass%, copper in an amount of 0.1 mass% to 0.4 mass%, manganese in an amount of 0.2 mass% to 0.5 mass%, chromium in an amount of more than 0 mass% and 0.3 mass% or less, and titanium in an amount of 0.001 mass% to 0.1 mass%, with the balance consisting of aluminum and inevitable impurities.
  • the aluminum alloy may further include zirconium in an amount of 0.001 mass% to 0.2 mass%.
  • the aluminum alloy tends to have a higher tensile strength.
  • the aluminum alloy according to (2) above may have the composition including silicon in an amount of 0.6 mass% to 1.5 mass%, magnesium in an amount of 0.7 mass% to 1.3 mass%, iron in an amount of 0.02 mass% to 0.4 mass%, copper in an amount of 0.5 mass% to 1.2 mass%, manganese in an amount of 0.5 mass% to 1.1 mass%, chromium in an amount of more than 0 mass% and 0.3 mass% or less, zinc in an amount of 0.005 mass% to 0.5 mass%, titanium in an amount of 0.01 mass% to 0.2 mass%, and zirconium in an amount of 0.05 mass% to 0.2 mass%, with the balance consisting of aluminum and inevitable impurities.
  • the aluminum alloy tends to have a higher tensile strength.
  • the aluminum alloy of the present disclosure may have a tensile strength of more than 425 MPa in a state of having been subjected to solution treatment and aging treatment.
  • the aluminum alloy has a high tensile strength and thus has a high-strength.
  • An aluminum alloy wire according to an embodiment of the present disclosure is composed of the aluminum alloy according to any one of (1) to (5) above.
  • the aluminum alloy wire of the present disclosure is composed of the aluminum alloy of the present disclosure, it has high-strength in a state of having been subjected to solution treatment and aging treatment.
  • the aluminum alloy wire of the present disclosure can be used as a raw material for a high-strength aluminum alloy member.
  • a method of manufacturing an aluminum alloy wire includes performing plastic working on a cast product of an aluminum alloy to manufacture a worked product, the aluminum alloy having a composition including silicon in an amount of 0.6 mass% to 1.5 mass%, magnesium in an amount of 0.5 mass% to 1.3 mass%, copper in an amount of 0.1 mass% to 1.2 mass%, and manganese in an amount of 0.2 mass% to 1.15 mass%, with the balance consisting of aluminum and inevitable impurities, performing first drawing on the worked product under cold conditions to manufacture a first drawn product, performing softening treatment on the first drawn product to manufacture a softened product, and performing second drawing on the softened product under cold conditions to manufacture a second drawn product.
  • the degree of working in the second drawing is 20% or more and is also higher than the degree of working in the first drawing.
  • a high-strength aluminum alloy wire can be manufactured in a state of having been subjected to solution treatment and aging treatment. The reason will be described later.
  • the aluminum alloy may further include at least one element selected from the group consisting of iron, chromium, zinc, titanium, and zirconium.
  • a content ratio of iron is more than 0 mass% and 0.8 mass% or less.
  • a content ratio of chromium is more than 0 mass% and 0.35 mass% or less.
  • a content ratio of zinc is more than 0 mass% and 0.5 mass% or less.
  • a content ratio of titanium is more than 0 mass% and 0.2 mass% or less.
  • a content ratio of zirconium is more than 0 mass% and 0.2 mass% or less.
  • an aluminum alloy wire having higher tensile strength can be manufactured.
  • the aluminum alloy of the embodiment has the following composition and the following sectional structure.
  • the composition of the aluminum alloy of the embodiment includes silicon, magnesium, copper, and manganese in the ranges described below, respectively, and the balance consisting of aluminum and inevitable impurities.
  • the aluminum alloy of the embodiment may further include at least one element selected from the group consisting of iron, chromium, zinc, titanium, and zirconium in the range described below.
  • the 111 plane of the crystal grains is oriented in the normal direction of the section in a state of having been subjected to solution treatment and aging treatment.
  • the 111 plane is oriented in the normal direction of the section.
  • Silicon, magnesium, copper and manganese are collectively referred to as a first element.
  • Iron, chromium, zinc, titanium, and zirconium are collectively referred to as a second element.
  • Si means silicon.
  • Mg means magnesium.
  • Cu means copper.
  • Mn means manganese.
  • Al means aluminum.
  • Fe means iron.
  • Cr means chromium.
  • Zn means zinc.
  • Ti means titanium.
  • Zr means zirconium.
  • An aluminum alloy in a state of having been subjected to solution treatment and aging treatment is referred to as a state after heat treatment.
  • the first element is an essential element
  • the second element is an optional element.
  • the aluminum alloy of the embodiment has a composition including silicon in an amount of 0.6 mass% to 1.5 mass%, magnesium in an amount of 0.5 mass% to 1.3 mass%, copper in an amount of 0.1 mass% to 1.2 mass%, manganese in an amount of 0.2 mass% to 1.15 mass%, iron in an amount of 0 mass% to 0.8 mass%, chromium in an amount of 0 mass% to 0.35 mass%, zinc in an amount of 0 mass% to 0.5 mass%, titanium in an amount of 0 mass% to 0.2 mass% and zirconium in an amount of 0 mass% to 0.2 mass% with the balance consisting of aluminum and inevitable impurities.
  • the content ratio of iron in the aluminum alloy of the embodiment including at least one second element is more than 0 mass% and 0.8 mass% or less.
  • the content ratio of chromium is more than 0 mass% and 0.35 mass% or less.
  • the content ratio of zinc is more than 0 mass% and 0.5 mass% or less.
  • the content ratio of titanium is more than 0 mass% and 0.2 mass% or less.
  • the content ratio of zirconium is more than 0 mass% and 0.2 mass% or less.
  • the content ratio of the first element is equal to or more than the above-described lower limit value, a compound or the like containing the first element is precipitated in a state after the heat treatment.
  • the precipitates of the compounds or the like are present in a dispersed manner, an effect of improving strength due to precipitation hardening can be obtained.
  • a part of the first element forms a solid solution in aluminum which is a main component of the matrix phase, an effect of improving strength by solid solution strengthening can also be obtained.
  • the content ratio of the first element is equal to or less than the upper limit value described above, grain boundary embrittlement due to segregation of the first element is suppressed, or a compound or the like containing the first element is unlikely to become coarse.
  • the coarse particles of the compound or the like can be the starting point of cracking. When the amount of the coarse particles is small, cracks caused by the coarse particles are less likely to occur. From these points of view, the aluminum alloy of the embodiment has a high tensile strength in a state after heat treatment. Since cracks caused by the coarse particles hardly occur in the manufacturing process, plastic working under cold conditions such as drawing under cold conditions can be favorably performed. From this point of view, the aluminum alloy of the embodiment is also excellent in manufacturability.
  • the second element When the second element is contained in addition to the first element, at least one effect selected from the group consisting of precipitation hardening, solid solution strengthening, suppression of grain boundary embrittlement, and suppression of coarsening of crystal grains can be expected. Due to such effects, the aluminum alloy of the embodiment containing the second element in addition to the first element tends to have higher tensile strength in a state after the heat treatment. When the content ratio of the second element satisfies the above-described upper limit range, the compound or the like containing the second element is unlikely to become coarse. In addition, depending on the type of the second element, the cast product can have a fine structure.
  • the aluminum alloy of the embodiment containing the second element in addition to the first element is excellent in workability when plastic working is included in the manufacturing process. Depending on the type of the second element, the casting temperature can be lowered. From these points of view, the aluminum alloy of the embodiment containing the second element in addition to the first element is more excellent in manufacturability.
  • composition containing the second element in addition to the first element include the following first composition, second composition, and third composition.
  • the first composition includes silicon in an amount of 1.0 mass% to 1.3 mass%, magnesium in an amount of 0.5 mass% to 1.2 mass%, iron in an amount of 0.3 mass% to 0.8 mass%, copper in an amount of 0.1 mass% to 0.4 mass%, manganese in an amount of 0.2 mass% to 0.5 mass%, chromium in an amount of more than 0 mass% and 0.3 mass% or less, titanium in an amount of 0.001 mass% to 0.1 mass%, and zirconium in an amount of 0 mass% to 0.2 mass%, with the balance consisting of aluminum and inevitable impurities.
  • the second composition includes silicon in an amount of 0.6 mass% to 1.5 mass%, magnesium in an amount of 0.7 mass% to 1.3 mass%, iron in an amount of 0.02 mass% to 0.4 mass%, copper in an amount of 0.5 mass% to 1.2 mass%, manganese in an amount of 0.5 mass% to 1.1 mass%, chromium in an amount of more than 0 mass% and 0.3 mass% or less, zinc in an amount of 0.005 mass% to 0.5 mass%, titanium in an amount of 0.01 mass% to 0.2 mass%, and zirconium in an amount of 0.05 mass% to 0.2 mass%, with the balance consisting of aluminum and inevitable impurities.
  • the second composition may further include strontium in an amount of 0.005 mass% to 0.05 mass%.
  • the third composition includes silicon in an amount of 0.9 mass% to 1.3 mass%, magnesium in an amount of 0.8 mass% to 1.2 mass%, iron in an amount of more than 0 mass% and 0.4 mass% or less, copper in an amount of 0.65 mass% to 1.1 mass%, manganese in an amount of 0.55 mass% to 1.15 mass%, chromium in an amount of more than 0 mass% and 0.35 mass% or less, zinc in an amount of 0.12 mass% to 0.25 mass%, titanium in an amount of more than 0 mass% and 0.075 mass% or less, and zirconium in an amount of 0.05 mass% to 0.17 mass%, with the balance consisting of aluminum and inevitable impurities.
  • the third composition generally corresponds to the composition of the alloy indicated by the International Alloy Designation A6056.
  • the content range of the first element and the content range of the second element in the first composition, the second composition, and the third composition will be exemplified.
  • the content ratio of silicon may be more than 1.0 mass% and 1.3 mass% or less, or may be 1.1 mass% to 1.3 mass%.
  • the content ratio of magnesium may be 0.6 mass% to 1.1 mass%, or may be 0.7 mass% to 1.0 mass%.
  • the content ratio of iron may be 0.3 mass% to 0.7 mass%, or may be 0.3 mass% to 0.6 mass%.
  • the content ratio of copper may be 0.2 mass% to 0.4 mass%.
  • the content ratio of manganese may be 0.2 mass% to 0.4 mass%, or may be 0.2 mass% to 0.3 mass%.
  • the content ratio of chromium may be 0.005 mass% to 0.20 mass%, or may be 0.01 mass% to 0.10 mass%.
  • the content ratio of titanium may be 0.005 mass% to 0.05 mass%, or may be 0.01 mass% to 0.05 mass%.
  • the content ratio of zirconium may be 0.001 mass% to 0.20 mass%, or may be 0.005 mass% to 0.10 mass%.
  • the total content ratio of titanium and zirconium may be 0.01 mass% to 0.10 mass%.
  • the content ratio of silicon may be 0.8 mass% to 1.4 mass%, or may be 1.1 mass% to 1.3 mass%.
  • the content ratio of magnesium may be 0.8 mass% to 1.3 mass%, or may be 0.8 mass% to 1.0 mass%.
  • the content ratio of iron may be 0.05 mass% to 0.40 mass%.
  • the content ratio of copper may be 0.8 mass% to 1.2 mass%.
  • the content ratio of manganese may be 0.7 mass% to 1.1 mass%.
  • the content ratio of chromium may be 0.01 mass% to 0.30 mass%, or may be 0.05 mass% to 0.30 mass%.
  • the content ratio of zinc may be 0.05 mass% to 0.25 mass%.
  • the content ratio of titanium may be 0.01 mass% to 0.15 mass%.
  • the content ratio of zirconium may be 0.08 mass% to 0.2 mass%.
  • the total content ratio of titanium and zirconium may be 0.10 mass% to 0.20 mass%.
  • strontium When strontium is included, the content ratio of strontium may be 0.005 mass% to 0.04 mass%.
  • the content ratio of silicon may be 0.9 mass% to 1.2 mass%.
  • the content ratio of magnesium may be 0.8 mass% to 1.0 mass%.
  • the content ratio of iron may be 0.10 mass% to 0.25 mass%.
  • the content ratio of copper may be 0.65 mass% to 0.85 mass%.
  • the content ratio of manganese may be 0.55 mass% to 0.80 mass%, or may be 0.55 mass% to 0.65 mass%.
  • the content ratio of chromium may be 0.01 mass% to 0.10 mass%, or may be 0.02 mass% to 0.05 mass%.
  • the content ratio of zinc may be 0.13 mass% to 0.25 mass%.
  • the content ratio of titanium may be 0.001 mass% to 0.075 mass%, or may be 0.01 mass% to 0.075 mass%.
  • the content ratio of zirconium may be 0.10 mass% to 0.17 mass%.
  • the total content ratio of titanium and zirconium may be 0.11 mass% to 0.20 mass%.
  • the aluminum alloy of the embodiment may further include boron in a range of 50 ppm by mass or less.
  • an aluminum alloy having a high tensile strength in a state after heat treatment preferably has the following structure.
  • a 111 plane of crystal grains is preferably more oriented than other crystal planes in the crystal grains. That is, most of the crystal grains constituting the section of the aluminum alloy are preferably oriented in the 111 plane.
  • an average of a degrees of orientation of a 111 plane determined by X-ray diffraction of a whole area of a section in a state after the heat treatment is 50% or more. Further, a variance of the degrees of orientation of the 111 plane is 45% or less.
  • the 111 plane When the average of the degrees of orientation of the 111 plane is 50% or more, the 111 plane is oriented in the normal direction of the section in half or more of the crystal grains constituting the section of the aluminum alloy. When the variance of the degrees of orientation of the 111 plane is 45% or less, the distribution of the oriented crystal planes among the crystal grains constituting the section of the aluminum alloy is a distribution concentrated on the 111 plane.
  • the aluminum alloy of such an embodiment has a high orientation of the 111 plane of crystal grains. In general, the tensile strength of an aluminum alloy tends to increase as the orientation of the 111 plane of crystal grains increases. Therefore, the aluminum alloy of the embodiment has high tensile strength in a state after heat treatment.
  • the average of the degrees of orientation of the 111 plane increases or as the variance of the degrees of orientation of the 111 plane decreases, the tensile strength tends to increase. From the viewpoint of improving the strength, the average of the degrees of orientation of the 111 plane may be 55% or more, or even 60% or more. The variance of the degrees of orientation of the 111 plane may be 40% or less, or even 38% or less.
  • the average of the degrees of orientation of the 111 plane is 50% to 100%.
  • the variance of the degrees of orientation of the 111 plane is more than 0% and 45% or less. In consideration of manufacturability, the average of the degrees of orientation of the 111 plane may be 99% or less, and the variance of the degrees of orientation of the 111 plane may be 1% or more.
  • the orientation of the 111 plane of the crystal grains is evaluated not in a part of the section but in the whole area of the section.
  • the aluminum alloy of the embodiment reliably has a higher strength structure in a state after heat treatment than that when only a portion of the section was evaluated.
  • a section to be measured for the degrees of orientation of the 111 plane is a section cut along a plane perpendicular to the longitudinal direction at an arbitrary position in the longitudinal direction of the wire.
  • a section taken along a plane perpendicular to the longitudinal direction of the wire composed of the aluminum alloy of the embodiment, that is, an aluminum alloy wire 1 of the embodiment may be referred to as cross section.
  • the 111 plane of the crystal grains is more oriented than the other crystal planes in the whole area of each cross section as described above.
  • the orientation direction of the 111 plane in each cross section is the normal direction of the cross section, i.e. the direction along the longitudinal direction of the wire. Such a wire is hardly broken even if it is pulled with the longitudinal direction of the wire as a pulling direction.
  • the average of the degrees of orientation of the 111 plane is 50% or more and the variance of the degrees of orientation of the 111 plane is 45% or less. That is, it is considered that the orientation of the 111 plane of the crystal grains does not substantially change before and after aging treatment.
  • the aluminum alloy of the embodiment have a tensile strength of more than 425 MPa at room temperature in a state after heat treatment, for example.
  • the room temperature is 5°C to 35°C.
  • the aluminum alloy of the embodiment having a tensile strength of more than 425 MPa have excellent strength.
  • the aluminum alloy of embodiment having a tensile strength of more than 427 MPa, 430 MPa or more, or even 440 MPa or more are more excellent in strength.
  • the aluminum alloy of embodiment has high tensile strength of 450 MPa or more, 460 MPa or more, or even 470 MPa or more.
  • the upper limit of the tensile strength is not particularly limited. In consideration of manufacturability, the tensile strength at room temperature may be more than 425 MPa and 550 MPa or less, for example.
  • the aluminum alloy of the embodiment can have various shapes.
  • the aluminum alloy of the embodiment has a somewhat elongated shape.
  • the aluminum alloy of such an embodiment has an end face consisting of a plane perpendicular to its longitudinal direction and a drawn portion extending in the longitudinal direction.
  • the length of the drawn portion along the longitudinal direction is longer than the diameter of a circle having an area equal to the area of the outer peripheral contour of the end face.
  • the section to be measured for the degrees of orientation of the 111 plane is obtained by cutting the drawn portion along a plane perpendicular to the longitudinal direction.
  • the aluminum alloy in the embodiment having the drawn portion are, for example, wire, pipe, plate, etc. That is, the drawn portion may be a solid body such as a wire or a plate, or a hollow body such as a pipe.
  • Aluminum alloy wire 1 of the embodiment is composed of the aluminum alloy of the embodiment. As shown in FIG. 1 , aluminum alloy wire 1 of the embodiment includes an end face 10 and a drawn portion 11. Here, end face 10 is a surface perpendicular to the longitudinal direction of aluminum alloy wire 1. Drawn portion 11 extends in the longitudinal direction. Aluminum alloy wire 1 of the embodiment typically has the same outer peripheral contour and the same wire diameter over the entire length of drawn portion 11 as shown in FIG. 1 . Here, the wire diameter is the diameter of a circle having the same area as the area of end face 10 or the area of a section cut along a plane perpendicular to the longitudinal direction. FIG.
  • the outer peripheral contour of end face 10 and the outer peripheral contour of an arbitrary section cut along a plane perpendicular to the longitudinal direction are circular.
  • the outer peripheral contour of end face 10 and the outer peripheral contour of the section may be polygonal shapes such as squares, or may be curved shapes such as ellipses.
  • the wire diameter of aluminum alloy wire 1 of the embodiment is not particularly limited. The wire diameter is, for example, about 3 mm to 15 mm.
  • a section to be measured for the degrees of orientation of the 111 plane is the cross section.
  • an average of the degrees of orientation of the 111 plane determined by X-ray diffraction of the whole area of the cross section is 50% or more. Further, a variance of the degrees of orientation of the 111 plane is 45% or less.
  • such cross sections are arranged in the longitudinal direction. Aluminum alloy wire 1 of such an embodiment has a high tensile strength of more than 425 MPa in a state after heat treatment.
  • the aluminum alloy of the embodiment can constitute an aluminum alloy member.
  • the aluminum alloy member is composed of the aluminum alloy of the embodiment and is subjected to solution treatment and aging treatment.
  • a specific example is an aluminum alloy member in which plastic working is performed on aluminum alloy wire 1 of the embodiment and then solution treatment and aging treatment are performed thereon.
  • Another example is an aluminum alloy member in which plastic working is performed on a plate composed of the aluminum alloy of the embodiment, and then solution treatment and aging treatment are performed thereon.
  • plastic working is performed so that the section of the aluminum alloy member has the above-described specific orientation after solution treatment and aging treatment.
  • Still another example is an aluminum alloy member in which solution treatment and aging treatment are performed on aluminum alloy wire 1 of the embodiment.
  • the aluminum alloy member may be linear or rod-shaped.
  • the aluminum alloy member may be tubular.
  • the aluminum alloy member is composed of an extruded material obtained by extruding aluminum alloy wire 1 with the longitudinal direction of aluminum alloy wire 1 of the embodiment as the extrusion direction.
  • the aluminum alloy member extends along the extrusion direction.
  • the section to be measured for the degrees of orientation of the 111 plane is obtained by cutting the aluminum alloy member along a plane perpendicular to the extrusion direction.
  • the average of the degrees of orientation of the 111 plane determined by X-ray diffraction of the whole area of the section is 50% or more. Further, a variance of the degrees of orientation of the 111 plane is 45% or less.
  • the above-described aluminum alloy member has high-strength because it is composed of an aluminum alloy having the above-described specific composition and the above-described specific structure.
  • the aluminum alloy member is lighter than a metal member composed of an iron-based alloy such as steel.
  • Such an aluminum alloy member can be used for applications in which light weight and high-strength are desired, such as automobile parts and various structural members.
  • the inventors have studied a method of manufacturing an aluminum alloy having the above-described specific composition and having excellent strength in a state of having been subjected to solution treatment and aging treatment. As a result, the inventors have found that the plastic working performed just before solution treatment is preferably a cold working and a large degree of working. Based on this finding, when the aluminum alloy of the embodiment is manufactured, for example, the following method of manufacturing an aluminum alloy can be used.
  • the method of manufacturing the aluminum alloy includes performing a cold working on a material composed of the aluminum alloy to manufacture a cold worked product.
  • the aluminum alloy has a composition including the above-described first element in the above-described range with the balance consisting of aluminum and inevitable impurities.
  • the material is the worked product which has been subjected to a first plastic working.
  • the cold working is a second plastic working with a degree of working of 20% or more.
  • the aluminum alloy may have a composition including the second element in addition to the first element in the above-described range.
  • the above-described aluminum alloy material is a cast product subjected to first plastic working.
  • the first plastic working is, for example, a rolling process.
  • the first plastic working is, for example, hot working.
  • the material described above can be subjected to a softening treatment under the following conditions.
  • the softening treatment performed to the material may be referred to as an initial softening treatment.
  • the heating temperature is a temperature selected from a range of equal to or more than 250°C and less than 500°C.
  • the holding time is a time selected from a range of 1 hour to 100 hours.
  • the atmosphere during softening is, for example, an air atmosphere or a non-oxidizing atmosphere.
  • the non-oxidizing atmosphere is, for example, a reduced-pressure atmosphere, an inert gas atmosphere, or a reducing gas atmosphere, etc.
  • the heating temperature may be 300°C to 480°C, or even 300°C to 460°C.
  • the plastic workability of the aluminum alloy after the initial softening treatment is enhanced. Therefore, the degree of working of the second plastic working can be increased.
  • the dislocations introduced by the first plastic working are accumulated in the aluminum alloy. As a result, it is easy to obtain an aluminum alloy in which many dislocations are accumulated.
  • the second plastic working performed to the material is a cold working as described above.
  • the second plastic working is, for example, drawing, rolling, extrusion, etc.
  • drawing a wire is obtained.
  • rolling typically, a plate is obtained.
  • extrusion a wire, a plate, a pipe or the like can be obtained depending on the shape of an extrusion die.
  • the degree of working of the second plastic working is larger, the orientation of the 111 plane is increased.
  • the degree of working of the second plastic working may be 30% or more, 40% or more, or 60% or more.
  • the degree of working is a ratio obtained by dividing the difference between the sectional area before the second plastic working and the sectional area after the second plastic working by the sectional area before the second plastic working.
  • a softening treatment can be performed during the second plastic working.
  • the softening treatment performed during the second plastic working may be referred to as an intermediate softening treatment.
  • the conditions of the intermediate softening treatment may refer to the conditions of the initial softening treatment described above.
  • the degree of working in the cold working after the intermediate softening treatment is preferably larger than the degree of working in the cold working before the intermediate softening treatment.
  • the degree of working in cold working after the intermediate softening treatment may be 30% or more, 40% or more, even 60% or more.
  • the method of manufacturing the aluminum alloy wire of the embodiment includes the following first step, second step, third step, and fourth step.
  • Drawing is carried out under cold conditions. During the drawing, a softening treatment is performed.
  • the degree of working of the drawing after the softening treatment is 20% or more and is more than the degree of working of the drawing before the softening treatment.
  • the first step is a step of performing plastic working on a cast product of an aluminum alloy containing the above-described first element in the above-described range and the balance consisting of aluminum and inevitable impurities to manufacture a worked product.
  • the aluminum alloy constituting the cast product may further include a second element in the range described above.
  • the second step is a step of performing first drawing on the worked product under cold conditions to manufacture a first drawn product.
  • the third step is a step of performing softening treatment on the first drawn product to manufacture a softened product.
  • the fourth step is a step of performing second drawing on the softened product under cold conditions to manufacture a second drawn product.
  • the degree of working in the second drawing is 20% or more.
  • the degree of working in the second drawing is more than the degree of working in the first drawing.
  • the plastic working of the first step corresponds to the first plastic working described above.
  • the softening treatment of the third step corresponds to the intermediate softening treatment described above.
  • the first drawing and the second drawing correspond to the second plastic working described above.
  • the cast product is manufactured using, for example, a mold casting method, a continuous casting method, or the like.
  • the plastic working is, for example, hot rolling
  • the worked product is, for example, a continuous-casted rolled product.
  • a continuous long aluminum alloy wire can be manufactured.
  • aluminum alloy wire 1 of the embodiment can be mass-manufactured when the worked product is a continuous-casted rolled product.
  • the worked product may be subjected to the initial softening treatment as described above.
  • the initial softening treatment is performed, the degree of working of the subsequent first drawing can be increased as described above.
  • the initial softening treatment is not performed, the aluminum alloy wire in which many dislocations are finally accumulated is likely to be obtained as described above.
  • the degree of working of the first drawing is preferably 30% or more.
  • the degree of working of the first drawing may be 35% or more, or 40% or more.
  • the degree of working of the first drawing depends on the final wire diameter, but is selected from a range of 30% to 80%, for example.
  • the degree of working of the first drawing is a ratio obtained by dividing the difference between the sectional area before the first drawing and the sectional area after the first drawing by the sectional area before the first drawing.
  • the conditions of the softening treatment in the third step may refer to the conditions of the initial softening treatment described above.
  • the processability of the softened product after the softening treatment is enhanced. Therefore, the degree of working of the second drawing in the fourth step can be increased.
  • the degree of working of the second drawing in the fourth step can be larger than the degree of working of the first drawing in the second step. As a result, dislocations can be accumulated in the aluminum alloy by the second drawing.
  • the degree of working of the second drawing in the fourth step is larger, the orientation of the 111 plane is enhanced.
  • the degree of working of the second drawing is 20% or more, an aluminum alloy wire in which many dislocations are finally accumulated can be easily obtained.
  • the degree of working of the second drawing is larger than the degree of working of the first drawing, an aluminum alloy wire in which many dislocations are finally accumulated is likely to be obtained.
  • the degree of working of the first drawing is preferably 30% or more as described above, the degree of working of the second drawing may be more than 30%, 40% or more, or even 60% or more.
  • the degree of working of the second drawing is selected from a range of 20% to 99.9% so as to obtain a second drawn product having a predetermined final wire diameter.
  • the degree of working of the second drawing is a ratio obtained by dividing the difference between the sectional area before the second drawing and the sectional area after the second drawing by the sectional area before the second drawing.
  • a method of manufacturing the above-described aluminum alloy member includes, for example, the following working step and heat treatment step.
  • the working step is a step of performing a third plastic working on the above-described second plastic working material subjected to the above-described second plastic working or the above-described second drawn product to manufacture a third worked product.
  • the heat treatment step is a step of sequentially performing a solution treatment and an aging treatment on the third worked product to manufacture an aged material.
  • the third plastic working is, for example, extrusion, forging, drawing, etc.
  • the conditions of solution treatment and aging treatment are as described above.
  • the aluminum alloy of the embodiment and aluminum alloy wire 1 of the embodiment have high tensile strength in a state of having been subjected to solution treatment and aging treatment.
  • aluminum alloy wire 1 of the embodiment is taken as an example to describe the above effect in detail.
  • aluminum alloy wire 1 of the embodiment having high tensile strength in a state of having been subjected to solution treatment and aging treatment can be manufactured.
  • the aluminum alloy wire having the composition shown in Table 1 was subjected to solution treatment and aging treatment, and the structure thereof was observed and the tensile strength thereof was measured.
  • the manufacturing conditions of the aluminum alloy wire and the examination results are shown in Tables 2 to 4.
  • COMPONENT (MASS%) Si Mg Fe Cu Mn Cr Zn Zr+Ti Ba I .
  • the aluminium alloy wire of each sample is basically manufactured by performing drawing on a continuous-casted rolled product under cold conditions.
  • the continuous-casted rolled product can be manufactured with, for example, a known Properzi type continuous casting/rolling apparatus.
  • the softening treatment is performed during the drawing except for some samples among the samples.
  • the first composition, the second composition, and the third composition in the item of the composition correspond to the first composition, the second composition, and the third composition shown in Table 1, respectively.
  • the item of softening treatment indicates the heating temperature (°C) and the holding time (hours).
  • “380°C ⁇ 10h” means that the heating temperature is 380°C and the holding time is 10 hours.
  • the samples whose conditions are described in three items of the degree of working (%) of the first drawing, the softening treatment, and the degree of working (%) of the second drawing in Tables 2 to 4 will be described.
  • the aluminum alloy wires of these samples are manufactured by sequentially performing first drawing under cold conditions, softening treatment, and second drawing under cold conditions on a continuous-casted rolled product.
  • the aluminum alloy wires of these samples are not subjected to the initial softening treatment.
  • Tables 2 to 4 the samples in which a hyphen "-" is described in the degree of working (%) of the first drawing and conditions are described in two items of the softening treatment and the degree of working (%) of the second drawing will be described.
  • the aluminum alloy wires of these samples were manufactured by subjecting a continuous-casted rolled product to a softening treatment and then to the drawing under cold conditions at the degree of working (%) of the second drawing.
  • the aluminum alloy wires of these samples were continuously subjected to the drawing under cold condition after the initial softening treatment of the continuous-casted rolled product, and were not subjected to the intermediate softening treatment.
  • Table 2 to Table 4 samples in which conditions are described in two items of the degree of working (%) of the first drawing and the degree of working (%) of the second drawing, and a hyphen "-" is described in the softening treatment will be described.
  • the aluminum alloy wires of these samples are manufactured by subjecting a continuous-casted rolled product to the drawing under cold conditions at the degree of working (%) of the first drawing and then to the drawing under cold conditions at the degree of working (%) of the second drawing without the intermediate softening treatment. That is, the aluminum alloy wires of these samples are continuously subjected to drawing under cold condition on the continuous-casted rolled product, and are not subjected to both the initial softening treatment and the intermediate softening treatment.
  • the total degree of working in this cold drawing is larger than the degree of working listed in the item of degree of working (%) of the second drawing in Tables 2-4.
  • the wire diameter of the continuous-casted rolled product is selected from a range of 5 mm to 30 mm.
  • the wire diameter of the second drawn product manufactured after the second drawing is a value selected from a range of about 1.0 mm to 21 mm according to the degree of working.
  • the obtained aluminum alloy wire of each sample was subjected to solution treatment and aging treatment under the above-described conditions to manufacture a heat-treated wire.
  • the obtained heat-treated wire is cut along a plane perpendicular to the longitudinal direction of the heat-treated wire to obtain a disk-shaped sample.
  • the sample has two circular cross sections.
  • the whole area of one of the two cross sections is smoothed by mechanical polishing.
  • the surface roughness of the cross section after polishing is about 0.2 ⁇ m in terms of arithmetic mean roughness Ra.
  • 2000 water-resistant paper can be used for the mechanical polishing.
  • the whole area of the polished cross section is subjected to X-ray diffraction as follows.
  • a sample 3 is arranged on a surface 51f consisting of a flat plane provided on a movable stage 51. This arrangement is performed so that a cross section 30 of sample 3, which has been mechanically polished as described above, is parallel to surface 51f and cross section 30 is irradiated with an X-ray 6 from a predetermined direction D.
  • Predetermined direction D is a direction corresponding to a predetermined plane index F.
  • Predetermined plane index F is a crystal plane specified by the Miller index.
  • plane index F is any one crystal plane of three crystal planes of the 111 plane, 200 plane, and 220 plane.
  • X-ray 6 from an X-ray source (not shown) and a diffracted X-ray 60 are indicated by dashed lines.
  • X-ray 60 diffracted from cross section 30 is detected by a detector 52.
  • the detection of X-ray 60 is repeated while moving sample 3 two dimensionally in a plane parallel to cross section 30 with movable stage 51 so that the whole area of cross section 30 is measured.
  • the distribution of the diffraction intensity in the whole area of cross section 30 is obtained.
  • an arithmetic unit 53 described later is set so as to exclude the diffraction intensity from the position where cross section 30 does not exist.
  • Angle ⁇ is an angle formed by plane index F and X-ray 6.
  • Angle 2 ⁇ is an angle formed by predetermined direction D and diffracted X-ray 60.
  • a value obtained by normalizing each diffraction intensity is calculated by using a theoretical value based on a predetermined direction D.
  • the normalized value is a value obtained by dividing each diffraction intensity by the theoretical value of the peak intensity of the diffraction intensity of X-ray diffraction.
  • a normalized distribution is calculated from the distribution of each diffraction intensity. That is, the normalized distribution of the 111 plane, the normalized distribution of the 200 plane, and the normalized distribution of the 220 plane are calculated.
  • the theoretical value may be acquired from a database of Powder Diffraction File (PDF) published by International Centre for Diffraction Data (ICDD).
  • PDF Powder Diffraction File
  • ICDD International Centre for Diffraction Data
  • the X-ray profile data at each measurement point may be fitted and the maximum value or the integral value of the fitting curve may be used as the peak intensity.
  • the fitting function used for the fitting is, for example, a Lorentz function or a Gauss function.
  • a value obtained by normalizing the diffraction intensity of the 111 plane, a value obtained by normalizing the diffraction intensity of the 200 plane, and a value obtained by normalizing the diffraction intensity of the 220 plane are obtained. Further, the sum of these three normalized values is obtained. Further, the ratio of the value obtained by normalizing the diffraction intensity of the 111 plane to the sum of value is obtained. This ratio is the degree of orientation of the 111 plane.
  • the average of the degrees of orientation of the 111 plane is a value obtained by averaging the degrees of orientation of the 111 plane at all the measurement points. The variance of the degrees of orientation of the 111 plane is obtained from the averaged value.
  • X-ray 6 for example, a BL16 existing in a radiation light facility SAGA-LS can be used.
  • 0.5 mm square can be used as the slit width.
  • detector 52 for example, a commercially available two dimensional detector such as PILATUS 100K manufactured by Dectris can be used. The distance from cross section 30 of sample 3 to the two dimensional detector is 0.512 m.
  • a commercially available computer can be used as arithmetic unit 53.
  • Angle ⁇ , 2 ⁇ is selected according to the wavelength described above. Angle ⁇ , 2 ⁇ is, for example, the following value when ⁇ is 0.0919 nm.
  • predetermined plane index F is the 111 plane
  • 11.3 degrees is used as angle ⁇ formed by the 111 plane of sample 3 and X-ray 6.
  • 22.6 degrees is used as angle 2 ⁇ formed by predetermined direction D and diffracted X-ray 60.
  • FIG. 6 shows ⁇ and 2 ⁇ , which are larger than the actual values.
  • predetermined plane index F is the 200 plane
  • 13 degrees is used as angle ⁇ formed by the 200 plane of sample 3 and X-ray 6.
  • 26 degrees is used as angle 2 ⁇ formed by predetermined direction D and diffracted X-ray 60.
  • the predetermined plane index is the 220 plane
  • 18.6 degrees is used as angle ⁇ formed by the 220 plane of sample 3 and X-ray 6.
  • 37.2 degrees is used as angle 2 ⁇ between predetermined direction D and diffracted X-ray 60.
  • the tensile strength (MPa) is measured in accordance with JIS Z 2241:2011. Here, the tensile strength at room temperature is measured.
  • the composition of the obtained aluminum alloy wire of each sample is the same as the composition shown in Table 1. That is, the aluminum alloy constituting the aluminum alloy wire of each sample includes the elements shown in Table 1 in the range shown in Table 1, with the balance consisting of Al and inevitable impurities.
  • a known method can be used to analyze the composition of the aluminum alloy wire. For example, an energy variance type X-ray analyzer or the like can be used for the analysis of the composition.
  • sample Nos. 1 to 9, sample Nos. 11 to 19, and sample Nos. 21 to 29 may be collectively referred to as a first sample group.
  • Sample Nos. 101 to 104 may be collectively referred to as a second sample group.
  • the aluminum alloy wires of the first sample group have higher tensile strength than the aluminum alloy wires of the second sample group. Quantitatively, the aluminum alloy wires of the first sample group have tensile strength more than 425 MPa. Many samples have tensile strength equal to or more than 440 MPa. Depending on the composition, some samples have tensile strength equal to or more than 470 MPa.
  • the average of the degrees of orientation of the 111 plane is larger and the variance of the degrees of orientation of the 111 plane is smaller than those of the aluminum alloy wires of the second sample group.
  • the average of the degrees of orientation of the 111 plane is 50% or more, and the variance of the degrees of orientation of the 111 plane is 45% or less.
  • the average of the degrees of orientation of the 111 plane is 60% or more, and the variance of the degrees of orientation of the 111 plane is 35% or less.
  • the average of the degrees of orientation of the 111 plane is 70% or more and the variance of the degrees of orientation of the 111 plane is 30% or less. This is shown visually with reference to FIGS. 2 to 5 .
  • FIGS. 2 and 3 show the distribution of the degrees of orientation of the 111 plane for the aluminum alloy wire of sample No. 3.
  • FIGS. 4 and 5 show the distribution of the degrees of orientation of the 111 plane for the aluminum alloy wire of sample No. 1.
  • FIG. 2 and FIG. 4 are diagrams in which the degree of orientation of the 111 plane for each measurement point is converted into gray scale shading in the whole area of the cross section of the aluminum alloy wire. The bars shown on the right side of FIG. 2 and on the right side of FIG. 4 indicate shading according to the number of counts.
  • the degree of orientation of the 111 plane of each measurement point is converted into the number of counts from 0 to 100, for example. Black means that the number of count is 0. White means that the number of count is 100.
  • the degree of orientation of the 111 plane increases, the number of counts increases, that is, the color becomes closer to white.
  • FIGS. 3 and 5 show the distribution of the degrees of orientation of the 111 plane by contour lines. Each contour line connects measurement points having the same degrees of orientation of the 111 plane.
  • FIG. 2 and FIG. 4 show the following four contours lines.
  • the thin solid line is a contour line connecting measurement points at which the degree of orientation of the 111 plane is 20%.
  • the thin dashed line is a contour line connecting measurement points at which the degree of orientation of the 111 plane is 40%.
  • a thin dotted line is a contour line connecting measurement points at which the degree of orientation of the 111 plane is 60%.
  • a thick solid line is a contour line connecting measurement points at which the degree of orientation of the 111 plane is 80%.
  • the variation is small is supported by the fact that, as shown in FIG. 3 , the regions surrounded by the four types of contour lines draw substantially the same shape.
  • the 111 plane is uniformly oriented in the normal direction of the cross section over the whole area of the cross section. It is considered that the aluminum alloy wire of sample No. 3 has a high tensile strength due to the structure in which the 111 plane is oriented.
  • this test shows the following. (1) The aluminum alloy wire having the first composition and the second composition tends to have a larger average of the degrees of orientation of the 111 plane and a smaller variance of the degrees of orientation of the 111 plane than the aluminum alloy wire having the third composition. From this point of view, the aluminum alloy wire having the first composition and the second composition has higher strength.
  • the aluminum alloy wire in which the average of the degrees of orientation of the 111 plane in a state of having been subjected to solution treatment and aging treatment is large and the variance of the degrees of orientation of the 111 plane is small can be manufactured with the manufacturing method that satisfies the above-described ⁇ Conditions>.
  • the aluminum alloy wires of the first sample group it is considered that dislocations are accumulated in the state after the second drawing by satisfying the above-described ⁇ Conditions>.
  • the degree of working of the second drawing is smaller than that of the aluminum alloy wires of the first sample group.
  • the degree of working of the second drawing is less than the degree of working of the first drawing or the same as the degree of working of the first drawing. From these facts, it is considered that dislocations are not sufficiently accumulated in the aluminum alloy wires of the second sample group in the state after the second drawing.
  • the present disclosure is not limited to these examples, but is defined by the scope of the claims, and is intended to include all modifications within the meaning and scope equivalent to the scope of the claims.
  • the composition of the aluminum alloy may be changed, or the manufacturing conditions such as the degree of working of drawing and the condition of the softening treatment may be changed.

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EP22810942.7A 2021-05-27 2022-03-15 Aluminiumlegierung, aluminiumlegierungsdraht und verfahren zur herstellung eines aluminiumlegierungsdrahts Pending EP4350020A1 (de)

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