WO2006075814A1 - Wrought magnesium alloy having excellent formability and method of producing same - Google Patents
Wrought magnesium alloy having excellent formability and method of producing same Download PDFInfo
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- WO2006075814A1 WO2006075814A1 PCT/KR2005/000697 KR2005000697W WO2006075814A1 WO 2006075814 A1 WO2006075814 A1 WO 2006075814A1 KR 2005000697 W KR2005000697 W KR 2005000697W WO 2006075814 A1 WO2006075814 A1 WO 2006075814A1
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- magnesium alloy
- wrought magnesium
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- wrought
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- 238000000034 method Methods 0.000 title claims abstract description 44
- 229910000861 Mg alloy Inorganic materials 0.000 title claims abstract description 43
- 238000005096 rolling process Methods 0.000 claims abstract description 36
- 239000011777 magnesium Substances 0.000 claims abstract description 33
- 239000000203 mixture Substances 0.000 claims abstract description 10
- 239000012535 impurity Substances 0.000 claims abstract description 5
- 229910000765 intermetallic Inorganic materials 0.000 claims description 24
- 238000007747 plating Methods 0.000 claims description 21
- 229910052725 zinc Inorganic materials 0.000 claims description 15
- 229910052782 aluminium Inorganic materials 0.000 claims description 8
- 229910052727 yttrium Inorganic materials 0.000 claims description 8
- 229910052796 boron Inorganic materials 0.000 claims description 5
- 229910052793 cadmium Inorganic materials 0.000 claims description 5
- 229910052791 calcium Inorganic materials 0.000 claims description 5
- 229910052710 silicon Inorganic materials 0.000 claims description 4
- 229910052712 strontium Inorganic materials 0.000 claims description 4
- 229910052747 lanthanoid Inorganic materials 0.000 claims description 3
- 150000002602 lanthanoids Chemical class 0.000 claims description 3
- 229910052706 scandium Inorganic materials 0.000 claims description 3
- 229910052726 zirconium Inorganic materials 0.000 claims description 3
- 229910052735 hafnium Inorganic materials 0.000 claims description 2
- 229910052719 titanium Inorganic materials 0.000 claims description 2
- 239000000463 material Substances 0.000 abstract description 25
- 229910052749 magnesium Inorganic materials 0.000 abstract description 23
- FYYHWMGAXLPEAU-UHFFFAOYSA-N Magnesium Chemical compound [Mg] FYYHWMGAXLPEAU-UHFFFAOYSA-N 0.000 abstract description 19
- 238000001125 extrusion Methods 0.000 abstract description 17
- 239000002131 composite material Substances 0.000 abstract description 3
- 239000012071 phase Substances 0.000 description 40
- 239000011159 matrix material Substances 0.000 description 25
- 230000008569 process Effects 0.000 description 25
- 239000011701 zinc Substances 0.000 description 22
- 239000000956 alloy Substances 0.000 description 19
- 230000007797 corrosion Effects 0.000 description 19
- 238000005260 corrosion Methods 0.000 description 19
- 238000000137 annealing Methods 0.000 description 18
- 238000010438 heat treatment Methods 0.000 description 18
- 229910045601 alloy Inorganic materials 0.000 description 17
- 230000005496 eutectics Effects 0.000 description 14
- 230000008018 melting Effects 0.000 description 14
- 238000002844 melting Methods 0.000 description 14
- 230000000694 effects Effects 0.000 description 12
- 239000002245 particle Substances 0.000 description 12
- 239000007789 gas Substances 0.000 description 11
- 239000000047 product Substances 0.000 description 10
- 230000009467 reduction Effects 0.000 description 10
- 238000005266 casting Methods 0.000 description 9
- 238000009792 diffusion process Methods 0.000 description 9
- 230000015572 biosynthetic process Effects 0.000 description 7
- 230000001427 coherent effect Effects 0.000 description 7
- 238000001953 recrystallisation Methods 0.000 description 7
- 230000002787 reinforcement Effects 0.000 description 7
- 239000006104 solid solution Substances 0.000 description 7
- 239000000843 powder Substances 0.000 description 6
- 238000005482 strain hardening Methods 0.000 description 5
- 238000011156 evaluation Methods 0.000 description 4
- 230000000977 initiatory effect Effects 0.000 description 4
- PXHVJJICTQNCMI-UHFFFAOYSA-N nickel Substances [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 description 4
- 230000006911 nucleation Effects 0.000 description 4
- 238000010899 nucleation Methods 0.000 description 4
- 239000013079 quasicrystal Substances 0.000 description 4
- 239000002994 raw material Substances 0.000 description 4
- 239000007787 solid Substances 0.000 description 4
- 238000007711 solidification Methods 0.000 description 4
- 230000008023 solidification Effects 0.000 description 4
- SHCMKWXVHLOSIU-UHFFFAOYSA-N 5-hydroxy-7-(4-hydroxy-2,5-dimethoxyphenyl)-2,2-dimethylpyrano[3,2-g]chromen-6-one Chemical compound C1=C(O)C(OC)=CC(C=2C(C3=C(O)C=4C=CC(C)(C)OC=4C=C3OC=2)=O)=C1OC SHCMKWXVHLOSIU-UHFFFAOYSA-N 0.000 description 3
- -1 AZ31B or AM20 Chemical compound 0.000 description 3
- HCHKCACWOHOZIP-UHFFFAOYSA-N Zinc Chemical compound [Zn] HCHKCACWOHOZIP-UHFFFAOYSA-N 0.000 description 3
- 229910001297 Zn alloy Inorganic materials 0.000 description 3
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 3
- 229910052786 argon Inorganic materials 0.000 description 3
- 238000009713 electroplating Methods 0.000 description 3
- 238000005516 engineering process Methods 0.000 description 3
- 230000005484 gravity Effects 0.000 description 3
- 238000004519 manufacturing process Methods 0.000 description 3
- 239000004033 plastic Substances 0.000 description 3
- 238000003303 reheating Methods 0.000 description 3
- 238000005204 segregation Methods 0.000 description 3
- 239000000126 substance Substances 0.000 description 3
- 239000013585 weight reducing agent Substances 0.000 description 3
- XKRFYHLGVUSROY-UHFFFAOYSA-N Argon Chemical compound [Ar] XKRFYHLGVUSROY-UHFFFAOYSA-N 0.000 description 2
- CURLTUGMZLYLDI-UHFFFAOYSA-N Carbon dioxide Chemical compound O=C=O CURLTUGMZLYLDI-UHFFFAOYSA-N 0.000 description 2
- 229910000968 Chilled casting Inorganic materials 0.000 description 2
- 229910018194 SF 6 Inorganic materials 0.000 description 2
- 229910052768 actinide Inorganic materials 0.000 description 2
- 150000001255 actinides Chemical class 0.000 description 2
- 230000004888 barrier function Effects 0.000 description 2
- AIYUHDOJVYHVIT-UHFFFAOYSA-M caesium chloride Chemical compound [Cl-].[Cs+] AIYUHDOJVYHVIT-UHFFFAOYSA-M 0.000 description 2
- 229910002091 carbon monoxide Inorganic materials 0.000 description 2
- 150000001875 compounds Chemical class 0.000 description 2
- 238000009749 continuous casting Methods 0.000 description 2
- 238000001816 cooling Methods 0.000 description 2
- 239000013078 crystal Substances 0.000 description 2
- 230000007547 defect Effects 0.000 description 2
- 210000001787 dendrite Anatomy 0.000 description 2
- 238000004512 die casting Methods 0.000 description 2
- 238000004090 dissolution Methods 0.000 description 2
- 229910052733 gallium Inorganic materials 0.000 description 2
- 229910052738 indium Inorganic materials 0.000 description 2
- 239000011572 manganese Substances 0.000 description 2
- 229910052751 metal Inorganic materials 0.000 description 2
- 239000002184 metal Substances 0.000 description 2
- 238000005272 metallurgy Methods 0.000 description 2
- 239000011148 porous material Substances 0.000 description 2
- 239000002244 precipitate Substances 0.000 description 2
- 230000002285 radioactive effect Effects 0.000 description 2
- 238000007712 rapid solidification Methods 0.000 description 2
- 229910052761 rare earth metal Inorganic materials 0.000 description 2
- 238000000926 separation method Methods 0.000 description 2
- 239000000243 solution Substances 0.000 description 2
- 229910052716 thallium Inorganic materials 0.000 description 2
- 238000010119 thixomolding Methods 0.000 description 2
- 238000011282 treatment Methods 0.000 description 2
- VYZAMTAEIAYCRO-UHFFFAOYSA-N Chromium Chemical compound [Cr] VYZAMTAEIAYCRO-UHFFFAOYSA-N 0.000 description 1
- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical compound [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 description 1
- 229910052688 Gadolinium Inorganic materials 0.000 description 1
- 239000004677 Nylon Substances 0.000 description 1
- 229910018503 SF6 Inorganic materials 0.000 description 1
- 229910000946 Y alloy Inorganic materials 0.000 description 1
- 230000004913 activation Effects 0.000 description 1
- 238000003483 aging Methods 0.000 description 1
- 230000032683 aging Effects 0.000 description 1
- 239000007864 aqueous solution Substances 0.000 description 1
- 229910052788 barium Inorganic materials 0.000 description 1
- 229910052790 beryllium Inorganic materials 0.000 description 1
- 229910002056 binary alloy Inorganic materials 0.000 description 1
- 238000009937 brining Methods 0.000 description 1
- 229910002092 carbon dioxide Inorganic materials 0.000 description 1
- 239000001569 carbon dioxide Substances 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 239000003795 chemical substances by application Substances 0.000 description 1
- 229910052804 chromium Inorganic materials 0.000 description 1
- 239000011651 chromium Substances 0.000 description 1
- 239000011362 coarse particle Substances 0.000 description 1
- 238000005097 cold rolling Methods 0.000 description 1
- 230000000052 comparative effect Effects 0.000 description 1
- 238000007796 conventional method Methods 0.000 description 1
- 229910052802 copper Inorganic materials 0.000 description 1
- 239000010949 copper Substances 0.000 description 1
- 229910000365 copper sulfate Inorganic materials 0.000 description 1
- ARUVKPQLZAKDPS-UHFFFAOYSA-L copper(II) sulfate Chemical compound [Cu+2].[O-][S+2]([O-])([O-])[O-] ARUVKPQLZAKDPS-UHFFFAOYSA-L 0.000 description 1
- DOBRDRYODQBAMW-UHFFFAOYSA-N copper(i) cyanide Chemical compound [Cu+].N#[C-] DOBRDRYODQBAMW-UHFFFAOYSA-N 0.000 description 1
- 238000005336 cracking Methods 0.000 description 1
- 230000032798 delamination Effects 0.000 description 1
- 239000006185 dispersion Substances 0.000 description 1
- 230000005489 elastic deformation Effects 0.000 description 1
- 238000007772 electroless plating Methods 0.000 description 1
- 230000006355 external stress Effects 0.000 description 1
- 238000005242 forging Methods 0.000 description 1
- 238000005098 hot rolling Methods 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 230000006698 induction Effects 0.000 description 1
- 229910000706 light magnesium alloy Inorganic materials 0.000 description 1
- 239000007788 liquid Substances 0.000 description 1
- 239000007791 liquid phase Substances 0.000 description 1
- 229910052748 manganese Inorganic materials 0.000 description 1
- WPBNNNQJVZRUHP-UHFFFAOYSA-L manganese(2+);methyl n-[[2-(methoxycarbonylcarbamothioylamino)phenyl]carbamothioyl]carbamate;n-[2-(sulfidocarbothioylamino)ethyl]carbamodithioate Chemical compound [Mn+2].[S-]C(=S)NCCNC([S-])=S.COC(=O)NC(=S)NC1=CC=CC=C1NC(=S)NC(=O)OC WPBNNNQJVZRUHP-UHFFFAOYSA-L 0.000 description 1
- 239000000155 melt Substances 0.000 description 1
- 229910052753 mercury Inorganic materials 0.000 description 1
- 229910052759 nickel Inorganic materials 0.000 description 1
- 229920001778 nylon Polymers 0.000 description 1
- 230000003647 oxidation Effects 0.000 description 1
- 238000007254 oxidation reaction Methods 0.000 description 1
- 239000010970 precious metal Substances 0.000 description 1
- 229910052705 radium Inorganic materials 0.000 description 1
- 238000011946 reduction process Methods 0.000 description 1
- 230000029058 respiratory gaseous exchange Effects 0.000 description 1
- 229910052702 rhenium Inorganic materials 0.000 description 1
- 238000007788 roughening Methods 0.000 description 1
- 229920006395 saturated elastomer Polymers 0.000 description 1
- 230000035945 sensitivity Effects 0.000 description 1
- 239000007790 solid phase Substances 0.000 description 1
- 238000005728 strengthening Methods 0.000 description 1
- 230000035882 stress Effects 0.000 description 1
- SFZCNBIFKDRMGX-UHFFFAOYSA-N sulfur hexafluoride Chemical compound FS(F)(F)(F)(F)F SFZCNBIFKDRMGX-UHFFFAOYSA-N 0.000 description 1
- 229960000909 sulfur hexafluoride Drugs 0.000 description 1
- 230000000153 supplemental effect Effects 0.000 description 1
- JBQYATWDVHIOAR-UHFFFAOYSA-N tellanylidenegermanium Chemical compound [Te]=[Ge] JBQYATWDVHIOAR-UHFFFAOYSA-N 0.000 description 1
- 229910002058 ternary alloy Inorganic materials 0.000 description 1
- 231100000331 toxic Toxicity 0.000 description 1
- 230000002588 toxic effect Effects 0.000 description 1
- 239000002341 toxic gas Substances 0.000 description 1
- 230000009466 transformation Effects 0.000 description 1
- 238000009423 ventilation Methods 0.000 description 1
- 230000004580 weight loss Effects 0.000 description 1
Classifications
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C23/00—Alloys based on magnesium
- C22C23/02—Alloys based on magnesium with aluminium as the next major constituent
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C23/00—Alloys based on magnesium
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C23/00—Alloys based on magnesium
- C22C23/06—Alloys based on magnesium with a rare earth metal as the next major constituent
Definitions
- the present invention relates to a wrought magnesium alloy, which contains a second phase consisting of an intermetallic compound, thereby having excellent strength, formability, and corrosion resistance. More particularly, the present invention pertains to a wrought magnesium alloy, which comprises 0.1 - 1.5 at% group ⁇ ia, 1.0 - 4.0 at% group nib, 0.35 at% or less of one selected from the group consisting of groups Ha, IVa, Vila, IVb, and a mixture thereof, 1.0 at% or less group lib, and a balance of Mg and unavoidable impurities and which thus has a second phase composite microstructure consisting of an intermetallic compound, and a method of producing the same.
- Background Art
- magnesium alloys have been developed as light structural materials for airplanes and automobiles.
- HCP hexagonal close packed
- formability is very low, and thus, the application is limited to a field in which the forming is achieved using a casting process.
- its practical use is limited due to problems, such as severe oxidation of melts, reduction of strength at high temperatures, and low corrosion resistance.
- Effort has been made to avoid the above disadvantages, thus enabling stable dissolution in atmospheric air, while employing a sulfur hexafluoride (SF 6 ) gas, a carbon dioxide gas, an argon gas and the like, and production of a plate by Direct Chilled casting process.
- SF 6 sulfur hexafluoride
- a Mg-Zn alloy shows an excellent age hardening behavior, and is advantageous in that since a microstructure is refined through heat treatments, strength and ductility significantly increase and it is easy to work and weld.
- it is disadvantageous in that since micropores are formed as a casting process due to the addition of Zn, it is difficult to apply the Mg-Zn alloy to a casting process, such as die-casting. Additionally, it is difficult to desirably improve strength because it is grown as the coarse grain.
- studies have been made to improve formability using a grain boundary slip, in which some alloy elements are added to Mg-Zn binary alloys to refine grains. With respect to this, J. P. Doan and G.
- Ansel suggest a method of improving the strength of an alloy, in which Zr is added to refine grains constituting a Mg-Zn alloy (J. P. Doan and G. Ansel, Trans, AIME, vol. 171 (1947), pp. 286-295).
- Zr has a high melting point and a low solubility to Mg at room temperature, it mostly exists at a grain boundary, thus acting as a fracture initiation site when external stress is applied.
- Laid-Open Publication No.2003-0048412 discloses an alloy, which contains 3.0 - 10.0 wt% Zn, 0.25 - 3.0wt% Mn, Al, Si, and Ca.
- the alloy containing Zn in an amount of 2 % or more has high strength, it has a disadvantage in that free zinc (Zn) readily forms a low melting point eutectic phase.
- Zn free zinc
- Mg Zn having a low melting point that is less than 350°C
- corrosion resistance is low.
- the plate is easily cracked at both sides during a rough rolling process for breaking the coarse dendrite structure, so draw-ability is poor because of high anisotropy.
- 2002-0078936 (U.S. Pat. No. 6471797) discloses a method of improving strength and formability using a Mg-Zn-Y eutectic ternary alloy quasi-crystalline phase which contains 1 - 10 at% Zn and 0.1 - 3 at% Y.
- this method is disadvantageous in that the amount of Zn must be enough so as to desirably assure a quasi-crystalline phase effect.
- the composition of a cast product is not uniform because a specific gravity between zinc and magnesium is significantly different.
- the micro-pores at the grain boundary reduce corrosion resistance, and tears form at sides of a plate during the hot rolling process.
- H07-54026 entitled 'magnesium alloy having high strength and method of producing the same'
- U.S. Pat. 4675157, 4765954, 4853035, 4857109, 4938809, 5071474, 5078806, 5078807, 5087304, 5129960, and 5316598, EP No. 0,361,136Al, and French Pat. No. 2,688,233 disclose the formation of an amorphous structure through a Rapid Solidification process. Since the cooling rate must be conducted at 10 - 10 °C /s to form the amorphous structure, the patents are useful to produce powder or a thin strip, but not to produce a common plate shape. Accordingly, an ingot, which is produced by compacting amorphous powder under the recrystallization temperature, is employed in order to conduct a rolling or a press forming.
- 5693158, 5800640 and 6395224 disclose a method of producing goods having low crack sensitivity, in which Sr, Li or B is employed and heat treatments are conducted to refine a particle size of crystals of a cast product.
- these patents are useful to cast products, but cannot be directly applied to wrought products.
- Japanese Pat. Laid-Open Publication No. H10-147830A discloses the use of 6 - 12 wt% Y and 1 - 6 wt% Gd, and hot forging and subsequent aging processes to improve creep resistance to be applied to engine parts.
- the patent cannot be applied to wrought products because the product cost significantly increases due to the use of a lot expensive elements, and the coarse intermetallic compounds are incoherent to the matrix.
- an object of the present invention is to provide a wrought magnesium alloy which contains the intermetallic compound coherent to a matrix microstructure and which has a second phase composite microstructure, thereby improving elongation and anisotropy to assure excellent formability and corrosion resistance.
- an alloy consisting of three or more elements is used to activate a slip plane.
- Ilia and nib groups are added together to reduce stacking fault energy and to improve corrosion resistance of the matrix microstructure.
- fine intermetallic compound particles dispersed during extrusion and rolling processes are employed to improve strain hardening ability and formability.
- the present invention provides a wrought magnesium alloy having excellent formability and plating properties, which comprises 0.1 - 1.5 at% group Ilia, 1.0 - 4.0 at% group HIb, 0.35 at% or less of one selected from the group consisting of groups Ha, IVa, Vila, IVb, and a mixture thereof, 1.0 at% or less of group lib, and a balance of Mg and impurities and which thus has a second phase intermetallic compound.
- FIG. 1 illustrates a box sample formed using a wrought magnesium alloy sheet, according to the present invention
- FIG. 2 illustrates a cup-shaped sample formed using the wrought magnesium alloy sheet, according to the present invention
- FIG. 3 illustrates the box sample formed using AZ31 sheet
- FlG. 4 illustrates a microstructure of a material of No. 1 in Table 1, which is cast and then diffusion annealed at 400 °C for 5 hours;
- FlG. 5 illustrates a microstructure of an extruded material according to the present invention, which is annealed
- FlG. 6 illustrates a microstructure of a rolled sheet according to the present invention. Best Mode for Carrying Out the Invention
- the present invention is characterized in that the fine 2nd phase precipitates, which is coherent to matrix microstructure, is formed in the solid solution microstructure having excellent ductility, thereby making grains fine and improving formability.
- the strength of most materials increases. The reason is that a dislocation moves along the specific slip plane in the course of plastic deformation of the metal in such a way that the dislocation does not directly move from one grain to another grain. But direction of dislocation changes its route because of the grain boundary barrier effect. Accordingly, since the grain boundaries act as barriers in the movement of the dislocation, dislocations are pile up at a grain boundary, thereby preventing deformation.
- the high temperature stable phase must be capable of being formed in order to make the grain fine, and desired solid solubility must be assured at high temperatures in order to be coherent to a matrix microstructure. Furthermore, a size difference between elements of a matrix metal and atoms must be about 15 % so as to assure a desirable matrix reinforcement effect.
- Many studies have been made of the effect of an intermetallic compound on a solid solution. Particularly, a matrix reinforcement effect caused by the dispersion of fine intermetallic compound particles is well known in the metallurgy engineering (Mechanical Metallurgy, 2nd ed., George E. Dieter, McGraw-Hill, 1981, pp. 221-227).
- the intermetallic compound has a high melting point and strong bonding strength, thus having high hardness and thermally stable. Because of the finely dispersed second phase particles, these alloys are much more resistant to recrystallization and grain growth than single-phase alloys. However, if the intermetallic compound has a microstructure that is incoherent to the matrix microstructure, it acts as a fracture initiation site and thus has increased strength, but elongation or total ductility is reduced even though the matrix microstructure has ductility.
- the second phase of conventional magnesium alloy is not a high melting point phase in the matrix microstructure.
- the 2 nd phase is low melting point eutectic phase during the solidification instead of the precipitates. Therefore, the eutectic phase is mostly incoherent to the matrix microstructure. It is scarcely an atomic match for the matrix microstructure, thus effectively preventing grain growth or over-aging.
- it reduces the formability of a material or acts as a fracture initiation site. And thus, these type alloys are unsuitable for wrought magnesium alloy. Even though a duplex microstructure is formed, the movement of the dislocation is ineffectively prevented if the second phase is not strong, resulting in undesirably improved anisotropy or strength.
- group Ilia elements employed in the present invention readily form intermetallic compounds having a cubic lattice and thus have high a matrix reinforcement effect and ductility.
- the stacking faults are formed because a stacking order of a closely packed side is changed unlike a normal stacking order, and it is known that they are mostly formed due to plastic deformation. It is difficult to form stacking faults if stacking fault energy is high, and thus, strain hardening required as a press material is not high. Accordingly, since pure aluminum or copper has high stacking fault energy, energy supplied during a room temperature process is mostly converted into heat. Thus, it is difficult to accumulate internal deformations, and a driving force for nucleation is reduced during recrystallization.
- the group HIb and ⁇ ia elements are alloyed with magnesium acting as a matrix element, thereby reducing the stacking fault energy of the intermetallic compound to provide ductility. Additionally, fine second phases promote nucleation during a reheating process to make fine grains. Intermetallic compound particles prevent grain growth at a recrystallization temperature or higher.
- the present inventor came to a conclusion that when a group Ilia is alloyed with magnesium to form a solid solution having low stacking fault energy, when a group IIIb is added to the solid solution to increase a solid-solution strengthening effect, and when a group lib and other miniaturized elements are added to form a structure which contains an intermetallic compound coherent thereto, it is possible to create a material having excellent strain hardening ability, fineness through recrystallization by heat treatment, and improved anisotropy.
- the group Ilia that is, an essential element in the present invention, includes Sc, Y, lanthanides, and actinides.
- Sc, Y, or lanthanides be employed alone or in combination instead of actinides radiating radioactive rays. They are solid-solved in Mg, thus reducing a c/a ratio to increase ductility and reducing the stacking fault energy to increase the driving force for nucleation by recrystallization.
- particles which exist in a form of Mg RE at high temperatures during a solidification process, form prism-shaped plate particles having a HCP structure, that is, a DO lattice structure, such as Mg RE or Mg RE , at about 550 °C through a peritectic transformation.
- RE is an abbreviated form of rare-earth elements belonging to the group ⁇ ia
- the particles have a high reinforcement effect and are coherent to the matrix, and consequently, they do not act as the fracture initiation site.
- the particles may be compacted into a rod, a sphere, or a cube.
- a eutectic phase which is not solid-solved after a diffusion heat-treatment, is finely dispersed during extrusion and rolling processes, thereby preventing grain growth during heat-treatment and acting as a site for nucleation by re- crystallization.
- the amount of the group Ilia is less than 0.1 %, the second phase is formed in an insufficient amount.
- the amount is more than 1.5 %, a fineness effect is saturated, and consequently, elongation is reduced and a production cost increases. This is the reason why that amount is limited.
- the group HIb includes B, Al, Ga, In, and Tl. Since Ga, In, and Tl having a low melting point form a low melting point eutectic phase, it is preferable to employ only Al or a mixture of B and Al. The group nib forms a fine deposit and thus contributes to reinforcement of the matrix. Al is used as a main alloy element. Since B has a low solid solubility to magnesium and forms a high melting point compound, such as B Y, B Y , or B Y , it is employed in conjunction with Al in an amount of 0.010 % or less so as to make the fine grains.
- Al of the group nib is solid-solved in Mg to increase corrosion resistance and to prevent the growth of a dendrite microstructure, thereby making a cast microstructure fine. Furthermore, since Al forms fine cubes, such as Al RE or Al RE during the solidification process and increases ductility of the matrix microstructure, it is possible to produce goods having high strength and excellent ductility.
- the amount of Al is less than 1.0 %, it is difficult to assure the desirable reinforcement effect.
- the amount is more than 4.0 %, since an unstable rod- or plate-shaped Al Mg or Al Mg phase is enlarged in a grain boundary, even though room temperature strength is high, high temperature strength and corrosion resistance are reduced. This is the reason why that amount is limited.
- group Ha % or less of group Ha, group IVa, group Vila, or group IVb is selectively employed alone or in combination, and 1.0 % or less of group lib is employed alone or in combination.
- the group Ha, group IVa, and group Vila are used as a supplemental agent of the group ⁇ ia and group i ⁇ b.
- group Ha it is preferable to use Ca and Sr. Since Be, Ba, and Ra make toxic gases, they can be used only if a special ventilation device is adopted. Ca and Sr are particularly useful to make a fine cast structure in the casting a billet having a diameter of 200 mm or more in the present invention, and form disk- shaped particles, such as (Mg, Al) Ca, thereby improving a reinforcement effect.
- Mn of the group Vila is a cheap alloy element, prevents the formation of Al Mg and Al Mg phases, and promotes the formation of high temperature cubic Al Y to contribute to the fining of the grains and the improvement of corrosion resistance.
- Tc and Re of the group Vila are costly and thus are used in unavoidable cases.
- the group Ha, group IVa, group Vila, and group IVb elements have low solid solubility to magnesium, and thus, if they are excessively added, segregation occurs or coarse particles having high brittleness are formed when a cooling rate is low after a casting process. Accordingly, the amount is limited to 0.35 % or less.
- the group lib includes Zn, Cd, and Hg. Since Hg is toxic to humans when breathing, use of Hg is limited, and it is used in conjunction with an additional protection device.
- Zn and Cd are added alone or in combination, a stacking fault structure is formed in a magnesium matrix microstructure to bring about strain hardening, and Zn and Cd are smoothly solid-solved with the group ⁇ ia and group IIIb elements to promote the formation of cubic particles, such as (Mg, Zn) 5 RE, Zn 6 Mg 2 RE, or (Mg, Zn) RE .
- the excessive amount of Zn and Cd increases gas solid solubility, thereby reducing corrosion resistance or plating workability and brining about the occurrence of hot tear and gravity separation phenomena.
- the amount is limited to 1.0 % or less, and preferably, 0.65 % or less.
- a slab for a magnesium alloy plate is produced through mold casting, Direct Chilled casting, continuous casting, or strip casting processes.
- a mold in which a cavity having a thickness of 30 mm, a width of 250 mm, and a height of 400 mm is formed, is preheated in a heating furnace heated to about 200°C.
- a molten magnesium alloy is poured into the mold at 710 - 760°C, and then machined so as to remove surface defects from a cast product.
- a surface temperature of a rolling roll must be maintained at 50 - 150°C so as to prevent the formation of fine surface cracks caused by the qu enched slab while the slab is in contact with the roll.
- the temperature of the rolling roll is more than 150°C, delamination, in which a portion of a rolling material clings to the rolling roll and then delaminates, occurs during the rolling process, thus roughening the surface of the slab. If the plate is not excessively cooled after the initial coarse rolling, it is possible to conduct the rolling process again without reheating.
- a second rolling process is repeatedly conducted in a reduction ratio of 50 % or less each time until the desired thickness is gained.
- the reduction ratio depends on the capacity of a motor of a rolling mill, a heat emitting state of a plate during a reduction process, elastic deformation of the rolling roll, and flatteness of the plate.
- a second process annealing be repeatedly conducted at 200 - 450°C each time while a duration time is maintained at 1 min/mm or more during the second rolling process.
- a rolled microstructure becomes fine, causing crack resistance.
- annealing is not necessarily conducted every rolling process.
- a duration time is maintained at 1 min/mm or more, which depends on the thickness, strength, and elongation of the plate.
- the annealing temperature is high and the time is long, elongation increases but strength is reduced.
- the annealing temperature is more than 350°C, undesirably, yield strength is significantly reduced.
- the heating temperature is more than 450°C, a free low melting point eutectic phase may be re-melted during the diffusion annealing and thus be separated from the material.
- the duration time and the heating temperature increase to improve workability.
- the diffusion-annealed material is reheated in a heating furnace at 250 - 400°C to be extruded.
- An extruder has an extrusion speed of a maximum of 20 m/min at an extrusion pressure of 850 MPa or more. If the extrusion is conducted at 500 MPa, the extrusion speed is significantly reduced to 3 - 4 m/min.
- a temperature of a container is 300 - 450°C. When the temperature is less than 300°C, many surface cracks are formed. When the temperature is more than 450°C, high temperature cracks or deformations are significantly formed during the extrusion process.
- the container is heated at about 350°C, and an extrusion ratio is typically 10 - 100. Additionally, in the present invention, the material may be wound in a coil form during the extrusion process, and thus, it is possible to conduct reciprocating rolling.
- the final annealing is conducted at 180 - 350°C while a duration time is maintained at 1 min/mm or more, which depends on a thickness, strength, and elongation of the plate.
- a duration time is maintained at 1 min/mm or more, which depends on a thickness, strength, and elongation of the plate.
- the annealing temperature is high and the time is long, elongation increases but strength is reduced.
- the annealing temperature is more than 350°C, undesirably, yield strength is significantly reduced.
- the heat treatment may be implemented using a rapidly heating device, such as a heater, employing a gas nozzle, or an induction heater, instead of the furnace.
- the annealing temperature may deviate from the above range, without departing from the scope and concept of the invention.
- O means that forming is achieved without cracks and local reduction of a thickness
- ⁇ means that cracks are not formed but a thickness deviation locally occurs
- x means that formability is very poor because of the formation of cracks.
- O means a state that plating thickness and adhesion of a plated surface are excellent.
- ⁇ means a state that adhesion is fair, pinhole is not observed, and plating thickness is ununiform.
- x means a state in which the pinholes are observed or plating layer comes off the surface somewhere in the specimen.
- a fine second phase intermetallic compound is dispersed so as to significantly improve the poor formability and corrosion resistance of a conventional magnesium plate.
- the magnesium plate has excellent properties as a structural material, and consequently, it is possible to apply the magnesium plate to structural materials used in portable electronic products, automobiles, or airplanes.
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- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Materials Engineering (AREA)
- Mechanical Engineering (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- Powder Metallurgy (AREA)
- Forging (AREA)
- Metal Rolling (AREA)
- Shielding Devices Or Components To Electric Or Magnetic Fields (AREA)
- Extrusion Of Metal (AREA)
Priority Applications (6)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US11/547,298 US20080304997A1 (en) | 2004-04-06 | 2005-03-11 | Process for Production of a Carboxylic Acid/Diol Mixture Suitable for Use in Polyester Production |
EP05856294A EP1759029B1 (en) | 2004-04-06 | 2005-03-11 | Wrought magnesium alloy having excellent formability and method of producing same |
DE602005024392T DE602005024392D1 (de) | 2004-04-06 | 2005-03-11 | Schmiedeprodukt aus magnesiumlegierung mit ausgezeichneter formbarkeit und verfahren zu dessen herstellung |
AT05856294T ATE486145T1 (de) | 2004-04-06 | 2005-03-11 | Schmiedeprodukt aus magnesiumlegierung mit ausgezeichneter formbarkeit und verfahren zu dessen herstellung |
AU2005324597A AU2005324597B2 (en) | 2004-04-06 | 2005-03-11 | Wrought magnesium alloy having excellent formability and method of producing same |
JP2007507237A JP5047778B2 (ja) | 2004-04-06 | 2005-03-11 | 優れた成形性を有する鍛造マグネシウム合金及びその製造方法 |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
KR1020040023288A KR100605741B1 (ko) | 2004-04-06 | 2004-04-06 | 내식성과 도금성이 우수한 마그네슘합금 단련재 |
KR10-2004-0023288 | 2004-04-06 |
Publications (1)
Publication Number | Publication Date |
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WO2006075814A1 true WO2006075814A1 (en) | 2006-07-20 |
Family
ID=36677821
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/KR2005/000697 WO2006075814A1 (en) | 2004-04-06 | 2005-03-11 | Wrought magnesium alloy having excellent formability and method of producing same |
Country Status (10)
Country | Link |
---|---|
US (1) | US20080304997A1 (ja) |
EP (1) | EP1759029B1 (ja) |
JP (1) | JP5047778B2 (ja) |
KR (1) | KR100605741B1 (ja) |
CN (1) | CN100441717C (ja) |
AT (1) | ATE486145T1 (ja) |
AU (1) | AU2005324597B2 (ja) |
DE (1) | DE602005024392D1 (ja) |
RU (1) | RU2384639C2 (ja) |
WO (1) | WO2006075814A1 (ja) |
Cited By (2)
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JP2008069418A (ja) * | 2006-09-14 | 2008-03-27 | Kumamoto Univ | 高耐食性を有する高強度マグネシウム合金 |
EP2492365A4 (en) * | 2010-10-05 | 2017-12-20 | Korea Institute Of Machinery & Materials | Flame retardant magnesium alloy with excellent mechanical properties, and preparation method thereof |
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-
2004
- 2004-04-06 KR KR1020040023288A patent/KR100605741B1/ko active IP Right Grant
-
2005
- 2005-03-11 DE DE602005024392T patent/DE602005024392D1/de active Active
- 2005-03-11 AU AU2005324597A patent/AU2005324597B2/en not_active Ceased
- 2005-03-11 US US11/547,298 patent/US20080304997A1/en not_active Abandoned
- 2005-03-11 CN CNB2005800104334A patent/CN100441717C/zh not_active Expired - Fee Related
- 2005-03-11 AT AT05856294T patent/ATE486145T1/de not_active IP Right Cessation
- 2005-03-11 WO PCT/KR2005/000697 patent/WO2006075814A1/en active Application Filing
- 2005-03-11 EP EP05856294A patent/EP1759029B1/en not_active Not-in-force
- 2005-03-11 RU RU2006134447/02A patent/RU2384639C2/ru not_active IP Right Cessation
- 2005-03-11 JP JP2007507237A patent/JP5047778B2/ja not_active Expired - Fee Related
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Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP2008069418A (ja) * | 2006-09-14 | 2008-03-27 | Kumamoto Univ | 高耐食性を有する高強度マグネシウム合金 |
EP2492365A4 (en) * | 2010-10-05 | 2017-12-20 | Korea Institute Of Machinery & Materials | Flame retardant magnesium alloy with excellent mechanical properties, and preparation method thereof |
Also Published As
Publication number | Publication date |
---|---|
JP2007538146A (ja) | 2007-12-27 |
DE602005024392D1 (de) | 2010-12-09 |
RU2006134447A (ru) | 2008-05-20 |
EP1759029A1 (en) | 2007-03-07 |
EP1759029A4 (en) | 2007-07-18 |
JP5047778B2 (ja) | 2012-10-10 |
AU2005324597B2 (en) | 2009-01-08 |
ATE486145T1 (de) | 2010-11-15 |
AU2005324597A1 (en) | 2006-07-20 |
EP1759029B1 (en) | 2010-10-27 |
CN1938440A (zh) | 2007-03-28 |
KR100605741B1 (ko) | 2006-08-01 |
RU2384639C2 (ru) | 2010-03-20 |
KR20040035646A (ko) | 2004-04-29 |
CN100441717C (zh) | 2008-12-10 |
US20080304997A1 (en) | 2008-12-11 |
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