USRE34262E - High modulus Al alloys - Google Patents
High modulus Al alloys Download PDFInfo
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- USRE34262E USRE34262E US07/705,969 US70596991A USRE34262E US RE34262 E USRE34262 E US RE34262E US 70596991 A US70596991 A US 70596991A US RE34262 E USRE34262 E US RE34262E
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- United States
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- titanium
- aluminum
- vanadium
- high modulus
- zirconium
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- 229910000838 Al alloy Inorganic materials 0.000 title description 4
- 229910045601 alloy Inorganic materials 0.000 claims abstract description 42
- 239000000956 alloy Substances 0.000 claims abstract description 42
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical group [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 claims abstract description 29
- 229910052720 vanadium Inorganic materials 0.000 claims abstract description 18
- 229910052726 zirconium Inorganic materials 0.000 claims abstract description 17
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims abstract description 13
- QCWXUUIWCKQGHC-UHFFFAOYSA-N Zirconium Chemical compound [Zr] QCWXUUIWCKQGHC-UHFFFAOYSA-N 0.000 claims abstract description 13
- 229910052799 carbon Inorganic materials 0.000 claims abstract description 12
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 claims abstract description 10
- 229910052760 oxygen Inorganic materials 0.000 claims abstract description 10
- 239000001301 oxygen Substances 0.000 claims abstract description 10
- LEONUFNNVUYDNQ-UHFFFAOYSA-N vanadium atom Chemical compound [V] LEONUFNNVUYDNQ-UHFFFAOYSA-N 0.000 claims abstract 9
- 239000010936 titanium Substances 0.000 claims description 34
- 229910052719 titanium Inorganic materials 0.000 claims description 32
- XEEYBQQBJWHFJM-UHFFFAOYSA-N Iron Chemical compound [Fe] XEEYBQQBJWHFJM-UHFFFAOYSA-N 0.000 claims description 10
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 claims description 10
- 229910052727 yttrium Inorganic materials 0.000 claims description 7
- VWQVUPCCIRVNHF-UHFFFAOYSA-N yttrium atom Chemical compound [Y] VWQVUPCCIRVNHF-UHFFFAOYSA-N 0.000 claims description 7
- 229910052782 aluminium Inorganic materials 0.000 claims description 6
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims description 6
- 229910052758 niobium Inorganic materials 0.000 claims description 6
- 239000010955 niobium Substances 0.000 claims description 6
- GUCVJGMIXFAOAE-UHFFFAOYSA-N niobium atom Chemical compound [Nb] GUCVJGMIXFAOAE-UHFFFAOYSA-N 0.000 claims description 6
- ZOXJGFHDIHLPTG-UHFFFAOYSA-N Boron Chemical compound [B] ZOXJGFHDIHLPTG-UHFFFAOYSA-N 0.000 claims description 5
- 229910052684 Cerium Inorganic materials 0.000 claims description 5
- VYZAMTAEIAYCRO-UHFFFAOYSA-N Chromium Chemical compound [Cr] VYZAMTAEIAYCRO-UHFFFAOYSA-N 0.000 claims description 5
- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical compound [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 claims description 5
- 229910052691 Erbium Inorganic materials 0.000 claims description 5
- WHXSMMKQMYFTQS-UHFFFAOYSA-N Lithium Chemical compound [Li] WHXSMMKQMYFTQS-UHFFFAOYSA-N 0.000 claims description 5
- XUIMIQQOPSSXEZ-UHFFFAOYSA-N Silicon Chemical compound [Si] XUIMIQQOPSSXEZ-UHFFFAOYSA-N 0.000 claims description 5
- 229910052790 beryllium Inorganic materials 0.000 claims description 5
- ATBAMAFKBVZNFJ-UHFFFAOYSA-N beryllium atom Chemical compound [Be] ATBAMAFKBVZNFJ-UHFFFAOYSA-N 0.000 claims description 5
- 229910052796 boron Inorganic materials 0.000 claims description 5
- 229910052804 chromium Inorganic materials 0.000 claims description 5
- 239000011651 chromium Substances 0.000 claims description 5
- 229910017052 cobalt Inorganic materials 0.000 claims description 5
- 239000010941 cobalt Substances 0.000 claims description 5
- GUTLYIVDDKVIGB-UHFFFAOYSA-N cobalt atom Chemical compound [Co] GUTLYIVDDKVIGB-UHFFFAOYSA-N 0.000 claims description 5
- 229910052802 copper Inorganic materials 0.000 claims description 5
- 239000010949 copper Substances 0.000 claims description 5
- UYAHIZSMUZPPFV-UHFFFAOYSA-N erbium Chemical compound [Er] UYAHIZSMUZPPFV-UHFFFAOYSA-N 0.000 claims description 5
- 229910052742 iron Inorganic materials 0.000 claims description 5
- 229910052744 lithium Inorganic materials 0.000 claims description 5
- 229910052759 nickel Inorganic materials 0.000 claims description 5
- 229910052710 silicon Inorganic materials 0.000 claims description 5
- 239000010703 silicon Substances 0.000 claims description 5
- 229910052715 tantalum Inorganic materials 0.000 claims description 5
- GUVRBAGPIYLISA-UHFFFAOYSA-N tantalum atom Chemical compound [Ta] GUVRBAGPIYLISA-UHFFFAOYSA-N 0.000 claims description 5
- 230000007704 transition Effects 0.000 claims description 5
- WFKWXMTUELFFGS-UHFFFAOYSA-N tungsten Chemical compound [W] WFKWXMTUELFFGS-UHFFFAOYSA-N 0.000 claims description 5
- 229910052721 tungsten Inorganic materials 0.000 claims description 5
- 239000010937 tungsten Substances 0.000 claims description 5
- 239000000463 material Substances 0.000 claims description 4
- PNEYBMLMFCGWSK-UHFFFAOYSA-N aluminium oxide Inorganic materials [O-2].[O-2].[O-2].[Al+3].[Al+3] PNEYBMLMFCGWSK-UHFFFAOYSA-N 0.000 claims description 2
- GWXLDORMOJMVQZ-UHFFFAOYSA-N cerium Chemical compound [Ce] GWXLDORMOJMVQZ-UHFFFAOYSA-N 0.000 claims 4
- OQPDWFJSZHWILH-UHFFFAOYSA-N [Al].[Al].[Al].[Ti] Chemical compound [Al].[Al].[Al].[Ti] OQPDWFJSZHWILH-UHFFFAOYSA-N 0.000 claims 1
- 238000013459 approach Methods 0.000 claims 1
- 239000006185 dispersion Substances 0.000 claims 1
- 238000006467 substitution reaction Methods 0.000 claims 1
- 229910021324 titanium aluminide Inorganic materials 0.000 claims 1
- 238000005551 mechanical alloying Methods 0.000 abstract description 3
- 239000000203 mixture Substances 0.000 abstract description 3
- 239000003795 chemical substances by application Substances 0.000 abstract description 2
- 238000004886 process control Methods 0.000 abstract description 2
- GPPXJZIENCGNKB-UHFFFAOYSA-N vanadium Chemical compound [V]#[V] GPPXJZIENCGNKB-UHFFFAOYSA-N 0.000 description 5
- 235000021355 Stearic acid Nutrition 0.000 description 3
- 239000004615 ingredient Substances 0.000 description 3
- QIQXTHQIDYTFRH-UHFFFAOYSA-N octadecanoic acid Chemical compound CCCCCCCCCCCCCCCCCC(O)=O QIQXTHQIDYTFRH-UHFFFAOYSA-N 0.000 description 3
- OQCDKBAXFALNLD-UHFFFAOYSA-N octadecanoic acid Natural products CCCCCCCC(C)CCCCCCCCC(O)=O OQCDKBAXFALNLD-UHFFFAOYSA-N 0.000 description 3
- 239000008117 stearic acid Substances 0.000 description 3
- 238000005275 alloying Methods 0.000 description 2
- 238000001125 extrusion Methods 0.000 description 2
- 229910052751 metal Inorganic materials 0.000 description 2
- 239000002184 metal Substances 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 229910010271 silicon carbide Inorganic materials 0.000 description 2
- 238000012360 testing method Methods 0.000 description 2
- 229910018404 Al2 O3 Inorganic materials 0.000 description 1
- 229910016373 Al4 C3 Inorganic materials 0.000 description 1
- 101150102561 GPA1 gene Proteins 0.000 description 1
- 239000006057 Non-nutritive feed additive Substances 0.000 description 1
- AZDRQVAHHNSJOQ-UHFFFAOYSA-N alumane Chemical class [AlH3] AZDRQVAHHNSJOQ-UHFFFAOYSA-N 0.000 description 1
- CAVCGVPGBKGDTG-UHFFFAOYSA-N alumanylidynemethyl(alumanylidynemethylalumanylidenemethylidene)alumane Chemical compound [Al]#C[Al]=C=[Al]C#[Al] CAVCGVPGBKGDTG-UHFFFAOYSA-N 0.000 description 1
- CSDREXVUYHZDNP-UHFFFAOYSA-N alumanylidynesilicon Chemical compound [Al].[Si] CSDREXVUYHZDNP-UHFFFAOYSA-N 0.000 description 1
- JNDMLEXHDPKVFC-UHFFFAOYSA-N aluminum;oxygen(2-);yttrium(3+) Chemical compound [O-2].[O-2].[O-2].[Al+3].[Y+3] JNDMLEXHDPKVFC-UHFFFAOYSA-N 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- INAHAJYZKVIDIZ-UHFFFAOYSA-N boron carbide Chemical class B12B3B4C32B41 INAHAJYZKVIDIZ-UHFFFAOYSA-N 0.000 description 1
- 238000005266 casting Methods 0.000 description 1
- ZMIGMASIKSOYAM-UHFFFAOYSA-N cerium Chemical compound [Ce][Ce][Ce][Ce][Ce][Ce][Ce][Ce][Ce][Ce][Ce][Ce][Ce][Ce][Ce][Ce][Ce][Ce][Ce][Ce][Ce][Ce][Ce][Ce][Ce][Ce][Ce][Ce][Ce][Ce][Ce][Ce][Ce][Ce][Ce][Ce][Ce][Ce] ZMIGMASIKSOYAM-UHFFFAOYSA-N 0.000 description 1
- 239000011246 composite particle Substances 0.000 description 1
- 150000001875 compounds Chemical class 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000005242 forging Methods 0.000 description 1
- 229910002804 graphite Inorganic materials 0.000 description 1
- 239000010439 graphite Substances 0.000 description 1
- 238000010348 incorporation Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 239000011159 matrix material Substances 0.000 description 1
- 238000002844 melting Methods 0.000 description 1
- 230000008018 melting Effects 0.000 description 1
- 150000001247 metal acetylides Chemical class 0.000 description 1
- 238000003801 milling Methods 0.000 description 1
- TWNQGVIAIRXVLR-UHFFFAOYSA-N oxo(oxoalumanyloxy)alumane Chemical compound O=[Al]O[Al]=O TWNQGVIAIRXVLR-UHFFFAOYSA-N 0.000 description 1
- 239000002245 particle Substances 0.000 description 1
- 239000000843 powder Substances 0.000 description 1
- 238000005096 rolling process Methods 0.000 description 1
- HBMJWWWQQXIZIP-UHFFFAOYSA-N silicon carbide Chemical compound [Si+]#[C-] HBMJWWWQQXIZIP-UHFFFAOYSA-N 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
- MTPVUVINMAGMJL-UHFFFAOYSA-N trimethyl(1,1,2,2,2-pentafluoroethyl)silane Chemical compound C[Si](C)(C)C(F)(F)C(F)(F)F MTPVUVINMAGMJL-UHFFFAOYSA-N 0.000 description 1
- 229910019901 yttrium aluminum garnet Inorganic materials 0.000 description 1
- RUDFQVOCFDJEEF-UHFFFAOYSA-N yttrium(III) oxide Inorganic materials [O-2].[O-2].[O-2].[Y+3].[Y+3] RUDFQVOCFDJEEF-UHFFFAOYSA-N 0.000 description 1
Classifications
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C32/00—Non-ferrous alloys containing at least 5% by weight but less than 50% by weight of oxides, carbides, borides, nitrides, silicides or other metal compounds, e.g. oxynitrides, sulfides, whether added as such or formed in situ
- C22C32/001—Non-ferrous alloys containing at least 5% by weight but less than 50% by weight of oxides, carbides, borides, nitrides, silicides or other metal compounds, e.g. oxynitrides, sulfides, whether added as such or formed in situ with only oxides
- C22C32/0015—Non-ferrous alloys containing at least 5% by weight but less than 50% by weight of oxides, carbides, borides, nitrides, silicides or other metal compounds, e.g. oxynitrides, sulfides, whether added as such or formed in situ with only oxides with only single oxides as main non-metallic constituents
- C22C32/0036—Matrix based on Al, Mg, Be or alloys thereof
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C1/00—Making non-ferrous alloys
- C22C1/04—Making non-ferrous alloys by powder metallurgy
- C22C1/0408—Light metal alloys
- C22C1/0416—Aluminium-based alloys
Definitions
- the present invention is concerned with aluminum-base alloys and, more particularly, with aluminum-base alloys having high room and elevated temperature strength, a modulus of elasticity in excess of about 90 GPa and good ductility.
- a light metal i.e. one having a density less than about 3 g/cm 3 , which is both strong (in terms of tensile and yield strength) and stiff.
- light metal (aluminum) composites with silicon carbide can have moduli measuring in excess of about 90 GPa and measuring as high as even 140 GPa. While these aluminum-silicon carbide or boron carbide composites are useful, they are not particularly strong at high temperatures and, at the higher moduli, are relatively brittle.
- the present invention contemplates a mechanically alloyed aluminum-base alloy containing in percent by weight about 10-20 or 25% titanium, about 1-4% carbon and about 0.2-2% oxygen other than oxygen present in stable oxides deliberately added to the mechanical alloying charge.
- the mechanically alloyed aluminum-base alloy of the invention has a modulus of elasticity of at least about 90 GPa and can contain small amounts of other elements in total up to about 10% by weight as described hereinafter. More particularly the alloy of the invention can contain transition elements such as vanadium or zirconium in amounts up to about 5% by weight in replacement of titanium on an atom-for-atom basis.
- vanadium can replace titanium on an equal weight basis up to 5% by weight and zirconium can replace up to about 2.5% titanium on the basis of two parts by weight of zirconium to one part by weight of titanium.
- the total weight percent of the elements titanium, vanadium and zirconium shall be interrelated such that
- the “defined range” in its broadest sense is 10-25% preferably 10-20% and, more narrowly 10-16% and still more narrowly 10-14% or any other range applicable to titanium alone or two or more of titanium, vanadium and zirconium as set forth in this description.
- auxiliary elements can be present in the mechanically alloyed aluminum-base alloys of the present invention.
- Lithium can be present in amounts up to about 3% and copper, nickel, cerium and erbium can be present in total amounts up to about 5%.
- Other elements such as silicon, beryllium, iron, chromium, cobalt, niobium, yttrium, tantalum and tungsten can be present in total amounts up to about 10%. Boron in small amounts up to about 1% can be advantageously present in the alloys of the invention.
- Those skilled in the art will appreciate that inclusion of elements other than titanium and elements substituted for titanium will generally tend to increase the hardness of the alloy while lowering ductility.
- auxiliary elements in the alloy are minimized, e.g. up to a total of 2% by weight and below 15% by weight of titanium the permissible amount of auxiliary elements, if any, gradually increases to the total maximas set forth hereinbefore.
- oxidic materials such as alumina, yttria or yttrium-containing oxide such as yttrium-aluminum-garnet and the like and carbon.
- the optional oxidic materials can be present in a total amount up to about 2% with the maximum being present only when titanium contents are low and auxiliary elements are either in low concentration or absent. Similarly except when the defined range is less than about 15%, carbon should be maintained at a maximum of about 2%.
- the alloys of the present invention consisting of aluminum and the aforestated elements and compounds in the aforestated ranges are made by mechanically alloying elemental or intermetallic ingredients (e.g. Al 3 Ti) as previously described in U.S. Pat. Nos. 3,740,210, 4,600,556, 4,624,705, 4,643,780, 4,668,470, 4,627,959, 4,668,282, 4,668,282, 4,668,470 and 4,557,893.
- a processing aid such as stearic acid or mixtures of stearic acid and graphite is used.
- the result of milling particulate aluminum and titanium with or without additional elements along with stearic acid is the formation of amounts of oxide and carbide essentially stoichiometrically equivalent to the amount of carbon and oxygen in the process control agent.
- these oxides and carbides are primarily Al 2 O 3 and aluminum carbide with or without modification by titanium. Relatively little titanium carbide is present in the alloy.
- the milled particles, sieved to exclude fines are placed in a container, degassed under reduced pressure, for example, at 500° C. for 2 to 12 hours, compacted in vacuum under applied pressure and are then extruded.
- the extrusion ratio can be from about 5 to 1 to about 50 to 1 and the extrusion temperature from about 250° C. to about 600° C.
- compositions, in weight percent, of high modulus aluminum-base alloys of the present invention are set forth in Table 1.
- alloys confirm to the range of about 10-16% titanium, about 1.3-2% carbon, about 0.5-1.2% oxygen, up to about 2.5% vanadium, balance essentially aluminum.
- Table 1 the alloys were examined as to microstructure.
- the microstructure shows a large volume fraction of Al 3 Ti intermetallic phase present as ultra-fine (usually less than 0.2 micrometer in size) grains very uniformly distributed through a fine grain aluminous matrix.
- Carbon is essentially present as a very finely divided Al 4 C 3 or a titanium-doped modification thereof and oxygen is present as grain boundary aluminum oxide.
- Table 2 shows that the alloys of the present invention are strong at high temperatures compared to the general run of aluminum alloys made by conventional melting and casting technology.
- Table 3 shows the high, room temperature moduli of elasticity exhibited by alloys of the present invention and also shows with respect to alloy 1 that the modulus of elasticity is not degraded by exposure to high temperature.
- An additional test of mechanical characteristics shows for alloy 2 that at 427° C. the 0.2% yield strength is 121 MPa, the ultimate tensile strength is 132 MPa and the elongation is 5.4%.
- Laboratory work with mechanically alloyed aluminum alloys has recently shown that mechanical characteristics of this nature at temperatures about 427° C. make the alloy amenable to hot working production processes such as rolling and forging thereby significantly increasing the utility of hard, aluminum alloys containing a solid insoluble intermetallic phase.
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- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Materials Engineering (AREA)
- Mechanical Engineering (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- Manufacture Of Alloys Or Alloy Compounds (AREA)
Abstract
High modulus aluminum-base alloys comprise mechanically alloyed aluminum-base compositions contain 10-25% titanium part of which may be replaced by vanadium or zirconium. Within described limits the alloys can contain elements other than oxygen and carbon ordinarily derived from the process control agent used in mechanical alloying.
Description
The present invention is concerned with aluminum-base alloys and, more particularly, with aluminum-base alloys having high room and elevated temperature strength, a modulus of elasticity in excess of about 90 GPa and good ductility.
In aircraft and in other structures, there is often a need for a light metal, i.e. one having a density less than about 3 g/cm3, which is both strong (in terms of tensile and yield strength) and stiff. It is known that light metal (aluminum) composites with silicon carbide can have moduli measuring in excess of about 90 GPa and measuring as high as even 140 GPa. While these aluminum-silicon carbide or boron carbide composites are useful, they are not particularly strong at high temperatures and, at the higher moduli, are relatively brittle.
It is the object of the invention to provide aluminum-base alloys having a combination of high moduli of elasticity and strengths and more particularly to provide aluminum-base alloys which have reasonable tensile elongations coupled with high room and elevated temperature strengths and high moduli.
The present invention contemplates a mechanically alloyed aluminum-base alloy containing in percent by weight about 10-20 or 25% titanium, about 1-4% carbon and about 0.2-2% oxygen other than oxygen present in stable oxides deliberately added to the mechanical alloying charge. The mechanically alloyed aluminum-base alloy of the invention has a modulus of elasticity of at least about 90 GPa and can contain small amounts of other elements in total up to about 10% by weight as described hereinafter. More particularly the alloy of the invention can contain transition elements such as vanadium or zirconium in amounts up to about 5% by weight in replacement of titanium on an atom-for-atom basis. Thus, as a practical matter vanadium can replace titanium on an equal weight basis up to 5% by weight and zirconium can replace up to about 2.5% titanium on the basis of two parts by weight of zirconium to one part by weight of titanium. For definition purposes then, the total weight percent of the elements titanium, vanadium and zirconium shall be interrelated such that
%Ti+%V+2% Zr=the defined range
The "defined range" in its broadest sense is 10-25% preferably 10-20% and, more narrowly 10-16% and still more narrowly 10-14% or any other range applicable to titanium alone or two or more of titanium, vanadium and zirconium as set forth in this description.
As mentioned hereinbefore, other elements, i.e. auxiliary elements, can be present in the mechanically alloyed aluminum-base alloys of the present invention. Lithium can be present in amounts up to about 3% and copper, nickel, cerium and erbium can be present in total amounts up to about 5%. Other elements such as silicon, beryllium, iron, chromium, cobalt, niobium, yttrium, tantalum and tungsten can be present in total amounts up to about 10%. Boron in small amounts up to about 1% can be advantageously present in the alloys of the invention. Those skilled in the art will appreciate that inclusion of elements other than titanium and elements substituted for titanium will generally tend to increase the hardness of the alloy while lowering ductility. Accordingly, it is advantageous to limit incorporation of other elements by reference to the defined range of titanium and elements substituted for titanium such that at the high end of the range, about 15% titanium, say from 15-20% by weight titanium, auxiliary elements in the alloy are minimized, e.g. up to a total of 2% by weight and below 15% by weight of titanium the permissible amount of auxiliary elements, if any, gradually increases to the total maximas set forth hereinbefore. A like situation exists with regard to deliberately added oxidic materials such as alumina, yttria or yttrium-containing oxide such as yttrium-aluminum-garnet and the like and carbon. In total the optional oxidic materials can be present in a total amount up to about 2% with the maximum being present only when titanium contents are low and auxiliary elements are either in low concentration or absent. Similarly except when the defined range is less than about 15%, carbon should be maintained at a maximum of about 2%.
As stated, the alloys of the present invention consisting of aluminum and the aforestated elements and compounds in the aforestated ranges are made by mechanically alloying elemental or intermetallic ingredients (e.g. Al3 Ti) as previously described in U.S. Pat. Nos. 3,740,210, 4,600,556, 4,624,705, 4,643,780, 4,668,470, 4,627,959, 4,668,282, 4,668,282, 4,668,470 and 4,557,893. In mechanically alloying ingredients to form the alloys of the present invention a processing aid such as stearic acid or mixtures of stearic acid and graphite is used. The result of milling particulate aluminum and titanium with or without additional elements along with stearic acid is the formation of amounts of oxide and carbide essentially stoichiometrically equivalent to the amount of carbon and oxygen in the process control agent. In the alloys of the invention these oxides and carbides are primarily Al2 O3 and aluminum carbide with or without modification by titanium. Relatively little titanium carbide is present in the alloy.
After mechanical alloying is complete, that is powder ingredients are thoroughly intermingled by repeated fracturing and refracturing of composite particles and have achieved or substantially achieved saturation hardness, the milled particles, sieved to exclude fines, are placed in a container, degassed under reduced pressure, for example, at 500° C. for 2 to 12 hours, compacted in vacuum under applied pressure and are then extruded. As practical ranges the extrusion ratio can be from about 5 to 1 to about 50 to 1 and the extrusion temperature from about 250° C. to about 600° C.
Compositions, in weight percent, of high modulus aluminum-base alloys of the present invention are set forth in Table 1.
TABLE 1 ______________________________________ Alloy No. Ti C O V Al ______________________________________ 1 15.0 1.8 0.90 -- Balance E 2 11.6 1.9 0.70 -- Balance E 3 12.5 1.5 0.80 -- Balance E 4 10.0 1.6 0.75 -- Balance E 5 9.8 1.56 0.62 2.2 Balance E ______________________________________
These exemplified alloys confirm to the range of about 10-16% titanium, about 1.3-2% carbon, about 0.5-1.2% oxygen, up to about 2.5% vanadium, balance essentially aluminum. After preparing the alloys set forth in Table 1 as described hereinbefore, the alloys were examined as to microstructure. Basically the microstructure shows a large volume fraction of Al3 Ti intermetallic phase present as ultra-fine (usually less than 0.2 micrometer in size) grains very uniformly distributed through a fine grain aluminous matrix. Carbon is essentially present as a very finely divided Al4 C3 or a titanium-doped modification thereof and oxygen is present as grain boundary aluminum oxide.
Room and elevated temperature mechanical characteristics of alloys Nos. 2-5 are set forth in Table 2.
TABLE 2 ______________________________________ Alloy Test 0.2% Y.S. U.T.S. Elong. No. Temp. (°C.) (MPa) (MPa) (%) ______________________________________ 2 24 427.7 496.3 7.5 149 353.5 374.5 3.6 315 217.0 228.2 3.6 427 123.2 134.4 5.4 3 24 371.7 228.0 10.0 149 N.A. N.A. N.A. 315 N.A. N.A. N.A. 427 N.A. N.A. N.A. 4 24 464.8 487.2 7.1 149 362.6 393.4 4.7 315 203.0 207.9 4.8 315 107.8 118.3 13.1 5 24 532.7 590.8 3.6 427 123.9 132.3 9.9 ______________________________________ N.A. Not Available
Table 2 shows that the alloys of the present invention are strong at high temperatures compared to the general run of aluminum alloys made by conventional melting and casting technology.
Moduli of elasticity at room temperature, determined by the method of S. Spinner et al, "A Method of Determining Mechanical Resonance Frequencies and for Calculating Elastic Modulus from the Frequencies", ASTM Proc. No. 61, pages 1221-1232, 1961, for alloys of the present invention are set forth in Table 3.
TABLE 3 ______________________________________ Alloy No. Modulus of Elasticity, GPa ______________________________________ 1 112.4 1* 115.8 2 102.7 3 102.7 4 95.2 5 103.6 ______________________________________ *Tested after exposure for 60 hours to a temperature of 482° C.
Table 3 shows the high, room temperature moduli of elasticity exhibited by alloys of the present invention and also shows with respect to alloy 1 that the modulus of elasticity is not degraded by exposure to high temperature. An additional test of mechanical characteristics shows for alloy 2 that at 427° C. the 0.2% yield strength is 121 MPa, the ultimate tensile strength is 132 MPa and the elongation is 5.4%. Laboratory work with mechanically alloyed aluminum alloys has recently shown that mechanical characteristics of this nature at temperatures about 427° C. make the alloy amenable to hot working production processes such as rolling and forging thereby significantly increasing the utility of hard, aluminum alloys containing a solid insoluble intermetallic phase.
While in accordance with the provisions of the statute, there is illustrated and described herein specific embodiments of the invention, those skilled in the art will understand that changes may be made in the form of the invention covered by the claims and that certain features of the invention may sometimes be used to advantage without a corresponding use of the other features.
Claims (8)
1. A mechanically alloyed, high modulus aluminum-base alloy containing at least one element from the group consisting of titanium, vanadium and zirconium, said vanadium, if present, being in an amount up to about 5% by weight, said zirconium, if present, being in an amount up to about 5% by weight, the percents by weight of titanium, vanadium and zirconium conforming to the relation
%Ti+%V+2% Zr=10-25%
about 0.1-2% oxygen, about 1-4% carbon with the balance principally being aluminum.
2. A high modulus aluminum-base alloy as in claim 1 wherein the element from said group is titanium and said alloy contains a dispersion of titanium aluminide.
3. A high modulus aluminum-base alloy as in claim 1 which contains as auxiliary elements up to about 3% lithium, up to about 5% total of copper, nickel, cerium and erbium, up to about 1% boron, up to about 10% total of silicon, beryllium, iron, chromium, cobalt, niobium, yttrium, tantalum and tungsten with the proviso that the total of all auxiliary elements does not exceed 10%.
4. A high modulus aluminum-base alloy as in claim 3 wherein said auxiliary elements are present in an amount up to about 2% total and carbon is less than 2% when the %Ti+%V+2% Zr>15% and said auxiliary elements are present in a gradually increasing total amount when the %Ti+%V+2%Zr>15% and approaches 10%.
5. A high modulus aluminum-base alloy as in claim 1 which contains up to 2% oxidic material in excess of that oxide indicated by the oxygen content specified in claim 1.
6. A high modulus aluminum-base alloy as in claim 5 wherein said oxidic material is selected from the group of alumina and yttrium-containing oxide.
7. A high modulus aluminum-base alloy as in claim 2 which contains about 10% to 16% titanium, about 1.3 to 2% carbon, about 0.5 to 1.2% oxygen, up to about 2.5% vanadium, balance essentially aluminum. .Iadd.
8. A mechanically alloyed, high modulus aluminum-base alloy containing, in weight percent, 10 to 25% of at least one transition element selected from the group consisting of titanium, vanadium, zirconium, niobium, tantalum, yttrium, tungsten, cerium, erbium, chromium, iron, cobalt, nickel and copper, said vanadium, zirconium, nickel, copper, cerium and erbium each being present in an amount less than about 5%, said niobium, tantalum, yttrium, tungsten, chromium, iron and cobalt each being present in an amount less than 10%, said transition elements being limited to atom-for-atom substitution of 10 to 25% titanium, said alloy further containing up to 1% boron, up to 3% lithium, up to 10% silicon and beryllium, about 0.1 to 2% oxygen, about 1-4% carbon, total of said boron, lithium, silicon and beryllium, being less than 2% and said carbon being less than 2% when titanium and transition elements substituted for titanium on an atom-for-atom basis are greater than 15% and total boron, lithium, copper, nickel, cerium, erbium, silicon, beryllium, iron, chromium, cobalt, niobium, yttrium, tantalum, tungsten, vanadium and zirconium being limited to about 10% and the balance being principally aluminum. .Iaddend. .Iadd.9. The alloy of claim 8 wherein said transition element is selected from the group consisting of titanium, vanadium, zirconium and niobium. .Iaddend.
Priority Applications (1)
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US07/705,969 USRE34262E (en) | 1988-05-06 | 1991-05-28 | High modulus Al alloys |
Applications Claiming Priority (2)
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US07/190,713 US4834810A (en) | 1988-05-06 | 1988-05-06 | High modulus A1 alloys |
US07/705,969 USRE34262E (en) | 1988-05-06 | 1991-05-28 | High modulus Al alloys |
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US07/190,713 Reissue US4834810A (en) | 1988-05-06 | 1988-05-06 | High modulus A1 alloys |
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US07/705,969 Expired - Lifetime USRE34262E (en) | 1988-05-06 | 1991-05-28 | High modulus Al alloys |
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Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
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US20150353424A1 (en) * | 2013-01-11 | 2015-12-10 | Commissariat A L'energie Atomique Et Aux Energies Alternatives | Method for producing an al/tic nanocomposite material |
CN116287876A (en) * | 2023-03-02 | 2023-06-23 | 海安宏宇合金材料有限公司 | High-performance aluminum alloy material free of heat treatment and preparation method thereof |
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US20150353424A1 (en) * | 2013-01-11 | 2015-12-10 | Commissariat A L'energie Atomique Et Aux Energies Alternatives | Method for producing an al/tic nanocomposite material |
US9650295B2 (en) * | 2013-01-11 | 2017-05-16 | Commissariat à l'énergie atomique et aux énergies alternatives | Method for producing an Al/TiC nanocomposite material |
CN116287876A (en) * | 2023-03-02 | 2023-06-23 | 海安宏宇合金材料有限公司 | High-performance aluminum alloy material free of heat treatment and preparation method thereof |
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