US2880088A - Titanium base alloys - Google Patents
Titanium base alloys Download PDFInfo
- Publication number
- US2880088A US2880088A US635593A US63559357A US2880088A US 2880088 A US2880088 A US 2880088A US 635593 A US635593 A US 635593A US 63559357 A US63559357 A US 63559357A US 2880088 A US2880088 A US 2880088A
- Authority
- US
- United States
- Prior art keywords
- titanium
- beta
- alloys
- titanium base
- vanadium
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Lifetime
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- 229910045601 alloy Inorganic materials 0.000 title claims description 18
- 239000000956 alloy Substances 0.000 title claims description 18
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 title claims description 15
- 239000010936 titanium Substances 0.000 title claims description 15
- 229910052719 titanium Inorganic materials 0.000 title claims description 15
- 229910052720 vanadium Inorganic materials 0.000 claims description 8
- LEONUFNNVUYDNQ-UHFFFAOYSA-N vanadium atom Chemical compound [V] LEONUFNNVUYDNQ-UHFFFAOYSA-N 0.000 claims description 8
- 229910052782 aluminium Inorganic materials 0.000 claims description 7
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims description 7
- 239000010955 niobium Substances 0.000 claims description 7
- 229910052715 tantalum Inorganic materials 0.000 claims description 7
- GUVRBAGPIYLISA-UHFFFAOYSA-N tantalum atom Chemical compound [Ta] GUVRBAGPIYLISA-UHFFFAOYSA-N 0.000 claims description 7
- GUCVJGMIXFAOAE-UHFFFAOYSA-N niobium atom Chemical compound [Nb] GUCVJGMIXFAOAE-UHFFFAOYSA-N 0.000 claims description 6
- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 description 2
- 238000010438 heat treatment Methods 0.000 description 2
- 239000003381 stabilizer Substances 0.000 description 2
- 238000005482 strain hardening Methods 0.000 description 2
- 229910001040 Beta-titanium Inorganic materials 0.000 description 1
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 1
- FYYHWMGAXLPEAU-UHFFFAOYSA-N Magnesium Chemical compound [Mg] FYYHWMGAXLPEAU-UHFFFAOYSA-N 0.000 description 1
- 238000007792 addition Methods 0.000 description 1
- 230000032683 aging Effects 0.000 description 1
- 238000004458 analytical method Methods 0.000 description 1
- 239000012300 argon atmosphere Substances 0.000 description 1
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 description 1
- 229910052799 carbon Inorganic materials 0.000 description 1
- 229910052749 magnesium Inorganic materials 0.000 description 1
- 239000011777 magnesium Substances 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 229910000734 martensite Inorganic materials 0.000 description 1
- 238000002844 melting Methods 0.000 description 1
- 230000008018 melting Effects 0.000 description 1
- 229910052751 metal Inorganic materials 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 229910052757 nitrogen Inorganic materials 0.000 description 1
- 239000001301 oxygen Substances 0.000 description 1
- 229910052760 oxygen Inorganic materials 0.000 description 1
- 238000010791 quenching Methods 0.000 description 1
- 230000000171 quenching effect Effects 0.000 description 1
- XJDNKRIXUMDJCW-UHFFFAOYSA-J titanium tetrachloride Chemical compound Cl[Ti](Cl)(Cl)Cl XJDNKRIXUMDJCW-UHFFFAOYSA-J 0.000 description 1
- 230000009466 transformation Effects 0.000 description 1
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-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
- C22C14/00—Alloys based on titanium
Definitions
- This invention pertains to titanium base alloys con- 2,880,088 V Patented Mar. 31, 1959 "ice have at room temperature either a mixed alpha-beta or an all-beta microstructure depending on the heat treatment. As quenched from above the beta transus,they will have in general a substantially all-beta mierostructure; whereas as annealed" or after cold working, the structure will be mixed alpha-beta, when'the .total' beta promoter content is at the low end ofits range, i.e., from more than to about while for total betapromoter contents above about 20%, the alloys will have a substantially all-beta structure.
- Table I gives the room temperature tensile properties of representative alloys according to the invention after fabrication at 1600 F. to 40-mil sheet and V1 hour solution heat treatment at 1600 F. and
- 71 98 20 33 about 0.5 to 8% aluminum and from more than 15% up to about 50% of one or more elements selected from the group consisting of vanadium, columbium and tan talum.
- the alloys of the invention on solution treating and quenching from above the beta transus generally are characterized by a relatively low yield strength and by excellent bend ductility and by high uniform and total tensile elongations, and hence are ideally adapted for forming into sheet parts such as skins or wing and body coverings for airplanes and the like, where the ability to stretch uniformly is required.
- An exception to this behavior are the alloys containing over about 25% vanadium, which do not possess the low yield strength and high uniform elongated characteristic of the other alloys by virtue of the substantial amounts of transformation to martensite they undergo during cold working.
- the alloys with the higher vanadium contents have excellent strength and tensile and bend ductility and are eminently suitable for sheet forming operations, except where the ability to stretch uniformly is required.
- these alloys in the form of rolled sheet and in the solution treated and quenched condition are easily formed to shape. Thereafter they may be strengthened and hardened by aging at about 300 to 500 C. ⁇ for about 1 to 16 hours.
- pure titanium metal assumes at temperatures below about 885 C. or 1625 F., a close-packed, hexagonal microstructure known as the alpha phase, while at this temperature and above, it assumes a bodycentered cubic structure known as the beta phase.
- Aluminum is a promoter or stabilizer of alpha titanium, while each of vanadium, columbium and tantalum, is a promoter or stabilizer of beta titanium. Vanadium, columbium and tantalum are, moreover, beta isomorphous with titanium.
- the alloys of the invention will The above alloys were prepared by are melting in a cold mold furnace in an inert or argon atmosphere.
- the titanium employed was of the commercial purity type as produced by the magnesium reduction of titanium tetrachloride according to the process of the Kroll US. Patent 2,205,854.
- alloys being generally of the beta type, will not tolerate excessive additions of the interstitials carbon, oxygen and nitrogen without embrittlement, ordinarily not more than about 0.2% each or in total amount.
- a titanium base alloy consisting essentially of about 0.5 to 9% aluminum, from more than 15% to about 50% of at least one beta promoter selected from the group consisting of vanadium, columbium and tantalum, balance substantially titanium, characterized in having a minimum bend ductility of not over 20T and a minimum tensile elongation of about 10%.
- a titanium base alloy consisting essentially of about 0.5 to 9% aluminum, from more than 15% to about 50% of at least one beta promoter selected from the group consisting of vanadium, columbium and tantalum, the aluminum content being on the low side of its range when the beta promoter content is on the high side .acteriized in having a minimum bend ductility ofnot over ZOT and a minimum tensile elongation of about 10%.
- a titanium base alloy consisting essentially of about 0.5 to 8% aluminum, from more than 15% to about 40% of tantalum, balance substantially titanium, characterized in having a minimum bend ductility of not over 201 and a minimum tensile elongation of about 10%.
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- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Materials Engineering (AREA)
- Mechanical Engineering (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- Conductive Materials (AREA)
Description
United States Patent TITANIUM BASE ALLOYS No Drawing. Applicationlanuary 23, 1957 Serial No. 635,593
Claims. (Cl. 75-1755) This invention pertains to titanium base alloys con- 2,880,088 V Patented Mar. 31, 1959 "ice have at room temperature either a mixed alpha-beta or an all-beta microstructure depending on the heat treatment. As quenched from above the beta transus,they will have in general a substantially all-beta mierostructure; whereas as annealed" or after cold working, the structure will be mixed alpha-beta, when'the .total' beta promoter content is at the low end ofits range, i.e., from more than to about while for total betapromoter contents above about 20%, the alloys will have a substantially all-beta structure.
The following Table I gives the room temperature tensile properties of representative alloys according to the invention after fabrication at 1600 F. to 40-mil sheet and V1 hour solution heat treatment at 1600 F. and
sisting essentially of about 0.5 to 9% and preferably 15 water quenched.
Table l Tensile Elongation, Average MBR, T Properties, Percent in p.s.1.X1,000 1 inch Percent Com osition, Percent VHN Reduc- (Ba anee Titanium) (Surface) tion in 0.2% Ult. Area (Long.) ('Irans.) Otiset Str. Uniform Total Yield 187 0. 8 0. 8 48 71 21 51 2Ai-1sv 227 0 0 66 96 18 24 32 2Al-24V..-. 251 0 0 92 102 9 12 20 0 5Al-30V 234 1. 0 1 0 102 107 10 26 0.5Al-40V 255 0 0 107 111 10 83 6.75Al38.25 291 0 0 114 115 7 24 8.25Al-40J5V. 317 0. 4/1. 50 10 133 134 10 27 2Al-18Ta 254 0 0. 8 86 104 7 ll 33 2Al24Ta.i- 247 0. 5 1. 0/7. 8 78 106 10 12 28 0 5Al-30Ta- 215 0. 5 1. 0 71 74 15 31 2111-1601) 246 1. 0 1. 7 04 105 13 14 17 2Al-20C 285 0.7 1.1 73 110 14 10 22 2Al-24Cb.. 247 0. 4 3. 0/6/2 73 110 14 16 22 0.5Al-Cb 222 0 0. 8 71 98 20 33 about 0.5 to 8% aluminum and from more than 15% up to about 50% of one or more elements selected from the group consisting of vanadium, columbium and tan talum.
The alloys of the invention on solution treating and quenching from above the beta transus generally are characterized by a relatively low yield strength and by excellent bend ductility and by high uniform and total tensile elongations, and hence are ideally adapted for forming into sheet parts such as skins or wing and body coverings for airplanes and the like, where the ability to stretch uniformly is required. An exception to this behavior are the alloys containing over about 25% vanadium, which do not possess the low yield strength and high uniform elongated characteristic of the other alloys by virtue of the substantial amounts of transformation to martensite they undergo during cold working. However, the alloys with the higher vanadium contents have excellent strength and tensile and bend ductility and are eminently suitable for sheet forming operations, except where the ability to stretch uniformly is required. Thus these alloys in the form of rolled sheet and in the solution treated and quenched condition are easily formed to shape. Thereafter they may be strengthened and hardened by aging at about 300 to 500 C.\ for about 1 to 16 hours.
As is known, pure titanium metal assumes at temperatures below about 885 C. or 1625 F., a close-packed, hexagonal microstructure known as the alpha phase, while at this temperature and above, it assumes a bodycentered cubic structure known as the beta phase.
Aluminum is a promoter or stabilizer of alpha titanium, while each of vanadium, columbium and tantalum, is a promoter or stabilizer of beta titanium. Vanadium, columbium and tantalum are, moreover, beta isomorphous with titanium. Hence the alloys of the invention will The above alloys were prepared by are melting in a cold mold furnace in an inert or argon atmosphere. The titanium employed was of the commercial purity type as produced by the magnesium reduction of titanium tetrachloride according to the process of the Kroll US. Patent 2,205,854.
It will be noted from the data of Table I that these alloys have excellent bend ductilities in both the longitudinal and transverse directions, on the order of 0 to 1 or 2T for most analyses. They also possess high tensile elongations both uniform and total, thus to permit of deep drawing and stretch forming operations. For these operations, bend ductilities up to about 20T and total tensile elongation values down to about 9 or 10% are permissible.
These alloys, being generally of the beta type, will not tolerate excessive additions of the interstitials carbon, oxygen and nitrogen without embrittlement, ordinarily not more than about 0.2% each or in total amount.
This application is a continuation-in-part of application Serial No. 398,868, filed December 17, 1953.
What is claimed is:
1. A titanium base alloy consisting essentially of about 0.5 to 9% aluminum, from more than 15% to about 50% of at least one beta promoter selected from the group consisting of vanadium, columbium and tantalum, balance substantially titanium, characterized in having a minimum bend ductility of not over 20T and a minimum tensile elongation of about 10%.
2. A titanium base alloy consisting essentially of about 0.5 to 9% aluminum, from more than 15% to about 50% of at least one beta promoter selected from the group consisting of vanadium, columbium and tantalum, the aluminum content being on the low side of its range when the beta promoter content is on the high side .acteriized in having a minimum bend ductility ofnot over ZOT and a minimum tensile elongation of about 10%.
5. A titanium base alloy consisting essentially of about 0.5 to 8% aluminum, from more than 15% to about 40% of tantalum, balance substantially titanium, characterized in having a minimum bend ductility of not over 201 and a minimum tensile elongation of about 10%.
References Cited in the file of this patent UNITED STATES PATENTS 2,754,204 Jafiee et al. July 10, 1956
Claims (1)
1. A TITANIUM BASE ALLOY CONSISTING ESSENTIALLY OF ABOUT 0.5 TO 9% ALUMINUM, FROM MORE THAN 15% TO ABOUT 50% OF AT LEAST ONE BETA PROMOTER SELECTED FROM THE GROUP CONSISTING OF VANADIUM, COLUMBIUM AND TANTALUM, BALANCE SUBSTANIALLY TITANIUM, CHARACTERIZED IN HAVING A MINIMUM BEND DUCTILITY OF NOT OVER 20T AND A MINIMUM TENSILE ELONGATION OF ABOUT 10%
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US635593A US2880088A (en) | 1957-01-23 | 1957-01-23 | Titanium base alloys |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US635593A US2880088A (en) | 1957-01-23 | 1957-01-23 | Titanium base alloys |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| US2880088A true US2880088A (en) | 1959-03-31 |
Family
ID=24548398
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| US635593A Expired - Lifetime US2880088A (en) | 1957-01-23 | 1957-01-23 | Titanium base alloys |
Country Status (1)
| Country | Link |
|---|---|
| US (1) | US2880088A (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3161503A (en) * | 1961-09-27 | 1964-12-15 | Titanium Metals Corp | Corrosion resistant alloy |
| US3411901A (en) * | 1964-02-15 | 1968-11-19 | Defense Germany | Alloy |
| US3441407A (en) * | 1964-03-11 | 1969-04-29 | Imp Metal Ind Kynoch Ltd | Titanium-base alloys |
| US4292077A (en) * | 1979-07-25 | 1981-09-29 | United Technologies Corporation | Titanium alloys of the Ti3 Al type |
| US4788035A (en) * | 1987-06-01 | 1988-11-29 | General Electric Company | Tri-titanium aluminide base alloys of improved strength and ductility |
Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2754204A (en) * | 1954-12-31 | 1956-07-10 | Rem Cru Titanium Inc | Titanium base alloys |
-
1957
- 1957-01-23 US US635593A patent/US2880088A/en not_active Expired - Lifetime
Patent Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2754204A (en) * | 1954-12-31 | 1956-07-10 | Rem Cru Titanium Inc | Titanium base alloys |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3161503A (en) * | 1961-09-27 | 1964-12-15 | Titanium Metals Corp | Corrosion resistant alloy |
| US3411901A (en) * | 1964-02-15 | 1968-11-19 | Defense Germany | Alloy |
| US3441407A (en) * | 1964-03-11 | 1969-04-29 | Imp Metal Ind Kynoch Ltd | Titanium-base alloys |
| US4292077A (en) * | 1979-07-25 | 1981-09-29 | United Technologies Corporation | Titanium alloys of the Ti3 Al type |
| US4788035A (en) * | 1987-06-01 | 1988-11-29 | General Electric Company | Tri-titanium aluminide base alloys of improved strength and ductility |
| EP0293689A3 (en) * | 1987-06-01 | 1990-01-31 | General Electric Company | Tri-titanium aluminide base alloys of improved strength and ductility |
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