US2596485A - Titanium base alloy - Google Patents
Titanium base alloy Download PDFInfo
- Publication number
- US2596485A US2596485A US198917A US19891750A US2596485A US 2596485 A US2596485 A US 2596485A US 198917 A US198917 A US 198917A US 19891750 A US19891750 A US 19891750A US 2596485 A US2596485 A US 2596485A
- Authority
- US
- United States
- Prior art keywords
- alloys
- titanium
- titanium base
- ductility
- base alloy
- 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
Links
- 229910045601 alloy Inorganic materials 0.000 title claims description 21
- 239000000956 alloy Substances 0.000 title claims description 21
- 239000010936 titanium Substances 0.000 title claims description 17
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 title claims description 16
- 229910052719 titanium Inorganic materials 0.000 title claims description 16
- VYZAMTAEIAYCRO-UHFFFAOYSA-N Chromium Chemical compound [Cr] VYZAMTAEIAYCRO-UHFFFAOYSA-N 0.000 claims description 8
- ZOKXTWBITQBERF-UHFFFAOYSA-N Molybdenum Chemical compound [Mo] ZOKXTWBITQBERF-UHFFFAOYSA-N 0.000 claims description 8
- 229910052782 aluminium Inorganic materials 0.000 claims description 8
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims description 8
- 229910052804 chromium Inorganic materials 0.000 claims description 8
- 239000011651 chromium Substances 0.000 claims description 8
- 229910052750 molybdenum Inorganic materials 0.000 claims description 8
- 239000011733 molybdenum Substances 0.000 claims description 8
- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 description 10
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 description 5
- 229910052757 nitrogen Inorganic materials 0.000 description 5
- 229910052760 oxygen Inorganic materials 0.000 description 5
- 239000001301 oxygen Substances 0.000 description 5
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 4
- 229910052799 carbon Inorganic materials 0.000 description 4
- 229910002059 quaternary alloy Inorganic materials 0.000 description 3
- 239000010953 base metal Substances 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 238000002791 soaking Methods 0.000 description 2
- 238000003860 storage Methods 0.000 description 2
- 241000331231 Amorphocerini gen. n. 1 DAD-2008 Species 0.000 description 1
- 229910001069 Ti alloy Inorganic materials 0.000 description 1
- 238000007792 addition Methods 0.000 description 1
- 230000032683 aging Effects 0.000 description 1
- 238000000137 annealing Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000001816 cooling Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005242 forging Methods 0.000 description 1
- XMBWDFGMSWQBCA-UHFFFAOYSA-N hydrogen iodide Chemical compound I XMBWDFGMSWQBCA-UHFFFAOYSA-N 0.000 description 1
- 239000012535 impurity Substances 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 229910052751 metal Inorganic materials 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000002360 preparation method Methods 0.000 description 1
- 230000002035 prolonged effect Effects 0.000 description 1
- 238000010791 quenching Methods 0.000 description 1
- 230000000171 quenching effect Effects 0.000 description 1
- 230000000717 retained effect Effects 0.000 description 1
- 238000005096 rolling process Methods 0.000 description 1
- 238000010583 slow cooling Methods 0.000 description 1
- 230000002311 subsequent effect Effects 0.000 description 1
- 239000000126 substance Substances 0.000 description 1
- 230000009466 transformation Effects 0.000 description 1
- 230000001131 transforming effect 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
- C22C14/00—Alloys based on titanium
Definitions
- This invention relates to titanium base alloys, and contemplates certain structurally useful quaternary alloys of titanium with aluminum, chromium and molybdenum, as well as a pro- 2 0.5%, if the alloys are to possess good ductility as cast or as Worked and annealed.
- certain ductile alloys of vention are quaternary alloys containing from titanium with aluminum and chromium; also about 2% to about 5% aluminum, 1% to 6% chroseveral alloys of titanium and aluminum with mium and 1% to 6% molybdenum, as additions relatively small amounts of chromium and to a titanium base which may be of high purity or molybdenum.
- the present application is a conmay contain up to 0.15% nitrogen, 0.25% oxygen tinuation-in-part of Application Serial No. /or car n; he t l itro y 122,576.
- ll ys are of hi h t il str h. alloys may contain substances or impurities beand of such ductility as to permit their forming sides titanium, as normally found in either high and fabrication by the usual metallurgical procpurity titanium or commercially pure titanium.
- esses such as rolling, drawing and forging. If It may be, for example, a high purity or iodide y the combined content of chromium and molybprocess titanium, as produced according to the denum is relatively low, say about 2.5%, the alloy Van Arkel U. S. Patent No. 1,671,213.
- Altermay b prepared for use by quenching from a natively it may be a commercial titanium, as temperatureof 850 C. to 950 C., and thereafter produced, for example, by magnesium-reduction annealing.
- Typical alloys of this group, and processes, such as the process of U. S. Patent No. their properties, are as follows:
- alloys containing for example aluminum and 4% each of chromium and molybdenum were inherently too b-rittle for structural use. It has been found, however, that if such alloys are slowly cooled from a temperature. high in the two-phase field or within" the all-beta field, say 850 C. t0 950 0., they are not only ductile as cooled but substantially retain their ductility after prolonged eX- posure to temperatures as high as 400 C. In. a typical processing, the alloy is heated to9'00 C., and retained at this temperature for about threequarters of an hour.
- the resulting alloys are not only ductile but remain ductile" upon subse quent' exposure to elevated temperatures such as 300 or 400C.
- the slowcooling has the effect of transforming a maximum amount of the metal from the high temperature beta phase to the lowtemperature alpha phase, thus avoiding the embrittling coherency hardening brought about by the aging transformation of the-unstable beta of quenched alloys;
- Bend ductility is a more severe and practical test of utility than is tensile elongation. Bend ductility is measured as the radius, expressed as a multiple of specimen thickness, at which the specimen can be bent" to an angle of without fracture Typical alloys" withinthe present invention, their hardness and bend ductility; as cooled in themanner above described and afterelevated l temperature exposure, areas follows:
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- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Materials Engineering (AREA)
- Mechanical Engineering (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- Forging (AREA)
Description
Patented May 13, 1952 TITANIUM BASE ALLOY Robert I. Jaffee and Horace It. Ogden, Columbus,
1 Ohio, assignors, by mesne assignments, to Remington Arms Company, Inc., Bridgeport, Conn, a corporation of Delaware No Drawing. Application December 2, 1950, Serial No. 198,917
4 Claims.
1 This invention relates to titanium base alloys, and contemplates certain structurally useful quaternary alloys of titanium with aluminum, chromium and molybdenum, as well as a pro- 2 0.5%, if the alloys are to possess good ductility as cast or as Worked and annealed.
It has been 'found, however, that the presence of a small amount of carbon, say 0.05% to 0.3%,
cess for the preparation of such alloys in a ductile 5 with or without 0.01% to 0.15% nitrogen or 0.01% condition. to 0.25% oxygen, or both oxygen and nitrogen, In application of Jafiee and Ogden, Serial No. may be beneficial. Among the alloys of this in- 122,5'77, filed October 20, 1949, now Patent No. vention are those made either with a commer- 2,554,031, issued May 22, 1951, there are disclosed cial titanium base meeting such specifications, or certain structural alloys containin aluminum with a high purity titanium base containing simiand molybdenum. In the application of Jaiiee lar amounts of added carbon, oxygen and/or and Ogden, Serial No. 122,576, filed October 20, nitrogen. Thus, within the purview of the in- 1949, there are disclosed certain ductile alloys of vention are quaternary alloys containing from titanium with aluminum and chromium; also about 2% to about 5% aluminum, 1% to 6% chroseveral alloys of titanium and aluminum with mium and 1% to 6% molybdenum, as additions relatively small amounts of chromium and to a titanium base which may be of high purity or molybdenum. The present application is a conmay contain up to 0.15% nitrogen, 0.25% oxygen tinuation-in-part of Application Serial No. /or car n; he t l itro y 122,576. and carbon content preferably not exceeding The titanium base metal used in the present 29 0.5% These ll ys are of hi h t il str h. alloys may contain substances or impurities beand of such ductility as to permit their forming sides titanium, as normally found in either high and fabrication by the usual metallurgical procpurity titanium or commercially pure titanium. esses, such as rolling, drawing and forging. If It may be, for example, a high purity or iodide y the combined content of chromium and molybprocess titanium, as produced according to the denum is relatively low, say about 2.5%, the alloy Van Arkel U. S. Patent No. 1,671,213. Altermay b prepared for use by quenching from a natively, it may be a commercial titanium, as temperatureof 850 C. to 950 C., and thereafter produced, for example, by magnesium-reduction annealing. Typical alloys of this group, and processes, such as the process of U. S. Patent No. their properties, are as follows:
Tensile properties Compo ition wi l: Propor 01? 027 C13}; 513;; (BalanceTi) Hard- Limit OiIS t Oiis t ig gm QEZ 11035 in ti 2,205,854, to Kroll, or modifications thereof; provided that the carbon, oxygen and nitrogen contents of these alloys, hence of the base metal, should not exceed 0.5%, 0.25% and 0.15% respectively, nor should they total more than about Quaternary alloys having a, higher content of molybdenum and/or chromium, as quenched from the all-beta field, possess acceptable ductility, but are severely embrittled by subsequent :55 exposure to moderately elevated temperatures.
Hitherto it has been believed that alloys containing for example aluminum and 4% each of chromium and molybdenum were inherently too b-rittle for structural use. It has been found, however, that if such alloys are slowly cooled from a temperature. high in the two-phase field or within" the all-beta field, say 850 C. t0 950 0., they are not only ductile as cooled but substantially retain their ductility after prolonged eX- posure to temperatures as high as 400 C. In. a typical processing, the alloy is heated to9'00 C., and retained at this temperature for about threequarters of an hour. Thereafter; it isccol'ed at a rate of about 1 per minute to a temperature oi about 500 C., after which cooling may be more rapid. The soaking may be; performed.- in an electric furnace and, after soaking, the furnace control set back 60 every hour until the tempera= ture is below about 500 C., after which the heat is turned completely off, the workremaining in the furnace until both are reduced substantially to room temperature. The resulting alloys are not only ductile but remain ductile" upon subse quent' exposure to elevated temperatures such as 300 or 400C. The slowcooling has the effect of transforming a maximum amount of the metal from the high temperature beta phase to the lowtemperature alpha phase, thus avoiding the embrittling coherency hardening brought about by the aging transformation of the-unstable beta of quenched alloys;
Bend ductility is a more severe and practical test of utility than is tensile elongation. Bend ductility is measured as the radius, expressed as a multiple of specimen thickness, at which the specimen can be bent" to an angle of without fracture Typical alloys" withinthe present invention, their hardness and bend ductility; as cooled in themanner above described and afterelevated l temperature exposure, areas follows:
Delayedcooling from 9001 0.
4 It will be seen that not only are these alloys ductile in the slow cooled condition, but that they largely retain their ductility after as much as 200 hours storage at 400 C. The same alloys in as quenched condition show hardness and ductility comparablewith' the slow cooled'icondition. but storage for 64 hours at 300 C.', raises average Vickers hardness well over points and virtually destroys all bend ductility. It is' thus in slow-cooled, or slow-cooled and aged condition,
to 5% aluminum/1% chromium, 4% molybdenum, balance titanium.
ROBERT L JAFFEE. HORACE a. OGDEN.
REFERENCES CITE-D The following references are of reoordi in the file of this patent:
UNITED STATES PATENTS Number Name Date 2,188,765 Young; Jam 30.19% 2,467,367 Austin Apr. 1 95.19.49 2,490,571 Anicetti -a. ....,Dec"-. 6-,,1949 2,554,031! Jaffee etal. an.-- May 22;. i
V Befbr-fistbraga l Storegfiggmat storciugllldiirsrat CotmiosltiorMBal emcee-Ti): I
Vlckers Bend Vickers Bend Vickers Bend- Hardness Radius: Hardness Radius: Hardness Radius" T v T T s55 2.0 362 j 2.2 V 382 6.7
347 as 390 2. (i 385 1 8:1
Claims (1)
1. A DUCTILE ALLOY CONSISTING ESSENTIALLY OF 2% TO 5% ALUMINUM, 1% TO 6% CHROMIUM, 1% TO 6% MOLYBDENUM, BALANCE TITANIUM.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US198917A US2596485A (en) | 1950-12-02 | 1950-12-02 | Titanium base alloy |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US198917A US2596485A (en) | 1950-12-02 | 1950-12-02 | Titanium base alloy |
Publications (1)
Publication Number | Publication Date |
---|---|
US2596485A true US2596485A (en) | 1952-05-13 |
Family
ID=22735432
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US198917A Expired - Lifetime US2596485A (en) | 1950-12-02 | 1950-12-02 | Titanium base alloy |
Country Status (1)
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US (1) | US2596485A (en) |
Cited By (10)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2810643A (en) * | 1953-08-13 | 1957-10-22 | Allegheny Ludlum Steel | Titanium base alloys |
US2829974A (en) * | 1952-10-08 | 1958-04-08 | Rem Cru Titanium Inc | Titanium-base alloys |
US2860079A (en) * | 1955-05-25 | 1958-11-11 | Gen Electric | Heat treating process for a 2% fe 2% cr 2% mo titanium base alloy |
US2860078A (en) * | 1955-05-25 | 1958-11-11 | Gen Electric | Heat treatment for titanium base alloy, circa 4% mn, and 4% al |
US2920957A (en) * | 1957-06-20 | 1960-01-12 | Chicago Dev Corp | Alloys of titanium-group metals |
DE1120152B (en) * | 1952-11-01 | 1961-12-21 | Crucible Steel Co America | Ternary or higher alloys based on titanium |
US3405016A (en) * | 1956-04-11 | 1968-10-08 | Crucible Steel Co America | Heat treatable titanium base alloys and method |
FR2616448A1 (en) * | 1987-04-22 | 1988-12-16 | Nippon Kokan Kk | HIGH-STRENGTH AND CORROSION-RESISTANT TITANIUM ALLOY HAVING EXCELLENT CORROSION WEAR RESISTANCE PROPERTIES |
US5587259A (en) * | 1994-03-09 | 1996-12-24 | Rayovac Corporation | Metal-air cathode and cell having a hardened current collecting substrate |
US6531091B2 (en) * | 2000-02-16 | 2003-03-11 | Kobe Steel, Ltd. | Muffler made of a titanium alloy |
Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2188765A (en) * | 1938-05-31 | 1940-01-30 | Laminated Shim Co Inc | Method of heat treating brass shims and shim stock |
US2467367A (en) * | 1948-06-08 | 1949-04-19 | Frank B Austin | Heat-treatment for metal articles |
US2490571A (en) * | 1948-12-29 | 1949-12-06 | Metal Hydrides Inc | Pyrophoric alloy of zirconium, lead, and titanium, and sparking device containing the same |
US2554031A (en) * | 1949-10-20 | 1951-05-22 | Remington Arms Co Inc | Titanium base alloy |
-
1950
- 1950-12-02 US US198917A patent/US2596485A/en not_active Expired - Lifetime
Patent Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2188765A (en) * | 1938-05-31 | 1940-01-30 | Laminated Shim Co Inc | Method of heat treating brass shims and shim stock |
US2467367A (en) * | 1948-06-08 | 1949-04-19 | Frank B Austin | Heat-treatment for metal articles |
US2490571A (en) * | 1948-12-29 | 1949-12-06 | Metal Hydrides Inc | Pyrophoric alloy of zirconium, lead, and titanium, and sparking device containing the same |
US2554031A (en) * | 1949-10-20 | 1951-05-22 | Remington Arms Co Inc | Titanium base alloy |
Cited By (11)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2829974A (en) * | 1952-10-08 | 1958-04-08 | Rem Cru Titanium Inc | Titanium-base alloys |
DE1120152B (en) * | 1952-11-01 | 1961-12-21 | Crucible Steel Co America | Ternary or higher alloys based on titanium |
US2810643A (en) * | 1953-08-13 | 1957-10-22 | Allegheny Ludlum Steel | Titanium base alloys |
US2860079A (en) * | 1955-05-25 | 1958-11-11 | Gen Electric | Heat treating process for a 2% fe 2% cr 2% mo titanium base alloy |
US2860078A (en) * | 1955-05-25 | 1958-11-11 | Gen Electric | Heat treatment for titanium base alloy, circa 4% mn, and 4% al |
US3405016A (en) * | 1956-04-11 | 1968-10-08 | Crucible Steel Co America | Heat treatable titanium base alloys and method |
US2920957A (en) * | 1957-06-20 | 1960-01-12 | Chicago Dev Corp | Alloys of titanium-group metals |
FR2616448A1 (en) * | 1987-04-22 | 1988-12-16 | Nippon Kokan Kk | HIGH-STRENGTH AND CORROSION-RESISTANT TITANIUM ALLOY HAVING EXCELLENT CORROSION WEAR RESISTANCE PROPERTIES |
US5587259A (en) * | 1994-03-09 | 1996-12-24 | Rayovac Corporation | Metal-air cathode and cell having a hardened current collecting substrate |
US5637117A (en) * | 1994-03-09 | 1997-06-10 | Rayovac Corporation | Method of hardening a metal current collecting strip of an air cathode and a method of making a button type battery |
US6531091B2 (en) * | 2000-02-16 | 2003-03-11 | Kobe Steel, Ltd. | Muffler made of a titanium alloy |
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