US2822268A - Compositions of matter - Google Patents
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- US2822268A US2822268A US601341A US60134156A US2822268A US 2822268 A US2822268 A US 2822268A US 601341 A US601341 A US 601341A US 60134156 A US60134156 A US 60134156A US 2822268 A US2822268 A US 2822268A
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- niobium
- alloy
- titanium
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- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C27/00—Alloys based on rhenium or a refractory metal not mentioned in groups C22C14/00 or C22C16/00
- C22C27/02—Alloys based on vanadium, niobium, or tantalum
Definitions
- TZiilitims (C1, 75- 174) This 'invefition relates fto "niobium-base alloys, and more particularly "to "niobium base “alloys containing titanium and. at least one'o'ther' element of thegronpcom (prising aluminumfberyllium, carbon, cobalt,-*iron, man- 'ganese,"'mo1y.bdenum, nickeL: silicon, tantalum, tungsten, "vanadium-and zirconium. v
- a combination-of workability, high temperature strength, and high temperature corrosionre sistance in an alloy has -'proved difii'c'ult to achieve,- and considerable time and efiforthave been dev'oted to the search for such metals.
- Ar'tother object of m'y invention is to provide' niobium- -base alloys which are responsive to heat-treatment.
- Aribtlier bject ofi my' -iiiveiitibn is to prdduee nieuiumb'ase alldys -"to wuieh a film or -metal oXide will fiimly adhere when the alloy is heated to relativel hi gh tempei'a'tur'es arid-cooled.
- Other ob'jeCts arid advantages of theupresent invention will be 1 apparent in VieW of the following-detailed descriptions thereof.
- meltingequipmnt Any of a number of types of meltingequipmnt may be used to prepare wthese newlalloys. lnutherspecificaexamples which'iappear daternini this i specification, an :arc melting s furnactzvotvthe type describedtbyawsKrolluin "iT'ransa'cfions. @flthEtElEC- trochemic-al 'Sd'cietyft'veil. r7 8,:'1p.-.,"35'-47, 1940,- was;11seid.
- This furnace has an integral, water-cooled copper crucible in which the charge mayBeLrnIted and solidified.
- A-eentinuous "fee'di't rnace such as listle- "'scfibedlinU..,S.;P..B..Report 111,083 would :also prepare 'TtheallQYs. Eurther'mormlmel ting.could be accomplished by inductively heating the charge"in.a suitablecrumaschine. Regardless of the melting apparatus used, care should be exercised to protect the' ir'io'lten metals from the normal atmosphere since-tcontaminatiomofi.theualloyabywoxygen, wnitrogen, ;etc., is -to-,be avoided.
- themeltirggashohldrbe:aearriedqo t underqinertcondition s such: asa-ane atmosphere efmrgon or a protective slag or a combination ;of:-,a'iprotect-ive slag and a controlled atmosphere.
- an inert atmosphere sudh as'argonf'helium, etc., when melting v me tals, iscwell known'iinttheiart.
- the "melting apparatus was an ard meltiijg furnace having .an zintegral, Mater-cooled eepp'er cru'eible, t as described ⁇ by eZKrou -in the fTraasactions of the lElect-roche'mieal '80- emery" publication reterrew to abeve.
- a weighedsampleof the-alloy (in aj'po'reelainerucible -Which'is slottedf'to" insn readequate access lfiair to 'the ingot) is p'laeed-inafG1obartfumace andreigposedltor at least 16 hours atl-OOO C. totinbiif'piirge em cu. tt/min. After exposure, the isample is cooled and weighed,,and the amount-.ofpxidatiomis determined as the percent 'weightggaid in" the, sa ple,
- Example 11 maintained and the alloy composition was alternately remelted and solidified six times, whereupon a homogeneous ingot was obtained.
- the weight gain according to the test described in Example I was 2.5%.
- Example Ill Using'the procedure of Example II, an alloy of the following composition was prepared: 20% titanium, 10% aluminum and 70% niobium. The weight gain according to the test described in Example I was 1.7%.
- Example IV Using the procedure of Example H, an alloy of the following'composition was prepared: 80% niobium, 17% titanium, 1% tungsten, 0.5% beryllium, 1.5% tantalum. The weight gain according to the test described in Example I was 2.0%.
- Example V Using the procedure of Example H, an alloy of the following composition was prepared: 55% niobium, 29% titanium, manganese, molybdenum, 1% aluminum. The weight gain according to the test described in Example I was 1.3%.
- Example VI Using the procedure of Example II, an alloy of the following composition was prepared: 78% niobium, 13.5% titanium, 3% aluminum, 2.5% iron, 3% molybdenum. The weight gain according to the test described in Example I was 2.2%.
- Example VII Using the procedure of Example II, an alloy of the following composition was prepared: 70% niobium, 16% titanium, 4% aluminum, 2% iron, 5% molybdenum, 3% beryllium. The weight gain according to the test described in Example I was 1.8%.
- Example VIII Using the procedure of Example H, an alloy of the following composition was prepared: 80% niobium, titanium, 1% silicon, 4% aluminum. The weight gain according to the test described in Example I was 2.0%.
- Example IX Using the procedure of Example II, an alloy of the following composition was prepared: 65% niobium, 15% titanium, 15 molybdenum, 5% aluminum. The weight gain according to the test described in Example I was 2.2%.
- Example X Using the procedure of Example II, an alloy of the following composition was prepared: 90% niobium, 7% titanium, 3% aluminum. The weight gain according to the test described in Example I was 2.5%.
- Example XI Example XII Using the procedure of Example II, an alloy of the following composition was prepared: 80% niobium, 5% titanium, 2.5% iron, 2.5% molybdenum, 10% aluminum. The weight gain according to the test described i E amplelwas 2.1%.
- Example XIII Using the procedure of Example II, an alloy of the following composition was prepared: 70% niobium, 10% titanium, 8% vanadium, 6% molybdenum, 6% aluminum. The weight gain according to the test described in Example I was 1.5
- Example XIV Using the procedure of Example II, an alloy of the following composition was prepared: 70% niobium, 15% titanium, 3.5% iron, 4.5% aluminum, 7% molybdenum. The weight gain according to the test described in Example I was 1.9.
- alloys of the working examples are made from commercially available metals containing less than 1% incidental impurities.
- Commercial niobium nearly always contains tantalum (usually in amounts up to 5%) which is hard to detect and very difficult to separate. Therefore, the niobium used in the specific examples no doubt contained tantalum which is reported as niobium rather than as an incidental impurity.
- this invention contemplates the addition of tantalum to the alloy composition in amounts up to 20%.
- the alloys of this invention have the advantages of strength at high temperatures, ease of. working, and resistance to corrosion. In addition to these advantageous properties, these alloys are superior base metals since they have resistance to oxidative deterioration at high temperatures. This property has been particularly deficient in niobium metal. These alloys are suitable for many diverse applications. Among these are the construction of pieces of equipment which must operate above 800 C.
- a niobium base alloy comprising about 1-30% b weight of titanium, about O10% by weight of aluminum, about 05% by weight of beryllium, about 02% by weight of carbon, about 0-5% by weight of cobalt, about 0-10% by weight of iron, about 010% by weight of manganese, about 0-20% by weight of molybdenum, about 05% by weight of nickel, about 0-2% by weight of silicon, about 0-20% by weight of tantalum, about 0-5% by weight of tungsten, about 0-10% by weight of vanadium, and about 020% by weight of zirconium, the'sum total of Al, Be, C, Co, Fe, Mn, Mo, Si, Ni, Ta, W, V and Zr ranging from about 1-20% by weight, the balance being essentially niobium.
- a niobium base alloy comprising about 5-25% by weight of titanium, about 05% by weight of aluminum, about 0 5 by weight of nickel, about 0-5 by weight of iron, about 07% by weight of molybdenum, the sum total of Al, Ni, Fe and Mo'being about 4-20% by Weight, the balance being essentially niobium.
Description
United States Patent :z,sz2,z6s
COMPOSITIONS or MATTER Hugh B. Hix, Wilmington, DeL, .assignor to E. I. duPont deNemours and-Company; Wilmington, Del.,"a corpo- "ratio'njof Delaware Nd-Drawing. Applicatiornarugustt 1,1956 Serial No. 601,341
TZiilitims. (C1, 75- 174) This 'invefition relates fto "niobium-base alloys, and more particularly "to "niobium base "alloys containing titanium and. at least one'o'ther' element of thegronpcom (prising aluminumfberyllium, carbon, cobalt,-*iron, man- 'ganese,"'mo1y.bdenum, nickeL: silicon, tantalum, tungsten, "vanadium-and zirconium. v
Superior,"workable' alloys which possess strength and oxidation resistance 'athigh temperature are used "as materials "Ioffcons'truction in 'all types of-technical and industrial e uipment. The' development efmor adva need nuclear reactors and gas turbines is dependent u ion thefava'ilabil'ity OfiSllCh' alloys. Furthermore, there is a need 'for betterj high temperature alloys in theconstruction of di'es for high temperature working ofm'etals and the-construction ofchemical reactors, oil refining e'quir'a'me'ntflnd"the like. A combination-of workability, high temperature strength, and high temperature corrosionre sistance in an alloy has -'proved difii'c'ult to achieve,- and considerable time and efiforthave been dev'oted to the search for such metals.
Ithas nowbeenfound 'that workable alloys possessin unusually high corrosionresistance'and strength at temperatures above ll00" C.can 'be produced by alloying titanium a'tid' 'niobium"and'specifid' added elements 'inthe aniounts seftorth herein. 7
u i-s, th'e'retore,'=an object of this invention to provide ear the I production of =ni6bium base --'all'oys which are paft iciilarly =re'sistai1t to h-igh temperatu're oxidation. Ar'tother object of m'y invention is to provide' niobium- -base alloys which are responsive to heat-treatment. Aribtlier bject ofi my' -iiiveiitibn is to prdduee nieuiumb'ase alldys -"to wuieh a film or -metal oXide will fiimly adhere when the alloy is heated to relativel hi gh tempei'a'tur'es arid-cooled. Other ob'jeCts arid advantages of theupresent invention will be 1 apparent in VieW of the following-detailed descriptions thereof.
The v alloys of this t invention comprise eoiiipositio'ns t eoritaining about "-1--30% by weight of titaiiium, -about 01T6%iby'we'ight' :of alununum, about 0+5% by-"Weight of beryllium, about 0-2% by weight of ca'rbOnJabout "by*weight-of cobalt,'-about -=0 10% by' weight of iron, .zabout ii-40% by "weight of manganese, 'about fa rtim -2thout l 14 -byweight," the balance being essenriallyuniobium. g
il-rt a mo're preferred embodiment' thealloy T'of-thisinfollow conventional 'me'tal "meltingand reme'lting' 'te'ch- 'ice 2 eniques usingwinertgcoriditions. Measured amounts of a the individual-metal constituents are melted together, solidified and remelted 'until homogeneity is :obtained. The final melt .thenallowe-d.tocoolandsolidify into a 5 .klesired shape. aThe ease materialzthus obtainedtis ,of. a -workablemetal rwi-thstrengthand oxidation. resistance at high temperatures,-and it is suitablerasia material oficonstruction in high temperature equipment. Any of a number of types of meltingequipmnt may be used to prepare wthese newlalloys. lnutherspecificaexamples which'iappear daternini this i specification, an :arc melting s furnactzvotvthe type describedtbyawsKrolluin "iT'ransa'cfions. @flthEtElEC- trochemic-al 'Sd'cietyft'veil. r7 8,:'1p.-.,"35'-47, 1940,- was;11seid. This furnace has an integral, water-cooled copper crucible in which the charge mayBeLrnIted and solidified. The @harge iaiif nlletal constituents for' 'thiwf-i-1rna'ee' maybe in an eofivenient renn, e *g povvde shoh wiregsponge, ete. A consumable arc"electrdde furnaee as describdf in U. S. Patent 2640860 is another' apparatus which would prove suitable. Also, one could use a cotnbination of non-consumable and consumable electrodes in a double melt furnace such has ..is described .in U. S. :Patent 12,541,764. A-eentinuous "fee'di't rnace such as listle- "'scfibedlinU..,S.;P..B..Report 111,083 would :also prepare 'TtheallQYs. Eurther'mormlmel ting.could be accomplished by inductively heating the charge"in.a suitablecru cible. Regardless of the melting apparatus used, care should be exercised to protect the' ir'io'lten metals from the normal atmosphere since-tcontaminatiomofi.theualloyabywoxygen, wnitrogen, ;etc., is -to-,be avoided. To -provide proteetion .againsta'contamination, themeltirggashohldrbe:aearriedqo t underqinertcondition s,-: such: asa-ane atmosphere efmrgon or a protective slag or a combination ;of:-,a'iprotect-ive slag and a controlled atmosphere. The practice of using an inert atmosphere sudh as'argonf'helium, etc., when melting v me tals, iscwell known'iinttheiart.
:Thevfo'llbwingiexamplesiaretgpresentedt to illustrate the upreparation of rspecific valleys of uthisuinveiitionuandtthe -outstanding cpropet tiesmf =t-heseitall'oysr These' eitatnples are illustrative only andnarelnotato be consttued as litniting the invention. --All, percentsvset forth in the ensuing examples refer to percents by weight.
.TExamplcII g -Aruniform melticontainingl 23 titanium, m ma-rel, 3 aluminum and 7 nib-him;waepreparednuy meuin the elemental metals--together and then alternately solidifying and remelting the alloy composition six times. The "melting apparatus was an ard meltiijg furnace having .an zintegral, Mater-cooled eepp'er cru'eible, t as described {by eZKrou -in the fTraasactions of the lElect-roche'mieal '80- emery" publication reterrew to abeve. 1 Apoit'ion ,fiffthe melt was poured into a water-cooled copper mold having a cylindrical cavity 4' intdiameter and 2" deep. During 5 the above-described operations an atmosphere of. helium Was maintained ahtive "the inetals'ito 'jmev'eint contamination. une:castingireenveredrrern me maid was" forged and -maehinedtntq -anozzle for sprayingdnolten salts; s'uch as MgCl inchemical rocesses. I 6 The alloy compositionpoftthis example Was tested for high temperature oxidation ,resistance by thegfollowing procedure: i
A weighedsampleof the-alloy (in aj'po'reelainerucible -Which'is slottedf'to" insn readequate access lfiair to 'the ingot) is p'laeed-inafG1obartfumace andreigposedltor at least 16 hours atl-OOO C. totinbiif'piirge em cu. tt/min. After exposure, the isample is cooled and weighed,,and the amount-.ofpxidatiomis determined as the percent 'weightggaid in" the, sa ple,
Under thesecoriditions' "the alloy showdsawei ghtpgain of Unallo'yednidbiumfshows,a weight,gain .'of26% "under theh'airiie conditions.
Example 11 maintained and the alloy composition was alternately remelted and solidified six times, whereupon a homogeneous ingot was obtained. The weight gain according to the test described in Example I was 2.5%.
Example Ill Using'the procedure of Example II, an alloy of the following composition was prepared: 20% titanium, 10% aluminum and 70% niobium. The weight gain according to the test described in Example I was 1.7%.
Example IV Using the procedure of Example H, an alloy of the following'composition was prepared: 80% niobium, 17% titanium, 1% tungsten, 0.5% beryllium, 1.5% tantalum. The weight gain according to the test described in Example I was 2.0%.
Example V Using the procedure of Example H, an alloy of the following composition was prepared: 55% niobium, 29% titanium, manganese, molybdenum, 1% aluminum. The weight gain according to the test described in Example I was 1.3%.
Example VI Using the procedure of Example II, an alloy of the following composition was prepared: 78% niobium, 13.5% titanium, 3% aluminum, 2.5% iron, 3% molybdenum. The weight gain according to the test described in Example I was 2.2%.
Example VII Using the procedure of Example II, an alloy of the following composition was prepared: 70% niobium, 16% titanium, 4% aluminum, 2% iron, 5% molybdenum, 3% beryllium. The weight gain according to the test described in Example I was 1.8%.
Example VIII Using the procedure of Example H, an alloy of the following composition was prepared: 80% niobium, titanium, 1% silicon, 4% aluminum. The weight gain according to the test described in Example I was 2.0%.
Example IX Using the procedure of Example II, an alloy of the following composition was prepared: 65% niobium, 15% titanium, 15 molybdenum, 5% aluminum. The weight gain according to the test described in Example I was 2.2%.
Example X Using the procedure of Example II, an alloy of the following composition was prepared: 90% niobium, 7% titanium, 3% aluminum. The weight gain according to the test described in Example I was 2.5%.
Example XI Example XII Using the procedure of Example II, an alloy of the following composition was prepared: 80% niobium, 5% titanium, 2.5% iron, 2.5% molybdenum, 10% aluminum. The weight gain according to the test described i E amplelwas 2.1%.
Example XIII Using the procedure of Example II, an alloy of the following composition was prepared: 70% niobium, 10% titanium, 8% vanadium, 6% molybdenum, 6% aluminum. The weight gain according to the test described in Example I was 1.5
Example XIV Using the procedure of Example II, an alloy of the following composition was prepared: 70% niobium, 15% titanium, 3.5% iron, 4.5% aluminum, 7% molybdenum. The weight gain according to the test described in Example I was 1.9.
Although it is preferable to use metals which are of a high purity, a fair amount of variance in purity can be tolerated before product quality suifers appreciably. The
alloys of the working examples are made from commercially available metals containing less than 1% incidental impurities. Commercial niobium nearly always contains tantalum (usually in amounts up to 5%) which is hard to detect and very difficult to separate. Therefore, the niobium used in the specific examples no doubt contained tantalum which is reported as niobium rather than as an incidental impurity. In addition to the tantalum which is present in commercial niobium, this invention contemplates the addition of tantalum to the alloy composition in amounts up to 20%. Those skilled in the art are readily aware of the presence of incidental impurities in commercial metals and of the presence of tantalum in commercial niobium, and these facts should be taken into consideration when practicing the invention and construing the claims.
The alloys of this invention have the advantages of strength at high temperatures, ease of. working, and resistance to corrosion. In addition to these advantageous properties, these alloys are superior base metals since they have resistance to oxidative deterioration at high temperatures. This property has been particularly deficient in niobium metal. These alloys are suitable for many diverse applications. Among these are the construction of pieces of equipment which must operate above 800 C.
Particular stress has been laid upon the use of these alloys in high temperature equipment, such as jet engine parts, nuclear reactor and gas turbine parts because of their outstanding properties. However, it should be emphasized that its use is not limited to high temperature conditions or to any piece of equipment described herein.
Since it is obvious that many changes and modifications can be made in the above-described details without departing from the nature and spirit of the invention, it is to be understood that the invention is not to be limited to said details except as set forth in the appended claims.
This case is a continuation in part of my copending application Serial No. 550,764, filed December 2, 1955.
I claim:
1. A niobium base alloy comprising about 1-30% b weight of titanium, about O10% by weight of aluminum, about 05% by weight of beryllium, about 02% by weight of carbon, about 0-5% by weight of cobalt, about 0-10% by weight of iron, about 010% by weight of manganese, about 0-20% by weight of molybdenum, about 05% by weight of nickel, about 0-2% by weight of silicon, about 0-20% by weight of tantalum, about 0-5% by weight of tungsten, about 0-10% by weight of vanadium, and about 020% by weight of zirconium, the'sum total of Al, Be, C, Co, Fe, Mn, Mo, Si, Ni, Ta, W, V and Zr ranging from about 1-20% by weight, the balance being essentially niobium.
2. A niobium base alloy comprising about 5-25% by weight of titanium, about 05% by weight of aluminum, about 0 5 by weight of nickel, about 0-5 by weight of iron, about 07% by weight of molybdenum, the sum total of Al, Ni, Fe and Mo'being about 4-20% by Weight, the balance being essentially niobium.
No references cited.
Claims (1)
1. A NIOBIUM BASE ALLOY COMPRISING ABOUT 1-30% BY WEIGHT OF TITANIUM, ABOUT 0-10% BY WEIGHT OF ALIMINUM, ABOUT 0-5% BY WEIGHT OF BERYLLIUM, ABOUT 0-2% BY WEIGHT OF CARBON, ABOUT 0-5% BY WEIGHT OF CABALT, ABOUT GANESE, ABOUT 0-20% BY WEIGHT OF MOLYBDENUM, ABOUT GANESE, ABOUT 0-20% BY WEIGHT OF MOLYBDENUM, ABOUT 0-5% BY WEIGHT OF NICKLE, ABOUT 0-2% BY WEIGHT OF SILICON, ABOUT 0-20% BY WEIGHT OF ZIRCONIUM, THE SUM TOTAL WEIGHT OF TUNGSTEN, ABOUT 0-10% BY WEIGHT OF VANADIUM, AND ABOUT 0-20% BY WEIGHT OF ZIRCONIUM, THE SUM TOTAL OF AL, BE, C, CO, FE, MN, MO, SI, NI, TA, W, V AND ZR RANGING FROM ABOUT 1-20% BY WEIGHT, THE BALANCE BEING ESSENTIALLY NIOBIUM.
Priority Applications (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US601341A US2822268A (en) | 1956-08-01 | 1956-08-01 | Compositions of matter |
| CH4475257A CH375903A (en) | 1956-08-01 | 1957-04-08 | Niobium alloy |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US601341A US2822268A (en) | 1956-08-01 | 1956-08-01 | Compositions of matter |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| US2822268A true US2822268A (en) | 1958-02-04 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| US601341A Expired - Lifetime US2822268A (en) | 1956-08-01 | 1956-08-01 | Compositions of matter |
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| Country | Link |
|---|---|
| US (1) | US2822268A (en) |
| CH (1) | CH375903A (en) |
Cited By (40)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2940845A (en) * | 1958-02-24 | 1960-06-14 | Kennecott Copper Corp | Columbium-titanium base oxidationresistant alloys |
| US2973261A (en) * | 1959-06-11 | 1961-02-28 | Gen Electric | Columbium base alloys |
| US3001870A (en) * | 1960-01-15 | 1961-09-26 | Gen Motors Corp | Niobium-titanium refractory alloy |
| US3012883A (en) * | 1959-07-09 | 1961-12-12 | Nat Res Corp | Niobium base alloy |
| US3027255A (en) * | 1960-02-08 | 1962-03-27 | Westinghouse Electric Corp | High strength niobium base alloys |
| US3028236A (en) * | 1958-12-22 | 1962-04-03 | Union Carbide Corp | Columbium base alloy |
| US3037858A (en) * | 1958-12-22 | 1962-06-05 | Union Carbide Corp | Columbium base alloy |
| US3038798A (en) * | 1960-05-02 | 1962-06-12 | Kennecott Copper Corp | Titanium-niobium alloys |
| US3043683A (en) * | 1959-09-23 | 1962-07-10 | Du Pont | Niobium-titanium chromium alloy |
| US3056672A (en) * | 1960-12-01 | 1962-10-02 | Gen Electric | Columbium base alloy |
| US3086859A (en) * | 1960-08-30 | 1963-04-23 | Du Pont | Columbium base alloys |
| US3113863A (en) * | 1960-05-31 | 1963-12-10 | Gen Electric | Columbium base alloy |
| US3115407A (en) * | 1960-12-06 | 1963-12-24 | Stauffer Chemical Co | Multicomponent columbium alloys |
| US3125445A (en) * | 1964-03-17 | Certificate of correction | ||
| US3152891A (en) * | 1960-02-08 | 1964-10-13 | Westinghouse Electric Corp | High strength niobium-base alloys |
| US3173784A (en) * | 1958-12-22 | 1965-03-16 | Union Carbide Corp | Columbium base alloy |
| US3186837A (en) * | 1961-02-28 | 1965-06-01 | California Research Corp | Columbium-tantalum base alloy |
| US3188205A (en) * | 1961-12-20 | 1965-06-08 | Fansteel Metallurgical Corp | Columbium alloy |
| US3188206A (en) * | 1961-12-20 | 1965-06-08 | Fansteel Metallurgical Corp | Columbium alloy |
| US3202585A (en) * | 1959-11-02 | 1965-08-24 | Harry P Kling | High temperature niobium-uo2 nuclear fuel sheet |
| US3203793A (en) * | 1963-01-28 | 1965-08-31 | Du Pont | Porous columbium and tantalum materials |
| US3206305A (en) * | 1963-02-25 | 1965-09-14 | Westinghouse Electric Corp | Niobium alloys |
| US3268373A (en) * | 1963-05-21 | 1966-08-23 | Westinghouse Electric Corp | Superconductive alloys |
| US3314785A (en) * | 1957-02-05 | 1967-04-18 | Fansteel Metallurgical Corp | Alloy |
| US3317314A (en) * | 1959-11-18 | 1967-05-02 | Union Carbide Corp | Columbium-base alloy |
| US3346379A (en) * | 1961-11-15 | 1967-10-10 | Union Carbide Corp | Niobium base alloy |
| US3379519A (en) * | 1961-12-11 | 1968-04-23 | Union Carbide Corp | Columbium-base alloy |
| DE1269365B (en) * | 1959-06-11 | 1968-05-30 | Gen Electric | Process to improve the high-temperature strength, oxidation resistance and processability of niobium alloys |
| US3442644A (en) * | 1966-01-26 | 1969-05-06 | Elektrometallurgie Gmbh | Ferro-alloys containing niobium and titanium |
| US3753699A (en) * | 1971-12-30 | 1973-08-21 | Trw Inc | Refractory metal alloys for use in oxidation environments |
| US3778260A (en) * | 1970-09-09 | 1973-12-11 | Hitachi Ltd | Superconducting materials |
| US3867209A (en) * | 1973-09-17 | 1975-02-18 | Kobe Steel Ltd | Method of treating Ti-Nb-Zr-Ta superconducting alloys |
| FR2674257A1 (en) * | 1991-03-20 | 1992-09-25 | Armines | Alloys based on niobium and titanium, resistant to high- temperature oxidation |
| US5374393A (en) * | 1990-08-22 | 1994-12-20 | Duke University | High temperature turbine engine alloys containing gold |
| US5741376A (en) * | 1996-05-09 | 1998-04-21 | The United States Of America As Represented By The Secretary Of The Air Force | High temperature melting niobium-titanium-chromium-aluminum-silicon alloys |
| WO2000068448A1 (en) * | 1999-05-05 | 2000-11-16 | Davitech, Inc. | Nb-Ti-Zr-Mo ALLOYS FOR MEDICAL AND DENTAL DEVICES |
| US20090042056A1 (en) * | 2007-08-08 | 2009-02-12 | General Electric Comapny | Oxide-forming protective coatings for niobium-based materials |
| US20090042054A1 (en) * | 2007-08-08 | 2009-02-12 | Bernard Patrick Bewlay | Nb-si based alloys having an al-containing coating, articles, and processes |
| US11198927B1 (en) * | 2019-09-26 | 2021-12-14 | United States Of America As Represented By The Secretary Of The Air Force | Niobium alloys for high temperature, structural applications |
| US11846008B1 (en) | 2019-09-26 | 2023-12-19 | United States Of America As Represented By Secretary Of The Air Force | Niobium alloys for high temperature, structural applications |
-
1956
- 1956-08-01 US US601341A patent/US2822268A/en not_active Expired - Lifetime
-
1957
- 1957-04-08 CH CH4475257A patent/CH375903A/en unknown
Non-Patent Citations (1)
| Title |
|---|
| None * |
Cited By (44)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3125445A (en) * | 1964-03-17 | Certificate of correction | ||
| US3314785A (en) * | 1957-02-05 | 1967-04-18 | Fansteel Metallurgical Corp | Alloy |
| US2940845A (en) * | 1958-02-24 | 1960-06-14 | Kennecott Copper Corp | Columbium-titanium base oxidationresistant alloys |
| US3028236A (en) * | 1958-12-22 | 1962-04-03 | Union Carbide Corp | Columbium base alloy |
| US3037858A (en) * | 1958-12-22 | 1962-06-05 | Union Carbide Corp | Columbium base alloy |
| US3173784A (en) * | 1958-12-22 | 1965-03-16 | Union Carbide Corp | Columbium base alloy |
| DE1269365B (en) * | 1959-06-11 | 1968-05-30 | Gen Electric | Process to improve the high-temperature strength, oxidation resistance and processability of niobium alloys |
| US2973261A (en) * | 1959-06-11 | 1961-02-28 | Gen Electric | Columbium base alloys |
| US3012883A (en) * | 1959-07-09 | 1961-12-12 | Nat Res Corp | Niobium base alloy |
| US3043683A (en) * | 1959-09-23 | 1962-07-10 | Du Pont | Niobium-titanium chromium alloy |
| US3202585A (en) * | 1959-11-02 | 1965-08-24 | Harry P Kling | High temperature niobium-uo2 nuclear fuel sheet |
| US3317314A (en) * | 1959-11-18 | 1967-05-02 | Union Carbide Corp | Columbium-base alloy |
| US3001870A (en) * | 1960-01-15 | 1961-09-26 | Gen Motors Corp | Niobium-titanium refractory alloy |
| US3152891A (en) * | 1960-02-08 | 1964-10-13 | Westinghouse Electric Corp | High strength niobium-base alloys |
| US3027255A (en) * | 1960-02-08 | 1962-03-27 | Westinghouse Electric Corp | High strength niobium base alloys |
| US3038798A (en) * | 1960-05-02 | 1962-06-12 | Kennecott Copper Corp | Titanium-niobium alloys |
| US3113863A (en) * | 1960-05-31 | 1963-12-10 | Gen Electric | Columbium base alloy |
| US3086859A (en) * | 1960-08-30 | 1963-04-23 | Du Pont | Columbium base alloys |
| US3056672A (en) * | 1960-12-01 | 1962-10-02 | Gen Electric | Columbium base alloy |
| US3115407A (en) * | 1960-12-06 | 1963-12-24 | Stauffer Chemical Co | Multicomponent columbium alloys |
| US3186837A (en) * | 1961-02-28 | 1965-06-01 | California Research Corp | Columbium-tantalum base alloy |
| US3346379A (en) * | 1961-11-15 | 1967-10-10 | Union Carbide Corp | Niobium base alloy |
| US3379519A (en) * | 1961-12-11 | 1968-04-23 | Union Carbide Corp | Columbium-base alloy |
| US3188206A (en) * | 1961-12-20 | 1965-06-08 | Fansteel Metallurgical Corp | Columbium alloy |
| US3188205A (en) * | 1961-12-20 | 1965-06-08 | Fansteel Metallurgical Corp | Columbium alloy |
| US3203793A (en) * | 1963-01-28 | 1965-08-31 | Du Pont | Porous columbium and tantalum materials |
| US3206305A (en) * | 1963-02-25 | 1965-09-14 | Westinghouse Electric Corp | Niobium alloys |
| US3268373A (en) * | 1963-05-21 | 1966-08-23 | Westinghouse Electric Corp | Superconductive alloys |
| US3442644A (en) * | 1966-01-26 | 1969-05-06 | Elektrometallurgie Gmbh | Ferro-alloys containing niobium and titanium |
| US3778260A (en) * | 1970-09-09 | 1973-12-11 | Hitachi Ltd | Superconducting materials |
| US3753699A (en) * | 1971-12-30 | 1973-08-21 | Trw Inc | Refractory metal alloys for use in oxidation environments |
| US3867209A (en) * | 1973-09-17 | 1975-02-18 | Kobe Steel Ltd | Method of treating Ti-Nb-Zr-Ta superconducting alloys |
| US5374393A (en) * | 1990-08-22 | 1994-12-20 | Duke University | High temperature turbine engine alloys containing gold |
| FR2674257A1 (en) * | 1991-03-20 | 1992-09-25 | Armines | Alloys based on niobium and titanium, resistant to high- temperature oxidation |
| US5284618A (en) * | 1991-03-20 | 1994-02-08 | Association Pour La Recherche Et Le Developpement Des Methodes Et Processus Industriels "A.R.M.I.N.E.S." | Niobium and titanium based alloys resistant to oxidation at high temperatures |
| US5741376A (en) * | 1996-05-09 | 1998-04-21 | The United States Of America As Represented By The Secretary Of The Air Force | High temperature melting niobium-titanium-chromium-aluminum-silicon alloys |
| WO2000068448A1 (en) * | 1999-05-05 | 2000-11-16 | Davitech, Inc. | Nb-Ti-Zr-Mo ALLOYS FOR MEDICAL AND DENTAL DEVICES |
| US6238491B1 (en) * | 1999-05-05 | 2001-05-29 | Davitech, Inc. | Niobium-titanium-zirconium-molybdenum (nbtizrmo) alloys for dental and other medical device applications |
| US20090042056A1 (en) * | 2007-08-08 | 2009-02-12 | General Electric Comapny | Oxide-forming protective coatings for niobium-based materials |
| US20090042054A1 (en) * | 2007-08-08 | 2009-02-12 | Bernard Patrick Bewlay | Nb-si based alloys having an al-containing coating, articles, and processes |
| US7981520B2 (en) * | 2007-08-08 | 2011-07-19 | General Electric Company | Oxide-forming protective coatings for niobium-based materials |
| US8039116B2 (en) * | 2007-08-08 | 2011-10-18 | General Electric Company | Nb-Si based alloys having an Al-containing coating, articles, and processes |
| US11198927B1 (en) * | 2019-09-26 | 2021-12-14 | United States Of America As Represented By The Secretary Of The Air Force | Niobium alloys for high temperature, structural applications |
| US11846008B1 (en) | 2019-09-26 | 2023-12-19 | United States Of America As Represented By Secretary Of The Air Force | Niobium alloys for high temperature, structural applications |
Also Published As
| Publication number | Publication date |
|---|---|
| CH375903A (en) | 1964-03-15 |
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