US2515185A - Age hardenable nickel alloy - Google Patents
Age hardenable nickel alloy Download PDFInfo
- Publication number
- US2515185A US2515185A US477142A US47714243A US2515185A US 2515185 A US2515185 A US 2515185A US 477142 A US477142 A US 477142A US 47714243 A US47714243 A US 47714243A US 2515185 A US2515185 A US 2515185A
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- alloys
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- titanium
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- 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.)
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- 229910000990 Ni alloy Inorganic materials 0.000 title description 8
- XUIMIQQOPSSXEZ-UHFFFAOYSA-N Silicon Chemical compound [Si] XUIMIQQOPSSXEZ-UHFFFAOYSA-N 0.000 claims description 14
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 claims description 14
- 239000010703 silicon Substances 0.000 claims description 14
- 229910052710 silicon Inorganic materials 0.000 claims description 14
- 239000010936 titanium Substances 0.000 claims description 14
- 229910052719 titanium Inorganic materials 0.000 claims description 14
- XEEYBQQBJWHFJM-UHFFFAOYSA-N Iron Chemical compound [Fe] XEEYBQQBJWHFJM-UHFFFAOYSA-N 0.000 claims description 13
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims description 13
- 229910052782 aluminium Inorganic materials 0.000 claims description 13
- 239000011651 chromium Substances 0.000 claims description 10
- VYZAMTAEIAYCRO-UHFFFAOYSA-N Chromium Chemical compound [Cr] VYZAMTAEIAYCRO-UHFFFAOYSA-N 0.000 claims description 9
- 229910052804 chromium Inorganic materials 0.000 claims description 9
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims description 7
- 229910052799 carbon Inorganic materials 0.000 claims description 7
- 229910052742 iron Inorganic materials 0.000 claims description 6
- 239000011572 manganese Substances 0.000 claims description 5
- PWHULOQIROXLJO-UHFFFAOYSA-N Manganese Chemical compound [Mn] PWHULOQIROXLJO-UHFFFAOYSA-N 0.000 claims description 4
- 229910052748 manganese Inorganic materials 0.000 claims description 4
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 description 26
- 229910045601 alloy Inorganic materials 0.000 description 26
- 239000000956 alloy Substances 0.000 description 26
- 229910052759 nickel Inorganic materials 0.000 description 13
- 235000010210 aluminium Nutrition 0.000 description 11
- 238000010438 heat treatment Methods 0.000 description 8
- 235000019589 hardness Nutrition 0.000 description 6
- 238000003754 machining Methods 0.000 description 4
- 238000001816 cooling Methods 0.000 description 3
- 239000004848 polyfunctional curative Substances 0.000 description 3
- 230000031070 response to heat Effects 0.000 description 3
- NINIDFKCEFEMDL-UHFFFAOYSA-N Sulfur Chemical compound [S] NINIDFKCEFEMDL-UHFFFAOYSA-N 0.000 description 2
- 238000003483 aging Methods 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 239000000203 mixture Substances 0.000 description 2
- 229910052717 sulfur Inorganic materials 0.000 description 2
- 239000011593 sulfur Substances 0.000 description 2
- 101100116570 Caenorhabditis elegans cup-2 gene Proteins 0.000 description 1
- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical compound [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 description 1
- 101100116572 Drosophila melanogaster Der-1 gene Proteins 0.000 description 1
- OAICVXFJPJFONN-UHFFFAOYSA-N Phosphorus Chemical compound [P] OAICVXFJPJFONN-UHFFFAOYSA-N 0.000 description 1
- 241001013262 Theages Species 0.000 description 1
- 239000010941 cobalt Substances 0.000 description 1
- 229910017052 cobalt Inorganic materials 0.000 description 1
- GUTLYIVDDKVIGB-UHFFFAOYSA-N cobalt atom Chemical compound [Co] GUTLYIVDDKVIGB-UHFFFAOYSA-N 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 239000010949 copper Substances 0.000 description 1
- 229910052802 copper Inorganic materials 0.000 description 1
- 238000005520 cutting process Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000004615 ingredient Substances 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 208000035824 paresthesia Diseases 0.000 description 1
- 229910052698 phosphorus Inorganic materials 0.000 description 1
- 239000011574 phosphorus Substances 0.000 description 1
- 238000001556 precipitation Methods 0.000 description 1
- 238000004881 precipitation hardening Methods 0.000 description 1
- 238000010791 quenching Methods 0.000 description 1
- 230000000171 quenching effect Effects 0.000 description 1
- 238000010583 slow cooling Methods 0.000 description 1
Classifications
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C19/00—Alloys based on nickel or cobalt
- C22C19/03—Alloys based on nickel or cobalt based on nickel
- C22C19/05—Alloys based on nickel or cobalt based on nickel with chromium
- C22C19/058—Alloys based on nickel or cobalt based on nickel with chromium without Mo and W
Definitions
- nickel alloys capable of being hardened by heat treatment to any selected hardness over a broad hardness rangeptoprovide nickel alloys having maximum hardness in the aged condition commensurate with satisfactory forgeabllity and good machining properties; and to produce nickel alloyshaving a broad range of hot malleability combined with high mechanical properties in theage hardened condition.
- the present invention is based upon the surprising discovery made by us that nickel base alloys containing chromium, and optionally iron, having among other desirable properties an advantageous combination of hot malleability, good machining properties, good response to heat treatment,- and high hardness in the heat treated condition can be produced by incorporating aluminum with titanium or silicon,
- z 35% while iron may vary from 0 to about 45%.
- the relative amounts of aluminum, silicon and titanium may vary over a range of several percent provided the ratio of nickel to the hardener content is maintained within the limits defined herein.
- Aluminum, and at least one of the elements of the group titanium and silicon must be present in the alloy in amounts greater than 0.25%.
- the third hardening element may be present in amounts more 'or less than 0.25%, the
- essential feature of this invention being that at least two of the hardening elements must be treatment can be obtained in chromium-containing nickel base, alloys by incorporating only one of the elements, aluminum, titanium or silicon in the alloy. but the amount necessary to produce maximum r sponse to heat treatment is relatively large and this is accompanied by working difllcultles.
- Chromium will be present within the range of about 5% to present in amounts greater than about 0.25%.
- Aluminum and silicon may be used in amounts up to about 8%, preferably not over 5% of either, while titanium should be less than'5% and preferably is employed in amounts less than 4%. Titanium exerts its greatest effect on age-hardenabilty within the range of about 0.25% to under 1%, in combination with proper amounts of aluminum and/or silicon.
- Element Per cent I Per cent I Per cent Commercial alloys embodying the present invention may contain small amounts of other elements such as sulfur, copper, cobalt and phosphorus.
- the sulfur is preferably low, e. g., about 0.01%.
- the alloys may be substantially carbonfree or carbon may be present up to about 0.5%. Ordinarily the carbon will not exceed about 0.2% and preferably is maintained below about 0.1%. Ordinarily carbon will be present within the range of about 0.02 to 0.1%. Manganese ordinarily will not exceed about 2% and preferably will be within the range of about 0.1% to 0.5%.
- the mechanical properties of the alloys embodying the present invention are substantially enhanced by age hardening and the alloys retain considerable strength even at the high temperature of about 1600 F. This property makes the alloys particularly suitable for fabricating metallic articles which are exposed in use to elevated temperatures under considerable stress.
- the chromium-containing nickel alloys may be worked within the range of about 1900 F. to 2400 F., preferably within the range of about 2100 F. to 2300 F. This is a valuable novel result since the prior art had not been able to produce hot workable alloys of this type capable of being age hardened. It is surprising that the use cf the hardening elements in combination makes it possible to produce age hardenable chromium-containing nickel alloys capable of being hot worked over as broad a range as indicated.
- the alloys of the present invention may be softened by quenching or rapidly cooling from above 1700 F.
- the alloys may be age hardened by the conventional hardening treatment comprising a solution heat treatment, a rapid cooling and a precipitation heat treatment; or they may be hardened by a controlledcooling following the solution heat treatment as disclosed in our prior application Serial No. 253,350, filed January 28, 1939, now Patent No. 2,234,955, dated March 18, 1941; or they may be heat treated in accordance with the process disclosed in our copending application Serial No. 483,760 filed April 20, 1943, now abandoned.
- the controlled cooling for alloys of the present invention preferably comprises holding them within the range of about 1200" to 1400 F.
- the softened condition the alloys may be deformed cold, and in this condition the alloys lend themselves readily to machining operations.
- the material may be worked cold either before or after the age-hardening treatment.
- the alloys as those skilled in the art will readily appreciate, are machinable with greater difliculty than in the annealed condition but, if necessary, machining can be performed by the use of carbide type tools.
- nickel alloys combining optimum response to heat-treatment with hot malleability.
- These alloys may be used for various articles of manufacture including rollers and bearing balls, bearings and races therefor, roller chains, drop i.org-- ings and tie rods for airplane construction, valve seats and other valve parts, pump rods and the like, pump rod sleeves, pump pistons for high pressui es and temperatures, plungers, turbine blades, turbine diaphragm blading, lock washers, screws and nuts, tools, cutting blades and the like, pins and needles, springs and other resilient elements, airplane instrument parts, nozzles for burners, rods, sheets, strip, wire, bars, rolled shapes, etc.
Description
Patented July 18,
AGE HARDENABLE NICKEL ALLOY Clarence George Bieber and Mortimer Pierce Buck, Huntington, W. Va., assignors to The International Nickel Company, Inc., New York, N. Y., a corporation of Delaware No Drawing. Application February 25, 1948, Serial No. 477,142 e 4 Claiml (Cl. 75-170) The present invention relates to nickel alloys,
and. more particularly, to age hardenable nickel It is among the objects of our invention to produce nickel alloys capable of being hardened by heat treatment to any selected hardness over a broad hardness rangeptoprovide nickel alloys having maximum hardness in the aged condition commensurate with satisfactory forgeabllity and good machining properties; and to produce nickel alloyshaving a broad range of hot malleability combined with high mechanical properties in theage hardened condition.
Other objects and advantages of the present invention will become apparent from the following description of the-present invention Generally speaking, the present invention is based upon the surprising discovery made by us that nickel base alloys containing chromium, and optionally iron, having among other desirable properties an advantageous combination of hot malleability, good machining properties, good response to heat treatment,- and high hardness in the heat treated condition can be produced by incorporating aluminum with titanium or silicon,
z 35% while iron may vary from 0 to about 45%. The relative amounts of aluminum, silicon and titanium may vary over a range of several percent provided the ratio of nickel to the hardener content is maintained within the limits defined herein. Aluminum, and at least one of the elements of the group titanium and silicon must be present in the alloy in amounts greater than 0.25%. The third hardening element may be present in amounts more 'or less than 0.25%, the
, essential feature of this invention being that at least two of the hardening elements must be treatment can be obtained in chromium-containing nickel base, alloys by incorporating only one of the elements, aluminum, titanium or silicon in the alloy. but the amount necessary to produce maximum r sponse to heat treatment is relatively large and this is accompanied by working difllcultles. .We have made the surprising discovery that by, using at least two of the elements from the group aluminum, silicon and titanium, the response to heat-treatment witha smaller total amount of hardening elements is as satisfactory or even better than in alloys containing only one of these hardening elements in effective amounts, and the new alloys are characterized by greatly improved hot malleability as compared with alloys of otherwise substantially the same composition containing only one of the hardening elements.
The, nickel content of the alloys embodying the present. invention in all cases .will be at least 45% by weight of the alloy and usually will be 50% or substantially more than 50%. Chromium will be present within the range of about 5% to present in amounts greater than about 0.25%. Aluminum and silicon may be used in amounts up to about 8%, preferably not over 5% of either, while titanium should be less than'5% and preferably is employed in amounts less than 4%. Titanium exerts its greatest effect on age-hardenabilty within the range of about 0.25% to under 1%, in combination with proper amounts of aluminum and/or silicon.
We have discovered that the optimum combination of hot malleability, hardenability and high hardness in the heat-treated condition is obtained when the ratio of nickel to the weighted hardener content as obtained from the formula Weighted hardener content=Al+2 T i+Si Element Per cent Cr 10 -22 Fe 0.1 l5 AL. 0. 25- 5 TL. 0. 25- 4 Si 0.05- 2.0 C 0. 00- 0 6 Mn. 0. 00- 2. 0 Ni Balance The preferred ranges of the various ingredients are as follows:
7 For the purpose of giving those skilled in the art a better understanding of the present invention, the following specific examples are given of alloys that are typical of the preferred compositions:
Element Per cent I Per cent I Per cent Commercial alloys embodying the present invention may contain small amounts of other elements such as sulfur, copper, cobalt and phosphorus. The sulfur is preferably low, e. g., about 0.01%. The alloys may be substantially carbonfree or carbon may be present up to about 0.5%. Ordinarily the carbon will not exceed about 0.2% and preferably is maintained below about 0.1%. Ordinarily carbon will be present within the range of about 0.02 to 0.1%. Manganese ordinarily will not exceed about 2% and preferably will be within the range of about 0.1% to 0.5%.
The mechanical properties of the alloys embodying the present invention are substantially enhanced by age hardening and the alloys retain considerable strength even at the high temperature of about 1600 F. This property makes the alloys particularly suitable for fabricating metallic articles which are exposed in use to elevated temperatures under considerable stress.
The chromium-containing nickel alloys may be worked within the range of about 1900 F. to 2400 F., preferably within the range of about 2100 F. to 2300 F. This is a valuable novel result since the prior art had not been able to produce hot workable alloys of this type capable of being age hardened. It is surprising that the use cf the hardening elements in combination makes it possible to produce age hardenable chromium-containing nickel alloys capable of being hot worked over as broad a range as indicated.
The alloys of the present invention may be softened by quenching or rapidly cooling from above 1700 F. The alloys may be age hardened by the conventional hardening treatment comprising a solution heat treatment, a rapid cooling and a precipitation heat treatment; or they may be hardened by a controlledcooling following the solution heat treatment as disclosed in our prior application Serial No. 253,350, filed January 28, 1939, now Patent No. 2,234,955, dated March 18, 1941; or they may be heat treated in accordance with the process disclosed in our copending application Serial No. 483,760 filed April 20, 1943, now abandoned. The controlled cooling for alloys of the present invention preferably comprises holding them within the range of about 1200" to 1400 F. for a period varying from about ,5 hour to 16 hours, followed by slow cooling to a temperature within the range of I about 1100 F. to 1000 F. at a rate not exceeding about 75 F. per hour, and preferably not over about 25 F. per hour. m the softened condition the alloys may be deformed cold, and in this condition the alloys lend themselves readily to machining operations. Where hardnesses higher than those obtainable by precipitation hardening of hot-worked material are desired, the material may be worked cold either before or after the age-hardening treatment. In the hardened condition the alloys, as those skilled in the art will readily appreciate, are machinable with greater difliculty than in the annealed condition but, if necessary, machining can be performed by the use of carbide type tools.
It will be seen from the foregoing description and the specific examples that we have provided nickel alloys combining optimum response to heat-treatment with hot malleability. These alloys may be used for various articles of manufacture including rollers and bearing balls, bearings and races therefor, roller chains, drop i.org-- ings and tie rods for airplane construction, valve seats and other valve parts, pump rods and the like, pump rod sleeves, pump pistons for high pressui es and temperatures, plungers, turbine blades, turbine diaphragm blading, lock washers, screws and nuts, tools, cutting blades and the like, pins and needles, springs and other resilient elements, airplane instrument parts, nozzles for burners, rods, sheets, strip, wire, bars, rolled shapes, etc.
The present application is a, continuation-inpart of our prior copending application Serial No.
374,208 filed January 13, 1941, which itself is a continuation-in-part of our prior application Serial No. 253,350 filed January 28, 1939, which latter application issued on March 18, 1941, as Patent No. 2,234,955.
Although the present invention has been described in conjunction with preferred embodiments, it is understood that modifications and variations may be resorted to without departing from the spirit and scope of the invention, as those skilled in the art will readily understand.
We claim:
1. An alloy containing 11% to 15% chromium, 5% to 8% iron, 0.25% to 3.5% aluminum, at least 0.25% and under 1% titanium, 0.5% to 1% silicon, 0.02% to 0.2% carbon, 0.1% to 0.5% manganese and the balance substantially all nickel, the ratio of the nickel content to the sum of the alu minum content, the silicon content, and two times the square root of the titanium content being between 13 and 17.
2. An alloy containing 10% to 22% chromium, 0. to 15% iron, 0.25% to 5% aluminum, at least 0.25% and under 1% titanium, 0.05% to V 2% silicon, carbon in an amount not greater than der 1% titanium, 0.05% to 2% silicon, 10% to B) 22% chromium, 0.1% to 15% iron, manganese in an amount not exceeding 2%, carbon in an amount not exceeding 0.5%, and the balance substantially all nickel, the nickel content being over 50% o! the alloy, and the ratio of the nickel con- 1 1 6 tent to the sum of the aluminum content, the silicon content and two times the square root oi the titanium content being between 11 and 20.
CLARENCE GEORGE BIEBER. MORTIMER Pnmcn: BUCK.
REFERENCES CITED The following references are of record in the tile of this patent:
UNITED STATES PA'i'ENTs Number Name Date 1,587,992 Spitzley June 8, 1926 2,048,166 Piiling July 21, 1936 Pilling July 21, 1936
Claims (1)
1. AN ALLOY CONTAINING 11% TO 15% CHROMIUM, 5% TO 8% IRON, 0.25% TO 3.5% ALUMINUM, AT LEAST 0.25% AND UNDER 1% TITANIUM, 0.5% TO 1% SILICON, 0.02% TO 0.2% CARBON, 0.1% TO 0.5% MANGANESE AND THE BALANCE SUBSTANTIALLY ALL NICKEL, THE RATIO OF THE NICKEL CONTENT TO THE SUM OF THE ALUMINUM CONTENT, THE SILICON CONTENT, AND TWO TIMES THE SQUARE ROOT OF THE TITANIUM CONTENT BEING BETWEEN 13 AND 17.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US477142A US2515185A (en) | 1943-02-25 | 1943-02-25 | Age hardenable nickel alloy |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US477142A US2515185A (en) | 1943-02-25 | 1943-02-25 | Age hardenable nickel alloy |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| US2515185A true US2515185A (en) | 1950-07-18 |
Family
ID=23894699
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| US477142A Expired - Lifetime US2515185A (en) | 1943-02-25 | 1943-02-25 | Age hardenable nickel alloy |
Country Status (1)
| Country | Link |
|---|---|
| US (1) | US2515185A (en) |
Cited By (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2664354A (en) * | 1950-10-12 | 1953-12-29 | Int Nickel Co | Valves for internal combustion engines |
| US2698633A (en) * | 1952-05-09 | 1955-01-04 | American Machine & Metals | Evacuated capsule for aneroid barometers |
| US2755183A (en) * | 1955-01-25 | 1956-07-17 | Coast Metals Inc | Nickel-silicon-boron alloys |
| US2793950A (en) * | 1953-07-03 | 1957-05-28 | Union Carbide & Carbon Corp | Heat-resistant nickel-base sheet alloy |
| US2873187A (en) * | 1956-12-07 | 1959-02-10 | Allegheny Ludlum Steel | Austenitic alloys |
| US3713788A (en) * | 1970-10-21 | 1973-01-30 | Chromalloy American Corp | Powder metallurgy sintered corrosion and heat-resistant, age hardenable nickel-chromium refractory carbide alloy |
| US4124381A (en) * | 1976-08-30 | 1978-11-07 | Sklar Steven D | Non-precious dental casting alloy |
| US4629521A (en) * | 1984-12-10 | 1986-12-16 | Special Metals Corporation | Nickel base alloy |
| WO2000011230A1 (en) * | 1998-08-24 | 2000-03-02 | Hoskins Manufacturing Company | Modified nickel-chromium-aluminum-iron alloy |
| EP1065290A1 (en) * | 1999-06-30 | 2001-01-03 | Sumitomo Metal Industries, Ltd. | Heat resistant nickel base alloy |
| US20030218411A1 (en) * | 2002-05-18 | 2003-11-27 | Klaus Hrastnik | Alloy, electrode with the alloy, and ignition device with the alloy |
| US20060051234A1 (en) * | 2004-09-03 | 2006-03-09 | Pike Lee M Jr | Ni-Cr-Co alloy for advanced gas turbine engines |
| US20060222557A1 (en) * | 2004-09-03 | 2006-10-05 | Pike Lee M Jr | Ni-Cr-Co alloy for advanced gas turbine engines |
| WO2014063222A1 (en) | 2012-10-24 | 2014-05-01 | Liburdi Engineering Limited | A composite welding wire and method of manufacturing |
| US10702953B2 (en) | 2014-10-15 | 2020-07-07 | Liburdi Engineering Limited | Composite welding wire and method of manufacturing |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US1587992A (en) * | 1924-11-15 | 1926-06-08 | Alloys Foundry Company | Composition of matter for alloys |
| US2048166A (en) * | 1931-10-01 | 1936-07-21 | Int Nickel Co | Copper-nickel-titanium alloys |
| US2048167A (en) * | 1936-04-11 | 1936-07-21 | Int Nickel Co | Nickel-chromium-iron-titanium alloys |
-
1943
- 1943-02-25 US US477142A patent/US2515185A/en not_active Expired - Lifetime
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US1587992A (en) * | 1924-11-15 | 1926-06-08 | Alloys Foundry Company | Composition of matter for alloys |
| US2048166A (en) * | 1931-10-01 | 1936-07-21 | Int Nickel Co | Copper-nickel-titanium alloys |
| US2048167A (en) * | 1936-04-11 | 1936-07-21 | Int Nickel Co | Nickel-chromium-iron-titanium alloys |
Cited By (19)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2664354A (en) * | 1950-10-12 | 1953-12-29 | Int Nickel Co | Valves for internal combustion engines |
| US2698633A (en) * | 1952-05-09 | 1955-01-04 | American Machine & Metals | Evacuated capsule for aneroid barometers |
| US2793950A (en) * | 1953-07-03 | 1957-05-28 | Union Carbide & Carbon Corp | Heat-resistant nickel-base sheet alloy |
| US2755183A (en) * | 1955-01-25 | 1956-07-17 | Coast Metals Inc | Nickel-silicon-boron alloys |
| US2873187A (en) * | 1956-12-07 | 1959-02-10 | Allegheny Ludlum Steel | Austenitic alloys |
| US3713788A (en) * | 1970-10-21 | 1973-01-30 | Chromalloy American Corp | Powder metallurgy sintered corrosion and heat-resistant, age hardenable nickel-chromium refractory carbide alloy |
| US4124381A (en) * | 1976-08-30 | 1978-11-07 | Sklar Steven D | Non-precious dental casting alloy |
| US4629521A (en) * | 1984-12-10 | 1986-12-16 | Special Metals Corporation | Nickel base alloy |
| US6093369A (en) * | 1994-04-08 | 2000-07-25 | Hoskins Manufacturing Company | Modified nickel-chromium-aluminum-iron alloy |
| WO2000011230A1 (en) * | 1998-08-24 | 2000-03-02 | Hoskins Manufacturing Company | Modified nickel-chromium-aluminum-iron alloy |
| EP1065290A1 (en) * | 1999-06-30 | 2001-01-03 | Sumitomo Metal Industries, Ltd. | Heat resistant nickel base alloy |
| US6458318B1 (en) | 1999-06-30 | 2002-10-01 | Sumitomo Metal Industries, Ltd. | Heat resistant nickel base alloy |
| US20030218411A1 (en) * | 2002-05-18 | 2003-11-27 | Klaus Hrastnik | Alloy, electrode with the alloy, and ignition device with the alloy |
| US7268474B2 (en) * | 2002-05-18 | 2007-09-11 | Robert Bosch Gmbh | Alloy, electrode with the alloy, and ignition device with the alloy |
| US20060051234A1 (en) * | 2004-09-03 | 2006-03-09 | Pike Lee M Jr | Ni-Cr-Co alloy for advanced gas turbine engines |
| US20060222557A1 (en) * | 2004-09-03 | 2006-10-05 | Pike Lee M Jr | Ni-Cr-Co alloy for advanced gas turbine engines |
| US8066938B2 (en) | 2004-09-03 | 2011-11-29 | Haynes International, Inc. | Ni-Cr-Co alloy for advanced gas turbine engines |
| WO2014063222A1 (en) | 2012-10-24 | 2014-05-01 | Liburdi Engineering Limited | A composite welding wire and method of manufacturing |
| US10702953B2 (en) | 2014-10-15 | 2020-07-07 | Liburdi Engineering Limited | Composite welding wire and method of manufacturing |
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