US2805154A - Nickel-base alloy - Google Patents
Nickel-base alloy Download PDFInfo
- Publication number
- US2805154A US2805154A US389867A US38986753A US2805154A US 2805154 A US2805154 A US 2805154A US 389867 A US389867 A US 389867A US 38986753 A US38986753 A US 38986753A US 2805154 A US2805154 A US 2805154A
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- United States
- Prior art keywords
- nickel
- alloys
- less
- high temperature
- cobalt
- 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 36
- 239000000956 alloy Substances 0.000 title claims description 36
- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 claims description 22
- XEEYBQQBJWHFJM-UHFFFAOYSA-N Iron Chemical compound [Fe] XEEYBQQBJWHFJM-UHFFFAOYSA-N 0.000 claims description 20
- VYZAMTAEIAYCRO-UHFFFAOYSA-N Chromium Chemical compound [Cr] VYZAMTAEIAYCRO-UHFFFAOYSA-N 0.000 claims description 13
- 229910052782 aluminium Inorganic materials 0.000 claims description 13
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims description 13
- 229910052804 chromium Inorganic materials 0.000 claims description 13
- 239000011651 chromium Substances 0.000 claims description 13
- 229910017052 cobalt Inorganic materials 0.000 claims description 13
- 239000010941 cobalt Substances 0.000 claims description 13
- GUTLYIVDDKVIGB-UHFFFAOYSA-N cobalt atom Chemical compound [Co] GUTLYIVDDKVIGB-UHFFFAOYSA-N 0.000 claims description 13
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 claims description 11
- 229910052757 nitrogen Inorganic materials 0.000 claims description 11
- 239000001301 oxygen Substances 0.000 claims description 11
- 229910052760 oxygen Inorganic materials 0.000 claims description 11
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims description 10
- 229910052799 carbon Inorganic materials 0.000 claims description 10
- 229910052742 iron Inorganic materials 0.000 claims description 10
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 description 20
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 description 12
- 235000010210 aluminium Nutrition 0.000 description 12
- 229910052719 titanium Inorganic materials 0.000 description 12
- 239000010936 titanium Substances 0.000 description 12
- 229910052759 nickel Inorganic materials 0.000 description 10
- ZOKXTWBITQBERF-UHFFFAOYSA-N Molybdenum Chemical compound [Mo] ZOKXTWBITQBERF-UHFFFAOYSA-N 0.000 description 8
- 229910052750 molybdenum Inorganic materials 0.000 description 8
- 239000011733 molybdenum Substances 0.000 description 8
- 238000005275 alloying Methods 0.000 description 5
- XKRFYHLGVUSROY-UHFFFAOYSA-N Argon Chemical compound [Ar] XKRFYHLGVUSROY-UHFFFAOYSA-N 0.000 description 4
- 238000004519 manufacturing process Methods 0.000 description 4
- 150000004767 nitrides Chemical class 0.000 description 3
- 229910052786 argon Inorganic materials 0.000 description 2
- 239000007789 gas Substances 0.000 description 2
- 239000001257 hydrogen Substances 0.000 description 2
- 229910052739 hydrogen Inorganic materials 0.000 description 2
- 230000008018 melting Effects 0.000 description 2
- 238000002844 melting Methods 0.000 description 2
- 229910052751 metal Inorganic materials 0.000 description 2
- 239000002184 metal Substances 0.000 description 2
- 150000002739 metals Chemical class 0.000 description 2
- 239000000203 mixture Substances 0.000 description 2
- 229910052710 silicon Inorganic materials 0.000 description 2
- 239000010703 silicon Substances 0.000 description 2
- 238000012360 testing method Methods 0.000 description 2
- UFHFLCQGNIYNRP-UHFFFAOYSA-N Hydrogen Chemical compound [H][H] UFHFLCQGNIYNRP-UHFFFAOYSA-N 0.000 description 1
- PWHULOQIROXLJO-UHFFFAOYSA-N Manganese Chemical compound [Mn] PWHULOQIROXLJO-UHFFFAOYSA-N 0.000 description 1
- HZEWFHLRYVTOIW-UHFFFAOYSA-N [Ti].[Ni] Chemical compound [Ti].[Ni] HZEWFHLRYVTOIW-UHFFFAOYSA-N 0.000 description 1
- 238000005266 casting Methods 0.000 description 1
- 238000007796 conventional method Methods 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 150000002431 hydrogen Chemical class 0.000 description 1
- 239000004615 ingredient Substances 0.000 description 1
- 235000015250 liver sausages Nutrition 0.000 description 1
- 229910052748 manganese Inorganic materials 0.000 description 1
- 239000011572 manganese Substances 0.000 description 1
- WPBNNNQJVZRUHP-UHFFFAOYSA-L manganese(2+);methyl n-[[2-(methoxycarbonylcarbamothioylamino)phenyl]carbamothioyl]carbamate;n-[2-(sulfidocarbothioylamino)ethyl]carbamodithioate Chemical compound [Mn+2].[S-]C(=S)NCCNC([S-])=S.COC(=O)NC(=S)NC1=CC=CC=C1NC(=S)NC(=O)OC WPBNNNQJVZRUHP-UHFFFAOYSA-L 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 229910001000 nickel titanium Inorganic materials 0.000 description 1
- 230000000737 periodic effect Effects 0.000 description 1
- 230000009257 reactivity Effects 0.000 description 1
- 238000007670 refining Methods 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 230000008016 vaporization Effects 0.000 description 1
- 238000009834 vaporization 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
- C22C19/051—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W
- C22C19/055—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W with the maximum Cr content being at least 20% but less than 30%
Definitions
- This invention relates to the production of metals and in particular to the production of improved high temperature alloys.
- a principal object of the invention is to provide improved high temperature nickel-base, age-hardenable alloys.
- Another object of the invention is to provide alloys of the above type which possess good ductility and high rupture strength.
- the present invention is directed to improved, high temperature, nickel-base, age-hardenable alloys containing appreciable quantities of chromium, cobalt, titanium, and aluminum which possess good ductility and high rupture strength.
- the nickel-base alloys of the invention may also contain, in addition to the above-mentioned elements, appreciable amounts of molybdenum, iron or other metals.
- the improved alloys of the present invention preferably contain between about 18% to 21% chromium, 9% to 21% cobalt, 2% to 4% titanium, 0.25% to 2% alumi num, 0.05% to 0.20% carbon and at least 50% nickel.
- the preferred alloys may contain, in addition to the above elements, between about 2% to 12% molybdenum and/or a maximum of 5% iron. In all cases, the alloys of the above compositions contain less than about 0.003% oxygen and less than about 0.01% nitrogen.
- the high temperature alloys of the present invention are prepared by melting nickel in a vacuum furnace. Alloying elements, such as cobalt, molybdenum and iron, may be charged and melted with the nickel during this initial melting operation. The melted nickel plus alloying ingredients are then subjected to a hydrogen impinge- 2,805,154 Patented Sept. 3, 19 57 has been reduced to about microns; This hydrogen treatment is more fully described in the copending application of Moore et a1. filed on even date herewith. At the conclusion of this'deoxida'tion, argon is introduced into the furnace to maintain a pressure of about 50 mm. Hg. abs.
- alloying elements are then added, with carbon, chromium, nickel-titanium master alloy, and aluminum being preferably added in the stated order.
- carbon, chromium, nickel-titanium master alloy, and aluminum being preferably added in the stated order.
- the addition of the latter elements under an argon pressure of 5 0 mm.- aids in preventing vaporization losses.- After a shortsoaking period to per+ mit solution of the alloying elrneiits', themelt is poured.
- Typical improved high temperature properties of the preferred nickel-base alloys may be illustrated by showing the stress rupture properties of the above-mentioned alloy designated as (I). At a temperature of 1350 F. and at a stress of 52,500 pounds per square inch, the minimum time to rupture was 230 hours, while the maximum time to rupture was recorded at 1275 hours.
- An improved high temperature nickel-base, agehardenable alloy consisting by weight approximately of 12.00 to 15.00% cobalt, 18.00 to 21.00% chromium, 2.00 to 4.00% titanium, 2.50 to 3.50% molybdenum, 0.75 to 2.00% aluminum, 0.05 to 0.15% carbon, less than 2.00% iron, less than 0.01% nitrogen and less than 0.003% oxygen, the balance being substantially all nickel.
- An improved high temperature nickel-base, agehardenable alloy consisting by weight approximately of 18.00 to 21.00% cobalt, 18.00 to 21.00% chromium, 2.00 to 4.00% titanium, 0.75 to 2.00% aluminum, 0.05 to 0.15% carbon, less than 1.00% iron, less than about 0.01% nitrogen and less than about 0.003% oxygen, the balance being substantially all nickel.
- An improved high temperature nickel-base, agehardenable alloy comprising by weight essentially 9.00 to 11.00% cobalt, 18.00 to 20.00% chromium, 9.00 to 11.00% molybdenum, 2.25 to 2.75% titanium, 0.25 to 0.75% aluminum, maximum 5.00% iron, 0.15 to 0.20% carbon, 1.00 to 1.50% manganese, 0.50 to 1.00% silicon,
- An improved high temperature nickel-base, agehardenable alloy essentially free of stringers of nitrides and oxides, said alloy consisting by weight approximately of 18.00 to 21.00% chromium, 9.00 to 21.00% cobalt, 2.00 to 4.00% titanium, 0.25 to 2.00%aluminnm, 0.05 to 0.20% carbon, less than about 0.01% nitrogen, and less than about 0.003% oxygen, the balance being substantially all nickel.
- An improved high temperature nickel-base, agehardenable alloy consisting by weight approximately of 18.00 to 21.00% chromium, 9.00 to 21.00% cobalt, 2.00 to 4.00% titanium, 0.25 to 2.00% aluminum, 0.05 to 0.20% carbon, 2.00 to 12.00% molybdenum, less than about 0.01% nitrogen, and less than about 0.003% oxygen, the balance being substantially all nickel.
- An improved high temperature nickel-base, agehardenable alloy consisting by weight approximately of 18.00 to 21.00% chromium, 9.00 to 21.00% cobalt, 2.00 to 4.00% titanium, 0.25 to 2.00% aluminum, 0.05 to 0.20% carbon, 2.00 to 12.00% molybdenum, a maximum of 5.00% iron, less than about 0.01% nitrogen, and less than about 0.003% oxygen, the balance being substantially all nickel.
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- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Materials Engineering (AREA)
- Mechanical Engineering (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Description
Unite States Pate p Research Corporation, Cambridge, Mass., 51 corpora tion of Massachusetts Serial No. 389,867
6 Claims. (Cl; 75 -171) No Drawing. Application November2,' 1-s3",
This invention relates to the production of metals and in particular to the production of improved high temperature alloys. g
A principal object of the invention is to provide improved high temperature nickel-base, age-hardenable alloys.
Another object of the invention is to provide alloys of the above type which possess good ductility and high rupture strength.
Other objects of the invention will in part be obvious and will in part appear hereinafter.
For a fuller understanding of the nature and objects of the invention, reference should be had to the following detailed description.
In the development of alloys for high temperature use, particularly for such applications as turbine blades in aircraft gas turbines, some of the most promising alloys have been nickel-base, age-hardenable alloys of the type having appreciable quantities of titanium and aluminum in addition to substantial quantities of chromium and cobalt.
However, the manufacture of these alloys has been subject to difficulties due to the reactivity of the alloying elements, particularly titanium and aluminum, which causes loss of workability and variation in alloy content. In addition, the more highly alloyed nickel-base, age-hardenable alloys have exhibited variation in high temperature properties which makes it difficult to use them safely in exacting applications. It has been found, however, that vacuum refining and casting of such nickel-base alloys provides a product which is clearly superior in the abovementioned respects to the same alloys which have been prepared according to the now existing conventional methods.
Thus, the present invention is directed to improved, high temperature, nickel-base, age-hardenable alloys containing appreciable quantities of chromium, cobalt, titanium, and aluminum which possess good ductility and high rupture strength. The nickel-base alloys of the invention may also contain, in addition to the above-mentioned elements, appreciable amounts of molybdenum, iron or other metals.
The improved alloys of the present invention preferably contain between about 18% to 21% chromium, 9% to 21% cobalt, 2% to 4% titanium, 0.25% to 2% alumi num, 0.05% to 0.20% carbon and at least 50% nickel. In one particular aspect of the invention, the preferred alloys may contain, in addition to the above elements, between about 2% to 12% molybdenum and/or a maximum of 5% iron. In all cases, the alloys of the above compositions contain less than about 0.003% oxygen and less than about 0.01% nitrogen.
The high temperature alloys of the present invention are prepared by melting nickel in a vacuum furnace. Alloying elements, such as cobalt, molybdenum and iron, may be charged and melted with the nickel during this initial melting operation. The melted nickel plus alloying ingredients are then subjected to a hydrogen impinge- 2,805,154 Patented Sept. 3, 19 57 has been reduced to about microns; This hydrogen treatment is more fully described in the copending application of Moore et a1. filed on even date herewith. At the conclusion of this'deoxida'tion, argon is introduced into the furnace to maintain a pressure of about 50 mm. Hg. abs. The remainder of the alloying elements are then added, with carbon, chromium, nickel-titanium master alloy, and aluminum being preferably added in the stated order. The addition of the latter elements under an argon pressure of 5 0 mm.- aids in preventing vaporization losses.- After a shortsoaking period to per+ mit solution of the alloying elrneiits', themelt is poured.
Alloys prepared according to the abovemethod and falling within the scope of this invention are found to possess the following composition:
(11) Cobalt -1 18.00 to 21.00 Chromium 18.00 to 21.00 Titanium 2.00 to 4.00 Aluminum .75 to 2.00 Iron max. 1.00 ...a -.a .05 116 .15 Nitrogen Max. .01 Oxygen Max. .003 Nickel Balance (III) Cobalt 9.00 to 11.00 Chromium 18.00 to 20.00 Titanium 2.25 to 2.75 Aluminum .25 to .75 Molybdenum 9.00 to 11.00 Iron Max. 5.00 Carbon .15 to .20 Nitrogen Max. .01 Oxygen Max. .003 Manganese 1.00 to 1.50 Silicon .50 to 1.00 Nickel Balance It has been found during a series of comparison tests that the above-mentioned alloys were superior to the corresponding conventionally melted alloys which often exhibited not only periodic fabrication difliculties and poor ductility, but also exhibited poor rupture strength at high temperatures and often failed to surpass a 40-hour time to rupture test at 1500 F. and at 32,500 p. s. i. The poor performance of the conventionally melted alloys is believed to be due to the presence of harmful oxides and nitrides. 'Ihe superiority of vacuum refined and cast alloys is indicated to be due principally to a freedom from stringers of nitrides and oxides and the fact that the alloy has a gas content of less than .003% oxygen and .01% nitrogen.
Typical improved high temperature properties of the preferred nickel-base alloys may be illustrated by showing the stress rupture properties of the above-mentioned alloy designated as (I). At a temperature of 1350 F. and at a stress of 52,500 pounds per square inch, the minimum time to rupture was 230 hours, while the maximum time to rupture was recorded at 1275 hours. The
. 3 percent elongation was from a minimum of 4.1 to a maximum of 8.3. At a temperature of 1500 F. and at a stress of 32,500 pounds per square inch, the minimum time to rupture was 89 hours, while themaximum time to rupture was recorded at 380 hours. The percent elongation was from a minimum of 7.8 to a maximum of Thus, it can be seen that the improved high temperature properties of the alloys of the present invention make them especially suitable for use on such exacting applications as turbineblades in aircraft 'gasturbines.
Since certain changes may be made in the above process without departing from the scope of the invention herein involved, it is intended that all matter contained in the description shall be interpretcd as illustrative and not in a limiting sense.-
What is claimedis: V
1. An improved high temperature nickel-base, agehardenable alloy consisting by weight approximately of 12.00 to 15.00% cobalt, 18.00 to 21.00% chromium, 2.00 to 4.00% titanium, 2.50 to 3.50% molybdenum, 0.75 to 2.00% aluminum, 0.05 to 0.15% carbon, less than 2.00% iron, less than 0.01% nitrogen and less than 0.003% oxygen, the balance being substantially all nickel.
2. An improved high temperature nickel-base, agehardenable alloy consisting by weight approximately of 18.00 to 21.00% cobalt, 18.00 to 21.00% chromium, 2.00 to 4.00% titanium, 0.75 to 2.00% aluminum, 0.05 to 0.15% carbon, less than 1.00% iron, less than about 0.01% nitrogen and less than about 0.003% oxygen, the balance being substantially all nickel.
3. An improved high temperature nickel-base, agehardenable alloy comprising by weight essentially 9.00 to 11.00% cobalt, 18.00 to 20.00% chromium, 9.00 to 11.00% molybdenum, 2.25 to 2.75% titanium, 0.25 to 0.75% aluminum, maximum 5.00% iron, 0.15 to 0.20% carbon, 1.00 to 1.50% manganese, 0.50 to 1.00% silicon,
less than about 0.01 nitrogen and less than about 0.003 oxygen, the balance being substantially all nickel.
4. An improved high temperature nickel-base, agehardenable alloy essentially free of stringers of nitrides and oxides, said alloy consisting by weight approximately of 18.00 to 21.00% chromium, 9.00 to 21.00% cobalt, 2.00 to 4.00% titanium, 0.25 to 2.00%aluminnm, 0.05 to 0.20% carbon, less than about 0.01% nitrogen, and less than about 0.003% oxygen, the balance being substantially all nickel.
5. An improved high temperature nickel-base, agehardenable alloy consisting by weight approximately of 18.00 to 21.00% chromium, 9.00 to 21.00% cobalt, 2.00 to 4.00% titanium, 0.25 to 2.00% aluminum, 0.05 to 0.20% carbon, 2.00 to 12.00% molybdenum, less than about 0.01% nitrogen, and less than about 0.003% oxygen, the balance being substantially all nickel.
6. An improved high temperature nickel-base, agehardenable alloy consisting by weight approximately of 18.00 to 21.00% chromium, 9.00 to 21.00% cobalt, 2.00 to 4.00% titanium, 0.25 to 2.00% aluminum, 0.05 to 0.20% carbon, 2.00 to 12.00% molybdenum, a maximum of 5.00% iron, less than about 0.01% nitrogen, and less than about 0.003% oxygen, the balance being substantially all nickel.
References Cited in the file of this patent UNITED STATES PATENTS 2,018,520 Halliwell Oct. 22, 1935 2,246,078 Rohn et al. June 17, 1941 2,570,193 Bieber et al. Oct. 9, 1951 2,712,498 Gresham et al. July 5, 1955 FOREIGN PATENTS 583,841 Great Britain Jan. l, 1947 114,424 Australia Sept. 25, 1947 626,204 Great Britain July 12, 1949
Claims (1)
1. AN IMPROVED HIGH TEMPERATURE NICKEL-BASE, AGEHARDENABLE ALLOY CONSISTING BY WEIGHT APPROXIMATELY OF 12.00 TO 15.00% COBALT, 18.00 TO 21.00% CHROMIUM, 2.00 TO 4.00% TITANIUMM, 2.50 TO 3.50% MOLYDENUM, 0.75 TO 2.00% ALUMINUM, 0.05 TO 0.15% CARBON, LESS THAN 2.00% IRON, LESS THAN 0.01% NITROGEN AND LESS THAN 0.00O% OXYGEN, THE BALANCE BEING SUBSTANTIALLY ALL NICKEL.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US389867A US2805154A (en) | 1953-11-02 | 1953-11-02 | Nickel-base alloy |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US389867A US2805154A (en) | 1953-11-02 | 1953-11-02 | Nickel-base alloy |
Publications (1)
Publication Number | Publication Date |
---|---|
US2805154A true US2805154A (en) | 1957-09-03 |
Family
ID=23540079
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
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US389867A Expired - Lifetime US2805154A (en) | 1953-11-02 | 1953-11-02 | Nickel-base alloy |
Country Status (1)
Country | Link |
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US (1) | US2805154A (en) |
Cited By (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3207599A (en) * | 1960-03-15 | 1965-09-21 | Int Nickel Co | Nickel-chromium-cobalt alloys |
US3222165A (en) * | 1958-11-26 | 1965-12-07 | Rolls Royce | Nickel chromium base alloy products |
DE1292871B (en) * | 1958-11-26 | 1969-04-17 | Rolls Royce | Use of a heat-resistant alloy based on nickel-chromium and its heat treatment |
DE1301585B (en) * | 1960-05-16 | 1969-08-21 | Rolls Royce | Use of a heat-resistant nickel-chromium alloy and process for its heat treatment |
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 |
Citations (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2018520A (en) * | 1932-03-03 | 1935-10-22 | Westinghouse Electric & Mfg Co | High strength alloy |
US2246078A (en) * | 1937-07-31 | 1941-06-17 | Rohn Wilhelm | Valve made of cobalt-nickel-chromium-iron alloy |
GB583841A (en) * | 1941-12-17 | 1947-01-01 | Mond Nickel Co Ltd | Improvements relating to heat-resisting alloys |
GB626204A (en) * | 1943-09-17 | 1949-07-12 | William Thomas Griffiths | Improvements relating to alloys for use at high temperatures |
US2570193A (en) * | 1946-04-09 | 1951-10-09 | Int Nickel Co | High-temperature alloys and articles |
US2712498A (en) * | 1948-06-01 | 1955-07-05 | Rolls Royce | Nickel chromium alloys having high creep strength at high temperatures |
-
1953
- 1953-11-02 US US389867A patent/US2805154A/en not_active Expired - Lifetime
Patent Citations (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2018520A (en) * | 1932-03-03 | 1935-10-22 | Westinghouse Electric & Mfg Co | High strength alloy |
US2246078A (en) * | 1937-07-31 | 1941-06-17 | Rohn Wilhelm | Valve made of cobalt-nickel-chromium-iron alloy |
GB583841A (en) * | 1941-12-17 | 1947-01-01 | Mond Nickel Co Ltd | Improvements relating to heat-resisting alloys |
GB626204A (en) * | 1943-09-17 | 1949-07-12 | William Thomas Griffiths | Improvements relating to alloys for use at high temperatures |
US2570193A (en) * | 1946-04-09 | 1951-10-09 | Int Nickel Co | High-temperature alloys and articles |
US2712498A (en) * | 1948-06-01 | 1955-07-05 | Rolls Royce | Nickel chromium alloys having high creep strength at high temperatures |
Cited By (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3222165A (en) * | 1958-11-26 | 1965-12-07 | Rolls Royce | Nickel chromium base alloy products |
DE1292871B (en) * | 1958-11-26 | 1969-04-17 | Rolls Royce | Use of a heat-resistant alloy based on nickel-chromium and its heat treatment |
US3207599A (en) * | 1960-03-15 | 1965-09-21 | Int Nickel Co | Nickel-chromium-cobalt alloys |
DE1301585B (en) * | 1960-05-16 | 1969-08-21 | Rolls Royce | Use of a heat-resistant nickel-chromium alloy and process for its heat treatment |
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 |
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