US2688536A - High-temperature creep resistant alloy - Google Patents
High-temperature creep resistant alloy Download PDFInfo
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- US2688536A US2688536A US208245A US20824551A US2688536A US 2688536 A US2688536 A US 2688536A US 208245 A US208245 A US 208245A US 20824551 A US20824551 A US 20824551A US 2688536 A US2688536 A US 2688536A
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- 229910045601 alloy Inorganic materials 0.000 title claims description 33
- 239000000956 alloy Substances 0.000 title claims description 33
- XEEYBQQBJWHFJM-UHFFFAOYSA-N Iron Chemical compound [Fe] XEEYBQQBJWHFJM-UHFFFAOYSA-N 0.000 claims description 28
- ZOXJGFHDIHLPTG-UHFFFAOYSA-N Boron Chemical compound [B] ZOXJGFHDIHLPTG-UHFFFAOYSA-N 0.000 claims description 18
- 229910052796 boron Inorganic materials 0.000 claims description 18
- XUIMIQQOPSSXEZ-UHFFFAOYSA-N Silicon Chemical compound [Si] XUIMIQQOPSSXEZ-UHFFFAOYSA-N 0.000 claims description 15
- 229910052782 aluminium Inorganic materials 0.000 claims description 15
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims description 15
- 229910052710 silicon Inorganic materials 0.000 claims description 15
- 239000010703 silicon Substances 0.000 claims description 15
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims description 14
- VYZAMTAEIAYCRO-UHFFFAOYSA-N Chromium Chemical compound [Cr] VYZAMTAEIAYCRO-UHFFFAOYSA-N 0.000 claims description 14
- ZOKXTWBITQBERF-UHFFFAOYSA-N Molybdenum Chemical compound [Mo] ZOKXTWBITQBERF-UHFFFAOYSA-N 0.000 claims description 14
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 claims description 14
- 229910052799 carbon Inorganic materials 0.000 claims description 14
- 229910052804 chromium Inorganic materials 0.000 claims description 14
- 239000011651 chromium Substances 0.000 claims description 14
- 229910052742 iron Inorganic materials 0.000 claims description 14
- 229910052750 molybdenum Inorganic materials 0.000 claims description 14
- 239000011733 molybdenum Substances 0.000 claims description 14
- 239000010936 titanium Substances 0.000 claims description 14
- 229910052719 titanium Inorganic materials 0.000 claims description 14
- PWHULOQIROXLJO-UHFFFAOYSA-N Manganese Chemical compound [Mn] PWHULOQIROXLJO-UHFFFAOYSA-N 0.000 claims description 11
- 229910052748 manganese Inorganic materials 0.000 claims description 11
- 239000011572 manganese Substances 0.000 claims description 11
- 230000003068 static effect Effects 0.000 claims description 11
- 230000001747 exhibiting effect Effects 0.000 claims description 6
- 229910000990 Ni alloy Inorganic materials 0.000 claims 1
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 description 38
- 229910052759 nickel Inorganic materials 0.000 description 19
- 239000000463 material Substances 0.000 description 8
- 238000005495 investment casting Methods 0.000 description 3
- 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 3
- 230000008018 melting Effects 0.000 description 3
- 238000002844 melting Methods 0.000 description 3
- 230000006698 induction Effects 0.000 description 2
- 230000001681 protective effect Effects 0.000 description 2
- 238000005452 bending Methods 0.000 description 1
- 239000000470 constituent Substances 0.000 description 1
- 230000003247 decreasing effect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000009661 fatigue test Methods 0.000 description 1
- 229910052751 metal Inorganic materials 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 150000002739 metals Chemical class 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000003647 oxidation Effects 0.000 description 1
- 238000007254 oxidation reaction 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
- C22C19/056—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W with the maximum Cr content being at least 10% but less than 20%
Definitions
- This invention has to do with an improved high temperature creep resistant alloy.
- the alloy of our invention is particularly adapted for parts which must withstand high stresses under elevated temperature conditions up to 1600 F., be resistant to oxidation at temperatures up to 2000 F. and at the same time have a relatively high ductility.
- Illustrative examples of parts for which our alloy is especially adapted are turbine blades or buckets and nozzle diaphragm vanes for gas turbines.
- Our new alloy is of nickel base and contains a minimum of strategic materials. It combines exceptional creep resistance at temperatures up to 1600 F. with good ductility.
- the high temperature creep resistant alloy in accordance with our invention preferably consists essentially as follows:
- Boron has a powerful effect on the alloy.
- the boron content above 0.10% the creep strength at elevated temperature is increased and the ductilitydecreased.
- Advantage may be taken of the increase in creep resistance at elevated temperature resulting from a higher boron content within the limits imposed by the ductility requirement in the particular application.
- the boron may range from about 0.01 to about 0.5%.
- the maximum amounts of silicon and manganese may be increased to as high as about 1% for specific applications.
- the aluminum content may be decreased to as low as about 1% for some applications.
- Emample I Test specimens were made by precision casting into investment molds an alloy melted in an induction furnace consisting essentially as follows: 0.15% carbon, 0.08% manganese, 0.30% silicon, 15.0% chromium, 4.63% molybdenum, 11.6% iron, 3.23% aluminum, 2.91% titanium, 0.02% boron, balance nickel.
- Test specimens of this material were subjected to a static tensile load of 24,250 pounds per square inch at a test temperature of 1500 F. It took 680 hours under these test conditions to elongate the test specimen 1% and 805 hours to rupture the test specimen. Impact resistance at room temperature on unnotched Charpy specimens was 28 to 36 foot pounds.
- a similar test on the alloy of Example I except that a temperature of 1600 F. was employed and a static tensile load of 25,000 pounds per square inch showed a cree life of 40 hours with 3.70% elongation at rupture. The time to produce 1% creep was 32 hours.
- Example II Test specimens were made by precision casting an alloy composed of 0.12% carbon, 0.09% manganese, 0.35% silicon, 15.5% chromium, 4.75% molybdenum, 10.6 iron, 2.85 aluminum, 2.51 titanium, 0.024% boron, and the balance nickel. Impact resistance at room temperature on unnotched Charpy specimens was 34 to 42 foot pounds. A test bar of this material was fatigue tested at a temperature of 1500 F. under a static tensile stress of 24,250 pounds per square inch and a dynamic bending stress of plus or minus 19,250 pounds per square inch. In other words, the stress repeatedly varied during the test from 5000 to 43,500 pounds per square inch. The loading varied 180 times each second. After 284 hours the bar had only elongated /2%.
- Example III ganese, 0.47% silicon, 14.6% chromium, 4.98%
- test specimen of this material was subjected to a static tensile load of 24,250 pounds per square inch at a temperature of 1500 F. It took 186 hours under these test conditions to elongate the test specimen 1% and 221 hours to rupture the test specimen. The percentage elongation of the test specimen at rupture was 2.28.
- Example IV Test specimens were made by precision casting an alloy composed of 0.14% carbon, 0.12% manganese, 0.43% silicon, 14.6% chromium, 4.72% molybdenum, 11.5% iron, 2.89% aluminum, 2.52% titanium, 0.122% boron and the balance nickel. Impact resistance at room temperature on unnotched Charpy specimenswas 22 to 30 foot pounds. A test specimen made of this material was subjected to a static tensile load of 24,250 pounds per square inch at a temperature of 1600 F. It took 50 /2 hours under these test conditions to elongate the test specimen 1%. The test was discontinued after 64 hours and the test specimen appeared in good condition. The percentage elongation at the time of discontinuance of the test was 3.75.
- test specimen made of this same material was fatigue tested.
- the part was fatigue tested at a temperature of 1600 F. under the loading conditions referred to above in connection with Example II. It took 20 hours under these test conditions to elongate the test specimen 1% and 37% hours to rupture the same. The percentage elongation at rupture was 4.25.
- the alloy or alloys of our invention may be compounded or made up in any desired manner. Any desired melting furnaces may be used. Typical examples of melting furnaces which have been used are the indirect arc and induction types. Protective atmospheres preferably are employed during the melting operation. It is preferable also to employ protective atmospheres in the molds in which the material is cast. Mold materials may be those employed for conventional high temperature alloys.
- a nickel base alloy exhibiting in the as cast condition a stress-rupture life of at least about 221 hours when subjected to a static tensile load of 24,250 pounds per square inch at a temperature of 1500 F. and a percentage elongation at rupture of at least about 2.28, said alloy consisting essentially as follows:
- a nickel base alloy exhibiting in the as cast condition a stress-rupture life of at least about 221 hours when subjected to a static tensile load of 24,250 pounds per square inch at a temperature of 1500 F. and a percentage elongation at rupture of at least about 2.28, said alloy consisting essentially as follows:
- a nickel base alloy exhibiting in the as cast condition a stress-rupture life of at least about 221 hours when subjected to a static tensile load of 24,250 pounds per square inch at a temperature of 1500 F. and a percentage elongation at rupture of at least about 2.28, said alloy consisting essentially as follows:
- a nickel base alloy exhibiting in the as cast condition a stress-rupture life of at least about 221 hours when subjected to a static tensile load of 24,250 pounds per square inch at a temperature of 1500 F. and a percentage elongation at rupture of at least about 2.28, said alloy consistingessentially as follows:
- a nickel base alloy exhibiting in the as cast condition a stress-rupture life of at least about 221 hours when subjected to a static tensile load of 24,250 pounds per square inch at a temperature of 1500 F. and a percentage elongation at rupture of at least about 2.28, said alloy consisting essentially as follows:
- a high temperature creep resistant alloy consisting as follows:
- a high temperature creep resistant alloy consisting as follows:
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- Engineering & Computer Science (AREA)
- Materials Engineering (AREA)
- Mechanical Engineering (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- Manufacture Of Alloys Or Alloy Compounds (AREA)
Description
Patented Sept. 7, 1954 HIGH-TEMPERATURE CREEP RESISTANT ALLOY Samuel R. Callaway, Huntington Woods, and Fred J. Webbere, Royal Oak, Mich., assignors to General Motors Corporation, Detroit, Mich.,
a corporation of Delaware No Drawing. Application January 27, 1951,
Serial No. 208,245
8 Claims.
This invention has to do with an improved high temperature creep resistant alloy.
The alloy of our invention is particularly adapted for parts which must withstand high stresses under elevated temperature conditions up to 1600 F., be resistant to oxidation at temperatures up to 2000 F. and at the same time have a relatively high ductility. Illustrative examples of parts for which our alloy is especially adapted are turbine blades or buckets and nozzle diaphragm vanes for gas turbines.
In common forms of high temperature alloys, creep resistance is obtained at the expense of ductility and lack of ductility is frequently an imposing limitation on an otherwise promising alloy.
Our new alloy is of nickel base and contains a minimum of strategic materials. It combines exceptional creep resistance at temperatures up to 1600 F. with good ductility.
The high temperature creep resistant alloy in accordance with our invention preferably consists essentially as follows:
0.10 to 0.20% carbon 0.25% maximum manganese 0.75% maximum silicon 13.00 to 17.00% chromium 4.00 to 6.00% molybdenum 1.50 to 3.00% titanium 2.00 to 4.00% aluminum 0.01 to 0.10% boron 8.00 to 12.00% iron Balance nickel While the foregoing is the preferred composition of the alloy of the present invention, some variation in the amounts of the several constituents is permissible without departing from the principles of the invention. For example in certain applications it is contemplated the carbon may be omitted entirely and in others may be as high as 0.25%.
Boron has a powerful effect on the alloy. By increasing the boron content above 0.10% the creep strength at elevated temperature is increased and the ductilitydecreased. Advantage may be taken of the increase in creep resistance at elevated temperature resulting from a higher boron content within the limits imposed by the ductility requirement in the particular application. In general the boron may range from about 0.01 to about 0.5%.
It is contemplated also that the maximum amounts of silicon and manganese may be increased to as high as about 1% for specific applications. The aluminum content may be decreased to as low as about 1% for some applications.
The following are illustrative examples of typical alloys in accordance with our invention and showing the results of tests thereon:
Emample I Test specimens were made by precision casting into investment molds an alloy melted in an induction furnace consisting essentially as follows: 0.15% carbon, 0.08% manganese, 0.30% silicon, 15.0% chromium, 4.63% molybdenum, 11.6% iron, 3.23% aluminum, 2.91% titanium, 0.02% boron, balance nickel.
Test specimens of this material were subjected to a static tensile load of 24,250 pounds per square inch at a test temperature of 1500 F. It took 680 hours under these test conditions to elongate the test specimen 1% and 805 hours to rupture the test specimen. Impact resistance at room temperature on unnotched Charpy specimens was 28 to 36 foot pounds. A similar test on the alloy of Example I except that a temperature of 1600 F. was employed and a static tensile load of 25,000 pounds per square inch showed a cree life of 40 hours with 3.70% elongation at rupture. The time to produce 1% creep was 32 hours.
Example II Test specimens were made by precision casting an alloy composed of 0.12% carbon, 0.09% manganese, 0.35% silicon, 15.5% chromium, 4.75% molybdenum, 10.6 iron, 2.85 aluminum, 2.51 titanium, 0.024% boron, and the balance nickel. Impact resistance at room temperature on unnotched Charpy specimens was 34 to 42 foot pounds. A test bar of this material was fatigue tested at a temperature of 1500 F. under a static tensile stress of 24,250 pounds per square inch and a dynamic bending stress of plus or minus 19,250 pounds per square inch. In other words, the stress repeatedly varied during the test from 5000 to 43,500 pounds per square inch. The loading varied 180 times each second. After 284 hours the bar had only elongated /2%. The test was discontinued after 307 hours and the bar appeared in good condition. When the test was discon tinued the bar had elongated 0.69. A similar fatigue test was made on the alloy of Example 11 except that a temperature of 1600 F. was used. It took 30 hours under these conditions to elongate the bar 1% and 42 hours to rupture the bar. The percentage elongation at rupture was 3.75.
Example III ganese, 0.47% silicon, 14.6% chromium, 4.98%
3 molybdenum, 10.1% iron, 2.20% aluminum, 2.71% titanium, 0.02% boron and the balance nickel. Impact resistance at room temperature on unnotched Charpy specimens was 34 to 44 foot pounds.
A test specimen of this material was subjected to a static tensile load of 24,250 pounds per square inch at a temperature of 1500 F. It took 186 hours under these test conditions to elongate the test specimen 1% and 221 hours to rupture the test specimen. The percentage elongation of the test specimen at rupture was 2.28.
Example IV Test specimens were made by precision casting an alloy composed of 0.14% carbon, 0.12% manganese, 0.43% silicon, 14.6% chromium, 4.72% molybdenum, 11.5% iron, 2.89% aluminum, 2.52% titanium, 0.122% boron and the balance nickel. Impact resistance at room temperature on unnotched Charpy specimenswas 22 to 30 foot pounds. A test specimen made of this material was subjected to a static tensile load of 24,250 pounds per square inch at a temperature of 1600 F. It took 50 /2 hours under these test conditions to elongate the test specimen 1%. The test was discontinued after 64 hours and the test specimen appeared in good condition. The percentage elongation at the time of discontinuance of the test was 3.75. Another test specimen made of this same material was fatigue tested. The part was fatigue tested at a temperature of 1600 F. under the loading conditions referred to above in connection with Example II. It took 20 hours under these test conditions to elongate the test specimen 1% and 37% hours to rupture the same. The percentage elongation at rupture was 4.25.
The alloy or alloys of our invention may be compounded or made up in any desired manner. Any desired melting furnaces may be used. Typical examples of melting furnaces which have been used are the indirect arc and induction types. Protective atmospheres preferably are employed during the melting operation. It is preferable also to employ protective atmospheres in the molds in which the material is cast. Mold materials may be those employed for conventional high temperature alloys.
Various changes and modifications of the embodiments of our invention described herein may bev made without departing from the spirit and principles of the invention.
We claim:
1. A nickel base alloy exhibiting in the as cast condition a stress-rupture life of at least about 221 hours when subjected to a static tensile load of 24,250 pounds per square inch at a temperature of 1500 F. and a percentage elongation at rupture of at least about 2.28, said alloy consisting essentially as follows:
0.0 to 0.25% carbon 0.0 to 1.00% manganese 0.0 to 1.00% silicon 13.00 to 17.00% chromium 4.00 to 6.00% molybdenum 1.50 to 3.00% titanium 1.00 to 4.00% aluminum 0.01 to 0.50% boron 8.00 to 12.00% iron Balance nickel.
2. A nickel base alloy exhibiting in the as cast condition a stress-rupture life of at least about 221 hours when subjected to a static tensile load of 24,250 pounds per square inch at a temperature of 1500 F. and a percentage elongation at rupture of at least about 2.28, said alloy consisting essentially as follows:
0.10 to 0.20% carbon 0.25% maximum manganese 0.75% maximum silicon 13.00 to 17.00% chromium 4.00 to 6.00% molybdenum 1.50 to 3.00% titanium 2.00 to 4.00% aluminum 0.01 to 0.10% boron 8.00 to 12.00% iron Balance nickel.
0.15% carbon 0.08% manganese 0.30% silicon 15.0% chromium 4.63 molybdenum 1 1.6 iron 3.23% aluminum 2.91% titanium 0.02% boron Balance nickel.
4. A nickel base alloy exhibiting in the as cast condition a stress-rupture life of at least about 221 hours when subjected to a static tensile load of 24,250 pounds per square inch at a temperature of 1500 F. and a percentage elongation at rupture of at least about 2.28, said alloy consisting essentially as follows:
0.12% carbon 0.09% manganese 0.35% silicon 15.5% chromium 4.75% molybdenum 10.6% iron 2.85% aluminum 2.51 titanium 0.024% boron Balance nickel.
5. A nickel base alloy exhibiting in the as cast condition a stress-rupture life of at least about 221 hours when subjected to a static tensile load of 24,250 pounds per square inch at a temperature of 1500 F. and a percentage elongation at rupture of at least about 2.28, said alloy consistingessentially as follows:
0.15% carbon 0.06% manganese 0.47% silicon 14.6% chromium 4.98% molybdenum 10.1% iron 2.20% aluminum 2.71% titanium 0.02% boron Balance nickel.
6. A nickel base alloy exhibiting in the as cast condition a stress-rupture life of at least about 221 hours when subjected to a static tensile load of 24,250 pounds per square inch at a temperature of 1500 F. and a percentage elongation at rupture of at least about 2.28, said alloy consisting essentially as follows:
0.14% carbon 0.12% manganese 0.43% silicon 14.6% chromium 4.72% molybdenum 11.5% iron 2.89% aluminum 2.52% titanium 0.122% boron Balance nickel.
7. A high temperature creep resistant alloy consisting as follows:
0.0 to 0.25% carbon 0.0 to 1.00% manganese 0.0 to 1.00% silicon 13.00 to 17.00% chromium 4.00 to 6.00% molybdenum 1.50 to 3.00% titanium 1.00 to 4.00% aluminum 0.01 to 0.50% boron 8.00 to 12.00% iron Balance nickel.
8. A high temperature creep resistant alloy consisting as follows:
6 0.10 to 0.20% carbon 0.25% maximum manganese 0.75% maximum silicon 13.00 to 17.00% chromium 4.00 to 6.00% molybdenum 1.50 to 3.00% titanium 2.00 to 4.00% aluminum 0.01 to 0.10% boron 8.00 to 12.00% iron Balance nickel.
References Cited in the file of this patent UNITED STATES PATENTS Number Number Name Date Rohn et a1 June 17, 1941 Scott et al July 2, 1946 Franks et a1 July 4, 1950 Bieber et al. Oct. 9, 1951 Guy Nov. 20, 1951 FOREIGN PATENTS Country Date Great Britain Oct. 26, 1945 Great Britain Mar. 29, 1949 OTHER REFERENCES Guy, Treatise in Trans. of Amer. Soc. for Metals, vol. 41, 1949, pages -140.
Claims (1)
1. A NICKEL ALLOY EXHIBITING IN THE AS CAST CONDITION A STRESS-RUPTURE LIFE AT LEAST ABOUT 221 HOURS WHEN SUBJECTED TO A STATIC TENSILE LOAD OF 24,250 POUNDS PER SQUARE INCH AT A TEMPERATURE OF 1500* F. AND A PERCENTAGE ELONGATION AT RUPTURE OF AT LEAST ABOUT 2.28, SAID ALLOY CONSISTING ESSENTIALLY AS FOLLOWS: 0.0 TO 0.25% CARBON 0.0 TO 1.00% MANGANESE 0.0 TO 1.00% SILICON 13.00 TO 17.00% CHROMIUM 4.00 TO 6.00% MOLYBDENUM 1.50 TO 3.00% TITANIUM 1.00 TO 4.00% ALUMINUM 0.01 TO 0.50% BORON 8.00 TO 12.00% IRON BALANCE NICKEL.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
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US208245A US2688536A (en) | 1951-01-27 | 1951-01-27 | High-temperature creep resistant alloy |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
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US208245A US2688536A (en) | 1951-01-27 | 1951-01-27 | High-temperature creep resistant alloy |
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US2688536A true US2688536A (en) | 1954-09-07 |
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US208245A Expired - Lifetime US2688536A (en) | 1951-01-27 | 1951-01-27 | High-temperature creep resistant alloy |
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Cited By (11)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2798827A (en) * | 1956-05-07 | 1957-07-09 | Gen Motors Corp | Method of casting and heat treating nickel base alloys |
US2873187A (en) * | 1956-12-07 | 1959-02-10 | Allegheny Ludlum Steel | Austenitic alloys |
US2899302A (en) * | 1959-08-11 | Mckel-silicon-boron alloys | ||
US2970065A (en) * | 1956-12-31 | 1961-01-31 | Gen Motors Corp | Forming an aluminum-containing alloy protective layer on metals |
US2977222A (en) * | 1955-08-22 | 1961-03-28 | Int Nickel Co | Heat-resisting nickel base alloys |
US3027254A (en) * | 1959-04-21 | 1962-03-27 | Gen Electric | Nickel-cobalt base alloys |
US3047381A (en) * | 1958-02-03 | 1962-07-31 | Gen Motors Corp | High temperature heat and creep resistant alloy |
US3457066A (en) * | 1959-04-10 | 1969-07-22 | Gen Electric | Nickel base alloy |
EP0066365A2 (en) * | 1981-04-20 | 1982-12-08 | International Nickel Inc. | Nickel-chromium-iron alloy and castings thereof |
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 |
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Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2246078A (en) * | 1937-07-31 | 1941-06-17 | Rohn Wilhelm | Valve made of cobalt-nickel-chromium-iron alloy |
GB572861A (en) * | 1942-04-09 | 1945-10-26 | Mond Nickel Co Ltd | Improvements in nickel and cobalt alloys |
US2403128A (en) * | 1942-06-24 | 1946-07-02 | Westinghouse Electric Corp | Heat resistant alloys |
GB620676A (en) * | 1946-03-26 | 1949-03-29 | High Duty Alloys Ltd | Improvements relating to nickel, cobalt, chromium base alloys |
US2513471A (en) * | 1946-05-09 | 1950-07-04 | Union Carbide & Carbon Corp | Alloy articles for high-temperature service |
US2570193A (en) * | 1946-04-09 | 1951-10-09 | Int Nickel Co | High-temperature alloys and articles |
US2575915A (en) * | 1945-05-21 | 1951-11-20 | Gen Electric | Nickel base high-temperature alloy |
-
1951
- 1951-01-27 US US208245A patent/US2688536A/en not_active Expired - Lifetime
Patent Citations (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2246078A (en) * | 1937-07-31 | 1941-06-17 | Rohn Wilhelm | Valve made of cobalt-nickel-chromium-iron alloy |
GB572861A (en) * | 1942-04-09 | 1945-10-26 | Mond Nickel Co Ltd | Improvements in nickel and cobalt alloys |
US2403128A (en) * | 1942-06-24 | 1946-07-02 | Westinghouse Electric Corp | Heat resistant alloys |
US2575915A (en) * | 1945-05-21 | 1951-11-20 | Gen Electric | Nickel base high-temperature alloy |
GB620676A (en) * | 1946-03-26 | 1949-03-29 | High Duty Alloys Ltd | Improvements relating to nickel, cobalt, chromium base alloys |
US2570193A (en) * | 1946-04-09 | 1951-10-09 | Int Nickel Co | High-temperature alloys and articles |
US2513471A (en) * | 1946-05-09 | 1950-07-04 | Union Carbide & Carbon Corp | Alloy articles for high-temperature service |
Cited By (14)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2899302A (en) * | 1959-08-11 | Mckel-silicon-boron alloys | ||
US2977222A (en) * | 1955-08-22 | 1961-03-28 | Int Nickel Co | Heat-resisting nickel base alloys |
US2798827A (en) * | 1956-05-07 | 1957-07-09 | Gen Motors Corp | Method of casting and heat treating nickel base alloys |
US2873187A (en) * | 1956-12-07 | 1959-02-10 | Allegheny Ludlum Steel | Austenitic alloys |
US2970065A (en) * | 1956-12-31 | 1961-01-31 | Gen Motors Corp | Forming an aluminum-containing alloy protective layer on metals |
US3047381A (en) * | 1958-02-03 | 1962-07-31 | Gen Motors Corp | High temperature heat and creep resistant alloy |
US3457066A (en) * | 1959-04-10 | 1969-07-22 | Gen Electric | Nickel base alloy |
US3027254A (en) * | 1959-04-21 | 1962-03-27 | Gen Electric | Nickel-cobalt base alloys |
EP0066365A2 (en) * | 1981-04-20 | 1982-12-08 | International Nickel Inc. | Nickel-chromium-iron alloy and castings thereof |
EP0066365A3 (en) * | 1981-04-20 | 1983-01-19 | Howmet Turbine Components Corporation | Nickel-chromium-iron alloy and castings thereof |
US4401622A (en) * | 1981-04-20 | 1983-08-30 | The International Nickel Co., Inc. | Nickel-chromium-iron 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 |
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