US3166412A - Cast nickel-base alloy for gas turbine rotors - Google Patents
Cast nickel-base alloy for gas turbine rotors Download PDFInfo
- Publication number
- US3166412A US3166412A US220857A US22085762A US3166412A US 3166412 A US3166412 A US 3166412A US 220857 A US220857 A US 220857A US 22085762 A US22085762 A US 22085762A US 3166412 A US3166412 A US 3166412A
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- United States
- Prior art keywords
- alloy
- cast
- nickel
- base alloy
- gas turbine
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- Expired - Lifetime
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Classifications
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- 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
-
- 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
- the present invention provides cast nickel alloys containing, in percent by weight, not more than about 0.05% or 0.06% carbon, e.g., about 0.03% carbon, about to about 18% chromium, about 5% to about 7% aluminum, up to about 1.5% titanium, e.g., 0.5% to about 1.5% titanium, about 1% to about 3% columbium, about 0.5% to about 6% molybdenum, with the chromium plus molybdenum contents being about to about 20% of the alloy, up to about 0.05%
- chromium advantageously is maintm'ned in the range of 10% to 14%.
- the total content of chromium and molybdenum in the alloy is import-ant and must be maintained in the range of 15% to 20% in order to provide the best combination that which exists in Thus, it is no longer It has accordinglybeen pro- .of corrosion resistance, strength, and ductility at elevated temperatures.
- Aluminum ⁇ is an important hardening and strengthening element in the alloy and is maintained in the range of 5% to ⁇ 7% because strength is ⁇ sacriticed if the concentration of this element is too low while the ductility is lowered if the concentration is above 7%.
- Titanium when present even in amounts of about 0.5%, contributes further hardening and strengthening to the alloy but should not exceed about 1.5% of the alloy because ductility and castability are reduced if the titanium content is higher than this value.
- Columbium also plays an important part in strengthening thealloy and is' employed in amounts of 1% to 3% because strength is sacrificed if Vthe concentration of this element is below 1%l while the ductility is reduced if the concentration is above'3r%; Boron and zirconium present in the alloy contribute-markedly to the development of satisfactory lem is crea-tedisince it is necessary to provide within a Y single unitary casting metallurgical structures'which will operate under vastly diiferent conditions of stress and temperature.
- the invention also contemplates providing gas turbinev are unsatisfactoryas OnV the other hand, it has been found' strength and ductility properties therein.
- the presence of fas little as 0.005% boron and at least about ⁇ ,0.02% zirconium provide good ductility- ⁇ at temperatures" ab'oveabout1000jo to 1200 F.
- Calcium in thealloy is employedin air melting to serve as a deoxidizer. It is omitted in vacuum melting..
- VIt is to be understood that ,carbon inthe ⁇ alloymust be Vmaintained at very low vales not exceeding 0.06% in order that the alloys will exhibit the required high elongation inthe as-cast condition at room temperature even in sections as heavy as three inches thick or more. Small carbon contents of about 0.03% arebeneiicial in producing the master alloy Vwhich is tobe remeltfed to make the finished castings.
- the alloy provided in accordance with the invention may also contain up toV 15% ⁇ cobalt, e.g., about V10% cobalt, assuch amounts of cobalt permit the inclusion in the alloy of as much as about 8% of aluminum without encounterling serious embrittling effects; vTungsten may be employed in ⁇ placebf apart or all of the molybdenum in the Aalloy.
- the alloy should be as devoid as practicable of impurities such as sulfur, phosphorus, lead, antimony, tin, selenium, tellurium, bismuth, etc. Elements such as silicon and 'manganese are undesirable and should not be present in amounts exceeding about 0.2% and 0.1%, respectively. 'Iron is also an undesirable element in the alloy ⁇ land should not be present in amounts exceeding about 0.5%, e.g., about 0.25%.
- the balance of the alloy is essentially nickel.
- the alloy provided in accordance with the invention is characterized by a room temperature'tensile strength -in the as-cast condition of at least about 100,000 p.s.i. and anelongation of at least about 10% in .the Ias-cast condition.
- the alloy provides relatively long service life at temperatures on the order of about 1700 ⁇ F. to
- The'following tables contain, respectively, the chemical :ompositions, in percent by Weight, of vacuum melted and vacuum cast alloys produced in accordance with the invention, the rupture lives of the alloys at 17.00 F. and 30,000 p.s.i. in the as-cast condition, and the room ternperature tensile properties of these alloys in the ⁇ as-cast j conditionz- Table I Alloy Perler- Per- Per- Per- Per- Per- Per- 'Per- Per- No. cent (eut cent cent ycent cent cent cent cent cent Cr Mo Cb A1 Ti C Zr Ni L v ,12 5 2 6 0.6 0.008 0.01 0.10 .Bal Z 12 5 2' 6 0.6 0.05 0.01 0.10 Bal.
- v f Y 1 A casting having atleast oneincluded section subjectedin use to high stressat temperatures on the order of Vabout 17009 F. and at least one included section subjected in use to high stress at temperatures on the order of about 1000* F., made of'anv alloy consisting' essentially of vabout0.008% ⁇ to 0.05%fcarbo'n, aboutv 12% chromium, about '5% molybdenum, Vabout 6% aluminum, .about 0.6% titanium, -about 2%, columbiurn, ⁇ about 0.01%
- i' f fAlloys in accorda ncewith the invention have particulalrly satisfactory properties when produced byr vacuum Y melting'. They may, however, be melted under argon or even under air'atmospheres with goodcastability and j. f
- the strength of the alloy at room temperature and atl i elevated temperatures may be improved by subjectingithe castings ,to a heat treatment comprising a heating at about j 215011?. for about 15 minutes to about'24'hours, e.g., about two hours, followed by acooling to roomtemperature. fjlffde'sired', a further stabilization treatment consisting of a heating at about 1700o F. for about one to about 24 hours, -ie.g.,about fourV hours, kmay also be employed. .in casting thefalloy, it is important to superheat the, melt 'topa temperature of, at least 300 F., butk more-advantageously at least about 400 F; or 500 F.,
- a pouring temperaturehvof about 2950 F. Y.
- a nickel-base al loy containing ⁇ not morey than about 0.06% carbon, about '10%.to 18% chromium, Vabout 0.5% to 6%V of a metal from the group consisting of molybdenum and tungsten andwith the total contents of chromium, molybdenum andtung'sten being about 15 to about 20%, about 5% to 8% aluminum, up to about 15% cobalt with the proviso that Wheri'theicobalt content isv lessthanvabout 10% ⁇ the aluminum content is about 5% to,7%, up to about 1.5% titanium, about 1% to 3% columbiurm about 0.01% boron,V up ,toV about 0.15%
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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)
- Moulds For Moulding Plastics Or The Like (AREA)
Description
Y temperature for relatively long periods of time.-
United States Patent Office f 3,166,412 Patented Jan. 19, 1965 3,166,412 CAST NICKEL-BASE ALLY FOR GAS TURBINE ROTRS Clarence G. Bieber, Roselie Park, NJ., assigner to The International Nickel Company, Inc., New York, N.Y., a corporation of Delaware No Drawing. Filed Aug. 31,1962, Ser. No. 220,857
4 Claims. (Cl. l5-171) in gas turbines employed in aircraft and in other applica-` tions. Generally, for aircraft applications, the nickelbase alloy bladesare produced individually and are ythen fastened into a rotor'hub which is made of a d ilferent alloy to produce a composite turbine rotor. Since the hub portion of the rotor is not required-to operate `.at the very high temperatures to which theblade portions of the rotor are-subjected, the metal or alloy which is employed for the rotor hub is required only to have good strength and ductility over the temperature range from approximately room temperature upv to, possibly l000 F. or
12009 F. ln the production ofturbine rotors for use in gas turbines of relativelyV small size which can be employed in automotive gas turbine applications, the economic picture is quite different from the case of aircraft gas turbines. economically feasible to produceithe blades separately and then fasten them to the rotor Ahub so as ,to form a composite turbine rotor.
posed to produce` the turbine Vrotor as a unitary casting having the blades integrallycast into` the hub., Since the i blade portions of therotor are subjected to completely different combinations of stress and temperature than is the hub portion ofthe rotor, a vexing metallurgical prob-` rotors made of the4 special cast alloy provided in accordance with the invention and which have the blades cast integrally with the hub.
Other objects and advantages will become apparent from the following description.
Generally speaking, the present invention provides cast nickel alloys containing, in percent by weight, not more than about 0.05% or 0.06% carbon, e.g., about 0.03% carbon, about to about 18% chromium, about 5% to about 7% aluminum, up to about 1.5% titanium, e.g., 0.5% to about 1.5% titanium, about 1% to about 3% columbium, about 0.5% to about 6% molybdenum, with the chromium plus molybdenum contents being about to about 20% of the alloy, up to about 0.05%
boron, up to about 0.15% zirconium, up to about 0.05%
calcium, andthe balance essentially nickel. For best combinations of strength and ductility, chromium advantageously is maintm'ned in the range of 10% to 14%. p
The total content of chromium and molybdenum in the alloy is import-ant and must be maintained in the range of 15% to 20% in order to provide the best combination that which exists in Thus, it is no longer It has accordinglybeen pro- .of corrosion resistance, strength, and ductility at elevated temperatures. Aluminum `is an important hardening and strengthening element in the alloy and is maintained in the range of 5% to`7% because strength is`sacriticed if the concentration of this element is too low while the ductility is lowered if the concentration is above 7%.
Titanium, when present even in amounts of about 0.5%, contributes further hardening and strengthening to the alloy but should not exceed about 1.5% of the alloy because ductility and castability are reduced if the titanium content is higher than this value. Columbium also plays an important part in strengthening thealloy and is' employed in amounts of 1% to 3% because strength is sacrificed if Vthe concentration of this element is below 1%l while the ductility is reduced if the concentration is above'3r%; Boron and zirconium present in the alloy contribute-markedly to the development of satisfactory lem is crea-tedisince it is necessary to provide within a Y single unitary casting metallurgical structures'which will operate under vastly diiferent conditions of stress and temperature. It is known that alloys which are satisfactory forservice in the rotor hub blade materials. in practice that the alloys which are satisfactory as the blade materials are notfsatisfactory for use in the hub portion of the rotor, Accordingly, a demand has arisen for a nickel-base lcas'tingalloy havingV properties which would render it at the same time satisfactory for use as a cast rotor hub material and for use as a cast turbine blade material. y
Although attempts havebeenmade to .overcome the foregoing diliculties and` other diiiieulties, none, as Vfar as I am aware, was entirely successful when carried into practice'commercially on anindustrial scale. i
It hasnow been discovered that particular cast nickel#V Another object ofthe present invention is `to provide a cast alloy having high combinationsV of strength and ductility at usual ambient temperatures.
The invention also contemplates providing gas turbinev are unsatisfactoryas OnV the other hand, it has been found' strength and ductility properties therein.. Thus, the presence of fas little as 0.005% boron and at least about `,0.02% zirconium provide good ductility-` at temperatures" ab'oveabout1000jo to 1200 F. Calcium in thealloy is employedin air melting to serve as a deoxidizer. It is omitted in vacuum melting.. VIt is to be understood that ,carbon inthe `alloymust be Vmaintained at very low vales not exceeding 0.06% in order that the alloys will exhibit the required high elongation inthe as-cast condition at room temperature even in sections as heavy as three inches thick or more. Small carbon contents of about 0.03% arebeneiicial in producing the master alloy Vwhich is tobe remeltfed to make the finished castings.
The alloy provided in accordance with the invention may also contain up toV 15%` cobalt, e.g., about V10% cobalt, assuch amounts of cobalt permit the inclusion in the alloy of as much as about 8% of aluminum without encounterling serious embrittling effects; vTungsten may be employed in` placebf apart or all of the molybdenum in the Aalloy. ,"The alloy should be as devoid as practicable of impurities such as sulfur, phosphorus, lead, antimony, tin, selenium, tellurium, bismuth, etc. Elements such as silicon and 'manganese are undesirable and should not be present in amounts exceeding about 0.2% and 0.1%, respectively. 'Iron is also an undesirable element in the alloy `land should not be present in amounts exceeding about 0.5%, e.g., about 0.25%. The balance of the alloy is essentially nickel.
The alloy provided in accordance with the invention is characterized by a room temperature'tensile strength -in the as-cast condition of at least about 100,000 p.s.i. and anelongation of at least about 10% in .the Ias-cast condition. In addition, the alloy provides relatively long service life at temperatures on the order of about 1700` F. to
The'following tables contain, respectively, the chemical :ompositions, in percent by Weight, of vacuum melted and vacuum cast alloys produced in accordance with the invention, the rupture lives of the alloys at 17.00 F. and 30,000 p.s.i. in the as-cast condition, and the room ternperature tensile properties of these alloys in the `as-cast j conditionz- Table I Alloy Perler- Per- Per- Per- Per- Per- 'Per- Per- No. cent (eut cent cent ycent cent cent cent cent Cr Mo Cb A1 Ti C Zr Ni L v ,12 5 2 6 0.6 0.008 0.01 0.10 .Bal Z 12 5 2' 6 0.6 0.05 0.01 0.10 Bal.
Table Il y Y Rupture Life, v Y y f .Alloy No. Hours,-1700 F., Percent Elongation v `30,000 psi.
1Q.' 57.2, 12:4 2 74.0 g l 24 Table III j Yield VUltimate Y Alloy No. Strength, Tensile `Percent',
f p.s.i. Strength, Elongation j Y 7 psi.
In contrast to the properties developed in the foregoing alloys, another alloy identical Vin composition to Alloy No.- 2 set forthhereinbefore except that incontained 0.12% carbon was found to have a satisfactory rupture life of 64 hours at 1700 Rand 30,000 p.s.i.ltogether Vention is particularly applicable to the production of castings, such `as turbine rotors having the blades integrally cast with the hub, which have at least one included section subjected in use to high stress at temperatures on the order of about 1700 F. andhave at least one included section subjected in use to high stress at temperatures on the order of about 1000o F. Such castingsproduced in accordance with the invention provide satisfactory properties although portions thereof `are subjected to very different service `temperatures from those to which other portions of the casting are subjected. The castings have improved fatigue strength.
As Will be readily understood by those skilled iu the art', the expression ,balance essentially nickel does not exclude the presence of other elements commonly present in such alloys as incidental elements, eg., deoxidizing and cleansingelements, andirnpurities ordinarily associated therewith in small amounts which do not adversely affect the basic characteristics of my alloys. p
VAlthough the present inventionhas been described in conjunction with .preferred embodiments, it is` to be understood rthat modifications and variations may be, resort'edftov Without departing from the spirit and scope of the invention as those skilled in the art will readily understand. Suchmodifications and variations are considered ,to be within the purview and scope of the invention and appendedclairns.. j
I claim: v f Y 1. A casting having atleast oneincluded section subjectedin use to high stressat temperatures on the order of Vabout 17009 F. and at least one included section subjected in use to high stress at temperatures on the order of about 1000* F., made of'anv alloy consisting' essentially of vabout0.008% `to 0.05%fcarbo'n, aboutv 12% chromium, about '5% molybdenum, Vabout 6% aluminum, .about 0.6% titanium, -about 2%, columbiurn,` about 0.01%
with a room temperature vyield strength of 104,000 psi.
and a room temperature tensile strength of 126,000 psi. but was found to have an elongation at room temperature j of yonly 6%. i' f fAlloys in accorda ncewith the invention have particulalrly satisfactory properties when produced byr vacuum Y melting'. They may, however, be melted under argon or even under air'atmospheres with goodcastability and j. f
with onlyslight sacrifice `in properties as compared tof those produced by vacuum melting.
The strength of the alloy at room temperature and atl i elevated temperatures may be improved by subjectingithe castings ,to a heat treatment comprising a heating at about j 215011?. for about 15 minutes to about'24'hours, e.g., about two hours, followed by acooling to roomtemperature. fjlffde'sired', a further stabilization treatment consisting of a heating at about 1700o F. for about one to about 24 hours, -ie.g.,about fourV hours, kmay also be employed. .in casting thefalloy, it is important to superheat the, melt 'topa temperature of, at least 300 F., butk more-advantageously at least about 400 F; or 500 F.,
e.g.,5600' F.,'about the 'freezingtemperature thereof. For example, a pouring temperaturehvof about 2950 F. Y.
is very satisfactory.A
The yalloy provided in accordance w ith the present yin-` boron, about 0.1% zirconium, and the balance essentially nickel. r` Y 2. A nickel-base al loy containing` not morey than about 0.06% carbon, about '10%.to 18% chromium, Vabout 0.5% to 6%V of a metal from the group consisting of molybdenum and tungsten andwith the total contents of chromium, molybdenum andtung'sten being about 15 to about=20%, about 5% to 8% aluminum, up to about 15% cobalt with the proviso that Wheri'theicobalt content isv lessthanvabout 10% `the aluminum content is about 5% to,7%, up to about 1.5% titanium, about 1% to 3% columbiurm about 0.01% boron,V up ,toV about 0.15%
.0 5 %V calcium, and thevbalanc'e References Citedin the file of this patent UNITED' STATESPATENTS y, Y 2,912,323 Bieber et a1. 1; 1 Nov. 10, 1959 2,975,051Y vviisonetal.maman111111.14,1961 3,0o5;7e4. Fsu1imer;; r oct. 24,1961
L I FOREIGN PATENTS 45218,77?, J Canada Y Nov. 12, 1957.
"loy according to claim 1 `vvherein i UNITED STATES PATENT OFFICE CERTIFICATE 0F CORRECTION Patent No. 5,166,412 January 19, 1965 Clarence G. Bieber It is hereby certified that error appears in the above vnumbered patent requiring correction and that the said Letters Patent should read as corrected below.
Column 3, line 65, for "about" read -above Signed and sealed this 6th day of July 1965e (SEAL) Attest:
Commissioner of Patents
Claims (1)
- 2. A NICKEL-BASE ALLOY CONTAINING NOT MORE THAN ABOUT 0.06% CARBON, ABOUT 10% TO 18% CHROMIUM, ABOUT 0.5% TO 6% OF A METAL FROM THE GROUP CONSISTING OF MOLYBDENUM AND TUNGSTEN AND WITH THE TOTAL CONTENTS OF CHROMIUM, MOLYBDENUM AND TUNGSTEN BEGING ABOUT 15% TO ABOUT 20%, ABOUT 5% TO 8% ALUMINUM, UP TO ABOUT 15% COBALT WITH THE PROVISO THAT WHEN THE COBALT CONTENT IS LESS THAN ABOUT 10% THE ALUMINUM CONTENT IS ABOUT 5% TO 7%, UP TO ABOUT 1.5% TITANIUM, ABOUT 1% TO 3% COLUMBIUM, ABOUT 0.01% BORON, UP TO ABOUT 0.15% ZIRCONIUM, UP TO ABOUT 0.05% CALCIUM, AND THE BALANCE ESSENTIALLY NICKEL.
Priority Applications (11)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US220857A US3166412A (en) | 1962-08-31 | 1962-08-31 | Cast nickel-base alloy for gas turbine rotors |
| GB33116/63A GB968495A (en) | 1962-08-31 | 1963-08-21 | Nickel alloys |
| AT690963A AT241133B (en) | 1962-08-31 | 1963-08-28 | Method of making a casting |
| ES291188A ES291188A1 (en) | 1962-08-31 | 1963-08-28 | A method of making a cold piece (Machine-translation by Google Translate, not legally binding) |
| CH1065763A CH420635A (en) | 1962-08-31 | 1963-08-29 | Method of manufacturing a nickel alloy casting |
| SE9421/63A SE307018B (en) | 1962-08-31 | 1963-08-29 | |
| DEJ24337A DE1219236B (en) | 1962-08-31 | 1963-08-29 | Process for the production of castings, in particular of gas turbine rotors with blades cast onto the hub, from a nickel-chromium alloy |
| FR946059A FR1367387A (en) | 1962-08-31 | 1963-08-29 | Nickel alloys |
| NL297339D NL297339A (en) | 1962-08-31 | 1963-08-30 | |
| BE636847D BE636847A (en) | 1962-08-31 | 1963-08-30 | |
| LU44364D LU44364A1 (en) | 1962-08-31 | 1963-08-31 |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US220857A US3166412A (en) | 1962-08-31 | 1962-08-31 | Cast nickel-base alloy for gas turbine rotors |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| US3166412A true US3166412A (en) | 1965-01-19 |
Family
ID=22825271
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| US220857A Expired - Lifetime US3166412A (en) | 1962-08-31 | 1962-08-31 | Cast nickel-base alloy for gas turbine rotors |
Country Status (11)
| Country | Link |
|---|---|
| US (1) | US3166412A (en) |
| AT (1) | AT241133B (en) |
| BE (1) | BE636847A (en) |
| CH (1) | CH420635A (en) |
| DE (1) | DE1219236B (en) |
| ES (1) | ES291188A1 (en) |
| FR (1) | FR1367387A (en) |
| GB (1) | GB968495A (en) |
| LU (1) | LU44364A1 (en) |
| NL (1) | NL297339A (en) |
| SE (1) | SE307018B (en) |
Cited By (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3310440A (en) * | 1964-10-21 | 1967-03-21 | United Aircraft Corp | Heat treatment of nickel base alloys |
| US3343950A (en) * | 1963-12-23 | 1967-09-26 | Int Nickel Co | Nickel-chromium alloys useful in the production of wrought articles for high temperature application |
| US3376132A (en) * | 1964-05-05 | 1968-04-02 | Int Nickel Co | Impact resistant nickel-chromium alloys |
| US3403059A (en) * | 1965-06-24 | 1968-09-24 | Gen Electric | Nickel base alloy |
| US4530727A (en) * | 1982-02-24 | 1985-07-23 | The United States Of America As Represented By The Department Of Energy | Method for fabricating wrought components for high-temperature gas-cooled reactors and product |
| JPS62167835A (en) * | 1985-11-26 | 1987-07-24 | ユナイテツド・テクノロジ−ズ・コ−ポレイシヨン | Nickel base superalloy |
| US4685977A (en) * | 1984-12-03 | 1987-08-11 | General Electric Company | Fatigue-resistant nickel-base superalloys and method |
| DE4412031A1 (en) * | 1993-04-07 | 1994-10-13 | Aluminum Co Of America | Method for manufacturing forgings made of nickel alloys |
| US5374323A (en) * | 1991-08-26 | 1994-12-20 | Aluminum Company Of America | Nickel base alloy forged parts |
| US5540789A (en) * | 1992-05-28 | 1996-07-30 | United Technologies Corporation | Oxidation resistant single crystal superalloy castings |
| US6284392B1 (en) | 1999-08-11 | 2001-09-04 | Siemens Westinghouse Power Corporation | Superalloys with improved weldability for high temperature applications |
| US6974508B1 (en) | 2002-10-29 | 2005-12-13 | The United States Of America As Represented By The United States National Aeronautics And Space Administration | Nickel base superalloy turbine disk |
| WO2018069666A1 (en) | 2016-10-12 | 2018-04-19 | Oxford University Innovation Limited | A nickel-based alloy |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB733489A (en) * | 1952-07-09 | 1955-07-13 | Mond Nickel Co Ltd | Improvements relating to nickel-chromium-cobalt alloys |
| CA548777A (en) * | 1957-11-12 | G. Bieber Clarence | Nickel-base heat-resistant alloy | |
| US2912323A (en) * | 1957-09-16 | 1959-11-10 | Int Nickel Co | Cast nickel base alloy for high temperature service |
| US2975051A (en) * | 1959-09-29 | 1961-03-14 | Gen Electric | Nickel base alloy |
| US3005704A (en) * | 1958-07-23 | 1961-10-24 | Union Carbide Corp | Nickel base alloy for service at high temperatures |
-
1962
- 1962-08-31 US US220857A patent/US3166412A/en not_active Expired - Lifetime
-
1963
- 1963-08-21 GB GB33116/63A patent/GB968495A/en not_active Expired
- 1963-08-28 AT AT690963A patent/AT241133B/en active
- 1963-08-28 ES ES291188A patent/ES291188A1/en not_active Expired
- 1963-08-29 DE DEJ24337A patent/DE1219236B/en active Pending
- 1963-08-29 CH CH1065763A patent/CH420635A/en unknown
- 1963-08-29 SE SE9421/63A patent/SE307018B/xx unknown
- 1963-08-29 FR FR946059A patent/FR1367387A/en not_active Expired
- 1963-08-30 NL NL297339D patent/NL297339A/nl unknown
- 1963-08-30 BE BE636847D patent/BE636847A/fr unknown
- 1963-08-31 LU LU44364D patent/LU44364A1/xx unknown
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CA548777A (en) * | 1957-11-12 | G. Bieber Clarence | Nickel-base heat-resistant alloy | |
| GB733489A (en) * | 1952-07-09 | 1955-07-13 | Mond Nickel Co Ltd | Improvements relating to nickel-chromium-cobalt alloys |
| US2912323A (en) * | 1957-09-16 | 1959-11-10 | Int Nickel Co | Cast nickel base alloy for high temperature service |
| US3005704A (en) * | 1958-07-23 | 1961-10-24 | Union Carbide Corp | Nickel base alloy for service at high temperatures |
| US2975051A (en) * | 1959-09-29 | 1961-03-14 | Gen Electric | Nickel base alloy |
Cited By (19)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3343950A (en) * | 1963-12-23 | 1967-09-26 | Int Nickel Co | Nickel-chromium alloys useful in the production of wrought articles for high temperature application |
| US3376132A (en) * | 1964-05-05 | 1968-04-02 | Int Nickel Co | Impact resistant nickel-chromium alloys |
| US3310440A (en) * | 1964-10-21 | 1967-03-21 | United Aircraft Corp | Heat treatment of nickel base alloys |
| US3403059A (en) * | 1965-06-24 | 1968-09-24 | Gen Electric | Nickel base alloy |
| US4530727A (en) * | 1982-02-24 | 1985-07-23 | The United States Of America As Represented By The Department Of Energy | Method for fabricating wrought components for high-temperature gas-cooled reactors and product |
| US4685977A (en) * | 1984-12-03 | 1987-08-11 | General Electric Company | Fatigue-resistant nickel-base superalloys and method |
| JPS62167835A (en) * | 1985-11-26 | 1987-07-24 | ユナイテツド・テクノロジ−ズ・コ−ポレイシヨン | Nickel base superalloy |
| JPH0430447B2 (en) * | 1985-11-26 | 1992-05-21 | ||
| US5374323A (en) * | 1991-08-26 | 1994-12-20 | Aluminum Company Of America | Nickel base alloy forged parts |
| US5360496A (en) * | 1991-08-26 | 1994-11-01 | Aluminum Company Of America | Nickel base alloy forged parts |
| US5660649A (en) * | 1992-05-28 | 1997-08-26 | United Technologies Corporation | Method of making oxidation resistant single crystal superalloy castings |
| US5540789A (en) * | 1992-05-28 | 1996-07-30 | United Technologies Corporation | Oxidation resistant single crystal superalloy castings |
| DE4412031A1 (en) * | 1993-04-07 | 1994-10-13 | Aluminum Co Of America | Method for manufacturing forgings made of nickel alloys |
| US6284392B1 (en) | 1999-08-11 | 2001-09-04 | Siemens Westinghouse Power Corporation | Superalloys with improved weldability for high temperature applications |
| US6974508B1 (en) | 2002-10-29 | 2005-12-13 | The United States Of America As Represented By The United States National Aeronautics And Space Administration | Nickel base superalloy turbine disk |
| WO2018069666A1 (en) | 2016-10-12 | 2018-04-19 | Oxford University Innovation Limited | A nickel-based alloy |
| CN110225985A (en) * | 2016-10-12 | 2019-09-10 | 牛津大学创新有限公司 | Nickel-base alloy |
| CN110225985B (en) * | 2016-10-12 | 2024-01-02 | 牛津大学创新有限公司 | Nickel-based alloy |
| US11859267B2 (en) | 2016-10-12 | 2024-01-02 | Oxford University Innovation Limited | Nickel-based alloy |
Also Published As
| Publication number | Publication date |
|---|---|
| AT241133B (en) | 1965-07-12 |
| FR1367387A (en) | 1964-07-17 |
| DE1219236B (en) | 1966-06-16 |
| CH420635A (en) | 1966-09-15 |
| NL297339A (en) | 1965-05-25 |
| GB968495A (en) | 1964-09-02 |
| ES291188A1 (en) | 1964-02-16 |
| BE636847A (en) | 1964-03-02 |
| SE307018B (en) | 1968-12-16 |
| LU44364A1 (en) | 1963-10-31 |
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