US3785877A - Treating nickel base alloys - Google Patents
Treating nickel base alloys Download PDFInfo
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- US3785877A US3785877A US00291859A US3785877DA US3785877A US 3785877 A US3785877 A US 3785877A US 00291859 A US00291859 A US 00291859A US 3785877D A US3785877D A US 3785877DA US 3785877 A US3785877 A US 3785877A
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- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22F—CHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS AND NON-FERROUS ALLOYS
- C22F1/00—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
- C22F1/10—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of nickel or cobalt or alloys based thereon
Definitions
- the present invention provides a sophisticated heat treatment which decreases dendritic segregation and minimizes the formation of carbide stringers. Instead of coarse and/or film-like carbides, it produces a structure characterized by dispersed discrete fine spherical carbides and an alloy with a high degree of chemical homogeneity. As a result the alloy has improved tensile strength and/or tensile ductility and/or stress rupture properties, and particularly in the direction transverse to metal solidification and/or metal flow. More specifically, the invention involves a high homogenization temperature and critically controlled cooling rates, as well as casting and hot working. Moreover, it is in part based upon processing which was previously considered detrimental. Previous technical reports have indicated that so called high homogenization temperatures cause a subsequent formation of carbide films and thereby decrease ductility.
- FIG. 1 is a photomicrograph at 50X of an ingot processed in accordance with the present invention.
- FIG. 2 is a photomicrograph at 50X of a billet processed in accordance with the present invention.
- FIG. 3 is a photomicrograph at 50X of an ingot processed in accordance with prior art techniques.
- FIG. 4 is a photomicrograph at 50X of a billet processed in accordance with prior art techniques.
- Nickel base alloys having a structure characterized by dispersed discrete fine spherical carbides, are produced, in accordance with the present invention, by a method which comprises the steps of: casting an ingot of nickel base alloy; homogenizing the ingot at a temperature of from 2,200" to 2,400 F, and preferably at a temperature of from 2,250 to 2,400 F, thereby dissolving primary carbides present in the alloy and increasing the chemical homogeneity thereof; cooling the alloy at a rate which substantially precludes the precipitation of coarse and film-like carbides at temperatures above l,900 F and at a rate in which dispersed fine spherical carbides precipitate at temperatures below 1,900 F; and hot working the alloy at a temperature lower than that at which the primary carbides dissolve.
- the primary carbides which form during the solidification of the ingot and/or during the cooling thereof are generally MC or M C carbides.
- MC carbides are comprised of titanium with optional amounts of molybdenum, nickel, chromium and zirconium
- M C carbides are comprised of molybdenum with optional amounts of tungsten, chromium, iron and cobalt. It is essential to dissolve the primary carbides in order for the desired dispersed discrete fine spherical carbides to form during cooling, and in order to do so homogenization must be at a temperature of at least 2,200 F. A maximum homogenization temperature of 2,400 F is, however, imposed as carbides melt at higher temperatures.
- carbide films would subsequently form following homogenization at temperatures as high as 2,2()0 F, and that these films would detrimentally affect the alloys ductility.
- a sufficient period of time is preferably allowed for the primary carbides to dissolve and to permit carbon and other elements to diffuse over a distance at least approaching one half the local dendrite-arm spacing.
- the required period for homogenization is in excess of 4 hours, although no specific time period can be set as it is dependent upon the homogenization temperature and the thickness of the ingot.
- To obtain the desired carbide structure cooling from the homogenization temperature to l,900 F must be conducted at a rate fast enough to preclude the precipitation of coarse and film-like carbides.
- the cooling rate to 1,900 F must be in excess of 25 F per hour, and is preferably in excess of F per hour.
- the cooling rate at temperatures below 1,900 F and during the period at which precipitation occurs is, on the other hand, one which is intentionally kept down. More specifically, it is maintained below 125 F per hour and preferably below 60 F per hour.
- the cooling rate to 1,900 F is in excess of that employed during the period of precipitation at temperatures below l,900 F. No specific numerical range can, however, be placed upon the period of time at which precipitation occurs, as the period is dependent upon both the cooling rate and the thickness of the ingot.
- the cooling rate during the period at which precipitation occurs often encompasses holding periods, as the desired carbide structure can be obtained by holding the alloy at a particular temperature for a period of time. For example, if the alloy is held at l,200 F for 1 hour the 1 hour is included in calculating its cooling rate from l,900 to 1,200 F. With regard to this, a preferred holding temperature is from 950 to l,350 F. After cooling the alloy is hot worked; e.g., forged, swaged, extruded, rolled, drawn or pressed, within a temperature range of from 1,750 to 2,l F and preferably within a temperature range of from 1,800" to 2,150 F.
- furnace temperatures are lower than metal temperatures during cooling, and cooling as discussed above is a critical part of the present invention.
- Metal temperatures do, however, reach furnace temperatures during homogenization due to the prolonged exposure at temperature.
- the nickel base alloy being treated is most often a gamma prime strengthened alloy and generally, but not necessarily, consists essentially of, in weight percent: up to 0.2 percent carbon, up to 2.0 percent manganese, up to 2 percent silicon, from 5 to 25 percent chromium, up to 20 percent cobalt, up to percent molybdenum, up to 10.0 percent titanium, up to 5 percent aluminum, up to 0.05 percent boron, up to 0.5 percent zirconium, up to 40.0 percent iron, up to 8.0 percent of metal from the group consisting of columbium, tantalum and hafnium, up to 2.0 percent vanadium, up to 10 percent tungsten, up to 0.5 percent rhenium, up to 0.02 percent of metal from Group 11 A of the periodic table, up to 0.5 percent of rare earth metal, balance essentially nickel, said percentage of nickel being at least 40 percent.
- an alloy which has proven to be particularly well suited for the treatment of the present invention consists essentially of, in weight percent, up to 0.15 percent carbon, up to 1.0 percent manganese, up to 1.0 percent silicon, from 15-23 percent chromium, from 10 to 18 percent cobalt, from 3 to 6 percent molybdenum, from 2 to 3.5 percent titanium,
- Another alloy within the broad range, for which there is reason to believe that it is particularly well suited for the treatment of the present invention consists essentially of, in weight percent, up to 0.15 percent carbon, up to 2.0 percent manganese, up to 1.0 percent silicon, from 5.0 to 15.0 percent chromium, up to 10.0 percent cobalt, from 2 to 7 percent molybdenum, from 1.0 to 3.75 percent titanium, up to 2 percent aluminum, up to 0.05 percent boron, from 25 to 40 percent iron, balance essentially nickel.
- gamma prime is defined, and believed to have, the general composition M (Al and/or Ti and possibly one or more additional metals from the group comprised of tantalum, columbium, molybdenum and- /or chromium).
- M Al and/or Ti and possibly one or more additional metals from the group comprised of tantalum, columbium, molybdenum and- /or chromium.
- the M" portion of the gamma prime is regarded as consisting mainly of nickel of 875 F per hour. Cooling was performed at a rate sufficiently fast to substantially preclude the precipitation of coarse and film-like carbides. From 1,900 F the ingot was cooled at a slower rate of 33.3 F per hour, to 900 F. Dispersed discrete fine spherical carbides precipitated during the cooling from 1,900 F. This desirable carbide morphology and distribution is seen in FIG.
- composition of the ingot was, in weight percent, 0.06 percent carbon, less than 0.10 percent manganese, less than 0.10 percent silicon, 19.1 percent chromium, 13.4 percent cobalt, 4.15 percent molybdenum, 3.15 percent titanium, 1.34 percent aluminum, 0.005 percent boron, 0.06 percent zirconium, 0.9 percent iron, balance essentially nickel.
- FIG. 2 is a photomicrograph of the hot worked and ground billet at 50X. Note that the billet is still characterized by dispersed discrete fine spherical carbides.
- FIGS. 3 and 4 respectively show photomicrographs at 50X of one of these typical prior art ingots and billets. Note that the carbides in FIG. 3 are large and angular, and that the carbides in FIG. 4 are concentrated in bands.
- Pancake property data for both the alloy treated in accordance with the present invention and for the average of the prior art billets is set forth below in Table l.
- the data which is more indicative of transverse properties than longitudinal properties clearly shows the value of the heat treatment of the present invention.
- a nickel base alloy ingot was cast and homogenized for 48 hours at 2,250 F. From the homogenization temperature the ingot was cooled to 1,900 F at a rate 1 claim:
- a method of treating a nickel base alloy so as to produce an alloy having a structure characterized by dispersed discrete fine spherical carbides which comprises the steps of: casting an ingot of nickel base alloy; homogenizing said ingot at a temperature of from 2,200 to 2,400 P, thereby dissolving primary carbides present in said alloy and increasing the chemical homogeneity thereof; cooling said alloy at a rate which substantially precludes the precipitation of coarse and film-like carbides at temperatures above 1,900 F and at a rate at which discrete fine spherical carbides precipitate at temperatures below 1,900 F, said cooling from said homogenizing temperature to 1,900 F being at a first cooling rate, said cooling at temperatures below l,900 F and during the period at which precipi' tation occurs being at a second cooling rate, said first cooling rate being in excess of said second cooling rate, said first cooling rate being in excess of 25 F per hour, said second cooling rate being less than 125 F per hour; and hot working said alloy at a temperature lower than that at which said primary carb
- said nickel base alloy consists essentially of, in weight percent, up to 0.2 percent carbon, up to 2.0 percent manganese, up to 2.0 percent silicon, from 5.0 to 25.0 percent chromium, up to 23 percent cobalt, up to percent molybdenum, up to 10.0 percent titanium, up to 5 percent aluminum, up to 0.05 percent boron, up to 0.5 percent zirconium, up to 40 percent iron, up to 8.0 percent of metal from the group consisting of columbium, tantalum and hafnium, up to 2.0 percent vanadium, up to 10 percent tungsten, up to 0.5 percent rhenium, up to 0.02 percent of metal from Group II A of the periodic table, up to 0.5 percent of rare earth metal, balance essentially nickel, said percentage of nickel being at least 40 percent.
- said nickel base alloy consists essentially of, in weight percent, up to 0.15 percent carbon, up to 1.0 percent manganese, up to 1.0 percent silicon, from -23 percent chr0- mium, from 10 to 18' percent cobalt, from 3 to 6 percent molybdenum, from 2 to 3.5 percent titanium, from 1.0 to 2.0 percent aluminum, from 0.0025 to 0.0125 percent boron, from 0.02 to 0.2 percent zirconium, up to 2 percent iron, up to 4.0 percent of metal from the group consisting of columbium, tantalum and hafnium, up to 0.5 percent vanadium, up to 0.02 percent of metal from Group II A of the periodic table, up to 0.5 percent of rare earth metal, balance essentially nickel.
- said nickel base alloy consists essentially of, in weight percent, up to 0.15 percent carbon, up to 2.0 percent manganese, up to 1.0 percent silicon, from 5.0 to 15.0 percent chromium, up to 10.0 percent cobalt, from 2 to 7 percent molybdenum, from 1.0 to 3.75 percent titanium, up to 2 percent aluminum, up to 0.05 percent boron, from 25 to 40 percent iron, balance essentially nickel.
- said nickel base alloy is a gamma prime strengthened alloy.
- said nickel base alloy consists essentially of, in weight percent, up to 0.2 percent carbon, up to 2.0 percentmanganese, up
- said nickel base alloy consists essentially of, in weight percent, up to 0.15 percent carbon, up to 1.0 percent manganese, up to 1.0 percent silicon, from 15-23 percent chromium, from 10 to 18 percent cobalt, from 3 to 6 percent molybdenum, from 2 to 3.5 percent titanium, from 1.0 to 2.0 percent aluminum, from 0.0025 to 0.0125 percent boron, from 0.02 to 0.2 percent zirconium, up to 2 percent iron, up to 4.0 percent of metal from the group consisting of columbium, tantalum and hafnium, up to 0.5 percent vanadium, up to 0.02 percent of metal from Group 11 A of the periodic table, up to 0.5 percent of rare earth metal, balance essentially nickel.
- said nickel base alloy consists essentially of, in weight percent, up to 0.15 percent carbon, up to 2.0 percent manganese,
- said nickel base alloy is a gamma prime strengthened alloy.
- said nickel base alloy consists essentially of, in weight percent, up to 0.2 percent carbon, up to 2.0 percent manganese, up to 2.0 percent silicon, from 5.0 to 25.0 percent chromium, up to 23 percent cobalt, up to 10 percent molybdenum, up to 10.0 percent titanium, up to 5 percent aluminum, up to 0.05 percent boron, up to 0.5 percent zirconium, up to 40.0 percent iron, up to 8.0 percent of metal from the group consisting of columbium, tantalum and hafnium, up to 2.0 percent vanadium, up to 10 percent tungsten, up to 0.5 percent rhenium, up to 0.02 percent of metal from Group 11 A of the periodic table, up to 0.5 percent of rare earth metal, balance essentially nickel, said percentage of nickel being at least 40 percent.
- said nickel base alloy consists essentially of, in weight percent, up to 0.15 percent carbon, up to 1.0 percent manganese, up to 1.0 percent silicon, from 15-23 percent chromium, from 10 to 18 percentcobalt, from 3 to 6 percent molybdenum, from 2 to 3.5 percent titanium, from 1.0 to 2.0 percent aluminum, from 0.0025 to ganese, up to 1.0 percent silicon, from 5.0 to 15.0 percent chromium, up to 10.0 percent cobalt, from 2 to 7 percent molybdenum, from 1.0 to 3.75 percent titanium, up to 2 percent aluminum, up to 0.05 percent boron, from 25 to 40 percent iron, balance essentially nickel.
- said nickel base alloy is a gamma prime strengthened alloy.
Abstract
Description
Claims (16)
- 2. A method according to claim 1 wherein said nickel base alloy consists essentially of, in weight percent, up to 0.2 percent carbon, up to 2.0 percent manganese, up to 2.0 percent silicon, from 5.0 to 25.0 percent chromium, up to 23 percent cobalt, up to 10 percent molybdenum, up to 10.0 percent titanium, up to 5 percent aluminum, up to 0.05 percent boron, up to 0.5 percent zirconium, up to 40.0 percent iron, up to 8.0 percent of metal from the group consisting of columbium, tantalum and hafnium, up to 2.0 percent vanadium, up to 10 percent tungsten, up to 0.5 percent rhenium, up to 0.02 percent of metal from Group II A of the periodic table, up to 0.5 percent of rare earth metal, balance essentially nickel, said percentage of nickel being at least 40 percent.
- 3. A method according to claim 1 wherein said nickel base alloy consists essentially of, in weight percent, up to 0.15 percent carbon, up to 1.0 percent manganese, up to 1.0 percent silicon, from 15-23 percent chromium, from 10 to 18 percent cobalt, from 3 to 6 percent molybdenum, from 2 to 3.5 percent titanium, from 1.0 to 2.0 percent aluminum, from 0.0025 to 0.0125 percent boron, from 0.02 to 0.2 percent zirconium, up to 2 percent iron, up to 4.0 percent of metal from the group consisting of columbium, tantalum and hafnium, up to 0.5 percent vanadium, up to 0.02 percent of metal from Group II A of the periodic table, up to 0.5 percent of rare earth metal, balance essentially nickel.
- 4. A method according to claim 1 wherein said nickel base alloy consists essentially of, in weight percent, up to 0.15 percent carbon, up to 2.0 percent manganese, up to 1.0 percent silicon, from 5.0 to 15.0 percent chromium, up to 10.0 percent cobalt, from 2 to 7 percent molybdenum, from 1.0 to 3.75 percent titanium, up to 2 percent aluminum, up to 0.05 percent boron, from 25 to 40 percent iron, balance essentially nickel.
- 5. A method according to claim 1 wherein said nickel base alloy is a gamma prime strengthened alloy.
- 6. A method according to claim 1 wherein said first cooling rate is in excess of 70* F per hour and said second cooling rate is less than 60* F per hour.
- 7. A method according to claim 6 wherein said nickel base alloy consists essentially of, in weight percent, up to 0.2 percent carbon, up to 2.0 percent manganese, up to 2.0 percent silicon, from 5.0 to 25.0 percent chromium, up to 23 percent cobalt, up to 10 percent molybdenum, up to 10.0 percent titanium, up to 5 percent aluMinum, up to 0.05 percent boron, up to 0.5 percent zirconium, up to 40.0 percent iron, up to 8.0 percent of metal from the group consisting of columbium, tantalum and hafnium, up to 2.0 percent vanadium, up to 10 percent tungsten, up to 0.5 percent rhenium, up to 0.02 percent of metal from Group II A of the periodic table, up to 0.5 percent of rare earth metal, balance essentially nickel, said percentage of nickel being at least 40 percent.
- 8. A method according to claim 6, wherein said nickel base alloy consists essentially of, in weight percent, up to 0.15 percent carbon, up to 1.0 percent manganese, up to 1.0 percent silicon, from 15-23 percent chromium, from 10 to 18 percent cobalt, from 3 to 6 percent molybdenum, from 2 to 3.5 percent titanium, from 1.0 to 2.0 percent aluminum, from 0.0025 to 0.0125 percent boron, from 0.02 to 0.2 percent zirconium, up to 2 percent iron, up to 4.0 percent of metal from the group consisting of columbium, tantalum and hafnium, up to 0.5 percent vanadium, up to 0.02 percent of metal from Group II A of the periodic table, up to 0.5 percent of rare earth metal, balance essentially nickel.
- 9. A method according to claim 6 wherein said nickel base alloy consists essentially of, in weight percent, up to 0.15 percent carbon, up to 2.0 percent manganese, up to 1.0 percent silicon, from 5.0 to 15.0 percent chromium, up to 10.0 percent cobalt, from 2 to 7 percent molybdenum, from 1.0 to 3.75 percent titanium, up to 2 percent aluminum, up to 0.05 percent boron, from 25 to 40 percent iron, balance essentially nickel.
- 10. A method according to claim 6 wherein said nickel base alloy is a gamma prime strengthened alloy.
- 11. A method according to claim 1 wherein said hot working occurs within a temperature range of from 1,800* to 2,150* F.
- 12. A method according to claim 1 wherein said ingot is homogenized for a period of time in excess of 4 hours.
- 13. A method according to claim 1 wherein said ingot is homogenized at a temperature of at least 2,250* F.
- 14. A method according to claim 13 wherein said nickel base alloy consists essentially of, in weight percent, up to 0.2 percent carbon, up to 2.0 percent manganese, up to 2.0 percent silicon, from 5.0 to 25.0 percent chromium, up to 23 percent cobalt, up to 10 percent molybdenum, up to 10.0 percent titanium, up to 5 percent aluminum, up to 0.05 percent boron, up to 0.5 percent zirconium, up to 40.0 percent iron, up to 8.0 percent of metal from the group consisting of columbium, tantalum and hafnium, up to 2.0 percent vanadium, up to 10 percent tungsten, up to 0.5 percent rhenium, up to 0.02 percent of metal from Group II A of the periodic table, up to 0.5 percent of rare earth metal, balance essentially nickel, said percentage of nickel being at least 40 percent.
- 15. A method according to claim 13 wherein said nickel base alloy consists essentially of, in weight percent, up to 0.15 percent carbon, up to 1.0 percent manganese, up to 1.0 percent silicon, from 15-23 percent chromium, from 10 to 18 percent cobalt, from 3 to 6 percent molybdenum, from 2 to 3.5 percent titanium, from 1.0 to 2.0 percent aluminum, from 0.0025 to 0.0125 percent boron, from 0.02 to 0.2 percent zirconium, up to 2 percent iron, up to 4.0 percent of metal from the group consisting of columbium, tantalum and hafnium, up to 0.5 percent vanadium, up to 0.02 percent of metal from Group II A of the periodic table, up to 0.5 percent of rare earth metal, balance esSentially nickel.
- 16. A method according to claim 13 wherein said nickel base alloy consists essentially of, in weight percent, up to 0.15 percent carbon, up to 2.0 percent manganese, up to 1.0 percent silicon, from 5.0 to 15.0 percent chromium, up to 10.0 percent cobalt, from 2 to 7 percent molybdenum, from 1.0 to 3.75 percent titanium, up to 2 percent aluminum, up to 0.05 percent boron, from 25 to 40 percent iron, balance essentially nickel.
- 17. A method according to claim 13 wherein said nickel base alloy is a gamma prime strengthened alloy.
Applications Claiming Priority (1)
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US29185972A | 1972-09-25 | 1972-09-25 |
Publications (1)
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US00291859A Expired - Lifetime US3785877A (en) | 1972-09-25 | 1972-09-25 | Treating nickel base alloys |
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US (1) | US3785877A (en) |
JP (1) | JPS568907B2 (en) |
CA (1) | CA992851A (en) |
DE (1) | DE2348247A1 (en) |
FR (1) | FR2200369B1 (en) |
GB (1) | GB1404538A (en) |
IT (1) | IT994766B (en) |
Cited By (27)
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US4908069A (en) * | 1987-10-19 | 1990-03-13 | Sps Technologies, Inc. | Alloys containing gamma prime phase and process for forming same |
US5169463A (en) * | 1987-10-19 | 1992-12-08 | Sps Technologies, Inc. | Alloys containing gamma prime phase and particles and process for forming same |
US5665180A (en) * | 1995-06-07 | 1997-09-09 | The United States Of America As Represented By The Secretary Of The Air Force | Method for hot rolling single crystal nickel base superalloys |
WO1998032887A1 (en) * | 1997-01-29 | 1998-07-30 | Krupp Vdm Gmbh | Austenitic nickel-chromium-molybdenum-silicon alloy with high corrosion resistance to hot chloride-containing gases and chloride |
US6132535A (en) * | 1999-10-25 | 2000-10-17 | Mitsubishi Heavy Industries, Ltd. | Process for the heat treatment of a Ni-base heat-resisting alloy |
US6521175B1 (en) * | 1998-02-09 | 2003-02-18 | General Electric Co. | Superalloy optimized for high-temperature performance in high-pressure turbine disks |
US20040076540A1 (en) * | 2002-10-16 | 2004-04-22 | Shinya Imano | Welding material, gas turbine blade or nozzle and a method of repairing a gas turbine blade or nozzle |
US20040156737A1 (en) * | 2003-02-06 | 2004-08-12 | Rakowski James M. | Austenitic stainless steels including molybdenum |
US20070187005A1 (en) * | 2006-02-13 | 2007-08-16 | Taylor Thomas A | Alloy powders and coating compositions containing same |
US20070190354A1 (en) * | 2006-02-13 | 2007-08-16 | Taylor Thomas A | Low thermal expansion bondcoats for thermal barrier coatings |
US20080032105A1 (en) * | 2006-02-13 | 2008-02-07 | Taylor Thomas A | Low thermal expansion bondcoats for thermal barrier coatings |
US20080257457A1 (en) * | 2007-04-19 | 2008-10-23 | Ati Properties, Inc. | Nickel-base alloys and articles made therefrom |
US20090074584A1 (en) * | 2007-09-14 | 2009-03-19 | Kabushiki Kaisha Toshiba | Nickel-based alloy for turbine rotor of steam turbine and turbine rotor of steam turbine |
US20090285692A1 (en) * | 2008-03-17 | 2009-11-19 | Kabushiki Kaisha Toshiba | Ni-base alloy for turbine rotor of steam turbine and turbine rotor of steam turbine |
US20090291016A1 (en) * | 2008-05-21 | 2009-11-26 | Kabushiki Kaisha Toshiba | Nickel-base casting superalloy and cast component for steam turbine using the same as material |
US20100239425A1 (en) * | 2009-03-18 | 2010-09-23 | Kabushiki Kaisha Toshiba | Nickel-base alloy for turbine rotor of steam turbine and turbine rotor of steam turbine using the same |
US20110064569A1 (en) * | 2009-09-17 | 2011-03-17 | Kabushiki Kaisha Toshiba | Nickel-base alloy for forging or rolling and steam turbine component made of the same |
US20110142712A1 (en) * | 2008-03-03 | 2011-06-16 | Magnus Hasselqvist | Nickel base gamma prime strengthened superalloy |
US20120189488A1 (en) * | 2009-04-27 | 2012-07-26 | Magnus Hasselqvist | Nickel base superalloy with multiple reactive elements and use of said superalloy in complex material systems |
US20120251840A1 (en) * | 2011-03-30 | 2012-10-04 | General Electric Company | Nickel-base weld materials, processes of using, and components formed therewith |
US20120315133A1 (en) * | 2011-06-10 | 2012-12-13 | Kabushiki Kaisha Toshiba | Ni-based alloy for casting used for steam turbine and casting component of steam turbine |
US20140271338A1 (en) * | 2013-03-15 | 2014-09-18 | Ut-Battelle, Llc | High Strength Alloys for High Temperature Service in Liquid-Salt Cooled Energy Systems |
US20150197832A1 (en) * | 2014-01-10 | 2015-07-16 | Ut-Battelle, Llc | Intermediate Strength Alloys for High Temperature Service in Liquid-Salt Cooled Energy Systems |
US20150306710A1 (en) * | 2014-04-04 | 2015-10-29 | Special Metals Corporation | High Strength Ni-Cr-Mo-W-Nb-Ti Welding Product and Method of Welding and Weld Deposit Using the Same |
US20150329942A1 (en) * | 2014-05-15 | 2015-11-19 | Ut-Battelle, Llc | Intermediate Strength Alloys for High Temperature Service in Liquid-Salt Cooled Energy Systems |
US9752468B2 (en) | 2014-06-18 | 2017-09-05 | Ut-Battelle, Llc | Low-cost, high-strength Fe—Ni—Cr alloys for high temperature exhaust valve applications |
US10563293B2 (en) | 2015-12-07 | 2020-02-18 | Ati Properties Llc | Methods for processing nickel-base alloys |
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GB2307483B (en) * | 1993-11-10 | 1998-07-08 | United Technologies Corp | Crack-resistant high strength super alloy articles |
US5679180A (en) * | 1995-06-22 | 1997-10-21 | United Technologies Corporation | γ strengthened single crystal turbine blade alloy for hydrogen fueled propulsion systems |
-
1972
- 1972-09-25 US US00291859A patent/US3785877A/en not_active Expired - Lifetime
-
1973
- 1973-09-24 IT IT52714/73A patent/IT994766B/en active
- 1973-09-24 GB GB4469373A patent/GB1404538A/en not_active Expired
- 1973-09-25 DE DE19732348247 patent/DE2348247A1/en active Pending
- 1973-09-25 JP JP10789973A patent/JPS568907B2/ja not_active Expired
- 1973-09-25 CA CA182,100A patent/CA992851A/en not_active Expired
- 1973-09-25 FR FR7334370A patent/FR2200369B1/fr not_active Expired
Cited By (42)
Publication number | Priority date | Publication date | Assignee | Title |
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US4908069A (en) * | 1987-10-19 | 1990-03-13 | Sps Technologies, Inc. | Alloys containing gamma prime phase and process for forming same |
US5169463A (en) * | 1987-10-19 | 1992-12-08 | Sps Technologies, Inc. | Alloys containing gamma prime phase and particles and process for forming same |
US5665180A (en) * | 1995-06-07 | 1997-09-09 | The United States Of America As Represented By The Secretary Of The Air Force | Method for hot rolling single crystal nickel base superalloys |
WO1998032887A1 (en) * | 1997-01-29 | 1998-07-30 | Krupp Vdm Gmbh | Austenitic nickel-chromium-molybdenum-silicon alloy with high corrosion resistance to hot chloride-containing gases and chloride |
US6521175B1 (en) * | 1998-02-09 | 2003-02-18 | General Electric Co. | Superalloy optimized for high-temperature performance in high-pressure turbine disks |
US6132535A (en) * | 1999-10-25 | 2000-10-17 | Mitsubishi Heavy Industries, Ltd. | Process for the heat treatment of a Ni-base heat-resisting alloy |
US7165325B2 (en) * | 2002-10-16 | 2007-01-23 | Hitachi, Ltd. | Welding material, gas turbine blade or nozzle and a method of repairing a gas turbine blade or nozzle |
US20070054147A1 (en) * | 2002-10-16 | 2007-03-08 | Shinya Imano | Welding material, gas turbine blade or nozzle and a method of repairing a gas turbine blade or nozzle |
US20040076540A1 (en) * | 2002-10-16 | 2004-04-22 | Shinya Imano | Welding material, gas turbine blade or nozzle and a method of repairing a gas turbine blade or nozzle |
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Also Published As
Publication number | Publication date |
---|---|
JPS4970820A (en) | 1974-07-09 |
GB1404538A (en) | 1975-09-03 |
FR2200369B1 (en) | 1978-09-08 |
CA992851A (en) | 1976-07-13 |
FR2200369A1 (en) | 1974-04-19 |
DE2348247A1 (en) | 1974-04-04 |
IT994766B (en) | 1975-10-20 |
JPS568907B2 (en) | 1981-02-26 |
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