US3677746A - Heat treatable alloy - Google Patents
Heat treatable alloy Download PDFInfo
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- US3677746A US3677746A US4044A US3677746DA US3677746A US 3677746 A US3677746 A US 3677746A US 4044 A US4044 A US 4044A US 3677746D A US3677746D A US 3677746DA US 3677746 A US3677746 A US 3677746A
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- 239000000956 alloy Substances 0.000 title description 36
- 229910045601 alloy Inorganic materials 0.000 title description 36
- 229910052735 hafnium Inorganic materials 0.000 abstract description 15
- VBJZVLUMGGDVMO-UHFFFAOYSA-N hafnium atom Chemical compound [Hf] VBJZVLUMGGDVMO-UHFFFAOYSA-N 0.000 abstract description 15
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 abstract description 12
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 abstract description 10
- 229910052799 carbon Inorganic materials 0.000 abstract description 10
- ZOKXTWBITQBERF-UHFFFAOYSA-N Molybdenum Chemical compound [Mo] ZOKXTWBITQBERF-UHFFFAOYSA-N 0.000 abstract description 6
- 229910052782 aluminium Inorganic materials 0.000 abstract description 6
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 abstract description 6
- 239000010941 cobalt Substances 0.000 abstract description 6
- 229910017052 cobalt Inorganic materials 0.000 abstract description 6
- GUTLYIVDDKVIGB-UHFFFAOYSA-N cobalt atom Chemical compound [Co] GUTLYIVDDKVIGB-UHFFFAOYSA-N 0.000 abstract description 6
- 229910052750 molybdenum Inorganic materials 0.000 abstract description 6
- 239000011733 molybdenum Substances 0.000 abstract description 6
- 229910052759 nickel Inorganic materials 0.000 abstract description 6
- VYZAMTAEIAYCRO-UHFFFAOYSA-N Chromium Chemical compound [Cr] VYZAMTAEIAYCRO-UHFFFAOYSA-N 0.000 abstract description 5
- QCWXUUIWCKQGHC-UHFFFAOYSA-N Zirconium Chemical compound [Zr] QCWXUUIWCKQGHC-UHFFFAOYSA-N 0.000 abstract description 5
- 229910052804 chromium Inorganic materials 0.000 abstract description 5
- 239000011651 chromium Substances 0.000 abstract description 5
- 229910052726 zirconium Inorganic materials 0.000 abstract description 5
- 238000005266 casting Methods 0.000 description 10
- 229910052751 metal Inorganic materials 0.000 description 6
- 239000002184 metal Substances 0.000 description 6
- ZOXJGFHDIHLPTG-UHFFFAOYSA-N Boron Chemical compound [B] ZOXJGFHDIHLPTG-UHFFFAOYSA-N 0.000 description 5
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 description 5
- 229910052796 boron Inorganic materials 0.000 description 5
- 239000000203 mixture Substances 0.000 description 5
- 239000010936 titanium Substances 0.000 description 5
- 229910052719 titanium Inorganic materials 0.000 description 5
- 239000003054 catalyst Substances 0.000 description 3
- 150000001247 metal acetylides Chemical class 0.000 description 3
- 230000006911 nucleation Effects 0.000 description 3
- 230000009467 reduction Effects 0.000 description 3
- 238000005275 alloying Methods 0.000 description 2
- 230000007547 defect Effects 0.000 description 2
- 230000007812 deficiency Effects 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 239000012535 impurity Substances 0.000 description 2
- 239000004615 ingredient Substances 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 238000010899 nucleation Methods 0.000 description 2
- 238000001556 precipitation Methods 0.000 description 2
- 238000007619 statistical method Methods 0.000 description 2
- 239000000126 substance Substances 0.000 description 2
- 238000007792 addition Methods 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 239000000356 contaminant Substances 0.000 description 1
- 238000011109 contamination Methods 0.000 description 1
- 238000002425 crystallisation Methods 0.000 description 1
- 230000008025 crystallization Effects 0.000 description 1
- 230000002950 deficient Effects 0.000 description 1
- WHJFNYXPKGDKBB-UHFFFAOYSA-N hafnium;methane Chemical compound C.[Hf] WHJFNYXPKGDKBB-UHFFFAOYSA-N 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 230000006698 induction Effects 0.000 description 1
- 230000008018 melting Effects 0.000 description 1
- 238000002844 melting Methods 0.000 description 1
- 239000012466 permeate Substances 0.000 description 1
- 238000012797 qualification Methods 0.000 description 1
- 238000007711 solidification Methods 0.000 description 1
- 230000008023 solidification Effects 0.000 description 1
- 230000007480 spreading Effects 0.000 description 1
- 238000003892 spreading 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
- the present invention is concerned with an alloy and, more particularly, with castings made from said alloy, said castings being particularly adapted for use as blades in gas turbine engines.
- Alloy Z Percent Carbon 0.08 Chromium 15.0 Cobalt 18.5 Molybdenum 5.2 Titanium 3.5 Aluminum 4.3 Boron 0.03 Nickel Balance
- This particular alloy identified hereinafter as Alloy Z, is currently being used as castings for various high temperature uses.
- the engine manufacturer requires that specimens machined from blades (mfb. specimens) and heat treated by solution treatment at 2125 F. for two hours, furnace cooled at 100 in Fahrenheit units per hour to 1975 F., cooled to room temperature and then held at 1400 F.
- Another object of the present invention is to provide novel castings made from said new alloy.
- the present invention contemplates alloys and castings made therefrom having a chemical compsition within the range (in percent by Weight) as set forth in Table I:
- the alloy as set forth in Table I can also contain small amounts of impurities and incidental elements normally associated with the ingredients thereof and such impurities and incidental elements are intended to be included within the term essentially when such term modifies the phase balance nickel.
- the alloy of Table I is made by melting the alloying ingredients including, if desired, graded and selected scrap and revert in a vacuum induction furnace and castings are made therefrom by pouring the molten alloy while under vacuum into suitably shaped precision investment molds. The metal is allowed to freeze in said molds and, when cool, is removed from the molds. After gates, risers and the like are cut from the cast objects, the objects are heat treated by solution treatment at 2100 F. to 2150 F. for about 2 hours, furnace cooled at a rate of about F. per hour to about 1975 F. and then cooled freely to room temperature. Subsequently the objects are reheated to about 1400 F. and held, for example, for 16 hours to effect further precipitation of gamma prime phase in the alloy structure.
- the modified heat had the following composition (in percent by weight):
- the modified alloy was poured into a turbine blade cluster identical to the clusters formed with the unmodified alloy. Samples were taken and treated in exactly the same manner as had been done previously. Results of creep tests at 1400 F. and 85 k.s.i. with this cluster are set forth in Table HI:
- the advantages of the present invention are obtained when the alloys of the invention contain from about 0.8% to 2% or even more of hafnium.
- the inclusion of hafnium in said alloys is not known to significantly degrade any useful characteristics of Alloy Z and is highly advantageous in that it eliminates, for all practical purposes, heats of Alloy Z which, for no apparent reason, fail to qualify for east turbine blade usage.
- the novel modified Alloy Z of the present invention can be advantageously used in the wrought form as well as in the cast form and is useful in the manufacture of various items subjected in use to stress at high temperature, e.g. gas turbine blades and other items of gas turbine hardware.
- hafnium combines with carbon to form ultra-microscopic hafnium carbide aggregates which permeate the solidifying metal. These carbide aggregates could serve to form crystallization sites as do the nucleation catalysts normally employed on investment mold surfaces.
- the difference between the nucleation actions of the conventionally used catalysts and the carbide aggregates is essentially a matter of location. Conventional catalysts are strictly surface acting whereas the carbide aggregates are distributed throughout the mass of metal.
- the carbide aggregates are sub-microscopic and the solidified alloy micro-structure appears to be substantially devoid of carbides. This apparent absence of carbides is accompanied by a substantial increase in the grain size of the cast alloy. Chemical analysis, of course, as well as the level of mechanical characteristics demonstrates that, even though it cannot be seen as carbides, carbon is certainly present in the alloys of the invention and serves its ordinary functions therein.
- a novel heat treatable alloy consisting in percent by weight essentially of about 0.05% to about 0.13% carbon, about 13% to about 17% chromium, about 14% to about 20% cobalt, about 3.9% to about 6% molybdenum, about 3% to about 4% titanium, about 3.5% to about 5.0% aluminum, about 0.005% to about 0.05% boron, up to about 0.3% zirconium, about 0.8% to about 2% hafnium with the balance being essentially nickel.
- a casting of the alloy of claim 1 having been heat treated for about 2 hours at 2100 F. to 2150" F., then furnace cooled at about 100 F. per hour to about 1975 F., then cooled to room temperature and subsequently subjected to a precipitation treatment at about 1400 F.
- An alloy as in claim 1 consisting of about 0.08% carbon, about 15% chromium, about 18.5% cobalt, about 5.2% molybdenum, about 3.5% titanium, about 4.3% aluminum, about 0.03% boron, up to about 0.3% zirconium, about 0.8% to about 2% hafnium, with the balance being essentially 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)
Abstract
AN ALLOY AND CASTINGS MADE THEREFROM CONTAINING IN PERCENT BY WEIGHT ABOUT 0.008% CARBON, ABOUT 15% CHROMIUM, ABOUT 18.5% COBALT, ABOUT 5.2% MOLYBDENUM, ABOUT 3.5% TIANIUM, ABOUT 4.3% ALUMINUM, ABOUT 0.03% BORON, UP TO ABOUT 0.3% ZIRCONIUM, ABOUT 0.8% TO ABOUT 2% HAFNIUM WITH THE BALANCE BEING ESSENTIALLY NICKEL.
Description
United States Patent 015cc 3,677,746 Patented July 18, 1972 3,677,746 HEAT TREATABLE ALLOY Carl H. Lund, Arlington Heights, John Hockin, Palatine, and Michael J. Woulds, Schaumburg, 111., assignors to Martin Marietta Corporation, New York, N.Y.
No Drawing. Continuation-impart of application Ser. No. 841,602, July 14, 1969. This application Jan. 19, 1970, Ser. No. 4,044
Int. Cl. C22c 19/00 U.S. Cl. 75-171 3 Claims ABSTRACT OF THE DISCLOSURE An alloy and castings made therefrom containing in percent by weight about 0.08% carbon, about 15% chrmium, about 18.5% cobalt, about 5.2% molybdenum, about 3.5% titanium, about 4.3% aluminum, about 0.03% boron, up to about 0.3% zirconium, about 0.8%
to about 2% hafnium with the balance being essentially nickel.
The present application is a continuation-in-part of application Ser. No. 841,602, filed July 14, 1969 (now abandoned).
The present invention is concerned with an alloy and, more particularly, with castings made from said alloy, said castings being particularly adapted for use as blades in gas turbine engines.
In U.S. patent application Ser. No. 725,074, filed Apr. 29, 1968, now abandoned it was disclosed that additions of hafnium to high temperature nickel-base alloys suitable for use as castings were effective in several respects to overcome defects and deficiencies there in. The present invention is concerned with overcoming deficiencies and defects in castings of a particular alloy which was initially developed as a heat treatable bar alloy that is an alloy which is designed to be wrought after being initially cast into a billet or other rudimentary form and thereafter heat treated to provide good high temperature characteristics. The nominal composition in percent by weight of this alloy is as follows:
Percent Carbon 0.08 Chromium 15.0 Cobalt 18.5 Molybdenum 5.2 Titanium 3.5 Aluminum 4.3 Boron 0.03 Nickel Balance This particular alloy, identified hereinafter as Alloy Z, is currently being used as castings for various high temperature uses. When cast Alloy Z is to be used as certain second stage blades in the turbine section of a gas turbine engine, the engine manufacturer requires that specimens machined from blades (mfb. specimens) and heat treated by solution treatment at 2125 F. for two hours, furnace cooled at 100 in Fahrenheit units per hour to 1975 F., cooled to room temperature and then held at 1400 F. for 16 hours exhibit a life-to-rupture of at least 23 hours with at least 4% prior creep (elongation at least two hours prior to failure) when tested at 1400 F. under a load of 85 thousands of pounds per square inch (k.s.i.) and a life of at least 23 hours with at least 5.0% prior creep when tested at 1600 F. under a load of 48 k.s.i. Normally, there is no problem of qualifying metal using the 1600 F. test. Quite often, however, for no apparent reason, heats of Alloy Z will fail to qualify under the 1400 F. test. There appears to be no noticeable differences in composition or handling between heats of Alloy Z which qualify and those heats which do not. The failure of certain heats of Alloy Z to qualify for use as second stage turbine blades is a particularly irksome phenomenon because the alloy manufacturer heretofore had no means of overcoming the problem. Further, on the theory that non-qualifying heats contained some unknown contaminant, an alloy manufacturer was reluctant to use the metal of such heats in diluted form for fear of spreading the contamination.
It has now been discovered that by inclusion of about 0.8% to about 2% by weight of hafnium in the composition, non-qualifying heats of Alloy Z can 'be substantially eliminated provided due care, as is customary in the art of high temperature alloy manufacture, be used in the formulating and treating of the alloy.
It is an object of the present invention to provide a new, highly advantageous alloy.
Another object of the present invention is to provide novel castings made from said new alloy.
Other objects and advantages will become apparent from the following description.
Generally speaking, the present invention contemplates alloys and castings made therefrom having a chemical compsition within the range (in percent by Weight) as set forth in Table I:
TABLE I Percent Carbon 0.05-0.13 Chromium 13-17 Cobalt 14.00-20 Molybdenum 3.90-6 Titanium 34 Aluminum 3.55.0 Boron 0.005-0.05 Zirconium Up to 0.3 Hafnium 0.82
Nickel, Balance essentially.
The alloy as set forth in Table I can also contain small amounts of impurities and incidental elements normally associated with the ingredients thereof and such impurities and incidental elements are intended to be included within the term essentially when such term modifies the phase balance nickel. The alloy of Table I is made by melting the alloying ingredients including, if desired, graded and selected scrap and revert in a vacuum induction furnace and castings are made therefrom by pouring the molten alloy while under vacuum into suitably shaped precision investment molds. The metal is allowed to freeze in said molds and, when cool, is removed from the molds. After gates, risers and the like are cut from the cast objects, the objects are heat treated by solution treatment at 2100 F. to 2150 F. for about 2 hours, furnace cooled at a rate of about F. per hour to about 1975 F. and then cooled freely to room temperature. Subsequently the objects are reheated to about 1400 F. and held, for example, for 16 hours to effect further precipitation of gamma prime phase in the alloy structure.
The advantages of the present invention are best exemplified by a case history of a particular heat of Alloy Z. This heat had the following composition in percent by weight:
Repeatedly metal of this heat was cast into turbine blade clusters, samples were taken and heat treated and subjected to qualification tests at 1400 F. under a load of 85 k.s.i. The results are set forth in Table II:
TABLE II Average Average prior li cree Cluster (hours) (percent? The data in Table II shows that this heat of Alloy Z is clearly not acceptable to the gas turbine engine manufacturer. Statistical analysis of the data in Table II shows that if a very large number of m.f.=b. samples were made from this heat of Alloy Z, greater than 99.9% of these samples would fail to meet the criterion of 4% prior creep. Furthermore, only about 33% of the samples would be expected to exceed the requirement of at least 23 hours of life-to-rupture.
One and one-half percent of hafnium was added to the particular heat of Alloy Z which exhibited the results set forth in Table II. The modified heat had the following composition (in percent by weight):
Carbon 0.06
The modified alloy was poured into a turbine blade cluster identical to the clusters formed with the unmodified alloy. Samples were taken and treated in exactly the same manner as had been done previously. Results of creep tests at 1400 F. and 85 k.s.i. with this cluster are set forth in Table HI:
TABLE III Lite-to Prior rupture cree Blade number (hours) (percent Statistical analysis of the data in Table III indicates that if a very large number of m.f.b. samples were made from the modified alloy, greater than 95% of such samples would exhibit greater than 4% prior creep and greater than 99% of such samples would exhibit a life-to-rupture in excess of 23 hours. The data in Table III clearly shows that by inclusion of about 1.5% hafnium in the unacceptable heat of Alloy Z, the unacceptable heat was transformed into a heat that is clearly acceptable under the criterion laid down by the gas turbine engine manufacturer.
The advantages of the present invention are obtained when the alloys of the invention contain from about 0.8% to 2% or even more of hafnium. The inclusion of hafnium in said alloys is not known to significantly degrade any useful characteristics of Alloy Z and is highly advantageous in that it eliminates, for all practical purposes, heats of Alloy Z which, for no apparent reason, fail to qualify for east turbine blade usage. The novel modified Alloy Z of the present invention can be advantageously used in the wrought form as well as in the cast form and is useful in the manufacture of various items subjected in use to stress at high temperature, e.g. gas turbine blades and other items of gas turbine hardware.
When hafnium is included in heats of Alloy Z which are not inherently defective, substantial advantages are also obtained. The data set forth in Table IV are representative of creep rupture data obtained on heat-treated samples machined from blades when tested at 1400 F. under a load of 85,000 p.s.i.
TABLE IV Percent Reduction Lite (hours) Prior creep Elongation in area Similar heat-treated samples of modified Alloy Z containing 1.5% hafnium in place of an equal weight percent of nickel exhibit, under the same test conditions, the creep rupture characteristics as set forth in Table V.
TABLE V Percent Reduction Lilo (hours) Prior creep Elongation in area In each characteristic measured at 1400" F., modified \Alloy Z is superior to unmodified Alloy Z. The life-torupture is longer; the percent prior creep is higher; the percent elongation is higher; and the percent reductionin-area is extraordinarily high. While most of these advantages of modified alloy as opposed to unmodified alloy apparent at 1400 F. appear to vanish at higher and lower temperatures, it has been noted that even at 1600 F. the modified alloy exhibits under creep rupture conditions an enhanced percent reduction-in-area. The data in Table V1 is representative of creep rupture data obtained on heat-treated samples machined from blades and tested at 1600 F. under a load of 48,000 p.s.i.
It is believed that a high percent reduction-in-area is advantageous as to resistance to low cycle fatigue since it would appear to permit relatively high localized deformation overall stretching or formation of incipient cracks in a member subjected to low cycle fatiguing conditions.
Part of the improvement of 1600 F. reduction-in-area observed to be obtained in Alloy Z by virture of the inclusion of hafnium therein could be due to a grain nucleation effect. It is possible that, during solidification, hafnium combines with carbon to form ultra-microscopic hafnium carbide aggregates which permeate the solidifying metal. These carbide aggregates could serve to form crystallization sites as do the nucleation catalysts normally employed on investment mold surfaces. The difference between the nucleation actions of the conventionally used catalysts and the carbide aggregates is essentially a matter of location. Conventional catalysts are strictly surface acting whereas the carbide aggregates are distributed throughout the mass of metal. At the lower levels of permissible carbon, for example, 0.05% to 0.09%, the carbide aggregates are sub-microscopic and the solidified alloy micro-structure appears to be substantially devoid of carbides. This apparent absence of carbides is accompanied by a substantial increase in the grain size of the cast alloy. Chemical analysis, of course, as well as the level of mechanical characteristics demonstrates that, even though it cannot be seen as carbides, carbon is certainly present in the alloys of the invention and serves its ordinary functions therein.
While the present invention has been described in conjunction with advantageous embodiments, those skilled in the art will recognize that modifications and variations may be resorted to without departing from the spirit and scope of the invention. Such modifications and variations are considered to be within the purview and scope of the invention.
What is claimed is:
1. A novel heat treatable alloy consisting in percent by weight essentially of about 0.05% to about 0.13% carbon, about 13% to about 17% chromium, about 14% to about 20% cobalt, about 3.9% to about 6% molybdenum, about 3% to about 4% titanium, about 3.5% to about 5.0% aluminum, about 0.005% to about 0.05% boron, up to about 0.3% zirconium, about 0.8% to about 2% hafnium with the balance being essentially nickel.
2. A casting of the alloy of claim 1 having been heat treated for about 2 hours at 2100 F. to 2150" F., then furnace cooled at about 100 F. per hour to about 1975 F., then cooled to room temperature and subsequently subjected to a precipitation treatment at about 1400 F.
3. An alloy as in claim 1 consisting of about 0.08% carbon, about 15% chromium, about 18.5% cobalt, about 5.2% molybdenum, about 3.5% titanium, about 4.3% aluminum, about 0.03% boron, up to about 0.3% zirconium, about 0.8% to about 2% hafnium, with the balance being essentially nickel.
References Cited UNITED STATES PATENTS 3,479,157 11/1969 Richards et a1. 171
RICHARD O. DEAN, Primary Examiner US. Cl. X.R.
UNITED STATES PATENT oTFTcE CER'HFICATE 0F CCRRECHCN Patent NO. Dated 18,
Inventor(s) Carl Lund, et 91 It is certified that error appears in the above-identified patent and that said.Letters Patent are hereby corrected as shown below:
Column 2, line 51 "phase" should be phrase Column 4, line 14 "characteristics" should be characteristic Column 4, Table VI column marked "Reduction in area" should be Reduction-in-Area Column 5, line 4 before "overall" the word Without was omitted.
Signed and sealed this 26th day of December 1972.
(SEAL) Attes't:
EDWARD M'QFLETCHERJRG ROBERT GOTTSCHALK Atteshing Officer Commissioner of Patents ORM PO-lOSO (10-69) USCOMM-DC 6O376-P59 U.S. GOVERNMENT PRINTING OFFICE: 1965 0366-334
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US404470A | 1970-01-19 | 1970-01-19 |
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US4044A Expired - Lifetime US3677746A (en) | 1970-01-19 | 1970-01-19 | Heat treatable alloy |
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Cited By (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4121950A (en) * | 1975-10-31 | 1978-10-24 | Association Pour La Recherche Et Le Developpement Des Methods Et Processus Industriels (A.R.M.I.N.E.S.) | Forged nickel alloy product and method |
US4755240A (en) * | 1986-05-12 | 1988-07-05 | Exxon Production Research Company | Nickel base precipitation hardened alloys having improved resistance stress corrosion cracking |
US5725692A (en) * | 1995-10-02 | 1998-03-10 | United Technologies Corporation | Nickel base superalloy articles with improved resistance to crack propagation |
US5820700A (en) * | 1993-06-10 | 1998-10-13 | United Technologies Corporation | Nickel base superalloy columnar grain and equiaxed materials with improved performance in hydrogen and air |
US6068714A (en) * | 1996-01-18 | 2000-05-30 | Turbomeca | Process for making a heat resistant nickel-base polycrystalline superalloy forged part |
CN103484649A (en) * | 2013-09-18 | 2014-01-01 | 太原钢铁(集团)有限公司 | GH4700 alloy ingot homogenizing treatment method |
-
1970
- 1970-01-19 US US4044A patent/US3677746A/en not_active Expired - Lifetime
Cited By (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4121950A (en) * | 1975-10-31 | 1978-10-24 | Association Pour La Recherche Et Le Developpement Des Methods Et Processus Industriels (A.R.M.I.N.E.S.) | Forged nickel alloy product and method |
US4755240A (en) * | 1986-05-12 | 1988-07-05 | Exxon Production Research Company | Nickel base precipitation hardened alloys having improved resistance stress corrosion cracking |
US5820700A (en) * | 1993-06-10 | 1998-10-13 | United Technologies Corporation | Nickel base superalloy columnar grain and equiaxed materials with improved performance in hydrogen and air |
US5725692A (en) * | 1995-10-02 | 1998-03-10 | United Technologies Corporation | Nickel base superalloy articles with improved resistance to crack propagation |
US5788785A (en) * | 1995-10-02 | 1998-08-04 | United Technology Corporation | Method for making a nickel base alloy having improved resistance to hydrogen embittlement |
US6068714A (en) * | 1996-01-18 | 2000-05-30 | Turbomeca | Process for making a heat resistant nickel-base polycrystalline superalloy forged part |
CN103484649A (en) * | 2013-09-18 | 2014-01-01 | 太原钢铁(集团)有限公司 | GH4700 alloy ingot homogenizing treatment method |
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