US3411899A - Nickel-chromium alloys with delayed aging characteristics - Google Patents
Nickel-chromium alloys with delayed aging characteristics Download PDFInfo
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- US3411899A US3411899A US565476A US56547666A US3411899A US 3411899 A US3411899 A US 3411899A US 565476 A US565476 A US 565476A US 56547666 A US56547666 A US 56547666A US 3411899 A US3411899 A US 3411899A
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- 230000032683 aging Effects 0.000 title description 12
- 239000000788 chromium alloy Substances 0.000 title description 5
- 230000003111 delayed effect Effects 0.000 title description 5
- 229910000623 nickel–chromium alloy Inorganic materials 0.000 title description 3
- 229910045601 alloy Inorganic materials 0.000 claims description 74
- 239000000956 alloy Substances 0.000 claims description 74
- XEEYBQQBJWHFJM-UHFFFAOYSA-N Iron Chemical compound [Fe] XEEYBQQBJWHFJM-UHFFFAOYSA-N 0.000 claims description 38
- 239000010941 cobalt Substances 0.000 claims description 22
- 229910017052 cobalt Inorganic materials 0.000 claims description 22
- GUTLYIVDDKVIGB-UHFFFAOYSA-N cobalt atom Chemical compound [Co] GUTLYIVDDKVIGB-UHFFFAOYSA-N 0.000 claims description 22
- 239000011651 chromium Substances 0.000 claims description 16
- 229910052742 iron Inorganic materials 0.000 claims description 16
- VYZAMTAEIAYCRO-UHFFFAOYSA-N Chromium Chemical compound [Cr] VYZAMTAEIAYCRO-UHFFFAOYSA-N 0.000 claims description 15
- 229910052804 chromium Inorganic materials 0.000 claims description 15
- 238000004881 precipitation hardening Methods 0.000 claims description 12
- 229910000531 Co alloy Inorganic materials 0.000 claims description 3
- SZMZREIADCOWQA-UHFFFAOYSA-N chromium cobalt nickel Chemical compound [Cr].[Co].[Ni] SZMZREIADCOWQA-UHFFFAOYSA-N 0.000 claims description 3
- 238000012545 processing Methods 0.000 claims description 3
- 230000002596 correlated effect Effects 0.000 claims description 2
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 description 28
- 238000011534 incubation Methods 0.000 description 23
- WFKWXMTUELFFGS-UHFFFAOYSA-N tungsten Chemical compound [W] WFKWXMTUELFFGS-UHFFFAOYSA-N 0.000 description 19
- 229910052721 tungsten Inorganic materials 0.000 description 19
- 239000010937 tungsten Substances 0.000 description 19
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 17
- ZOKXTWBITQBERF-UHFFFAOYSA-N Molybdenum Chemical compound [Mo] ZOKXTWBITQBERF-UHFFFAOYSA-N 0.000 description 17
- 229910052799 carbon Inorganic materials 0.000 description 17
- 229910052750 molybdenum Inorganic materials 0.000 description 17
- 239000011733 molybdenum Substances 0.000 description 17
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 description 14
- 229910052759 nickel Inorganic materials 0.000 description 14
- 239000010936 titanium Substances 0.000 description 14
- 229910052719 titanium Inorganic materials 0.000 description 14
- 239000010955 niobium Substances 0.000 description 13
- GUCVJGMIXFAOAE-UHFFFAOYSA-N niobium atom Chemical compound [Nb] GUCVJGMIXFAOAE-UHFFFAOYSA-N 0.000 description 12
- 229910052715 tantalum Inorganic materials 0.000 description 11
- GUVRBAGPIYLISA-UHFFFAOYSA-N tantalum atom Chemical compound [Ta] GUVRBAGPIYLISA-UHFFFAOYSA-N 0.000 description 11
- 230000035882 stress Effects 0.000 description 8
- ZOXJGFHDIHLPTG-UHFFFAOYSA-N Boron Chemical compound [B] ZOXJGFHDIHLPTG-UHFFFAOYSA-N 0.000 description 7
- QCWXUUIWCKQGHC-UHFFFAOYSA-N Zirconium Chemical compound [Zr] QCWXUUIWCKQGHC-UHFFFAOYSA-N 0.000 description 7
- 229910052796 boron Inorganic materials 0.000 description 7
- 230000000694 effects Effects 0.000 description 7
- 239000000203 mixture Substances 0.000 description 7
- 238000012360 testing method Methods 0.000 description 7
- 229910052726 zirconium Inorganic materials 0.000 description 7
- 239000002244 precipitate Substances 0.000 description 6
- 238000007792 addition Methods 0.000 description 5
- 238000010438 heat treatment Methods 0.000 description 5
- 238000001556 precipitation Methods 0.000 description 5
- XUIMIQQOPSSXEZ-UHFFFAOYSA-N Silicon Chemical compound [Si] XUIMIQQOPSSXEZ-UHFFFAOYSA-N 0.000 description 4
- 229910052782 aluminium Inorganic materials 0.000 description 4
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 4
- 229910052710 silicon Inorganic materials 0.000 description 4
- 239000010703 silicon Substances 0.000 description 4
- 239000000243 solution Substances 0.000 description 4
- 239000000470 constituent Substances 0.000 description 3
- 238000001816 cooling Methods 0.000 description 3
- 238000004519 manufacturing process Methods 0.000 description 3
- 239000000463 material Substances 0.000 description 3
- PWHULOQIROXLJO-UHFFFAOYSA-N Manganese Chemical compound [Mn] PWHULOQIROXLJO-UHFFFAOYSA-N 0.000 description 2
- FAPWRFPIFSIZLT-UHFFFAOYSA-M Sodium chloride Chemical compound [Na+].[Cl-] FAPWRFPIFSIZLT-UHFFFAOYSA-M 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 2
- 238000005266 casting Methods 0.000 description 2
- 239000012535 impurity Substances 0.000 description 2
- 229910052748 manganese Inorganic materials 0.000 description 2
- 239000011572 manganese Substances 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- PMZURENOXWZQFD-UHFFFAOYSA-L Sodium Sulfate Chemical compound [Na+].[Na+].[O-]S([O-])(=O)=O PMZURENOXWZQFD-UHFFFAOYSA-L 0.000 description 1
- 238000000137 annealing Methods 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 239000010883 coal ash Substances 0.000 description 1
- 238000005336 cracking Methods 0.000 description 1
- 230000007423 decrease Effects 0.000 description 1
- 230000001419 dependent effect Effects 0.000 description 1
- 230000001627 detrimental effect Effects 0.000 description 1
- NRUQNUIWEUZVLI-UHFFFAOYSA-O diethanolammonium nitrate Chemical compound [O-][N+]([O-])=O.OCC[NH2+]CCO NRUQNUIWEUZVLI-UHFFFAOYSA-O 0.000 description 1
- 238000009826 distribution Methods 0.000 description 1
- 238000007542 hardness measurement Methods 0.000 description 1
- 238000010348 incorporation Methods 0.000 description 1
- 238000003754 machining Methods 0.000 description 1
- WPBNNNQJVZRUHP-UHFFFAOYSA-L manganese(2+);methyl n-[[2-(methoxycarbonylcarbamothioylamino)phenyl]carbamothioyl]carbamate;n-[2-(sulfidocarbothioylamino)ethyl]carbamodithioate Chemical compound [Mn+2].[S-]C(=S)NCCNC([S-])=S.COC(=O)NC(=S)NC1=CC=CC=C1NC(=S)NC(=O)OC WPBNNNQJVZRUHP-UHFFFAOYSA-L 0.000 description 1
- 239000011159 matrix material Substances 0.000 description 1
- 238000005259 measurement Methods 0.000 description 1
- 229910052751 metal Inorganic materials 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 230000000750 progressive effect Effects 0.000 description 1
- 230000002035 prolonged effect Effects 0.000 description 1
- 238000001226 reprecipitation Methods 0.000 description 1
- 239000011780 sodium chloride Substances 0.000 description 1
- 229910052938 sodium sulfate Inorganic materials 0.000 description 1
- 235000011152 sodium sulphate Nutrition 0.000 description 1
- 239000006104 solid solution Substances 0.000 description 1
- 238000005482 strain hardening Methods 0.000 description 1
- 238000005728 strengthening Methods 0.000 description 1
- 238000011282 treatment Methods 0.000 description 1
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 1
- 238000003466 welding Methods 0.000 description 1
Images
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%
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C19/00—Alloys based on nickel or cobalt
- C22C19/03—Alloys based on nickel or cobalt based on nickel
- C22C19/05—Alloys based on nickel or cobalt based on nickel with chromium
- C22C19/051—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W
- C22C19/055—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W with the maximum Cr content being at least 20% but less than 30%
Definitions
- NICKEL-CHROMIUM ALLOYS WITH DELAYED AGING CHARACTERISTICS Filed July 15, 1966 INVENTORS fob/ 99 Gamay Fm y 0M0 Maps/ml WW0 United States Patent 3,411,899 NICKEL-CHROMIUM ALLOYS WITH DELAYED AGING CHARACTERISTICS Edward Gordon Richards, West Hagley, and David Marshall Ward, Birmingham, England, assiguors to The International Nickel Company, Inc., New York. N.Y., a corporation of Delaware Filed July 15, 1966, Ser. No. 565,476 Claims priority, application Great Britain, July 22, 1965, 31,326/65 7 Claims. (Cl.
- the present invention relates to nickel-containing alloys and more particularly to precipitation hardening nickelchromium-cobalt alloys of such composition that the alloys manifest the unique capability to self-retard the onset of precipitation hardening whereby ease in carrying out various processing operations is facilitated.
- nickelrich alloys of the nickel-chromium-cobalt type, with or Without iron are characterized by high strength at elevated temperatures, i.e., the alloys sustain high stress for prolonged periods before fracture.
- a useful improvement in high temperature strength is afforded by the addition of certain elements, e.g., molybdenum and tungsten, which enter into solid solution in the basic composition. But the greatest strengthening effect is generally obtained by the incorporation of constituents which produce stable precipitates in the nickel-rich matrix.
- Titanium, aluminum and columbium, which combine with nickel either individually or in combination to produce very stable precipitates, are notable in this regard and are particularly effective in improving high temperature strength, a property which generally increases with the amount of stable precipitate and, thus, with the contents of the effective addition elements.
- the alloys must be suitably heat treated. This generally consists in solution heating at a very high temperature to dissolve the stable phases followed by aging at a lower temperature below the temperature of solubility of the stable phases to cause reprecipitation thereof.
- the aging temperature is dependent on the alloy composition but generally falls within the range of about 500 C, to 1100 C. At temperatures Within the aging range, precipitation commences almost immediately and is manifested by an immediate and progressive increase in alloy hardness. The rate of increase in hardness and the maximum hardness obtained both depend on the aging temperature but usually increase with the content in the alloy of the elements which produce the stable precipitates.
- alloys in accordance herewith contain (in percent by weight) from about 16% to 24% chromium, about 5% to 35% cobalt, up to iron, provided that 2 (Prcent Fe)+(percent Co) does not exceed and that 2x (percent Fe)+3 (percent Co) is not less than from 1% to about 2.8% titanium, up to 4% columbium, up to 8% tantalum, provided that (percent Cb)+0.5 (percent Ta) is from 2% to 4%, up to 4% molybdenum, up to 8% tungsten, provided that 2 (Percent Mo)+(percent W) does not exceed 8.5%, carbon in an amount not exceeding about 0.15%, up to about 0.004% boron, up to 0.05% zirconium and the balance, apart from impurities, being essentially nickel.
- the contents of the major impurities, silicon and manganese, should not exceed 0.5% each, Silicon impairs weldability and advantageously is kept below 0.3%, and preferably
- Alloys within the foregoing ranges exhibit a remarkable ability to resist the immediate onset of precipitation hardening.
- the time to the onset of aging that is to say, the time before any significant increase in hardness occurs, may be referred to as the incubation period and varies with the aging temperature.
- Alloys having incubation periods of several hours, to wit, at least five hours and advantageously 25 hours have been developed in reaching the objective, and such alloys are deemed quite beneficial since alloys in which the precipitation hardening response has been thus delayed have marked advantages over existing high temperature alloys for heavy section components and welded or cold worked fabrications.
- castings or hot worked parts can be cooled naturally without significantly increasing their hardness, and internally stressed components can be readily reheated to annealing temperatures and stress relieved before precipitation hardening commences. It Will be appreciated, however, that the incubation period should not be too long, not greater than about hours, since otherwise the period of heating required to age the alloys satisfactorily would be impractica-bly long.
- the alloys can be precipitation hardened by heating at temperatures in the range of 550 C. to 850 C., most advantageously 3 650 C. to 750 C. Generally speaking, the incubation period should be at least five hours at 750 C. On the other hand, it should not exceed 50 hours.
- Initial solution heating of the alloys can be carried out at temperatures above about 950 C., e.g., in the range of about 1000 C. to 1100" C.
- testpieces were machined from forged bar of the alloy that had been solution heated for one hour at 1000 C. Stress-rupture tests were carried out at 650 C. under a stress of 36 long tons per square inch (t.s.i.) after aging for 16 hours at 700 C., the stressrupture lives and elongation values being determined at fracture. Impact values were determined at room temperature using a notched impact testpiece that had been heated at 650 C. for 10,000 hours.
- Incubation periods were determined by hardness measurements on specimens heated at 750 C. for different periods of time and Water quenched to room temperature. The shortest time to give an increase in hardness above that of the solution treated In the absence of iron, the incubation period is too long and the stress-rupture life too low if the cobalt content is less than 15 while if the cobalt content exceeds 35%, the incubation period is too short and the stress-rupture ductility is too low.
- Tungsten in the alloys is wholly or partly replaceable 0.05% carbon, the balance, except for the chromium, by half its weight of molybdenum provided being nickel.
- Alloy No. 3 is in accordance with the invention, whereas Alloys Nos. 1, 2 and 4 are not.
- percent Life, hrs. El, ItJlbs. hrs. percent Percent W+2 (p rcent M0) is from 0 to 8.5
- the alloys preferably contain one or both of tungsten and molybdenum so that the value of this expression is at least 1.
- titanium 3% columbium and 0.05 carbon, the balance being nickel.
- columbium as indicated herein, may be partly or wholly replaced by twice its weight of tantalum, i.e., on an atom-for-atom basis.
- the alloys almost inevitably contain small amounts of carbon and preferably at least 0.03% carbon is present to inhibit grain growth. Amounts of carbon in excess of 0.15% drastically reduce the stress-rupture life of the alloys, and preferably the carbon content does not exceed 0.1%.
- the effect of varying carbon content is shown by the test results in Table V, which relate to alloys that nominally contain, besides carbon, 20% chromium, 20% cobalt, 1.5% titanium, 3% columbium and 2% tungsten, the balance being nickel.
- the ductility in stress-rupture tests at 650 C. and the impact strength of the alloys can be somewhat increased by small additions of boron and zirconium, up to 0.004% and 0.05 respectively. However, the presence of these elements impairs the weldability of the alloys and prefer ably the boron content does not exceed 0.003% and the zirconium content 0.02%. No additions of boron or zirconium were made to any of the alloys tested in the tables above.
- the incubation period for a given alloy will vary somewhat with the temperature within the range of possible aging temperatures.
- the incubation period of Alloy No. 3 varied with temperature as shown in Table VI.
- the alloys of the invention have incubation periods very much greater than those of nickel-chromiumbase high temperature alloys hitherto used which are typically only a few seconds.
- a particularly advantageous alloy range is as follows: about 17% to 23% chromium, about 17% to 25% cobalt, up to 1% iron, about 1.25% to 2.75% titanium, up to 4% columbium, up to 6% tantalum with the sum of the percent columbium plus one half the percent tantalum not exceeding 6%, up to 6% tungsten, up to 3% molybdenum, the sum of the percent tungsten plus two times the percent molybdenum being from 1 to 8.5, up to 0.1% carbon, up to 0.003% boron, up to 0.02% zirconium and the balance essentially nickel.
- the alloys of the invention are resistant to corrosive attack by a molten mixture consisting of 25% sodium chloride and 75% sodium sulfate at 900 C. which simulates the cororsive effects of coal ash. They are therefore suitable for other parts, such as superheater tubes, which are exposed to these conditions.
- a preciptation-hardenable nickel-chrominum-cobalt alloy adapted for elevated temperature use and characterized by the unique capability of delaying the onset of precipitation hardening whereby ease in processing the alloys is facilitated, said alloy consisting essentially of from about 16% to 24% chromium, about 5% to 35% cobalt, up to 15% iron with the cobalt and iron being correlated such that the following relationships are satisfied:
- 2 (P rcent Fe)+(percent Co) does not exceed 35% and 2X (percent Fe)+3 (percent Co) is not less than 45% from 1% to about 2.8% titanium, up to 4% columbian, up to 8% tantalum, the sum of the .columbian plus onehalf the tantalum being from 2% to 4%, up to 4% molybdenum, up to 8% tungsten, the sum of twice the molybdenum plus the tungsten not exceeding about 8.5%, carbon in an amount not exceeding about 0.15%, up to about 0.004% boron, up to 0.05 zirconium up to 0.5 silicon, up to 0.5 manganese and the balance essentially nickel.
- the alloy set forth in claim 1 and containing about 17% to 23% chromium, about 17% to 25% cobalt, up to 1% iron, about 1.25% to 2.75 titanium, up to 4% columbian, up to 6% tantalum with the columbian plus 3,411,899 7 8 one-half the tantalum not exceeding about 6%, up to exceeding about 8%, about 0.03% to 0.1% carbon and 6% tungsten, up to 3% molybdenum, the sum of the the balance essentially nickel.
- tungsten plus twice the molybdenum being from 1% to 8.5%, up to 0.1% carbon, up to 0.003% boron, up to References Cited 0.02% zirconium, up to 0.3% silicon and up to 0.3% 5 UNITED STATES PATENTS manganese' 2,981,621 4/1961 Thi leman 75-1 7.
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- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Materials Engineering (AREA)
- Mechanical Engineering (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- Heat Treatment Of Steel (AREA)
- Manufacture And Refinement Of Metals (AREA)
- Heat Treatment Of Articles (AREA)
- Manufacture Of Alloys Or Alloy Compounds (AREA)
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB31326/65A GB1148390A (en) | 1965-07-22 | 1965-07-22 | Nickel-chromium alloys |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| US3411899A true US3411899A (en) | 1968-11-19 |
Family
ID=10321472
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| US565476A Expired - Lifetime US3411899A (en) | 1965-07-22 | 1966-07-15 | Nickel-chromium alloys with delayed aging characteristics |
Country Status (5)
| Country | Link |
|---|---|
| US (1) | US3411899A (enEXAMPLES) |
| AT (1) | AT264853B (enEXAMPLES) |
| ES (1) | ES329332A1 (enEXAMPLES) |
| GB (1) | GB1148390A (enEXAMPLES) |
| SE (1) | SE336232B (enEXAMPLES) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3713788A (en) * | 1970-10-21 | 1973-01-30 | Chromalloy American Corp | Powder metallurgy sintered corrosion and heat-resistant, age hardenable nickel-chromium refractory carbide alloy |
| US4492672A (en) * | 1982-04-19 | 1985-01-08 | The United States Of America As Represented By The Secretary Of The Navy | Enhanced microstructural stability of nickel alloys |
| US5476555A (en) * | 1992-08-31 | 1995-12-19 | Sps Technologies, Inc. | Nickel-cobalt based alloys |
| JP2016211074A (ja) * | 2015-05-07 | 2016-12-15 | ゼネラル・エレクトリック・カンパニイ | 物品及び物品の形成方法 |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2981621A (en) * | 1957-07-29 | 1961-04-25 | Sierra Metals Corp | High temperature nickel-iron base alloy |
| US3046108A (en) * | 1958-11-13 | 1962-07-24 | Int Nickel Co | Age-hardenable nickel alloy |
| US3151981A (en) * | 1961-02-28 | 1964-10-06 | Int Nickel Co | Nickel-chromium-cobalt alloy |
| US3222165A (en) * | 1958-11-26 | 1965-12-07 | Rolls Royce | Nickel chromium base alloy products |
-
1965
- 1965-07-22 GB GB31326/65A patent/GB1148390A/en not_active Expired
-
1966
- 1966-07-15 US US565476A patent/US3411899A/en not_active Expired - Lifetime
- 1966-07-20 AT AT692266A patent/AT264853B/de active
- 1966-07-21 ES ES0329332A patent/ES329332A1/es not_active Expired
- 1966-07-22 SE SE10027/66A patent/SE336232B/xx unknown
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2981621A (en) * | 1957-07-29 | 1961-04-25 | Sierra Metals Corp | High temperature nickel-iron base alloy |
| US3046108A (en) * | 1958-11-13 | 1962-07-24 | Int Nickel Co | Age-hardenable nickel alloy |
| US3222165A (en) * | 1958-11-26 | 1965-12-07 | Rolls Royce | Nickel chromium base alloy products |
| US3151981A (en) * | 1961-02-28 | 1964-10-06 | Int Nickel Co | Nickel-chromium-cobalt alloy |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3713788A (en) * | 1970-10-21 | 1973-01-30 | Chromalloy American Corp | Powder metallurgy sintered corrosion and heat-resistant, age hardenable nickel-chromium refractory carbide alloy |
| US4492672A (en) * | 1982-04-19 | 1985-01-08 | The United States Of America As Represented By The Secretary Of The Navy | Enhanced microstructural stability of nickel alloys |
| US5476555A (en) * | 1992-08-31 | 1995-12-19 | Sps Technologies, Inc. | Nickel-cobalt based alloys |
| US5637159A (en) * | 1992-08-31 | 1997-06-10 | Sps Technologies, Inc. | Nickel-cobalt based alloys |
| US5888316A (en) * | 1992-08-31 | 1999-03-30 | Sps Technologies, Inc. | Nickel-cobalt based alloys |
| JP2016211074A (ja) * | 2015-05-07 | 2016-12-15 | ゼネラル・エレクトリック・カンパニイ | 物品及び物品の形成方法 |
Also Published As
| Publication number | Publication date |
|---|---|
| GB1148390A (en) | 1969-04-10 |
| AT264853B (de) | 1968-09-25 |
| ES329332A1 (es) | 1967-05-01 |
| DE1533292B2 (de) | 1972-11-23 |
| DE1533292A1 (de) | 1969-12-18 |
| SE336232B (enEXAMPLES) | 1971-06-28 |
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