US3015558A - Nickel-chromium-aluminum heat resisting alloy - Google Patents

Nickel-chromium-aluminum heat resisting alloy Download PDF

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US3015558A
US3015558A US840326A US84032659A US3015558A US 3015558 A US3015558 A US 3015558A US 840326 A US840326 A US 840326A US 84032659 A US84032659 A US 84032659A US 3015558 A US3015558 A US 3015558A
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chromium
nickel
alloy
alloys
aluminum
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Nicholas J Grant
Albert G Bucklin
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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
    • 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
    • C22C19/052—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W with the maximum Cr content being at least 40%

Definitions

  • composition range would make available a non-ferrous heat resistant alloy of high hardenability through age hardening heat treatment, particularly a composition for use in high temperature bearings, gears and the like capable of sustaining high hot hardness, i.e. resist softening, at elevated temperatures ranging up to about 1200 F.
  • an alloy could be made available from the composition range characterized by delayed age hardening but which is easily fabricated into sheets and other shapes for use at elevated temperatures ranging up to 1800 F. under applied stress.
  • Another object is to provide a heat resistant nickel alloy capable of being quickly age hardened Vto relatively high hardnesses at temperatures in the range of 1000 F. to 1600 F., particularly at temperatures within the range of 1000 F. to l400 F.
  • a further object is to provide an age-hardened composition characterized by resistance to softening at temperatures ranging up to about 1200 F.
  • Still another object is to provide a hot workable, aluminum-containing, high chromium nickel alloy with delayed aging characteristics and capable of being fabricated into a high strength sheet metal product.
  • This invention is based on the discovery by us that heat resistant nickel alloys of improved combination of phys- ⁇ ical properties at room and elevated temperatures can be produced by controlling in combination the essential elements nickel, chromium and aluminum.
  • the chromium content range from about 28% to 45%,Vv aluminum from about 1% to 6%, and the balance substantially nickel by weight, the sum of the nickel and chromium content being at least about 70%, the ratio of nickel to chromium being maintained at least about 1 to l, and being particularly maintained at a ratio ranging from about 1 to l to about 2.25 to l.
  • alloying ingredients may be present in the alloy in optional amounts providedpthe foregoing conditions with respect to the nickel and chromium contents are maintained.
  • other alloying ingredients are the following by weight: up to about 20% iron, up to about V10% molybdenum, up to about 15% cobalt, up to about 3% titanium, up to about 2% columbium and/or tantalum,
  • FIG. l contains age hardening curves showing Vthe eifect of time and temperature on the age hardening response of Type I alloy compositions
  • FIG. 2 depicts curves showing the resistance of an age hardened Type I alloy to softening at temperatures ranging up to about 1200 F.; and v Y 2% tin.
  • Optional ingredients may likewise be present in the amounts as stated above. However, we prefer when the sum of the nickel and chromium content is above 80%, for example above 85%, to employ optional ingredients in the following amounts: up to about-5% iron, up to about 5% molybdenum, up to aboutY 10% cobalt, up to about 2% titanium, up to about 2% columbium and/ or tantalum and up to about 4% silicon.
  • certain other optional elemental additions may be made, such as carbon, nitrogen and certain of the deoxidizers such as boron, magnesium, cerium, zirconium, etc. With respect to carbon and nitrogen, they may each be present singly or together in amounts ranging up to about 0.4%. Boron may be added in small amounts up to about 0.1%, calcium or magnesium in amounts up to about 0.2% and rare earth elements in amounts up to about 0.2%. Zirconium may be employed over a range starting with a small but effective amount (e.g. 0.002%) and range up to about 0.3%.
  • the composition may range from about 30 to 45% chromium, from about 3 to 6% aluminum and the balance substantially nickel, the sum of nickel and chromium being at least 85% of the total composition at a nickel to chromium ratio ranging yfrom about 1 to 1 to about 2.25 to 1.
  • Type I alloys are given in the following Table:V
  • a method for producing the foregoing alloys comprises melting the nickel and chromium together in a high frequency induction furnaceV in air but, preferably, in an inert gas cover.
  • the aluminum or other elements are added after the usuall deoxidation treatment.
  • These alloys have also been melted as non-consumable or consumable electrode ingots under sub-atmospheric pressure (about ⁇ 100-400 mm. Hg' of argon. After the ingot has cooled'to room temperature, it is removed from its mold and surface imperfections removed ⁇ from the ingot by grinding before being subjected to hot working.
  • the resulting ingot is then hot worked by hammer forging, press forging, or extrusion using a maximum of about 2300 F.
  • the ingot structure is renedyit is possible to work the alloy a-t progressively lower -tempe'ratures to refine .the grain size; however, working .below *1600 F. should be avoided to prevent, hardening due p to aging.
  • alloy No. 2 which was cast as a ten pound ingot two and VoneV half inches square by five inches high, vwas hot forged at a temperature of about 2300 F. to a one inch squarerbar. The ⁇ bar was then .solution treated at a temperature of about 2250 F. ⁇ for about one half hour, water quenched and then vcold rolled to one half inch square Vand kagain solution treated as above.
  • Ydetermining hardeningresponse through aging heat treatments samples of the various alloys were subjected to solutionV heat treatment followed by aging at Various times at'temperatures of from 1000 E. to 1800D F. in approxi- Y mately 100 intervals.
  • FIG. 1 shows the eiect of time and temperature on the aging of alloy Nos. 2, 3 and 10. It will be noted-'that No. 2 responds more rapidlyl at 1200" ⁇ F. (in less lthan half an hourV at temperature) as compared to Nos. 3,-and 10 which takes several hours before the age hardening becomes appreci- Vably eiective. However,V at 1350 F. it will be noted that Nos. 3 and 10 gain rapidly in hardness and harden almost as fast as alloy No. 2 at l400P.
  • the alloys are age hardenable broadly over the temperature range of about 1000 to 1600v F., but preferably over the range of about 1000 to 1400o F., the'preferredV time and tempera- 70 ture depending on the aggregate properties desired for any alloy.
  • Ni to Cr ratios vary :from 1.13 to 2.13 which falls within the desired range of about 1.1 to 2.25. It is preferred, where the ratio exceeds 1.6, to employ aluminum at .the higher range (above 4%) in order to achieve full benefit of the hardening effect.
  • hardnesses By controlling the conditions of hardening, a wide range of hardnesses is possible ranging yfrom about 60 to over 80 Rockwell A (corresponding to 20 to 60 RC) and preferably ranging from 70 to 80 RA (corresponding to 40 to 60 RC).
  • FIG. 2 shows the hot hardness of alloy No. 2 (40% Cr, 4% Al and 56% Ni) up #to 1200 F. It will be noted that while the initial hardness values (aged at 1250 and 1300 F.) were in the neighborhood of about 78 Rockwell A, alloy No. 2 maintained its hardness to above 74 Rockwell A at about 1000 F., the hardness Afalling off more rapidly -between 1050 F. and 1300 F. n
  • Y Alloy No. 12 exhibited a rather high tensile strength at room temperature in the cold'swaged condition of.210,000 p.s.i. with 11% elongation (0.250" diameter and gage length of 1.25").
  • the :alloy also exhibited a modulus of elasticity in theneighborhood of -about 30 to 33 X106 p.s.i.
  • the method employed ⁇ comprisedtaking a casting ofallo.)I No. 12 about 6 inches longV and 1 inch in diameter and forgingit at 2250 F.. to: 1900 F. to a one half inch square.
  • Type II alloy is particularly useful in aircraft gas turbine combustion liners and after burners; high temperature, high pressure piping and other Vparts subjected in use to erosive and/or corrosive conditions at elevated temperatures. These alloys couple outstanding oxidation resistance With great formability, yet offer Very high strength at temperatures up to about 1200 F. for other parts.
  • the Type III alloys find particular use in the production of sheet material or thermal elements subjected in use to high stresses at elevated temperature ranging up to about 1800 F.
  • the Type III alloys will Vcontain from aboutV 28% to 35%v Cr, 1% to 4% Al and the balance substantially nickel, the sum of the chromium and nickel being at least about 70% of the total composition, with the nickel to chromium ratio ranging from about 1.3 to 1'to about 1.75 to 1. It is desirable that the aluminum Vcontent not substantially exceed 3% nor chromium exceed 35% as aluminum and chromium together ,above Athese amounts render hot working more diicult.
  • alloying ingredients be used provided the foregoing compositions are maintained, the other ingredients comprising up to about 20% iron (preferably up to 10% Fe), up to about- 10% molybdenum (preferably up to 5% Mo), up to about 15% cobalt (preferably up to 10% Co), up to about 3% titanium (preferably up to 1% Ti), up to about 2% columbium and/or tantalum (preferably up to 1%), up to about 4% silicon, and up to about 2% manganese.
  • iron preferably up to 10% Fe
  • molybdenum preferably up to 5% Mo
  • cobalt preferably up to 10% Co
  • titanium preferably up to 1% Ti
  • columbium and/or tantalum preferably up to 1%
  • up to about 4% silicon up to about 2% manganese.
  • Alloy No; 20 also exhibited high ultimate tensile strength at elevated temperatures. For example, after solution quenching at 27250 F. followed -by aging at 1600" F., the alloy exhibited an ultimate strength of about 132,500 p.s.'i. at 130C
  • VAn advantage of complex"Y alloys of Type TH is that the alloys are capable of'being softenedto as low as 70 Rockwell B (44 Rockwell A) for fabrication purposes and thereafter hardened to any desired ⁇ hardness ranging up to as 'high asf75, l ⁇ ookwell A and higher.
  • the high temperature treatment is conducted at temperatures far exceeding the temperature at which precipitable phases which impart age hardenabiilty go into complete solution.
  • the high temperature treatment compirses heating the alloy to a solution temperature of at elast about 1950 F. for a time suflicient to effect substantially complete solution, preferably for at least about 2 hours and more preferably within the range of about 2050 F. to 2250" F. usually between l to 4 hours followed by sufficiently rapid cooling to preserve the solid solution.
  • Such rapid cooling may be elfected by water or oil quenching or in some instances by air cooling.
  • the cooling rate should be such that the alloy will cool to below 1300u F. in a relatively short time, forv example within 3 minutes. If desired the cooling can be interrupted at the desired aging temperature and held there for the required time.
  • the cooled alloys are then subjected to aging comprising'heating the alloys at a temperature from about 1000 F. to l600 F. for a time at least suflcient to obtain substantial hardening, preferably for at least 4 hours, and more preferably from about 12 hours to 48 hours.
  • the aging treatment imparts high temperature strength and hardness to the alloys.
  • the aging treatment may be conducted in several steps, for example at l500 F. for 4 hours, then at 1400 F. for 4 hours, and finish up at 1300 F. for 4 hours or any other combination of aging steps between the temperature ranges of 1000 F. to 1600 F.
  • the aging temperature will generally range from 1200u F. to 1600 FL, but we prefer aging temperatures in the range of 1400 F. to l600 F. to insure high resistance to high loads at elevated temperatures for prolonged periods of time.
  • these alloys In the age hardened condition the structure of these alloys compirses a gamma, face centered cubic matrix in which there are present two other precipitated phases which are responsible for the high hardness and high strength of the alloys. These phases are the ordered face centered cubic gamma prime phase basically of the formula Ni3Al into which titanium, cobalt and some chromium may be substituted without changing the lattice structure except for changes in the size of the lattice.
  • a second precipitated phase which differentiates these alloys from conventional nickel-chromiurn-aluminumtitanium alloys of the super alloy classication is the alpha, body centered cubic chromium rich phase.
  • the precipitation of this phase results in the observed higher hardness values compared to those reported in the past for the conventional Nil-Cr-Ti-Alsuper alloys.
  • Examination of solution treated alloy No. 7 showed a structure comprised of gamma nickel solid solution with small islands of alpha chromium solid solution. In the aged condition the alloy showed a structure comprising a ne precipitate of essentially unresolvable gamma prime phase (Ni3Al) and alpha chromium in gamma.
  • Different dispersions and particle size of the precipitates can be achieved by variations in composition, aging time and aging temperature.
  • the softness of the more highly alloyed materials will depend on the solution treatment temperature. Higher solution temperatures will increase the softness due to greater solution of the complex structure in the single phase gamma eld. Thus, by using higher solution ternperatures, it is possible to achieve greater age hardening after the aging treatment.
  • the alloys of the invention may be employed as cast alloys or as wrought products. Where hot working is resorted to in the production of shapes, precaution must be taken when the aluminum content exceeds about 4%. Where the aluminum is on the high side, we prefer to keep chromium on the lower end of the range so as to maintain the Ni to Cr ratio above 1.5 or preferably above 1.75.
  • the alloys are particularly adapted to precision casting in the production of preciseshapes such as turbine blades and the like.
  • Other articles for which the alloy may be employed include valves, valve seats, extrusion dies, furnace parts, supports and elements in vacuum tubes, brick mold linings and the like.
  • An age-hardenable, aluminum-containing, heat resistant, high chromium nickel alloy characterized by improved resistance'to softening in the aged condition at elevated temperatures ranging lup to about l200 F. which comprises by weight about 30% to 40% chromium, about 2% to 5% aluminum and the balance substantially nickel, the sum of the chromium and nickel content being at least about 85% of the total composition at a ratio of nickel to chromium of about 1.3 to 1 to about 1.75 to 1.
  • An age-hardenable, aluminum-containing, heat resistant, high chromium nickel alloy characterized by improved resistance to softening in the aged condition at elevated temperatures ranging up to about 1200 F. which comprises by weight about 30% to 40% chromium, about 2% to 5% aluminum and nickel in an amount such that the sum of the chromium and nickel content is at least about of the total compositionat a ratio of nickel to chromium of about 1.3 to l to about 1.75 to l and the balance up to 5% iron, up to 5% molybdenum, up to 10% cobalt, up to 2% titanium, up to 2% columbium and up to 4% silicon.
  • An age-hardenable, aluminum-containing, heat-resistant, high chromium nickel alloy characterized by improved resistance to softening at elevated temperatures ranging up to about 120 F. which comprises by weight about 30% to 45% chromium, about 3% to 6% aluminum and the balance substantially nickel, the sum of the chromium and nickel content being at least about at a ratio of nickel to chromium of about 1 to 1 to about 1.75 to l.
  • An age-hardened, aluminum-containing, heat resistant, high chromium nickel alloy characterized by improved resistance to softening in the aged condition at elevated temperatures ranging up to about 1200 F., said alloy comprising by weight about to 40% chromium, about 2% to 5% aluminum and the balance substantially nickel,rthe sum of the chromium and nickel content being at least about 80% of the total composition at a ratio of nickel to lchromium of at least about'1.3 to- 1 to about 1.75 to 1, said alloy being further characterized by a microstructurel comprising a gamma nickel Ysolid solution containing precipitated alpha chromiumy phase and a face centered gamma prime phase of the type NiaAl.
  • An age-hardened, aluminum-containing, heat resistant, high chromiunirnickel alloy characterized by improved resistance to softening in the aged condition at elevated temperatures ranging up to about 1200 F.
  • said alloy comprising by weight about 30% to 40% chromium, about 2% to 5% aluminum and the balance substantially nickel, the sum of the chromiumv and nickel content being at least about 85% of the total cornposition at a ratio of nickel to chromium of about 1.3 to 1 to about 1.75 to l, said alloy being further characterized by a microstructure comprisingr a gamma nickel solid solution containing precipitatedv alpha chromium phase and a face centered Vgamma prime'phase of the type NiaAl.
  • An age-hardened, aluminum-containing, heat resistant, high chromium nickel alloy characterized by improved resistance to softening in the aged condition atV elevated temperatures ranging up to about 1200" F., said alloy comprising by weight about 30% to 40% chromium, about 2% to 5% aluminum and nickel in an amount such that the sumof the chromium and nickel ycontent is at least about 80% of the total composition at a ratio of nickelY to chromium of at least about 1.3 to 1 to about 1.75 to 1 and the balance up to 5% iron,
  • Y up to 5% molybdenum, up to 10% cobalt, up to 2% 12 titanium, up to 2% columbium and up to 4% silicon, said alloy being further characterized by a Vmicrostructure comprising a gamma nickel solid solution containing precipitated alpha chromium phase and a face centered gamma prime phase of the type Ni3Al.
  • An age-hardened, aluminum-containing, Vheat resistant, high chromium nickel alloy characterized by improved rcsistance to softening at elevated temperatures ranging up to about 1200 F., said alloy comprising by weight about 30% to 45% chromium, about V3% to 6% aluminum and the balance substantially nickel, the sum of thev chromium Vand. nickel content being at least about at a ratio of nickel to chromium of about 1 to 1 to about 1.75 to l, said alloy being further characterized by a microstructure comprising a gamma nickel solid solution containing precipitated alpha chromium phase and a face centered gamma prime phase of the type NiaAl.
  • An age-hardened, aluminum-containing, heat resistant, high chromium nickel alloy characterized by improved resistance to softening at elevatedV temperatures ranging up to about 1200 F., said alloy comprising by weight about 30% to 40% chromium, about.3% to 5% aluminum and the balance substantially nickel, the sum of the chromium and nickel content being at least about .at a ratio of nickel to chromium of-vabout 1.3 to 1 to about 1.75 to 1, said alloy being further characterized by a microstructure comprising a gamma Vnickel solid solution containing precipitated alpha chromium phase and a face centered gamma prime phase of the type NiBAl.

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US840326A 1959-09-16 1959-09-16 Nickel-chromium-aluminum heat resisting alloy Expired - Lifetime US3015558A (en)

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US840326A US3015558A (en) 1959-09-16 1959-09-16 Nickel-chromium-aluminum heat resisting alloy
GB31694/60A GB933240A (en) 1959-09-16 1960-09-14 Improvements in chromium nickel aluminium alloy and methods of heat treating such alloys
CH1051760A CH400578A (fr) 1959-09-16 1960-09-16 Alliage nickel, chrome, aluminium résistant à la chaleur

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Cited By (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3310394A (en) * 1963-09-17 1967-03-21 Raytheon Co Nickel alloys possessing controlled mechanical q properties
US3519419A (en) * 1966-06-21 1970-07-07 Int Nickel Co Superplastic nickel alloys
US3816110A (en) * 1971-04-15 1974-06-11 Tokyo Shibaura Electric Co Heat-resistant and corrosion-resistant high chromium-nickel alloy
FR2347451A1 (fr) * 1976-04-07 1977-11-04 Wiggin & Co Ltd Henry Alliages contenant du nickel, du chrome et du cobalt
US4155782A (en) * 1975-11-12 1979-05-22 Tokyo Shibaura Electric Co., Ltd. Watch case
US4246048A (en) * 1976-07-28 1981-01-20 Tokyo Shibaura Electric Co., Ltd. Forged atomic power plant parts
DE3240188A1 (de) * 1981-10-31 1983-05-11 Tokyo Shibaura Denki K.K., Kawasaki, Kanagawa Hartmetallegierung
WO2000014290A1 (fr) * 1998-09-04 2000-03-16 Inco Alloys International, Inc. Alliage haute temperature de pointe resistant a la corrosion
US20040152935A1 (en) * 2002-10-21 2004-08-05 Jones Jeffrey P. Method and system for reducing decomposition byproducts in a methanol to olefin reactor system
US20050167010A1 (en) * 2002-05-15 2005-08-04 Kabushiki Kaisha Toshiba Ni-cr alloy cutting tool
US20060207696A1 (en) * 2005-03-03 2006-09-21 Daido Tokushuko Kabushiki Kaisha Nonmagnetic high-hardness alloy
US20070044872A1 (en) * 2003-04-14 2007-03-01 General Electric Company Precipitation-strengthened nickel-iron-chromium alloy and process therefor
US20080121319A1 (en) * 2004-09-30 2008-05-29 Takashi Rokutanda High Hardness, High Corrosion Resistance and High Wear Resistance Alloy
US20090038717A1 (en) * 2005-11-07 2009-02-12 Huntington Alloys Corporation Process for Manufacturing High Strength Corrosion Resistant Alloy For Oil Patch Applications
US20100163101A1 (en) * 2007-04-25 2010-07-01 Ferro Corporation Thick Film Conductor Formulations Comprising Silver And Nickel Or Silver And Nickel Alloys And Solar Cells Made Therefrom
US20110011500A1 (en) * 2007-11-19 2011-01-20 Huntington Alloys Corporation Ultra high strength alloy for severe oil and gas environments and method of preparation
US10253382B2 (en) 2012-06-11 2019-04-09 Huntington Alloys Corporation High-strength corrosion-resistant tubing for oil and gas completion and drilling applications, and process for manufacturing thereof
EP3915717A1 (fr) * 2020-05-26 2021-12-01 Daido Steel Co., Ltd. Alliage à base de ni, et produit d'alliage à base de ni et leurs procédés de production

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB583841A (en) * 1941-12-17 1947-01-01 Mond Nickel Co Ltd Improvements relating to heat-resisting alloys
US2460590A (en) * 1946-05-11 1949-02-01 Driver Harris Co Electric resistance element and method of heat-treatment
US2533736A (en) * 1946-05-11 1950-12-12 Driver Harris Co Electric resistance element and method of heat-treatment

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB583841A (en) * 1941-12-17 1947-01-01 Mond Nickel Co Ltd Improvements relating to heat-resisting alloys
US2460590A (en) * 1946-05-11 1949-02-01 Driver Harris Co Electric resistance element and method of heat-treatment
US2533736A (en) * 1946-05-11 1950-12-12 Driver Harris Co Electric resistance element and method of heat-treatment

Cited By (30)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3310394A (en) * 1963-09-17 1967-03-21 Raytheon Co Nickel alloys possessing controlled mechanical q properties
US3519419A (en) * 1966-06-21 1970-07-07 Int Nickel Co Superplastic nickel alloys
US3816110A (en) * 1971-04-15 1974-06-11 Tokyo Shibaura Electric Co Heat-resistant and corrosion-resistant high chromium-nickel alloy
US4155782A (en) * 1975-11-12 1979-05-22 Tokyo Shibaura Electric Co., Ltd. Watch case
FR2347451A1 (fr) * 1976-04-07 1977-11-04 Wiggin & Co Ltd Henry Alliages contenant du nickel, du chrome et du cobalt
US4246048A (en) * 1976-07-28 1981-01-20 Tokyo Shibaura Electric Co., Ltd. Forged atomic power plant parts
DE3240188A1 (de) * 1981-10-31 1983-05-11 Tokyo Shibaura Denki K.K., Kawasaki, Kanagawa Hartmetallegierung
US6761854B1 (en) 1998-09-04 2004-07-13 Huntington Alloys Corporation Advanced high temperature corrosion resistant alloy
WO2000014290A1 (fr) * 1998-09-04 2000-03-16 Inco Alloys International, Inc. Alliage haute temperature de pointe resistant a la corrosion
US20050167010A1 (en) * 2002-05-15 2005-08-04 Kabushiki Kaisha Toshiba Ni-cr alloy cutting tool
US7740719B2 (en) * 2002-05-15 2010-06-22 Kabushiki Kaisha Toshiba Cutter composed of Ni-Cr alloy
US20080302449A1 (en) * 2002-05-15 2008-12-11 Kabushiki Kaisha Toshiba Cutter composed of ni-cr alloy
US7682474B2 (en) 2002-05-15 2010-03-23 Kabushiki Kaisha Toshiba Cutter composed of Ni-Cr-Al Alloy
US20040152935A1 (en) * 2002-10-21 2004-08-05 Jones Jeffrey P. Method and system for reducing decomposition byproducts in a methanol to olefin reactor system
US7338645B2 (en) * 2002-10-21 2008-03-04 Exxonmobil Chemical Patents Inc. Method and system for reducing decomposition byproducts in a methanol to olefin reactor system
US7507306B2 (en) * 2003-04-14 2009-03-24 General Electric Company Precipitation-strengthened nickel-iron-chromium alloy and process therefor
US20070044872A1 (en) * 2003-04-14 2007-03-01 General Electric Company Precipitation-strengthened nickel-iron-chromium alloy and process therefor
US20080121319A1 (en) * 2004-09-30 2008-05-29 Takashi Rokutanda High Hardness, High Corrosion Resistance and High Wear Resistance Alloy
US8062441B2 (en) * 2004-09-30 2011-11-22 Kabushiki Kaisha Toshiba High hardness, high corrosion resistance and high wear resistance alloy
US20060207696A1 (en) * 2005-03-03 2006-09-21 Daido Tokushuko Kabushiki Kaisha Nonmagnetic high-hardness alloy
US8696836B2 (en) * 2005-03-03 2014-04-15 Daido Tokushuko Kabushiki Kaisha Nonmagnetic high-hardness alloy
US20090038717A1 (en) * 2005-11-07 2009-02-12 Huntington Alloys Corporation Process for Manufacturing High Strength Corrosion Resistant Alloy For Oil Patch Applications
US8133334B2 (en) * 2005-11-07 2012-03-13 Huntington Alloys Corporation Process for manufacturing high strength corrosion resistant alloy for oil patch applications
US20100163101A1 (en) * 2007-04-25 2010-07-01 Ferro Corporation Thick Film Conductor Formulations Comprising Silver And Nickel Or Silver And Nickel Alloys And Solar Cells Made Therefrom
US20110011500A1 (en) * 2007-11-19 2011-01-20 Huntington Alloys Corporation Ultra high strength alloy for severe oil and gas environments and method of preparation
US9017490B2 (en) 2007-11-19 2015-04-28 Huntington Alloys Corporation Ultra high strength alloy for severe oil and gas environments and method of preparation
US10100392B2 (en) 2007-11-19 2018-10-16 Huntington Alloys Corporation Ultra high strength alloy for severe oil and gas environments and method of preparation
US10253382B2 (en) 2012-06-11 2019-04-09 Huntington Alloys Corporation High-strength corrosion-resistant tubing for oil and gas completion and drilling applications, and process for manufacturing thereof
EP3915717A1 (fr) * 2020-05-26 2021-12-01 Daido Steel Co., Ltd. Alliage à base de ni, et produit d'alliage à base de ni et leurs procédés de production
US11732331B2 (en) 2020-05-26 2023-08-22 Daido Steel Co., Ltd. Ni-based alloy, and Ni-based alloy product and methods for producing the same

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GB933240A (en) 1963-08-08

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