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Publication numberUS2515185 A
Publication typeGrant
Publication dateJul 18, 1950
Filing dateFeb 25, 1943
Priority dateFeb 25, 1943
Publication numberUS 2515185 A, US 2515185A, US-A-2515185, US2515185 A, US2515185A
InventorsGeorge Bieber Clarence, Pierce Buck Mortimer
Original AssigneeInt Nickel Co
Export CitationBiBTeX, EndNote, RefMan
External Links: USPTO, USPTO Assignment, Espacenet
Age hardenable nickel alloy
US 2515185 A
Abstract  available in
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Claims  available in
Description  (OCR text may contain errors)

Patented July 18,

AGE HARDENABLE NICKEL ALLOY Clarence George Bieber and Mortimer Pierce Buck, Huntington, W. Va., assignors to The International Nickel Company, Inc., New York, N. Y., a corporation of Delaware No Drawing. Application February 25, 1948, Serial No. 477,142 e 4 Claiml (Cl. 75-170) The present invention relates to nickel alloys,

and. more particularly, to age hardenable nickel It is among the objects of our invention to produce nickel alloys capable of being hardened by heat treatment to any selected hardness over a broad hardness rangeptoprovide nickel alloys having maximum hardness in the aged condition commensurate with satisfactory forgeabllity and good machining properties; and to produce nickel alloyshaving a broad range of hot malleability combined with high mechanical properties in theage hardened condition.

Other objects and advantages of the present invention will become apparent from the following description of the-present invention Generally speaking, the present invention is based upon the surprising discovery made by us that nickel base alloys containing chromium, and optionally iron, having among other desirable properties an advantageous combination of hot malleability, good machining properties, good response to heat treatment,- and high hardness in the heat treated condition can be produced by incorporating aluminum with titanium or silicon,

z 35% while iron may vary from 0 to about 45%. The relative amounts of aluminum, silicon and titanium may vary over a range of several percent provided the ratio of nickel to the hardener content is maintained within the limits defined herein. Aluminum, and at least one of the elements of the group titanium and silicon must be present in the alloy in amounts greater than 0.25%. The third hardening element may be present in amounts more 'or less than 0.25%, the

, essential feature of this invention being that at least two of the hardening elements must be treatment can be obtained in chromium-containing nickel base, alloys by incorporating only one of the elements, aluminum, titanium or silicon in the alloy. but the amount necessary to produce maximum r sponse to heat treatment is relatively large and this is accompanied by working difllcultles. .We have made the surprising discovery that by, using at least two of the elements from the group aluminum, silicon and titanium, the response to heat-treatment witha smaller total amount of hardening elements is as satisfactory or even better than in alloys containing only one of these hardening elements in effective amounts, and the new alloys are characterized by greatly improved hot malleability as compared with alloys of otherwise substantially the same composition containing only one of the hardening elements.

The, nickel content of the alloys embodying the present. invention in all cases .will be at least 45% by weight of the alloy and usually will be 50% or substantially more than 50%. Chromium will be present within the range of about 5% to present in amounts greater than about 0.25%. Aluminum and silicon may be used in amounts up to about 8%, preferably not over 5% of either, while titanium should be less than'5% and preferably is employed in amounts less than 4%. Titanium exerts its greatest effect on age-hardenabilty within the range of about 0.25% to under 1%, in combination with proper amounts of aluminum and/or silicon.

We have discovered that the optimum combination of hot malleability, hardenability and high hardness in the heat-treated condition is obtained when the ratio of nickel to the weighted hardener content as obtained from the formula Weighted hardener content=Al+2 T i+Si Element Per cent Cr 10 -22 Fe 0.1 l5 AL. 0. 25- 5 TL. 0. 25- 4 Si 0.05- 2.0 C 0. 00- 0 6 Mn. 0. 00- 2. 0 Ni Balance The preferred ranges of the various ingredients are as follows:

7 For the purpose of giving those skilled in the art a better understanding of the present invention, the following specific examples are given of alloys that are typical of the preferred compositions:

Element Per cent I Per cent I Per cent Commercial alloys embodying the present invention may contain small amounts of other elements such as sulfur, copper, cobalt and phosphorus. The sulfur is preferably low, e. g., about 0.01%. The alloys may be substantially carbonfree or carbon may be present up to about 0.5%. Ordinarily the carbon will not exceed about 0.2% and preferably is maintained below about 0.1%. Ordinarily carbon will be present within the range of about 0.02 to 0.1%. Manganese ordinarily will not exceed about 2% and preferably will be within the range of about 0.1% to 0.5%.

The mechanical properties of the alloys embodying the present invention are substantially enhanced by age hardening and the alloys retain considerable strength even at the high temperature of about 1600 F. This property makes the alloys particularly suitable for fabricating metallic articles which are exposed in use to elevated temperatures under considerable stress.

The chromium-containing nickel alloys may be worked within the range of about 1900 F. to 2400 F., preferably within the range of about 2100 F. to 2300 F. This is a valuable novel result since the prior art had not been able to produce hot workable alloys of this type capable of being age hardened. It is surprising that the use cf the hardening elements in combination makes it possible to produce age hardenable chromium-containing nickel alloys capable of being hot worked over as broad a range as indicated.

The alloys of the present invention may be softened by quenching or rapidly cooling from above 1700 F. The alloys may be age hardened by the conventional hardening treatment comprising a solution heat treatment, a rapid cooling and a precipitation heat treatment; or they may be hardened by a controlledcooling following the solution heat treatment as disclosed in our prior application Serial No. 253,350, filed January 28, 1939, now Patent No. 2,234,955, dated March 18, 1941; or they may be heat treated in accordance with the process disclosed in our copending application Serial No. 483,760 filed April 20, 1943, now abandoned. The controlled cooling for alloys of the present invention preferably comprises holding them within the range of about 1200" to 1400 F. for a period varying from about ,5 hour to 16 hours, followed by slow cooling to a temperature within the range of I about 1100 F. to 1000 F. at a rate not exceeding about 75 F. per hour, and preferably not over about 25 F. per hour. m the softened condition the alloys may be deformed cold, and in this condition the alloys lend themselves readily to machining operations. Where hardnesses higher than those obtainable by precipitation hardening of hot-worked material are desired, the material may be worked cold either before or after the age-hardening treatment. In the hardened condition the alloys, as those skilled in the art will readily appreciate, are machinable with greater difliculty than in the annealed condition but, if necessary, machining can be performed by the use of carbide type tools.

It will be seen from the foregoing description and the specific examples that we have provided nickel alloys combining optimum response to heat-treatment with hot malleability. These alloys may be used for various articles of manufacture including rollers and bearing balls, bearings and races therefor, roller chains, drop i.org-- ings and tie rods for airplane construction, valve seats and other valve parts, pump rods and the like, pump rod sleeves, pump pistons for high pressui es and temperatures, plungers, turbine blades, turbine diaphragm blading, lock washers, screws and nuts, tools, cutting blades and the like, pins and needles, springs and other resilient elements, airplane instrument parts, nozzles for burners, rods, sheets, strip, wire, bars, rolled shapes, etc.

The present application is a, continuation-inpart of our prior copending application Serial No.

374,208 filed January 13, 1941, which itself is a continuation-in-part of our prior application Serial No. 253,350 filed January 28, 1939, which latter application issued on March 18, 1941, as Patent No. 2,234,955.

Although the present invention has been described in conjunction with preferred embodiments, it is understood that modifications and variations may be resorted to without departing from the spirit and scope of the invention, as those skilled in the art will readily understand.

We claim:

1. An alloy containing 11% to 15% chromium, 5% to 8% iron, 0.25% to 3.5% aluminum, at least 0.25% and under 1% titanium, 0.5% to 1% silicon, 0.02% to 0.2% carbon, 0.1% to 0.5% manganese and the balance substantially all nickel, the ratio of the nickel content to the sum of the alu minum content, the silicon content, and two times the square root of the titanium content being between 13 and 17.

2. An alloy containing 10% to 22% chromium, 0. to 15% iron, 0.25% to 5% aluminum, at least 0.25% and under 1% titanium, 0.05% to V 2% silicon, carbon in an amount not greater than der 1% titanium, 0.05% to 2% silicon, 10% to B) 22% chromium, 0.1% to 15% iron, manganese in an amount not exceeding 2%, carbon in an amount not exceeding 0.5%, and the balance substantially all nickel, the nickel content being over 50% o! the alloy, and the ratio of the nickel con- 1 1 6 tent to the sum of the aluminum content, the silicon content and two times the square root oi the titanium content being between 11 and 20.

CLARENCE GEORGE BIEBER. MORTIMER Pnmcn: BUCK.

REFERENCES CITED The following references are of record in the tile of this patent:

UNITED STATES PA'i'ENTs Number Name Date 1,587,992 Spitzley June 8, 1926 2,048,166 Piiling July 21, 1936 Pilling July 21, 1936

Patent Citations
Cited PatentFiling datePublication dateApplicantTitle
US1587992 *May 22, 1925Jun 8, 1926Alloys Foundry CompanyComposition of matter for alloys
US2048166 *Oct 1, 1931Jul 21, 1936Int Nickel CoCopper-nickel-titanium alloys
US2048167 *Apr 11, 1936Jul 21, 1936Int Nickel CoNickel-chromium-iron-titanium alloys
Referenced by
Citing PatentFiling datePublication dateApplicantTitle
US2664354 *Oct 12, 1950Dec 29, 1953Int Nickel CoValves for internal combustion engines
US2698633 *May 9, 1952Jan 4, 1955American Machine & MetalsEvacuated capsule for aneroid barometers
US2755183 *Jan 25, 1955Jul 17, 1956Coast Metals IncNickel-silicon-boron alloys
US2793950 *Jul 3, 1953May 28, 1957Union Carbide & Carbon CorpHeat-resistant nickel-base sheet alloy
US2873187 *Dec 7, 1956Feb 10, 1959Allegheny Ludlum SteelAustenitic alloys
US3713788 *Oct 21, 1970Jan 30, 1973Chromalloy American CorpPowder metallurgy sintered corrosion and heat-resistant, age hardenable nickel-chromium refractory carbide alloy
US4124381 *Aug 30, 1976Nov 7, 1978Sklar Steven DNon-precious dental casting alloy
US4629521 *Dec 10, 1984Dec 16, 1986Special Metals CorporationNickel base alloy
US6093369 *Aug 24, 1998Jul 25, 2000Hoskins Manufacturing CompanyModified nickel-chromium-aluminum-iron alloy
US6458318Jun 29, 2000Oct 1, 2002Sumitomo Metal Industries, Ltd.Heat resistant nickel base alloy
US7268474 *May 13, 2003Sep 11, 2007Robert Bosch GmbhAlloy, electrode with the alloy, and ignition device with the alloy
US8066938Jun 13, 2006Nov 29, 2011Haynes International, Inc.Ni-Cr-Co alloy for advanced gas turbine engines
US20030218411 *May 13, 2003Nov 27, 2003Klaus HrastnikAlloy, electrode with the alloy, and ignition device with the alloy
US20060051234 *Sep 3, 2004Mar 9, 2006Pike Lee M JrNi-Cr-Co alloy for advanced gas turbine engines
US20060222557 *Jun 13, 2006Oct 5, 2006Pike Lee M JrNi-Cr-Co alloy for advanced gas turbine engines
EP1065290A1 *Jun 27, 2000Jan 3, 2001Sumitomo Metal Industries, Ltd.Heat resistant nickel base alloy
WO2000011230A1 *Aug 11, 1999Mar 2, 2000Hoskins Mfg CoModified nickel-chromium-aluminum-iron alloy
Classifications
U.S. Classification420/446, 148/410, 420/452
International ClassificationC22C19/05
Cooperative ClassificationC22C19/058
European ClassificationC22C19/05R