US3107999A - Creep-resistant nickel-chromiumcobalt alloy - Google Patents

Creep-resistant nickel-chromiumcobalt alloy Download PDF

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Publication number
US3107999A
US3107999A US66440A US6644060A US3107999A US 3107999 A US3107999 A US 3107999A US 66440 A US66440 A US 66440A US 6644060 A US6644060 A US 6644060A US 3107999 A US3107999 A US 3107999A
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United States
Prior art keywords
alloys
creep
alloy
vacuum
chromiumcobalt
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Expired - Lifetime
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US66440A
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English (en)
Inventor
Gittus Jolm Henry
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Huntington Alloys Corp
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International Nickel Co Inc
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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
    • C22C19/056—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 relates to alloys resistant to the deleterious effects of high stress and high temperatures and, more particularly, to heat-resistant, nickelchromium-cobali alloys.
  • gas turbine blades and other articles and parts that are required to be resistant to creep when subjected to stress at elevated temperatures are commonly made of alloys in which the principal constituent is nickel or nickel plus cobalt and which also contain chromium, aluminum and titanium, these last two elements forming a precipitable phase with some of the nickel.
  • Other elements, for example, molybdenum and tungsten, can also be present with beneficial effects on the creep resistance and it has also been found that melting the alloys under vacuum may further improve the properties.
  • Another object of the invention is to provide a novel process for producing a novel, hot-workable alloy.
  • the present invention contemplates hot-workable alloys having particularly good creep resistance which contain about 3% to about 7% cobalt, about 13% to about 17% chromium, about 3% to about 7% molybdenum, about 0.10% to about 0.2% carbon and also titanium and aluminum in such amounts that the Ti/Al ratio is from 0.1 to 3.0 and the total content of 'titanium and aluminum (i.e., Ti plus Al) is given by the formula:
  • the invention is based on the discovery that in alloys containing cobalt, chromium and molybdenum which have been vacuum melted or treated by holding in the molten state under vacuum, the creep resistance depends not only on the basic composition of the alloys but also both on the ratio of the content of titanium (Ti) to that of aluminum (Al) and on the total content of titanium 3,107,990 Patented Oct. 22., 1953 series of alloys having a given Ti/Al ratio, the life-to rupture under given conditions of stress and temperature passes through a maximum as the Ti plus Al content is increased; and the Ti plus Al content at which this maximum occurs increases as the Ti/Al ratio is increased. Accordingly, for the highest creep resistance, the Ti/Al ratio must be correlated with the Ti plus Al content.
  • Correlation of the Ti/Al ratio with the Ti plus Al content according to the formula ensures that the life-torupture lies at or near the maximum value obtainable for the particular ratio or content used.
  • the maximum life-to-rupture also increases and advantageously, therefore, the Ti/Al ratio is at least 1.5.
  • the upper limit of 3.0 is imposed by the increasing difficulty of working the alloys as the total amount of titanium and muminum present also increases.
  • the vacuum melting or vacuum treatment of th alloys is carried out at a pressure not exceeding 100 micron of mercury, advantageously, at five microns of mercury or less.
  • the molten alloy is subjected to such a pressure for at least five minutes and, advantageously, for at least ten minutes at a temperature of 1400 C.-1600C.
  • the alloys are first vacuum melted and then held under vacuum before casting, but the invention also includes alloys which have been melted in air and then held under vacuum in the molten state. Once the alloys have been vacuum melted or maintained in the molten state under vacuum or both, it makes little difference to their properties whether they are cast in vacuum or in air.
  • Ingots cast from the vacuum-treated metal can be hot worked to produce bar, and to develop their creep-resistin-g properties the alloys are subjected to a precipitationhardening treatment consisting of solution heating at a temperature in the range 1l50 C. to 1250 C., followed by ageing at a temperature in the range 700 C. to 1100 C.
  • the solution temperature should be as high as possible, the limit being set by the desirability of avoiding excessive grain-growth.
  • the ageing temperature should be higher than the anticipated service temperature of components made from the bar.
  • the present invention is particularly applicable to alloys and the production of alloys having an optimum combination of hot workability, heat resistance and resistance to stress for use as components in gas turbine structures such as turbine blades, stator blades, guide vanes, etc.
  • the alloys of the present invention can be employed as bolts, fastenings, etc., in structures subject to the deleterious action of high temperature and high stress.
  • a vacuum treated alloy for structural members subjected in use to a combination of high stress and high temperature consisting essentially of about 5% cobalt, about 1 15% chromium, about 5% molybdenum, about 0.15% carbon, about 0.05% zirconium, about 0.01% boron, about 0.3%silic0n and aluminum and titanium in a ratio of titanium to aluminum of 0.1 to 3.0 and a total per:

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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)
US66440A 1959-11-04 1960-11-01 Creep-resistant nickel-chromiumcobalt alloy Expired - Lifetime US3107999A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB37434/59A GB887746A (en) 1959-11-04 1959-11-04 Creep-resistant nickel-base alloys

Publications (1)

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US3107999A true US3107999A (en) 1963-10-22

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US66440A Expired - Lifetime US3107999A (en) 1959-11-04 1960-11-01 Creep-resistant nickel-chromiumcobalt alloy

Country Status (5)

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US (1) US3107999A (fr)
BE (1) BE596719A (fr)
CH (1) CH405723A (fr)
DE (1) DE1433117A1 (fr)
GB (1) GB887746A (fr)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3148054A (en) * 1959-06-08 1964-09-08 Int Nickel Co Casting alloy
US3228095A (en) * 1960-04-13 1966-01-11 Rolls Royce Method of making turbine blades
US3232751A (en) * 1962-01-26 1966-02-01 Int Nickel Co Nickel-chromium-cobalt alloys
US3648832A (en) * 1970-08-21 1972-03-14 David Kirshenbaum Card carrying case

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CA548778A (fr) * 1957-11-12 The International Nickel Company Of Canada Alliage a base de nickel resistant a la chaleur

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CA548778A (fr) * 1957-11-12 The International Nickel Company Of Canada Alliage a base de nickel resistant a la chaleur

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3148054A (en) * 1959-06-08 1964-09-08 Int Nickel Co Casting alloy
US3228095A (en) * 1960-04-13 1966-01-11 Rolls Royce Method of making turbine blades
US3232751A (en) * 1962-01-26 1966-02-01 Int Nickel Co Nickel-chromium-cobalt alloys
US3648832A (en) * 1970-08-21 1972-03-14 David Kirshenbaum Card carrying case

Also Published As

Publication number Publication date
DE1433117A1 (de) 1968-10-17
GB887746A (en) 1962-01-24
CH405723A (fr) 1966-01-15
BE596719A (fr) 1961-05-03

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