US3376132A - Impact resistant nickel-chromium alloys - Google Patents

Impact resistant nickel-chromium alloys Download PDF

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Publication number
US3376132A
US3376132A US452366A US45236665A US3376132A US 3376132 A US3376132 A US 3376132A US 452366 A US452366 A US 452366A US 45236665 A US45236665 A US 45236665A US 3376132 A US3376132 A US 3376132A
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United States
Prior art keywords
alloys
alloy
stress
chromium
carbon
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Expired - Lifetime
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US452366A
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English (en)
Inventor
Shaw Stuart Walter Ker
Cook Reginald Massey
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
Original Assignee
International Nickel Co Inc
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Publication date
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Publication of US3376132A publication Critical patent/US3376132A/en
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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

Definitions

  • the present invention relates to nickle-base alloys and, more particularly, to cast nickel-chromium base alloys having improved impact resistance characteristics together with good stress-rupture properties at elevated temperatures.
  • 3,166,413 we have described various alloys having a highly satisfactory combination of stressrupture properties and high temperature ductility, the alloys containing the following constituents within the given ranges: about 5% to chromium, about 7% to 16% tungsten, up to about 5% molybdenum, up to about 4% columbium (niobium) with the sum of the percentages of tungsten, molybdenum and columbium plus two-thirds the percentage of chromium being about 17.5% to 20.5%, about 2% to 8% aluminum, about 0.03% to 0.3% carbon, up to 1% zirconium, up to 0.05% boron, up to 3% total of iron, manganese and silicon (principal impurities), up to 1% cobalt, the balance of the alloys-being essentially nickel and impurities.
  • Another object of the invention is to provide a novel, nickel-base alloy characterized by a high degree of resistance to impact at elevated temperature.
  • the invention also contemplates providing novel cast nickel-base alloys which afford a good level of impact resistance and other mechanical properties at high temperatures, e.g., 850 C. and above.
  • the carbon content of the above-described alloys is controlled such that it is less than 0.03%, e.g., 0.001% to 0.02'/5%.
  • the carbon content is preferably as low as possible, e.g., less than 0.02% or even less than 0.01%, though a trace of carbon will inevitably be present.
  • the chromium content should not exceed 9% and, advantageously, is present in an amount of from 5% to 7%.
  • the stress-rupture life also depends on the total content of tungsten, molybdenum and columbium and at a given chromium content there is an optimum value of this total at which the longest lives are obtained.
  • both molybdenum and columbium are present in the alloys in amounts not exceeding 4% and 2.5%, respectively, and the tungsten content is from 9% to 14%.
  • the aluminum content of the alloys is important and in alloys of any given base composition variation of aluminum content has a marked effect on stress-rupture life.
  • the longest life is obtained with aluminum contents in a range of 5% to 7% and alloys with aluminum contents within this range are therefore particularly suitable for gas turbine rotor blades which require the best possible stress-rupture properties.
  • the alloys have higher melting points and alloys with from 5% down to 3.5% or even 2% aluminum are suitable for parts such as gas turbine stator blades which require a high melting point but are less highly stressed than rotor blades.
  • the alloys are advantageously subjected to a vacuum refining treatment comprising holding them in the molten state under high vacuum before casting the melt.
  • a vacuum refining treatment comprising holding them in the molten state under high vacuum before casting the melt.
  • the alloys are preferably cast under vacuum but when making large castings from a melt that has been produced or refined under vacuum, it makes little difference to the properties obtained whether casting is carried out in vacuum, inert gas or air.
  • the alloys according to the invention are particularly zirconium. suitable for making cast rotor blades for gas turbine en- While carbon exerts a remarkable influence regarding gines.
  • Articles and parts cast from the alloys may be used the resistance to impact of the alloys of the invention, it in the as-cast condition for high temperature service. If does not necessarily at all follow that this influence manidesired, the alloys may be homogenized by heating in the tests itself regarding other nickel-chromium base alloys, temperature range 850 C to 125 C. before being put even those of compositions which might be considered into service.
  • All alloys nominally contained 0.015% boron, balance nickel. Alloys Nos. 3 and 4 are of the same composition except for the carbon content. The same applies to Alloys Nos. 5 and 6 but it is to be observed that the alloys of low carbon (Nos. 4 and 6) did not afford any appreciable improvement in impact resistance. The low carbon 0! Alloy No. 4 drastieally adversely affected the stress-rupture life.
  • the alloys contain at least 0.01% and up to 1% zirconium and at least 0.003% and up to 0.075% or 0.08% boron.
  • the alloys contain about 0.05 to 0.7% zirconium and about 0.01% to 0.05% boron, and it is further preferred that the amounts of zirconium and boron be correlated such that the value of the expression:
  • tective coating for example, of aluminum.
  • titanium is an undesirable impurity and should not be made from the alloys are preferably provided with a pro- Although the present invention has been described in e present in an amount exceeding 0.5% and, advantageously, it is less than 0.25
  • An alloy characterized by a combination of good impact resistance and stress-rupture life at elevated temperatures consisting essentially of about 5% to 10% chromium, about 7% to 16% tungsten, up to about 5% molybdenum, up to about 4% columbium with the sum of the percentages of tungsten, molybdenum and columbium plus two-thirds the percentage of chromium being about 17.5% to 20.5%, about 2% to 8% aluminum, carbon in an amount up to less than 003%, about 0.01% to 1% zirconium, about 0.003% to 0.08% boron and the balance being essentially nickel.
  • a cast alloy characterized by a combination of good impact resistance and stress-rupture life at elevated temperatures, said alloy consisting essentially of about 6% chromium, about 11% tungsten, about 2% molybdenum, about 1.5% columbium, about 6% aluminum, about 0.004% carbon, about 0.25% zirconium, about 0.02%
  • a cast nickel-chromium-base alloy characterized by a combination of good impact resistance and stress-rupture life at elevated temperatures, said alloy being suitable for use in turbine structures and characterized by good impact resistance and stress-rupture properties at relatively high stress and elevated temperatures, said alloy consisting essentially of about 5% to 10% chromium, about 7% to 16% tungsten, up to about 5% molybdenum, up to about 4% columbium, the sum of the percentages of tungsten, molybdenum and columbium and two-thirds the percentage of chromium being about 17.5% to 20.5%, about 2% to 8% aluminum, about 0.001% to 0.0275% carbon, about 0.05% to about 0.7% zirconium, about 0.01% to about 0.05% boron up to not more than 0.5% titanium, up to not more than 1% cobalt, and the balance essentially nickel.
  • a cast alloy in accordance with claim 3 containing about 5% to 7% aluminum, about 0.001% to 0.02% carbon, about 5% to 9% chromium, about 9% to 14% tungsten, up to 4% molybdenum and up to 4% columbium.

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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)
  • Powder Metallurgy (AREA)
  • Treatment Of Steel In Its Molten State (AREA)
US452366A 1964-05-05 1965-04-30 Impact resistant nickel-chromium alloys Expired - Lifetime US3376132A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB18647/64A GB1033715A (en) 1964-05-05 1964-05-05 Nickel-chromium alloys

Publications (1)

Publication Number Publication Date
US3376132A true US3376132A (en) 1968-04-02

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US452366A Expired - Lifetime US3376132A (en) 1964-05-05 1965-04-30 Impact resistant nickel-chromium alloys

Country Status (4)

Country Link
US (1) US3376132A (fr)
CH (1) CH448541A (fr)
DE (1) DE1483235A1 (fr)
GB (1) GB1033715A (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4530727A (en) * 1982-02-24 1985-07-23 The United States Of America As Represented By The Department Of Energy Method for fabricating wrought components for high-temperature gas-cooled reactors and product

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3160500A (en) * 1962-01-24 1964-12-08 Int Nickel Co Matrix-stiffened alloy
US3166413A (en) * 1962-02-07 1965-01-19 Int Nickel Co Tungsten-containing nickel-chromium alloys
US3166412A (en) * 1962-08-31 1965-01-19 Int Nickel Co Cast nickel-base alloy for gas turbine rotors

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3160500A (en) * 1962-01-24 1964-12-08 Int Nickel Co Matrix-stiffened alloy
US3166413A (en) * 1962-02-07 1965-01-19 Int Nickel Co Tungsten-containing nickel-chromium alloys
US3166412A (en) * 1962-08-31 1965-01-19 Int Nickel Co Cast nickel-base alloy for gas turbine rotors

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4530727A (en) * 1982-02-24 1985-07-23 The United States Of America As Represented By The Department Of Energy Method for fabricating wrought components for high-temperature gas-cooled reactors and product

Also Published As

Publication number Publication date
CH448541A (fr) 1967-12-15
DE1483235A1 (de) 1969-03-20
GB1033715A (en) 1966-06-22

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