US3301670A - Cast nickel-base alloy - Google Patents

Cast nickel-base alloy Download PDF

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Publication number
US3301670A
US3301670A US336458A US33645864A US3301670A US 3301670 A US3301670 A US 3301670A US 336458 A US336458 A US 336458A US 33645864 A US33645864 A US 33645864A US 3301670 A US3301670 A US 3301670A
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US
United States
Prior art keywords
nickel
alloy
cast
titanium
base alloy
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Lifetime
Application number
US336458A
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English (en)
Inventor
Clarence G Bieber
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
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Priority to BE658054D priority Critical patent/BE658054A/xx
Application filed by International Nickel Co Inc filed Critical International Nickel Co Inc
Priority to US336458A priority patent/US3301670A/en
Priority to GB288/65A priority patent/GB1019679A/en
Priority to FR1023A priority patent/FR1426415A/fr
Priority to ES0307887A priority patent/ES307887A1/es
Priority to DE19651483231 priority patent/DE1483231B2/de
Priority to AT4265A priority patent/AT247010B/de
Priority to CH27565A priority patent/CH432012A/fr
Priority to NL6500236A priority patent/NL6500236A/xx
Application granted granted Critical
Publication of US3301670A publication Critical patent/US3301670A/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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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
    • 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

  • Theaforementioned alloy produced under specification AMS 5391 has a life to rupture at 1800 F. and 29,000 p.s.i. of only about 10 hours.
  • the aforementioned alloy possesses original ductility for long periods of time. In this connection, it can be pointed out that the expected time in of 2,500 hours.
  • a new alloy composition for use in cast'aircraft gas turbine blades and for other high temperature service has now been discovered which has improved stress rupture life together with excellent castability, good resistance to oxidation and sulfidation, and improved structural stability when exposed to the deleterious effects of temperature and stress for extended periods of time.
  • a further object of the invention is to provide a new cast nickel-base alloy having high stress rupture properties together with excellent structural stability.
  • the present invention comprises a nickelbase alloy having high stress rupture properties and improved structural stability when produced in the vacuum melted and vacuum cast form which contains about 4% to about 11% chromium, about 0.5% to 3% columbium, about 0.5% to 4% tantalum, about 2% to 6% molybdenum, about 0.5 to 4% tungsten, about 5% to 8% aluminum, upto about 1.25% titanium, up to about 0.18%
  • - talum about 3%to about-5% molybdenum,--about 1% to about 3% tungsten, about 6% to about 7% aluminum, up to about 1.1% titanium, up to about 0.15% carbon, with the titanium content and the carbon content being so related that when the carbon content does not exceed about 0.1% the titanium content does not exceed about 0.6%, about 0.005% to 0.02% boron, about 0.05% to 0.15% zirconium, and the balance essentially nickel.
  • alloys provided in accordance with the invention be produced using the purest materials commensurate with reasonable cost.
  • subversive impurities such as lead, bismuth, telluriurn, sulfur, oxygen, nitrogen, hydrogen, arsenic, antimony, tin
  • Cobalt and iron may be present in impurity amounts, e.g., up to about 1% of each, as these elements decrease the ability of the alloy to resist microstructural changes after long exposure to elevated temperature. Silicon and mangagese are detrishould not exceed about 4% as otherwise the density of the alloy is appreciably increased with deleterious effects on the strength-weight ratio. In dynamic machinery such as a gas turbine, this factor is quite important. Castings produced from the alloy No. 4 composition were subjected mental elements and should not be present in amounts ex- 5 to oxidation tests and sulfidation tests. Oxidation tests ceeding about 0.1% of each.
  • the compositions set forth hereinbefore are maintained at 1900 F., and to a cooling for 8 hours.
  • the weight loss for the alloy of bination of strength properties and other properties char- 10 the invention was only 0.005%.
  • the sulfidation test comacterizing the same as it is found that if any of the eleprised exposure to a molten mixture of 90% sodium sul ments is employed in greater or lesser amounts than those fate and 10% sodium chloride for one hour at 1700 F. specified, the properties of the alloy are detrimentally No weight loss resulted. effected.
  • the foregoing alloys were produced by vacuum melting any condition of load or temperature within the ambit and vacuum casting into various forms, including cast-to- 90 of the chart depicted. size test bars having gage sections about 0.250 inch in 0 Castings produced from the alloy provided in accorddiameter and about one inch long.
  • the stress rupture ance with the invention may be employed not only in properties of the castings in the as-cast condition were aircraft and automotive gas turbine blades but also in determined under a number of conditions with the folextrusion dies, hot forging dies, and turbine rotors.
  • castings so produced may vary widely in section up to TABLE H about 12 inches in diameter and good properties such as illustrated hereinbefore are obtained even in such Tempera- Life to Elongation, heavy Section Castings- Y N0 f .P- 3511151116, Percent Castings may be produced from the alloy provided ours in accordance with the invention by a process comprising investment casting, static casting, etc. 1 i288 231888 331 3:? Although the present invention has been described in 2 1 igconjunction with preferred embodiments, it is to be 11650 301000 5g() 1.; understood that modifications and variations may be 1 588 338% 2g?
  • the denaluminum, p to about titanium, p 0 about sity of the alloy is about 0.290 pound per cubic inch (8.04 0.15% carbon, with the titanium content and the cargrams per cubic centimeter).
  • the tungsten content of the alloy tent does not exceed about 0.1% the titanium content 5 does not exceed about 06%, about 0.005% to 0.02% boron, about 0.05%, to 0.15% zirconium, and the balance essentially nickel.
  • a nickel-base alloy having a high combination of mechanical properties together with structural stability when subjected to the combined efiects of temperature and stress for extended time periods in cast form and consisting essentially of about 10% chromium, about 4% molybdenum, about 2% tungsten, about 1% co1um bium, about 2% tantalum, about 6.5% aluminum, about 1% titanium, about 0.15 carbon, about 0.02% boron,

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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)
  • Mold Materials And Core Materials (AREA)
  • Extrusion Moulding Of Plastics Or The Like (AREA)
US336458A 1964-01-08 1964-01-08 Cast nickel-base alloy Expired - Lifetime US3301670A (en)

Priority Applications (9)

Application Number Priority Date Filing Date Title
BE658054D BE658054A (is") 1964-01-08
US336458A US3301670A (en) 1964-01-08 1964-01-08 Cast nickel-base alloy
GB288/65A GB1019679A (en) 1964-01-08 1965-01-04 Nickel alloys
FR1023A FR1426415A (fr) 1964-01-08 1965-01-06 Alliages de nickel
ES0307887A ES307887A1 (es) 1964-01-08 1965-01-07 Mejoras introducidas en la fabricacion de aleaciones de fundicion.
DE19651483231 DE1483231B2 (de) 1964-01-08 1965-01-07 Verwendung einer nickel-chrom-legierung
AT4265A AT247010B (de) 1964-01-08 1965-01-07 Nickellegierung und Verfahren zu ihrer Herstellung
CH27565A CH432012A (fr) 1964-01-08 1965-01-08 Alliage de nickel
NL6500236A NL6500236A (is") 1964-01-08 1965-01-08

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US336458A US3301670A (en) 1964-01-08 1964-01-08 Cast nickel-base alloy

Publications (1)

Publication Number Publication Date
US3301670A true US3301670A (en) 1967-01-31

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Family Applications (1)

Application Number Title Priority Date Filing Date
US336458A Expired - Lifetime US3301670A (en) 1964-01-08 1964-01-08 Cast nickel-base alloy

Country Status (8)

Country Link
US (1) US3301670A (is")
AT (1) AT247010B (is")
BE (1) BE658054A (is")
CH (1) CH432012A (is")
DE (1) DE1483231B2 (is")
ES (1) ES307887A1 (is")
GB (1) GB1019679A (is")
NL (1) NL6500236A (is")

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3389992A (en) * 1964-10-20 1968-06-25 Int Nickel Co Nickel-base alloy for use at elevated temperature
US3459545A (en) * 1967-02-20 1969-08-05 Int Nickel Co Cast nickel-base alloy

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS57207145A (en) * 1981-06-15 1982-12-18 Toshiba Corp Wear resistant alloy
JP3294029B2 (ja) * 1994-11-16 2002-06-17 財団法人電気磁気材料研究所 耐摩耗性高透磁率合金およびその製造法ならびに磁気記録再生ヘッド

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2920956A (en) * 1956-10-08 1960-01-12 Universal Cyclops Steel Corp Method of preparing high temperature alloys
US3085005A (en) * 1958-01-16 1963-04-09 Fansteel Metallurgical Corp Alloys
US3228095A (en) * 1960-04-13 1966-01-11 Rolls Royce Method of making turbine blades

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2920956A (en) * 1956-10-08 1960-01-12 Universal Cyclops Steel Corp Method of preparing high temperature alloys
US3085005A (en) * 1958-01-16 1963-04-09 Fansteel Metallurgical Corp Alloys
US3228095A (en) * 1960-04-13 1966-01-11 Rolls Royce Method of making turbine blades

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3389992A (en) * 1964-10-20 1968-06-25 Int Nickel Co Nickel-base alloy for use at elevated temperature
US3459545A (en) * 1967-02-20 1969-08-05 Int Nickel Co Cast nickel-base alloy

Also Published As

Publication number Publication date
GB1019679A (en) 1966-02-09
BE658054A (is")
AT247010B (de) 1966-05-25
NL6500236A (is") 1965-07-09
DE1483231A1 (de) 1969-01-30
CH432012A (fr) 1967-03-15
ES307887A1 (es) 1965-05-01
DE1483231B2 (de) 1973-04-05

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