US3166412A - Cast nickel-base alloy for gas turbine rotors - Google Patents

Cast nickel-base alloy for gas turbine rotors Download PDF

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Publication number
US3166412A
US3166412A US220857A US22085762A US3166412A US 3166412 A US3166412 A US 3166412A US 220857 A US220857 A US 220857A US 22085762 A US22085762 A US 22085762A US 3166412 A US3166412 A US 3166412A
Authority
US
United States
Prior art keywords
alloy
cast
nickel
base alloy
gas turbine
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
US220857A
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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
Application filed by International Nickel Co Inc filed Critical International Nickel Co Inc
Priority to US220857A priority Critical patent/US3166412A/en
Priority to GB33116/63A priority patent/GB968495A/en
Priority to AT690963A priority patent/AT241133B/de
Priority to ES291188A priority patent/ES291188A1/es
Priority to SE9421/63A priority patent/SE307018B/xx
Priority to CH1065763A priority patent/CH420635A/fr
Priority to FR946059A priority patent/FR1367387A/fr
Priority to DEJ24337A priority patent/DE1219236B/de
Priority to BE636847D priority patent/BE636847A/fr
Priority to NL297339D priority patent/NL297339A/nl
Priority to LU44364D priority patent/LU44364A1/xx
Application granted granted Critical
Publication of US3166412A publication Critical patent/US3166412A/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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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
    • 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 provides cast nickel alloys containing, in percent by weight, not more than about 0.05% or 0.06% carbon, e.g., about 0.03% carbon, about to about 18% chromium, about 5% to about 7% aluminum, up to about 1.5% titanium, e.g., 0.5% to about 1.5% titanium, about 1% to about 3% columbium, about 0.5% to about 6% molybdenum, with the chromium plus molybdenum contents being about to about 20% of the alloy, up to about 0.05%
  • chromium advantageously is maintm'ned in the range of 10% to 14%.
  • the total content of chromium and molybdenum in the alloy is import-ant and must be maintained in the range of 15% to 20% in order to provide the best combination that which exists in Thus, it is no longer It has accordinglybeen pro- .of corrosion resistance, strength, and ductility at elevated temperatures.
  • Aluminum ⁇ is an important hardening and strengthening element in the alloy and is maintained in the range of 5% to ⁇ 7% because strength is ⁇ sacriticed if the concentration of this element is too low while the ductility is lowered if the concentration is above 7%.
  • Titanium when present even in amounts of about 0.5%, contributes further hardening and strengthening to the alloy but should not exceed about 1.5% of the alloy because ductility and castability are reduced if the titanium content is higher than this value.
  • Columbium also plays an important part in strengthening thealloy and is' employed in amounts of 1% to 3% because strength is sacrificed if Vthe concentration of this element is below 1%l while the ductility is reduced if the concentration is above'3r%; Boron and zirconium present in the alloy contribute-markedly to the development of satisfactory lem is crea-tedisince it is necessary to provide within a Y single unitary casting metallurgical structures'which will operate under vastly diiferent conditions of stress and temperature.
  • the invention also contemplates providing gas turbinev are unsatisfactoryas OnV the other hand, it has been found' strength and ductility properties therein.
  • the presence of fas little as 0.005% boron and at least about ⁇ ,0.02% zirconium provide good ductility- ⁇ at temperatures" ab'oveabout1000jo to 1200 F.
  • Calcium in thealloy is employedin air melting to serve as a deoxidizer. It is omitted in vacuum melting..
  • VIt is to be understood that ,carbon inthe ⁇ alloymust be Vmaintained at very low vales not exceeding 0.06% in order that the alloys will exhibit the required high elongation inthe as-cast condition at room temperature even in sections as heavy as three inches thick or more. Small carbon contents of about 0.03% arebeneiicial in producing the master alloy Vwhich is tobe remeltfed to make the finished castings.
  • the alloy provided in accordance with the invention may also contain up toV 15% ⁇ cobalt, e.g., about V10% cobalt, assuch amounts of cobalt permit the inclusion in the alloy of as much as about 8% of aluminum without encounterling serious embrittling effects; vTungsten may be employed in ⁇ placebf apart or all of the molybdenum in the Aalloy.
  • the alloy should be as devoid as practicable of impurities such as sulfur, phosphorus, lead, antimony, tin, selenium, tellurium, bismuth, etc. Elements such as silicon and 'manganese are undesirable and should not be present in amounts exceeding about 0.2% and 0.1%, respectively. 'Iron is also an undesirable element in the alloy ⁇ land should not be present in amounts exceeding about 0.5%, e.g., about 0.25%.
  • the balance of the alloy is essentially nickel.
  • the alloy provided in accordance with the invention is characterized by a room temperature'tensile strength -in the as-cast condition of at least about 100,000 p.s.i. and anelongation of at least about 10% in .the Ias-cast condition.
  • the alloy provides relatively long service life at temperatures on the order of about 1700 ⁇ F. to
  • The'following tables contain, respectively, the chemical :ompositions, in percent by Weight, of vacuum melted and vacuum cast alloys produced in accordance with the invention, the rupture lives of the alloys at 17.00 F. and 30,000 p.s.i. in the as-cast condition, and the room ternperature tensile properties of these alloys in the ⁇ as-cast j conditionz- Table I Alloy Perler- Per- Per- Per- Per- Per- Per- 'Per- Per- No. cent (eut cent cent ycent cent cent cent cent cent Cr Mo Cb A1 Ti C Zr Ni L v ,12 5 2 6 0.6 0.008 0.01 0.10 .Bal Z 12 5 2' 6 0.6 0.05 0.01 0.10 Bal.
  • v f Y 1 A casting having atleast oneincluded section subjectedin use to high stressat temperatures on the order of Vabout 17009 F. and at least one included section subjected in use to high stress at temperatures on the order of about 1000* F., made of'anv alloy consisting' essentially of vabout0.008% ⁇ to 0.05%fcarbo'n, aboutv 12% chromium, about '5% molybdenum, Vabout 6% aluminum, .about 0.6% titanium, -about 2%, columbiurn, ⁇ about 0.01%
  • i' f fAlloys in accorda ncewith the invention have particulalrly satisfactory properties when produced byr vacuum Y melting'. They may, however, be melted under argon or even under air'atmospheres with goodcastability and j. f
  • the strength of the alloy at room temperature and atl i elevated temperatures may be improved by subjectingithe castings ,to a heat treatment comprising a heating at about j 215011?. for about 15 minutes to about'24'hours, e.g., about two hours, followed by acooling to roomtemperature. fjlffde'sired', a further stabilization treatment consisting of a heating at about 1700o F. for about one to about 24 hours, -ie.g.,about fourV hours, kmay also be employed. .in casting thefalloy, it is important to superheat the, melt 'topa temperature of, at least 300 F., butk more-advantageously at least about 400 F; or 500 F.,
  • a pouring temperaturehvof about 2950 F. Y.
  • a nickel-base al loy containing ⁇ not morey than about 0.06% carbon, about '10%.to 18% chromium, Vabout 0.5% to 6%V of a metal from the group consisting of molybdenum and tungsten andwith the total contents of chromium, molybdenum andtung'sten being about 15 to about 20%, about 5% to 8% aluminum, up to about 15% cobalt with the proviso that Wheri'theicobalt content isv lessthanvabout 10% ⁇ the aluminum content is about 5% to,7%, up to about 1.5% titanium, about 1% to 3% columbiurm about 0.01% boron,V up ,toV about 0.15%

Landscapes

  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Moulds For Moulding Plastics Or The Like (AREA)
US220857A 1962-08-31 1962-08-31 Cast nickel-base alloy for gas turbine rotors Expired - Lifetime US3166412A (en)

Priority Applications (11)

Application Number Priority Date Filing Date Title
US220857A US3166412A (en) 1962-08-31 1962-08-31 Cast nickel-base alloy for gas turbine rotors
GB33116/63A GB968495A (en) 1962-08-31 1963-08-21 Nickel alloys
ES291188A ES291188A1 (es) 1962-08-31 1963-08-28 Un método de hacer una pieza colada
AT690963A AT241133B (de) 1962-08-31 1963-08-28 Verfahren zur Herstellung eines Gußstückes
CH1065763A CH420635A (fr) 1962-08-31 1963-08-29 Procédé de fabrication d'un moulage en alliage de nickel
FR946059A FR1367387A (fr) 1962-08-31 1963-08-29 Alliages au nickel
SE9421/63A SE307018B (en:Method) 1962-08-31 1963-08-29
DEJ24337A DE1219236B (de) 1962-08-31 1963-08-29 Verfahren zur Herstellen von Gussstuecken, insbesondere von Gasturbinenlaeufern mit an die Nabe angegossenen Schaufeln, aus einer Nickel-Chrom-Legierung
BE636847D BE636847A (en:Method) 1962-08-31 1963-08-30
NL297339D NL297339A (en:Method) 1962-08-31 1963-08-30
LU44364D LU44364A1 (en:Method) 1962-08-31 1963-08-31

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US220857A US3166412A (en) 1962-08-31 1962-08-31 Cast nickel-base alloy for gas turbine rotors

Publications (1)

Publication Number Publication Date
US3166412A true US3166412A (en) 1965-01-19

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Family Applications (1)

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US220857A Expired - Lifetime US3166412A (en) 1962-08-31 1962-08-31 Cast nickel-base alloy for gas turbine rotors

Country Status (11)

Country Link
US (1) US3166412A (en:Method)
AT (1) AT241133B (en:Method)
BE (1) BE636847A (en:Method)
CH (1) CH420635A (en:Method)
DE (1) DE1219236B (en:Method)
ES (1) ES291188A1 (en:Method)
FR (1) FR1367387A (en:Method)
GB (1) GB968495A (en:Method)
LU (1) LU44364A1 (en:Method)
NL (1) NL297339A (en:Method)
SE (1) SE307018B (en:Method)

Cited By (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3310440A (en) * 1964-10-21 1967-03-21 United Aircraft Corp Heat treatment of nickel base alloys
US3343950A (en) * 1963-12-23 1967-09-26 Int Nickel Co Nickel-chromium alloys useful in the production of wrought articles for high temperature application
US3376132A (en) * 1964-05-05 1968-04-02 Int Nickel Co Impact resistant nickel-chromium alloys
US3403059A (en) * 1965-06-24 1968-09-24 Gen Electric Nickel base alloy
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
JPS62167835A (ja) * 1985-11-26 1987-07-24 ユナイテツド・テクノロジ−ズ・コ−ポレイシヨン Ｗａｓｐａｌｏｙ成形品の製造方法
US4685977A (en) * 1984-12-03 1987-08-11 General Electric Company Fatigue-resistant nickel-base superalloys and method
DE4412031A1 (de) * 1993-04-07 1994-10-13 Aluminum Co Of America Verfahren zur Herstellung von Schmiedeteilen aus Nickellegierungen
US5374323A (en) * 1991-08-26 1994-12-20 Aluminum Company Of America Nickel base alloy forged parts
US5540789A (en) * 1992-05-28 1996-07-30 United Technologies Corporation Oxidation resistant single crystal superalloy castings
US6284392B1 (en) 1999-08-11 2001-09-04 Siemens Westinghouse Power Corporation Superalloys with improved weldability for high temperature applications
US6974508B1 (en) 2002-10-29 2005-12-13 The United States Of America As Represented By The United States National Aeronautics And Space Administration Nickel base superalloy turbine disk
WO2018069666A1 (en) 2016-10-12 2018-04-19 Oxford University Innovation Limited A nickel-based alloy

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB733489A (en) * 1952-07-09 1955-07-13 Mond Nickel Co Ltd Improvements relating to nickel-chromium-cobalt alloys
CA548777A (en) * 1957-11-12 G. Bieber Clarence Nickel-base heat-resistant alloy
US2912323A (en) * 1957-09-16 1959-11-10 Int Nickel Co Cast nickel base alloy for high temperature service
US2975051A (en) * 1959-09-29 1961-03-14 Gen Electric Nickel base alloy
US3005704A (en) * 1958-07-23 1961-10-24 Union Carbide Corp Nickel base alloy for service at high temperatures

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CA548777A (en) * 1957-11-12 G. Bieber Clarence Nickel-base heat-resistant alloy
GB733489A (en) * 1952-07-09 1955-07-13 Mond Nickel Co Ltd Improvements relating to nickel-chromium-cobalt alloys
US2912323A (en) * 1957-09-16 1959-11-10 Int Nickel Co Cast nickel base alloy for high temperature service
US3005704A (en) * 1958-07-23 1961-10-24 Union Carbide Corp Nickel base alloy for service at high temperatures
US2975051A (en) * 1959-09-29 1961-03-14 Gen Electric Nickel base alloy

Cited By (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3343950A (en) * 1963-12-23 1967-09-26 Int Nickel Co Nickel-chromium alloys useful in the production of wrought articles for high temperature application
US3376132A (en) * 1964-05-05 1968-04-02 Int Nickel Co Impact resistant nickel-chromium alloys
US3310440A (en) * 1964-10-21 1967-03-21 United Aircraft Corp Heat treatment of nickel base alloys
US3403059A (en) * 1965-06-24 1968-09-24 Gen Electric Nickel base alloy
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
US4685977A (en) * 1984-12-03 1987-08-11 General Electric Company Fatigue-resistant nickel-base superalloys and method
JPS62167835A (ja) * 1985-11-26 1987-07-24 ユナイテツド・テクノロジ−ズ・コ−ポレイシヨン Ｗａｓｐａｌｏｙ成形品の製造方法
US5360496A (en) * 1991-08-26 1994-11-01 Aluminum Company Of America Nickel base alloy forged parts
US5374323A (en) * 1991-08-26 1994-12-20 Aluminum Company Of America Nickel base alloy forged parts
US5540789A (en) * 1992-05-28 1996-07-30 United Technologies Corporation Oxidation resistant single crystal superalloy castings
US5660649A (en) * 1992-05-28 1997-08-26 United Technologies Corporation Method of making oxidation resistant single crystal superalloy castings
DE4412031A1 (de) * 1993-04-07 1994-10-13 Aluminum Co Of America Verfahren zur Herstellung von Schmiedeteilen aus Nickellegierungen
US6284392B1 (en) 1999-08-11 2001-09-04 Siemens Westinghouse Power Corporation Superalloys with improved weldability for high temperature applications
US6974508B1 (en) 2002-10-29 2005-12-13 The United States Of America As Represented By The United States National Aeronautics And Space Administration Nickel base superalloy turbine disk
WO2018069666A1 (en) 2016-10-12 2018-04-19 Oxford University Innovation Limited A nickel-based alloy
CN110225985A (zh) * 2016-10-12 2019-09-10 牛津大学创新有限公司 镍基合金
US11859267B2 (en) 2016-10-12 2024-01-02 Oxford University Innovation Limited Nickel-based alloy
CN110225985B (zh) * 2016-10-12 2024-01-02 牛津大学创新有限公司 镍基合金

Also Published As

Publication number Publication date
GB968495A (en) 1964-09-02
BE636847A (en:Method) 1964-03-02
NL297339A (en:Method) 1965-05-25
ES291188A1 (es) 1964-02-16
DE1219236B (de) 1966-06-16
FR1367387A (fr) 1964-07-17
LU44364A1 (en:Method) 1963-10-31
SE307018B (en:Method) 1968-12-16
CH420635A (fr) 1966-09-15
AT241133B (de) 1965-07-12

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