US3322534A - High temperature nickel-chromium base alloys - Google Patents

High temperature nickel-chromium base alloys Download PDF

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US3322534A
US3322534A US457240A US45724065A US3322534A US 3322534 A US3322534 A US 3322534A US 457240 A US457240 A US 457240A US 45724065 A US45724065 A US 45724065A US 3322534 A US3322534 A US 3322534A
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alloys
percent
alloy
chromium
stress
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Shaw Stuart Walter Ker
Cook Reginald Massey
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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
    • 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 nickel-alloys, and, more particularly, to cast nickel-base alloys suitable for use under high stress at temperatures of at least 1000 C. (1832 F.) and above as, for example, stator and rotor blades for gas turbine engines.
  • Stator and rotor blades in cast form have received considerable attention in recent years for various reasons and there is a present need for cast alloys suitable for use in the production of such blades designed to operate ,at temperatures over 1800 F., e.g., 1900 F., and under relatively high stress. It was not too long ago that efforts were being expended to develop alloys capable of performing satisfactorily at the now comparatively low temperatures of 1200 F. or 1300 F. to 1500 F. Ina relatively short period of time the temperature demands have increased to 1800 F. and even 1900 F. and there is little reason to believe that future developments will reverse this trend.
  • This tantalumand vanadium-containing nickel-base NASA alloy nominally contained 8% tantalum, 6% chromium, 6% aluminum, 4% molybdenum, 4% tungsten, 2.5% vanadium, 0.125% carbon, the balance being nickel, and had a stress-rupture life of 100 hours under a stress of 15,000 p.s.i. at the high temperature of 1915 F.
  • vanadium inter alia, is an essential constituent of the NASA alloy since it improved stress-rupture life.
  • vanadium impairs oxidation resistance at high temperatures, e.g., 1900 F., and adversely elfects stress Patented May 30, 1967 rupture life. Good oxidation resistance becomes increasingly important the longer the period of exposure of an alloy to high temperature.
  • Another object of the invention is to provide a novel cast alloy suitable for use in precision cast gas turbine structures.
  • a further object of the invention is to provide nickelbase alloys which provide a highly satisfactory combination of stress-rupture and impact resistant properties a elevated temperature.
  • the alloys of the present invention contain about 2% to about 10% chromium, from 5%, and most advantageously, from about 7%, to 19% tungsten, up to about 5% molybdenum, from 0.5% to 7% tantalum, with the sum of the contents of tungsten and tantalum being at least 7% and the sum of these two elements together with twice the content of molybdenum and two-thirds of the content of chromium being from 17.5% to 24%, from 2% to about 8% aluminum, up to about 4% titanium, up to about 0.5 carbon, e.g., 0.03% to 0.5%, up to 2.5% columbium, with the proviso that the columbium content is not greater than and advantageously is less than the tantalum content, up to 0.05% boron, up to 1.5% zirconium and the balance, apart from impurities, being nickel.
  • the principal impurities that may be present are iron, silicon and manganese and the total amount of these elements should be as low as possible and
  • the stress-rupture lives of the alloys at temperatures above 1000 C. fall as their chromium content increases above about 5%, i.e., as the chromium content of the alloys increases, their stress-rupture lives above 1000 C. increase to a maximum at a chromium content of about 5% and then falls.
  • the chromium content should not exceed 9%, and most advantageously, it is from 3% to 7%.
  • the resistance of the alloys to oxidation at high temperatures falls sharply when the chromium content is reduced below 2%. At higher chromium contents it increases progressively as the chromium content is increased, and the best combination of stress-rupture properties and oxidation resistance is exhibited by alloys with from to 7% chromium.
  • the stress-rupture lives of the alloys also depend on their aluminum content and in titanium-free alloys is greatest when the aluminum content is from 5.2% to 7.1%.
  • the value of the ex- The amount of chromium can be raised from 7% to 9% 5 pression or where maximum oxidation resistance is of impercentAl+0.7 (percent Ti) portance. is
  • g is zi 'i ig g; 23 68 31 5 2; 52 52 3 gg
  • Particularly satisfactory stress-rupture properties are t h g t exhibited by alloys having compositions within the fola a f 6 mmlllm COD en 9 an Va P 10 lowing range: 0.10% to 0.16% carbon, 5.0% to 7.0% of this total at which the longest lives are obtained.
  • the tantalum content of the alloys is preferably from 2% t0 6%, since poorer stress-rupture lives are obtained outside this range. The longest lives are exhibited with alloys containing not more than 5% tantalum. For the same reason the molybdenum content preferably does not exceed 3% and the tungsten content is, as noted above herein, advantageously at least 7%.
  • Table I illustrates that poorer properties are obtained when the contents of tungsten, molybdenum and tantalum are such that the value of the expression 2 (percent Mo) +percent W+percent Ta /3 (percent Cr) therefore, the columbium content does not exceed threequarters of the tantalum content and most advantageously does not exceed one-half the percentage of tantalum. This efilect is illustrated by the results in Table II, which relate to alloys of the same nominal carbon, chromium,
  • Alloy No. 3 under various conditions of stress and temperature are set forth in Table HI, 'which also inclules the properties of an alloy (Alloy A) of otherwise identical composition that is free from aluminum and zirconium contents as those in Table I. tantalum but contains an equiatomic amount (1.5% by TABLE II Stress-Rupture Properties 2 Mo+W+ at 7 t.s.i./l,070 0. Alloy N0. M0, Percent W, Percent Ta, Percent Cb, Percent Ta-l-3 Cr Life (hrs) El. (percent) 0 13 4 0 21 5.6 0 13 4 1 21 146, 147 6.
  • t stress-rupture life of about 146 hours at the comparatively rs) (Damn (hrs) (percent) very temperure f 10 C-
  • a Preferred range of 5 C 75 7 g 129 28 compositions for columbium-containing alloys is as Gramp0tt.s .i.1/9(520; 1, 2 9.6 699 15.6 lows: 0.10% to 0.16% carbon, 5% to 7% chromium, 131 1 5 5 5 33 2:? 12.5% to 13.5% tungsten, 3.6% to 4.4% tantalum, 0.7% Hat/1,070 o.--
  • the carbon content is at least 0.03% and is preferably at least 0.05% but variation of the carbon content of the alloys within the range 0.05 to 0.3% has little effect on their stress-rupture properties.
  • the carbon content be less than 0.03%, e.g., 0.001% to 0.0275
  • 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 almost inevitably be present.
  • the alloys While it is not absolutely essential (although much pre ferred) that the alloys contain boron when the carbon content is above 0.03%, at least 0.01% boron should be present with lower carbon contents in order to achieve a good combination of stress-rupture life and resistance to impact. Further in this regard, it is preferred that the boron content not exceed 0.035% when the alloys contain more than 0.03% carbon.
  • Table VIII The effect of zirconium and boron on alloys containing more than 0.03% carbon is illustrated in Table VIII, the alloys containing, apart from zirconium and boron in the amounts indicated, 0.13% carbon, 6% chromium, 2% molybdenum, 11% tungsten, 3% tantalum, 6% aluminum, balance nickel and impurities.
  • Table IXa further illustrate the effects of varying the boron content in a series of low-carbon alloys each containing 0.004% carbon, 0.25% zirconium and otherwise having the same base composition as those in Table IX.
  • Table X contains some examples of low-chromium alloys and shows that their properties are good as long as the value of the expression 2(percent Mo) +percent W-l-percent Ta+ /3 (percent Cr) lies between 17.5% and 24%, and the tungsten content does not exceed 19%.
  • alloys nominally contained, in addition to the elements mentioned, 0.13% carbon, 6% aluminium, 3% chromium, 10% cobalt, 0.5% zirconium, balance nickel and impurities.
  • the alloys may be air melted, but are preferably melted under vacuum. This is particularly apropos in obtaining alloys with low carbon contents. Under such conditions, carbon reacts with oxides introduced by the charge materials and is substantially eliminated as carbon monoxide. Whether or not they are vacuum-melted, the alloys are advantageously subjected to a vacuum-refining treatment comprising holding them in the molten state under high vacuum before casting the melt. We prefer to hold the melt at a temperature of 1400 C. to 1600 C. at not more than 100 microns pressure for a period of at least 15 minutes and advantageously for 60 minutes or more. The duration of the treatment depends to some extent on the purity of the ingredients of the melt, a longer time being required when less pure ingredients are employed.
  • 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. All the stress-rupture test results given in this specification were obtained in testpieces machined from cast specimens that had been vacuum-cast from vacuum-melted material that had been vacuum-refined for at least 15 minutes at 1500 C. under a pressure of less than 1 micron.
  • Articles and parts cast from the alloys may be used in the as-cast condition for high temperature service, for example, as rotor blades in gas turbine engines. If desired, the alloys may be homogenized by heating in the temperature range 850 C. to 1250 C. before being put into service.
  • articles and parts made from the alloys are preferably provided with a protective coating, for example, of aluminum.
  • a nickel-base alloy characterized by good stressrupture properties at temperatures of 1800 F. and above, said alloy consisting essentially, in weight percent, of about to about 7% chromium, about 10.5% to 11.5% tungsten, about 1.7% to 2.3% molybdenum, about 2.6% to 3.4% tantalum, about 5.7% to 6.8% aluminum, about 0.1% to 0.16% carbon, up to 0.035% boron, about 0.03% to 1% zirconium and the balance nickel.
  • a nickel-base alloy characterized by good stressrupture properties at temperatures of 1800 F. and above, said alloy consisting essentially, in weight ercent, of about 5% to 7% chromium, about 12.5% to 13.5% tungsten, about 3.6% to 4.4% tantalum, about 0.7% to 1.3% columbium, about 5.7% to 6.8% aluminum, about 0.1% to 0.16% carbon, up to about 0.035% boron, about 0.03% to 1% zirconium and the balance essentially nickel.
  • a nickel-base alloy characterized by a combination of good stress-rupture life and resistance to impact at high temperatures, said alloy consisting essentially, in weight percent, of about 2% to about chromium, from 5% to 19% tungsten, up to 5% molybdenum, from 0.5% to 7% tantalum with the sum of the contents of tungsten and tantalum being at least 7% and the sum of these two elements plus twice the percentage of molybdenum plus two-thirds the percentage of chromium being from 17.5% to 24%, from 2% to 8% aluminum,
  • An alloy according to claim 3 containing 5% to 9% chromium, 7% to 16% tungsten, up to 5% molybdenum, 0.5% to 7% tantalum, 2% to 8% aluminum, up to 4% titanium, up to 2.5% columbium, 0.001% to 0.0275% carbon, about 0.01% to 0.05% boron, about 0.1% to 1% zirconium, and the balance nickel.
  • An alloy in accordance with claim 3 containing 7% to 16% tungsten, up to 3% molybdenum, 2% to 6% tantalum, 5.2% to 7.1% aluminum with the aluminum and any copresent titanium being correlated such that the percentage of aluminum plus 0.7 times the percentage of titanium equals 5.2% to 7.1%, 0.001% to 0.0275% carbon, 0.01% to 0.05% boron and 0.1% to 1% zircomum.
  • a nickel-base alloy characterized by good stressrupture properties at temperatures of 1800 F. and above, said alloy consisting essentially, in weight percent, of about 2% to about 10% chromium, from 5% to 19% tungsten, up to 5% molybdenum, from 0.5% to 7% tantalum with the sum of the contens of tungsten and tantalum being at least 7% and the sum of these two elements plus twice the percentage of molybdenum plus two-thirds the percentage of chromium being from 17.5 to 24%, from 2% to 8% aluminum, up to about 4% titanium, up to about 0.5% carbon, up to 2.5% columbium with the proviso that the columbium content is not greater than the tantalum content, up to 0.05% boron, up to about 1.5% zirconium, up to a total of 3% of iron, manganese and silicon, and the balance nickel.
  • a nickel-base alloy characterized by good stressrupture properties at temperatures of 1800 F. and above, said alloy consisting essentially, in weight percent, of about 2% to about 5% chromium, from 5% to 19% tungsten, up to 5% molybdenum, from 0.5% to 7% tantalum with the sum of the contents of tungsten and tantalum being at least 7% and the sum of these two elements plus twice the percentage of molybdenum plus two-thirds the percentage of chromium being from 17.5 to 24%, from 2% to 8% aluminum, up to about 4% titanium, up to about 0.5% carbon, up to 2.5% columbium with the proviso that the columbium content is not greater than the tantalum content, up to 0.05% boron, up to about 1.5% zirconium, up to 15% cobalt, up to a total of 3% of iron, manganese and silicon, and the balance nickel.
  • An alloy in accordance with claim 9 containing 7% to 16% tungsten, 2% to 6% tantalum, 5.2% to 7.1% aluminum with the aluminum and any copresent titanium being correlated such that the percentage of aluminum plus 0.7 times the percentage of titanium equals 5.2% to 7.1%, up to 0.3% carbon, up to 0.035% boron and 0.1% to 1% zirconium.
  • An alloy in accordance with claim 8 containing 7% to 16% tungsten, 2% to 6% tantalum, 5.2% to 7.1% aluminum with the aluminum and any copresent titanium being correlated such that the percentage of aluminum plus 0.7 times the percentage of titanium equals 5.2% to 7.1%, up to 0.3% carbon, up to 0.035% boron and 0.1% to 1% zirconium.

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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)
  • Heat Treatment Of Steel (AREA)
  • Manufacture And Refinement Of Metals (AREA)
US457240A 1964-08-19 1965-04-30 High temperature nickel-chromium base alloys Expired - Lifetime US3322534A (en)

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AT (1) AT258590B (enrdf_load_stackoverflow)
BE (1) BE668503A (enrdf_load_stackoverflow)
FR (1) FR88743E (enrdf_load_stackoverflow)
GB (1) GB1106087A (enrdf_load_stackoverflow)
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SE (1) SE317519B (enrdf_load_stackoverflow)

Cited By (10)

* 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
US3415641A (en) * 1966-08-24 1968-12-10 Gen Electric Wrought nickel base alloy
US3617262A (en) * 1967-12-06 1971-11-02 Int Nickel Co Nickel-chromium-tantalum alloys
US3617261A (en) * 1968-02-08 1971-11-02 Cyclops Corp Specialty Steel D Wrought nickel base superalloys
US3793011A (en) * 1971-11-08 1974-02-19 Avco Corp 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
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
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

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2578554B1 (fr) * 1985-03-06 1987-05-22 Snecma Alliage monocristallin a matrice a base de nickel

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2948606A (en) * 1957-05-31 1960-08-09 Sierra Metals Corp High temperature nickel base alloy
US2994605A (en) * 1959-03-30 1961-08-01 Gen Electric High temperature alloys
US3026198A (en) * 1960-04-11 1962-03-20 Sierra Metals Corp Nickel base casting alloy
US3085005A (en) * 1958-01-16 1963-04-09 Fansteel Metallurgical Corp Alloys
US3164465A (en) * 1962-11-08 1965-01-05 Martin Metals Company Nickel-base alloys

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2948606A (en) * 1957-05-31 1960-08-09 Sierra Metals Corp High temperature nickel base alloy
US3085005A (en) * 1958-01-16 1963-04-09 Fansteel Metallurgical Corp Alloys
US2994605A (en) * 1959-03-30 1961-08-01 Gen Electric High temperature alloys
US3026198A (en) * 1960-04-11 1962-03-20 Sierra Metals Corp Nickel base casting alloy
US3164465A (en) * 1962-11-08 1965-01-05 Martin Metals Company Nickel-base alloys

Cited By (11)

* 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
US3415641A (en) * 1966-08-24 1968-12-10 Gen Electric Wrought nickel base alloy
US3617262A (en) * 1967-12-06 1971-11-02 Int Nickel Co Nickel-chromium-tantalum alloys
US3617261A (en) * 1968-02-08 1971-11-02 Cyclops Corp Specialty Steel D Wrought nickel base superalloys
US3793011A (en) * 1971-11-08 1974-02-19 Avco Corp 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
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
DE4412031A1 (de) * 1993-04-07 1994-10-13 Aluminum Co Of America Verfahren zur Herstellung von Schmiedeteilen aus Nickellegierungen
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

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AT258590B (de) 1967-12-11
FR88743E (enrdf_load_stackoverflow) 1967-06-02
BE668503A (enrdf_load_stackoverflow)
NL6510768A (enrdf_load_stackoverflow) 1966-02-21
GB1106087A (en) 1968-03-13
SE317519B (enrdf_load_stackoverflow) 1969-11-17

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