US3904402A - Composite eutectic alloy and article - Google Patents

Composite eutectic alloy and article Download PDF

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US3904402A
US3904402A US366047A US36604773A US3904402A US 3904402 A US3904402 A US 3904402A US 366047 A US366047 A US 366047A US 36604773 A US36604773 A US 36604773A US 3904402 A US3904402 A US 3904402A
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superalloy
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Russell W Smashey
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General Electric Co
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General Electric Co
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Priority to US366047A priority Critical patent/US3904402A/en
Priority to CA196,785A priority patent/CA1013176A/en
Priority to GB2086474A priority patent/GB1475711A/en
Priority to FR7418584A priority patent/FR2231767B1/fr
Priority to DE2425994A priority patent/DE2425994C2/de
Priority to BE145016A priority patent/BE815845A/xx
Priority to JP49061019A priority patent/JPS5852015B2/ja
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Publication of US3904402A publication Critical patent/US3904402A/en
Priority to JP58128038A priority patent/JPS5953647A/ja
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    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C49/00—Alloys containing metallic or non-metallic fibres or filaments
    • C22C49/02—Alloys containing metallic or non-metallic fibres or filaments characterised by the matrix material
    • C22C49/08—Iron group metals
    • 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
    • C30—CRYSTAL GROWTH
    • C30B—SINGLE-CRYSTAL GROWTH; UNIDIRECTIONAL SOLIDIFICATION OF EUTECTIC MATERIAL OR UNIDIRECTIONAL DEMIXING OF EUTECTOID MATERIAL; REFINING BY ZONE-MELTING OF MATERIAL; PRODUCTION OF A HOMOGENEOUS POLYCRYSTALLINE MATERIAL WITH DEFINED STRUCTURE; SINGLE CRYSTALS OR HOMOGENEOUS POLYCRYSTALLINE MATERIAL WITH DEFINED STRUCTURE; AFTER-TREATMENT OF SINGLE CRYSTALS OR A HOMOGENEOUS POLYCRYSTALLINE MATERIAL WITH DEFINED STRUCTURE; APPARATUS THEREFOR
    • C30B21/00—Unidirectional solidification of eutectic materials
    • C30B21/02—Unidirectional solidification of eutectic materials by normal casting or gradient freezing

Definitions

  • the present invention relates to eutectic superalloy articles and compositions and, more particularly, to such articles and compositions which include a superalloy matrix reinforced with embedded aligned carbide fibers.
  • Such degradation can occur from formation at the fiber matrix interface of undesirable structures, for example related to gamma prime and to the effect of various elements on the formation of the fibers themselves or on adjacent phases or structures.
  • undesirable structures for example related to gamma prime and to the effect of various elements on the formation of the fibers themselves or on adjacent phases or structures.
  • stability and high temperature properties of the alloy and the article made therefrom were affected.
  • Another object is to provide such an alloy which can be used in unidirectional solidification to provide an improved article.
  • a more specific object is to provide an improved composite eutectic alloy and article having a predomi- 2 nantly TaC reinforcing fibrous phase embedded in an improved nickel base superalloy matrix, the composition of which has been adjusted to inhibit formation of phases or compounds which tend to degrade the carbide reinforcing fibrous phase.
  • the present invention provides an article having a unidirectionally solidified anisotropic metallic composite body which includes a solid solution matrix and an aligned carbide reinforcing fibrous phase embedded in the matrix.
  • the matrix is of a superalloy based on Ni or C0 and includes, by weight, at least about 2% Re to strengthen the matrix along with less than 0.8% Ti to avoid generation of phases or compounds which would tend to degrade the carbide reinforcing fibrous phaseflt is preferred that such carbide reinforcing fibrous phase be predominantly TaC or VC or their combinations, particularly when the superalloy is based on Ni.
  • the alloy composition comprises, by weight, 3 to less than 10% Cr, 2 to less than 8.6% Al, less than about 0.8% Ti, 3-15% Ta, 0.1 to about 1% C, at least about 2% Re, up to about 10% of each of Co, W and V, up to 3% Mo, less than about 3% Ch with the balance essentially nickel and incidental impurities.
  • An example of one preferred form of the alloy within that range consists essentially of, by weight, 3-8% Cr, 4-7% Al, less than 0.8% Ti, 5-1 1% Ta, 0.4-0.8% C, 27% Re, up to about 5% Co, up to about 4% W, 2-7% V, with the balance essentially Ni and incidental impurities.
  • the alloy composition comprises, by weight, up to 20% Cr, 5-20% Ni, up to 8% W, 720% Ta, 0.5-1 .3% C, 2-9% Re with the balance essentially Co and incidental impurities.
  • An example of a preferred form within that range consists essentially of, by weight, 10-16% Cr, 715% Ni, 1-6% W, 10-15% Ta, 0.5-1% C, 26% Re with the balance Co and incidental impurities.
  • the alloy of the present invention which is capable of developing an improved combination of stability and high temperature properties through unidirectional solidification, comprises either a Ni-base or a Co-base superalloy which includes, by weight, at least 2% Re, less than about 0.8% Ti, 0.1 to about 1.3% C and about 3-20% Ta.
  • FIG. 1 is a graphical comparison of stress rupture data of the present invention with another TaC fiber strengthened alloy structure and with a very strong ordinary superalloy;
  • FIG. 2 is a graphical comparison of ultimate tensile strength data of the present invention with another TaC fiber strengthened alloy structure and with a very strong ordinary superalloy;
  • FlG. 3 is a graphical Comparison of 0.2% yield strength data of the present invention with another TaC fiber strengthened alloy structure and with a very strong ordinary superalloy.
  • the superalloy matrix in which the aligned carbide reinforcing fibrous phase is formed and embedded, includes less than about 0.8% Ti and at least about 2% Re in the presence, in the Nibase form, of relatively low amounts of Cr.
  • the alloy of the present invention consists essentially of, by weight, 3 to less than Cr, 2 to less than 8.6% A1, less than 0.8% Ti, 315% Ta, 0.1 to about 1% C, at least about 2% Re, up to about 10% of each of Co, W and V, up to 3% Mo, less than about 3% Cb with the balance essentially nickel and incidental impurities.
  • another form of the present invention selects such composition to be, by weight, about 3-870 Cr, about 47% Al, less than about 0.8% Ti, 5-11% Ta, O.4O.8% C, 27% Re, 27% V, up to about 5% Co, up to about 4% W with the balance essentially Ni and incidental impurities.
  • a more specifically preferred form by weight is 3-6% Cr, 47% Al, less than about 0.8% Ti, 7-1 1% Ta, O.5O.7% C, 57% Re, 2-4% Co, 24% W, 47% V with the balance essentially Ni and incidenta] impurities.
  • the composition of the alloy of the present invention which can be unidirectionally solidified to form the present inventions article of manufacture, includes a careful balance of elements to strengthen the matrix and to provide the capability of producing a higher volume fraction of carbide fibers.
  • One of the important matrix strengtheners included in the alloy of the present invention is Re which also has a tendency to force hardeners such as Ta and V into gamma prime in the Ni-base form. This increases the stress rupture properties dramatically, as will be shown in more detail later.
  • Re is not a carbide former.
  • the present invention includes the element Re in the amount of at least about 2 weight percent. From a practical viewpoint, based on the high cost of Re and the decreasing benefit in greater amounts, it is less practical to include greater than about 9% Re.
  • Ti interfers with the formation of the carbide fibers. It has been found that as low as 0.8 weight percent Ti disrupts carbide fiber formation. Therefore the alloy of the present invention specifies that at most only a trace of Ti should be present and in any event less than 0.8 weight percent.
  • the inclusion of the element Cr is beneficial from the standpoint of improving oxidation resistance, in the Ni-base form of the present invention it is maintained relatively low because of an instability it can introduce in the carbide fiber.
  • the Ni-base product is metallurgically unstable and causes the precipitation of M C reflecting the degeneration of the MC fiber, principally TaC fiber.
  • the strength is only somewhat better than that of an ordinary, good superalloy.
  • the properties are significantly improved, as will be shown by the following examples. It has been recognized, however, that less than about 3 weight percent Cr in the Ni-base form is insufficient to provide meaningful benefit either from an oxidation resistance or a strength viewpoint.
  • the principal carbide fiber former in the present invention is the element Ta.
  • the element Ta In the Ni-base form, it can be included within the range of about 3-15 weight percent and preferably in the range of 510% along with a balance of other elements so as not to deplete the gamma prime content in the alloy.
  • the element Ta also is a gamma prime former in the Ni-base form. Amounts of Ta less than about 3 weight percent in the Ni-base form and about 7% in the Co-base form are insufficient to react with carbon in the formation of TaC.
  • greater than about 15 weight percent Ta, in combination with Al, V and W levels included within the scope of this invention exceeds matrix solubility resulting in undesirable phases or carbide morphologies.
  • the element Cb which is sometimes associated with Ta, is not a full substitute for Ta and tends to weaken the alloy structure when included. Even as little as 1.6 weight percent Cb has been seen to have a weakening effect when substituted directly for an equivalent amount of Ta.
  • the present invention specifies that less than 3 weight percent Cb be included in the alloy and article of the present invention provided the balance of the composition is adjusted to accommodate Cb.
  • V An element which can react along with Ta to form a carbide fiber is V.
  • it also reacts with Ni in the Nibase form to form gamma prime and thus can replace Ti which is substantially removed from the composition of the alloy of the present invention.
  • V is specifically preferred to be included in the Ni-base form of the present invention and in the range of about 4-7 weight percent. Below about 4 weight percent V the alloy tends to become somewhat weaker though still an imprc't ed composition, for example at 2.3 weight percent as will be shown in the subsequent examples. In excess of about 7 weight percent, oxidation resistance tends to decrease progressively so that at about weight percent V oxidation resistance is reduced to an undesirable level.
  • V can be detrimental to oxidation resistance, it can be included in the Ni-base alloy of the present invention up to about 10 weight percent and preferably in the range of 4-7 weight percent to provide additional reaction with Ta and C to fonn carbide fiber as well as to provide additional gamma prime for matrix strengthening.
  • Another of the gamma prime formers included in the composition of the Ni-base form of the present invention is Al in the range of 2 to less than 8.6 weight percent. Amounts of 8.6% A1 or more approaches too closely to a full gamma prime matrix. Such a matrix is different from that of the present invention which is a solid solution reinforced with gamma prime and carbide fibers. As will be shown, an 8.6% A1 content places the composition past the eutectic point, introducing primary gamma prime dendrites in the matrix. Thus aluminum at about 8.6 weight percent causes serious loss of stress rupture strength. However, although A1 is needed for gamma prime strengthening in the carefully balanced composition of the present invention, it has been recognized that less than about 2 weight percent is insufficient for such purposes. In a preferred Nibase form of the present invention, the sum of the gamma prime formers Ta, V and Al should be no greater than about 25 weight percent when Ta is in the range of 3-15 weight percent.
  • the element C which is needed to combine with Ta or with Ta and V to produce the carbide fiber which strengthens the matrix. Less than 0.1 weight percent C is insufficient to form the carbide fiber. Greater than about 1 weight percent C produces free carbon because there are not enough desirable carbide formers in 6 the present composition to react with more than about 1% C. However, any such free carbon will slag off or will collect in the sorting-out portion of the casting which is adjacent the chill and which is later removed from the cast article.
  • the amount of C included in the composition of this invention is a function of the amount of Ta, and of V, when included, sufficient to form a monocarbide of one or both of such elements.
  • An element which is preferred to be omitted from the composition but which can be tolerated up to about 3 weight percent is Mo. Like Cb, it tends to degrade the carbide fiber structure and reduce properties.
  • An element which can be included in the composition in the range of up to about 10 weight percent, is W. It functions principally as a solid solution strengthener although it contributes somewhat to gamma prime formation. In excess of about 10 weight percent, it interfers with carbide fiber formation. Its preferred contribution occurs in the range up to about 4% and preferably in the range of about 24% in Ni-base and up to about 6% and preferably 1 6% in Co-base.
  • the element Co substitutes for nickel up to about 10 weight percent and contributes to the solubility relationship. In such smaller amounts, for example up to about 5 weight percent and preferably 2-4 weight percent, Co increases the melting point. However, at the higher amounts, for example greater than about 10 weight percent, it tends to result in matrix instabilities.
  • the alloy having the above-described careful balance of elements must be unidirectionally solidified to enable the carbide eutectic fibers to form integrally within and be bonded to the reinforced solid solution matrix.
  • Such unidirectional solidification can be conducted in one or more of the many methods and using apparatus Well-known and widely reported in the art.
  • One of the essential features of the present invention is the inclusion of the element Re principally to strengthen the alloy matrix. Such strength improvement is particularly evident in the stress rupture properties of the unidirectionally solidified specimens made from the alloy composition.
  • Table 11 shows the dramatic effect on stress rupture strength of the inclusion of Re within the range of the present invention on alloy compositions which otherwise are substantially the same as shown by Table l.
  • the data presented in Table ll resulted from stress rupture testing in air.
  • ksi means thousands of pounds per square inch
  • RA means reduction in area
  • Elong. means elongation
  • P means the well-known and widely used metallurgical stress rupture relationship known as the Larson- Miller parameter P T(C Log t) X lwhere C 20, described in more detail in American Society of Engineers Transactions, 1952, Volume 74, at pages 765-771. Use of such a parameter allows a wide variety of comparisons between stress rupture lives at various temperatures and at selected stress levels.
  • alloys 1 and 4 were prepared to study the effect of Ti on the cast structure. After preparation and unidirectionally solidifying alloy 1, it was noted from photomicrographs that the structure was unsatisfactory: it included few aligned fibers and predominantly a dendrite structure. Thus it was recognized that the carbide fiber reinforcement desired in the article of the present invention could not be attained through alloy 1. Similarly, a mi crographic evaluation of alloy 4 showed that the as-cast structure was a solid solution matrix with gamma prime and equiaxed carbide particles which are known not to form the desired aligned carbide fiber structure. Thus, even as little as 0.8% Ti is detrimental to the composition of the present invention.
  • the specifically preferred Ni-base form of the present invention includes the optional elements Co, W and V along with the other required elements.
  • Typical of such specifically preferred form is alloy example 13 which was selected for more extensive evaluation as represented not only by the data of Table 111 but also the comparative data shown in the drawings. As can be seen from the following Table III the stress rupture properties of alloy example 13 are better than other forms of the alloy of the present invention presented here and dramatically better than known alloys or cast articles of a type similar to that to which the present invention relates.
  • Examples 18, 21 and 24 through 28 show the effect of varying amounts of Al and V along with variation in the level of TaC.
  • comparison of examples l8 and 28 shows that at an Al level of 8.6%, there is too much aluminum thus forcing the Ni-base alloy past the eutectic point and introducing primary gamma prime dendrites into the matrix. This has been observed from photomicrographic evaluations.
  • This comparison along with consideration of example 27 which shows good strength properties and is within the scope of the present invention, indicates'that the maximum allowable Al content within the scope of the Ni-base form of the present invention lies at a point between 7.4% and less than 8.6%. From these considerations, the present invention has been defined as having an Al content of less than 8.6% and preferably in the range of about 4-7%.
  • example 13 Article specimens of this alloy form were prepared for evaluation in a variety of stress rupture and tensile tests, both in the longitudinal and transverse direction in respect to the unidirectionally solidified structure. Comparison of example 13 test data with data for the strongest TaC fiber strengthened structures and with the best reported equiaxed cast superalloy are shown in FlGS. l, 2 and 3. These figures, respectively, compare the longitudinal and transverse stress rupture strength, the longitudinal and transverse ultimate tensile strength and the longitudinal and transverse 0.2% yield strengths of the unidirectionally solidified TaC structures and those same properties for the ordinary cast superalloy.
  • Alloy C in the drawing was in the form of a unidirectionally solidified structure the composition of which consisted nominally, by weight, of 9.5% Ni, 15.7% Cr, 3.0% W, 12.0% Ta, 0.77% C with the balance essentially Co and incidental impurities.
  • Alloy R sometimes referred to as Rene 120 alloy, was an ordinary superalloy with an equiaxed structure and consisted nominally, by weight, of 0.17% C, 9% Cr, 4% Ti, 0.015% B, 4.3% A1, 7% W, 2% Mo, 10% Co, 3.8% Ta, 0,08% Zr, with the balance essentially Ni and incidental impurities.
  • Review of the data presented in the drawings shows clearly the advantage of the present invention as represented by example 13.
  • Cobase forms as well as Ni-base alloys were evaluated.
  • the following Tables IV and V list the composition and stress rupture properties of two of such alloys evaluated within the broad range of up to Cr, 520% Ni, up to 8% W, 720% Ta, 0.51.3% C and 29% Re in a C0- base.
  • the specimens were prepared by unidirectional solidification.
  • Co-base alloys of the type to which the present invention relates are not gamma prime strengthened, they depend solely on solution strengthening within the matrix.
  • the high strength properties are achieved from the combination of improved matrix strength through the presence of Re and reinforcement strengthening from aligned carbide fibers predominantly TaC.
  • the composition particularly the preferred range of 10-1 6% Cr, 715% Ni, 16% W, 10-15% Ta, 0.71% C and 26% Re in the Co-base, is selected to avoid detrimental interaction between the matrix and the aligned fibers and to assure matrix stability for example to avoid allotropic transformation.
  • An article of manufacture having an improved combination of stability and high temperature properties comprising a unidirectionally solidified anisotropic metallic composite body comprising:
  • a matrix of a Ni-base or Co-base superalloy consisting essentially of, by weight, about 2- 9% Re and less than about 0.8% Ti, along with elements selected from the group consisting of Cr, Al, Ta, C, Ni, Co, W, V, Mo, Cb, Hf, Zr and B, the matrix being a solid solution; and
  • an aligned eutectic reinforcing fibrous phase selected from carbides of the group consisting of Ta, V and their alloys and mixtures embedded in the matrix.
  • the superalloy is Nibase consisting essentially of by weight, 3 to less than 10% Cr, 2 to less than 8.6% A1, less than about 0.8% Ti, 315% Ta, 0.1 to about 1% C, about 27% Re, up to about 10% Co, up to about 10% W, up to about 10% V, up to 3% Mo and less than about 3% Cb.
  • the article of claim 4 in which the superalloy consists essentially of, by weight, 3-6% Cr, 47% Al, less than about 0.8% Ti, 7-11% Ta, 0.50.7% C. 57% Re, 24% Co, 2-4% W, 4-7% V with the balance essentially Ni and incidental impurities.
  • An alloy capable of developing in a unidirectionally solidified anisotropic article an improved combination of stability and high temperature properties comprising a Ni-base or Co-base superalloy consisting essentially of, by weight, about 2-9% Re, less than about 0.8% Ti, 0.4t0 about 1.3% C and about 3-20% Ta, along with elements selected from the group consisting of Cr, Al, Ni, Co, W, V, Mo, Cb, Hf, Zr and 10.
  • the superalloy is Nibase consisting essentially of, by weight, 3 to less than 10% Cr, 2 to less than 8.6% A1, less than about 0.8% Ti, 3-l5% Ta, 0.4 to about 1% C, about 2-7% Re, up to 12 about 10% Co, up to about 10% W, up to about 10% V, up to 3% Mo and less than about 3% Cb.
  • the alloy of claim 10 consisting essentially of, by weight, about 38% Cr, about 47% A], less than about 0.8% Ti, 5-1 1% Ta, 0.4-0.8% C, 2-7% Re, up to about 5% Co, up to about 4% W, 27% V with the balance essentially Ni and incidental impurities.
  • the alloy of claim 11 consisting essentially of, by weight, 3-6% Cr, 47% Al, less than about 0.8% Ti, 7-] 1% Ta, 05-07% C, 57% Re, 2-4% Co, 2-4% W, 4-7% V with the balance essentially Ni and incidental impurities.
  • the alloy of claim 13 consisting essentially of, by weight, lO-l6% Cr, 7l5% Ni, l6% W, 10-15% Ta, 0.5-l% C, 26% Re, with the balance essentially Co and incidental impurities.

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US366047A 1973-06-01 1973-06-01 Composite eutectic alloy and article Expired - Lifetime US3904402A (en)

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Application Number Priority Date Filing Date Title
US366047A US3904402A (en) 1973-06-01 1973-06-01 Composite eutectic alloy and article
CA196,785A CA1013176A (en) 1973-06-01 1974-04-04 Composite eutectic alloy and article
GB2086474A GB1475711A (en) 1973-06-01 1974-05-10 Eutectic alloy and article
FR7418584A FR2231767B1 (de) 1973-06-01 1974-05-29
DE2425994A DE2425994C2 (de) 1973-06-01 1974-05-30 Werkstoff mit gerichteter faserförmiger Ausbildung des Tantal- und/oder Vanadiumkarbids
BE145016A BE815845A (fr) 1973-06-01 1974-05-31 Produit composite a base de ni ou co
JP49061019A JPS5852015B2 (ja) 1973-06-01 1974-05-31 耐熱ニッケル基超合金
JP58128038A JPS5953647A (ja) 1973-06-01 1983-07-15 耐熱コバルト基超合金

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JP (2) JPS5852015B2 (de)
BE (1) BE815845A (de)
CA (1) CA1013176A (de)
DE (1) DE2425994C2 (de)
FR (1) FR2231767B1 (de)
GB (1) GB1475711A (de)

Cited By (19)

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US4119458A (en) * 1977-11-14 1978-10-10 General Electric Company Method of forming a superalloy
US4162918A (en) * 1977-11-02 1979-07-31 General Electric Company Rare earth metal doped directionally solidified eutectic alloy and superalloy materials
DE3016027A1 (de) * 1979-04-27 1980-11-13 Gen Electric Gegenstand aus einer nickellegierung sowie legierung dafuer
DE3016028A1 (de) * 1979-04-27 1980-11-13 Gen Electric Gegenstand aus einer superlegierung auf nickelbasis und legierung dafuer
US4318756A (en) * 1978-11-14 1982-03-09 Office National D'etudes Et De Recherches Aerospatiales O.N.E.R.A. Multi-phase metallic systems of the γ,γ', NBC type with improved structural stability
DE3139035A1 (de) * 1980-11-03 1982-06-09 General Electric Co., Schenectady, N.Y. "verfahren zum herstellen eines hohlen gegenstandes"
US4388124A (en) * 1979-04-27 1983-06-14 General Electric Company Cyclic oxidation-hot corrosion resistant nickel-base superalloys
DE3412458A1 (de) * 1983-04-04 1984-10-04 General Electric Co., Schenectady, N.Y. Phasenstabile, karbidverstaerkte nickelbasis-superlegierungseutektika mit verbesserter festigkeit gegenueber spannungsbruch bei hoher temperatur und verbesserter bestaendigkeit gegenueber der bildung von oberflaechenkarbiden
US5035958A (en) * 1983-12-27 1991-07-30 General Electric Company Nickel-base superalloys especially useful as compatible protective environmental coatings for advanced superaloys
US5043138A (en) * 1983-12-27 1991-08-27 General Electric Company Yttrium and yttrium-silicon bearing nickel-base superalloys especially useful as compatible coatings for advanced superalloys
US5270123A (en) * 1992-03-05 1993-12-14 General Electric Company Nickel-base superalloy and article with high temperature strength and improved stability
US5455120A (en) * 1992-03-05 1995-10-03 General Electric Company Nickel-base superalloy and article with high temperature strength and improved stability
US6074602A (en) * 1985-10-15 2000-06-13 General Electric Company Property-balanced nickel-base superalloys for producing single crystal articles
US6143141A (en) * 1997-09-12 2000-11-07 Southwest Research Institute Method of forming a diffusion barrier for overlay coatings
US6306544B1 (en) * 1999-02-25 2001-10-23 Wilson Greatbatch Ltd. Cobalt-based alloys as positive electrode current collectors in nonaqueous electrochemical cells
US6632299B1 (en) 2000-09-15 2003-10-14 Cannon-Muskegon Corporation Nickel-base superalloy for high temperature, high strain application
US20050135962A1 (en) * 2003-12-22 2005-06-23 Henry Michael F. Directionally solidified eutectic superalloys for elevated temperature applications
ITCO20090027A1 (it) * 2009-07-29 2011-01-30 Nuovo Pignone Spa Superlega a base di nichel, componente meccanico realizzato con detta superlega, turbomacchina comprendente tale componente e metodi relativi
US9816159B2 (en) 2012-03-09 2017-11-14 Indian Institute Of Science Nickel-aluminium-zirconium alloys

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JPS5814016B2 (ja) * 1978-03-31 1983-03-17 株式会社日立製作所 直熱形酸化物陰極用基体金属板材
US4222794A (en) * 1979-07-02 1980-09-16 United Technologies Corporation Single crystal nickel superalloy
JP2512802Y2 (ja) * 1986-12-27 1996-10-02 キヤノン株式会社 モ―タ

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US3526499A (en) * 1967-08-22 1970-09-01 Trw Inc Nickel base alloy having improved stress rupture properties

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US3276865A (en) * 1964-06-15 1966-10-04 John C Freche High temperature cobalt-base alloy
US3366478A (en) * 1965-07-21 1968-01-30 Martin Marietta Corp Cobalt-base sheet alloy
US3526499A (en) * 1967-08-22 1970-09-01 Trw Inc Nickel base alloy having improved stress rupture properties

Cited By (26)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4162918A (en) * 1977-11-02 1979-07-31 General Electric Company Rare earth metal doped directionally solidified eutectic alloy and superalloy materials
US4119458A (en) * 1977-11-14 1978-10-10 General Electric Company Method of forming a superalloy
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US20110165012A1 (en) * 2009-07-29 2011-07-07 Marco Innocenti Nickel-based superalloy, mechanical component made of the above mentioned super alloy, piece of turbomachinery which includes the above mentioned component and related methods
US9359658B2 (en) 2009-07-29 2016-06-07 Nuovo Pignone S.P.A Nickel-based superalloy, mechanical component made of the above mentioned super alloy, piece of turbomachinery which includes the above mentioned component and related methods
US9816159B2 (en) 2012-03-09 2017-11-14 Indian Institute Of Science Nickel-aluminium-zirconium alloys

Also Published As

Publication number Publication date
DE2425994A1 (de) 1975-01-02
GB1475711A (en) 1977-06-01
JPS5852015B2 (ja) 1983-11-19
FR2231767B1 (de) 1977-03-11
JPS6221859B2 (de) 1987-05-14
BE815845A (fr) 1974-09-16
CA1013176A (en) 1977-07-05
JPS5953647A (ja) 1984-03-28
FR2231767A1 (de) 1974-12-27
JPS5032017A (de) 1975-03-28
DE2425994C2 (de) 1985-12-05

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