US3887363A - Nickel-base superalloy cast article - Google Patents

Nickel-base superalloy cast article Download PDF

Info

Publication number
US3887363A
US3887363A US426092A US42609273A US3887363A US 3887363 A US3887363 A US 3887363A US 426092 A US426092 A US 426092A US 42609273 A US42609273 A US 42609273A US 3887363 A US3887363 A US 3887363A
Authority
US
United States
Prior art keywords
percent
nickel
present
essentially
nial
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
US426092A
Other languages
English (en)
Inventor
Russell W Smashey
Carl S Wukusick
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.)
General Electric Co
Original Assignee
General Electric Co
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 General Electric Co filed Critical General Electric Co
Priority to US426092A priority Critical patent/US3887363A/en
Priority to GB2991674A priority patent/GB1473134A/en
Priority to CA215,680A priority patent/CA1053482A/fr
Priority to DE19742458540 priority patent/DE2458540A1/de
Priority to IT30578/74A priority patent/IT1027700B/it
Priority to JP49144123A priority patent/JPS5095122A/ja
Priority to BE151573A priority patent/BE823437A/fr
Priority to FR7441455A priority patent/FR2254651B1/fr
Application granted granted Critical
Publication of US3887363A publication Critical patent/US3887363A/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Images

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
    • C22C19/057—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W with the maximum Cr content being less 10%

Definitions

  • the superalloy consists, in atomic percent, essentially of 4-11 Cr, 75/171, l48/3(2:,2l2:81/;/26g 546 A], at least 05 Re p to about 10 V p to about I 15 C0, p to about 5 Ta p to about 5 w, p to about [58] Field of Search 75/171, 170, 148/32, 32.5 1 M0 u to about 2.5 Mn u to about 2'5 Rh with p p e n 0 [56] References Cited the balance nickel and incidental impurities.
  • Such alloys include reinforcing carbide members such as fibers which can be formed in situ during solidification of the alloy.
  • One form of such solidification which has been used and has been widely reported is generally referred to as unidirectional solidification.
  • the gamma prime former Ti when included in a nickel-base superalloy structure, depresses the alloys incipient melting temperature and tends to promote the formation of a eutectic phase for example, the gamma-gamma prime, eutectic.
  • the incipient melting temperature is about 2250F.
  • Another object is to provide a castable nickel-base superalloy substantially free of carbon and titanium and which is particulary useful in the casting of unidirectionally solidified articles.
  • the present invention in one form, provides a cast'nickel-base superalloy article the microstructure of which comprises aligned cellular dendrites and is further characterized by the substantial absence of the detrimental NiAl phase, carbon, carbides and Ti.
  • the superalloy associated with the present invention consists, in atomic percent, essentially of 4-1 1 Cr, 5-16 A1, at least 0.5 Re, up to about V, up to about Co, up to about 5 Ta, up to about 5 W, up to about 1 Mo, up to about 2.5 Mn, up to about 2.5 Rh, with the balance Ni and incidental impurities.
  • incidental 'impurities may include Ti at less than 1 and C at less than 0.1 at. percent which, by weight, is less than about 0.017 percent.
  • the elements Zr and B be omitted from the composition, their presence being limited to those levels which result from normal pick-up of stray elements during melting and casting, for example up to about 0.03 percent Zr and 0.0] percent B by weight.
  • the approximate percent by weight equivalent of this form of the invention consists essentially of 3.5-10 Cr; 2.2-7.2 A1; at least 1.5 Re; up to about 8.5 V; up to about l5 each of Co, Ta and W; up to about 1.5 Mo; up to about 2.5 Mn; up to about 4.5 Rh; with the balance Ni and incidental impurities.
  • the composition, and atomic percent consist essentially of 3-8 Co, 4-9 Cr, 8-14 Al, l-4 Ta, l-7 V, 0.5-5 Re, up to about 2 W, up to about 1 each of Mo, Mn and Rh, with the balance essentially nickel and incidental impurities.
  • the approximate percent by weight equivalent of this preferred form consists essentially Qf 3-8 Co; 3.5-8 Cr; 3.6-6.3 Al; 3-12 Ta; 0.8-6 V; 1.5-1 5 Re; up to about 6 W; up to about 1.5 Mo; up to about 1 Mn; up to about 1.8 Rh; with the balance Ni and incidental impurities.
  • FIG. 1 is a photomicrographic view at magnifications of the structure of example within the scope of the present invention showing the aligned cellular dendrites in the transverse direction the absence of NiAl;
  • FIG. 2 is a photomicrographic view at 100 magnifications of the structure of example 105 within the scope of the present invention showing the aligned cellular dendrites in the longitudinal direction and the absence of NiAl;
  • FIG. 3 is a photomicrographic view at 100 magnifications in the transverse direction of the alloy of example 87 outside the scope of the present invention showing the presence of abundant gamma-gamma prime eutectic phase;
  • FIG. 4 is a photomicrographic view at 100 magnifications in the transverse direction of the alloy of example outside the scope of the present invention showing the presence of MA] phase;
  • FIG. 5 is a graphical comparison of creep properties.
  • the incipient melting temperature of the alloy associated with the present invention is at least about lOOF higher than an ordinary superalloys incipient melting temperature of about 2250F.ln addition, F.
  • the gamma prime solution temperature is at least 100 higher than that of the ordinary superalloy.
  • the alloy is uniquely adapted for unidirectional solidification to provide the structure defined as an aligned cellular dendritic structure.
  • an article having such a structure and made 4 consists essentially of 3-8 Co, 4-9 Cr, 8-14 Al, 1-4 Ta, l-7 V, 0.5- and more preferably 0.5-3 Re, up to about 2 W, up to about 1 each of Mo, Mn and Rh, with the balance essentially Ni and incidental impurities.
  • Table 1 lists the compositions of selected forms of such alloy within the preferred range of the present invention and Table II lists some of each form s mechanical property data. None of the elements C, Ti, B or Zr, usually found in nickel-base superalloys, were 10 added and are to be specifically avoided, except in impurity amounts, according to the present invention. Unless otherwise specified throughout this specification, all compositions are in atomic percent.
  • FIGS. 1 and 2 are photomicrographs at magnifications of example 105, typical of the microstructure of the present invention. They show the aligned cellular dendritic structure which resulted from unidirectional solidification, FIG.
  • FIG. 1 being in the transverse direction and FIG. 2 being in the longitudinal direction.
  • FIG. 2 being in the longitudinal direction.
  • the elongated dendrites are more clearly shown in FIG. 2.
  • the absence of the dark NiAl phase. shown in FIG. 4, to be discussed later, is particularly evident in FIGS. 1 and 2.
  • NiAl phase is dramatically detrimental to stress rupture properties and hence one of the important characteristics of the present invention is that no NiAl is present in the alloys microstructure.
  • Table II clearly shows the significantly improved stress rupture properties of the present invention at no sacrifice of tensile properties even though no carbide strengthening is present and the gamma prime strengthener Ti has not been included as an al loying addition.
  • the present invention specifically excludes the alloying addition of the elements C. Ti. B and Zr.
  • the element C although it plays a significant part in ordinary nickel-base superalloys in the carbide strengthening mechanism, can provide a source for crack initiation. lts elimination, except perhaps as an impurity in very small amounts. defines the alloy associated with the present invention as a different kind than the more classical types of nickel-base superalloys.
  • the elements Zr and B can function in nickel-base superalloys as grain boundary modifiers but have a tendency to lower melting temperature. Therefore, Zr and B are not included as alloying additions in the present invention and are present only as residual elements which can be picked up during normal melting practices. For example, up to about 0.03 percent Zr and up to about 0.01 percent B, by weight, can be tolerated by the present invention without seriously affecting its characteristics.
  • FIG. 3 of the drawings is a photomicrograph at 100 magnifications in the transverse direction of the example 87 after unidirectional solidification.
  • FIG. 3 shows the presence of large amounts of the gammagamma prime eutectic which is the lighter constituent in the photomicrograph.
  • the incipient melting temper- (omposition (Atomic '6 1 Base: 3.5 (1). 12.7 Al. Balance Ni ature of example 87 is about 2250F or at least about F lower than that of the present invention.
  • Al because of the virtual elimination of the strong gamma prime former Ti, a relatively large amount of Al, which in itselfis a strong gamma prime former, is included in the alloy composition associated with the present invention. In this type of alloy, less than 5 at. percent Al does not form sufficient gamma prime and therefore leads to a weak structure. Greater than about 16 at. percent Al, even with a careful balance of other elements, tends to drop out NiAl or excess eutectic and in some alloys tends to reduce incipient melting temperature. In addition to its being a strong gamma prime former, Al also improves oxidation resistance. Its preferred range is 8-14 at. percent.
  • V a gamma prime former without titaniums tendency toward the formation of the gamma-gamma prime eutectic phase which can lower melting temperature.
  • V also provides some solid solution strengthening.
  • V is included in the range of up to 10 percent although l-7 percent is preferred. Greater than about 10 percent will have a tendency toward the rejection of NiAl and thus dramatically reduce stress rupture properties. When higher strength is desired, it is specifically preferred that V be included in the range of about 4-7 at. percent.
  • Re for solid solution strengthening and precipitation hardening. It affects both the gamma prime precipitate as well as the gamma matrix. At least 0.5 at. percent Re, equivalent to at least about 1.5 percent Re by weight, is required for its significant effect in strengthening the matrix, particularly to increase high temperature stress rupture life. In addition, it also affects the gamma prime in that it has a tendency to force hardeners such as Ta and V into the gamma prime. In addition to this function, Re can substitute in amounts up to about 2.5 at. percent for such elements as W, Mn, Ta, Mo, and Cr, all of which tend to partition between the gamma prime precipitate and the gamma matrix. Thus.
  • Re is included in the present invention within the range of 0.5-5 at. percent and preferably in the range of 0.5-3 percent. As shown by the examples of the following Table III, Re in the specific range of 05-2 at. percent is particularly desirable for increasing high temperature stress rupture properties and while considering alloy cost. Comparison of example 123 with example 1 10 shows that the absence of Re is not compensated for by an increase in W to maintain the 1800F stress rupture properties of example 123.
  • Ta in the type of alloy to which the present invention relates partitions between the gamma prime precipitate and the gamma matrix.
  • it is both a gamma prime former as well as a solid solution strengthener.
  • it has a tendency to increase incipient melting temperature.
  • W and Mo Two elements which act similarly to Ta are W and Mo. Although W can be included up to about 5 at. percent. it is preferred that such element be maintained in the range of up to about 2 percent for improved properties.
  • Mo which can be included up to about 1 at. percent, in the absence of Ti will partition to gamma prime. However, it has a tendency to impair corrosion and oxidation resistance. Therefore, it is included only up to about 1 at. percent.
  • Cr which can be included in the range of about 4-1 1 at. percent and preferably in the range of about 4-9 at. percent. Less than 4 percent insufficient for oxidation resistance; greater than 11 percent tends to introduce alloy instability. At such higher levels, the alloy is either too weak or is unstable. Therefore, it is preferred that Cr be included in the range of 4-9 at. percent with higher amounts being tolerable provided other elements, within the range of the present inven- Photomicrographic studies of the examples of Table IV showed that only examples 144, 145 and 148 exhibited the undesirable NiAl structure. The dramatic difference in properties can be seen from the stress rupture data presented in Table IV. Referring to the drawings, FIG.
  • Example 4 is a photomicrograph at 100 magnifications in the transverse direction of the structure of example 145 showing a large amount of the dark NiAl detrimental phase which produced the dramatic reduction in stress rupture properties in examples 144, I45 and 148 even though example 148 included 2 at. percent Re.
  • the present invention is characterized by the absence of NiAl in its microstructurewhich also has the aligned cellular dentrites.
  • the element Co can be included in the present invention as a substitute for nickel in an amount up to about 15 at. percent. It has a slight tendency toward the increase of melting temperature and lowers the stacking fault energy. Preferably, Co is included in the range of about 38 at. percent.
  • Mn and Rh can be included as partial substitutes for Re in the present invention. However, they are not as effective as is Re. Each of Mn and Rh can be included within the present invention in amounts up to 2.5 at. percent but preferably are included in amounts up to l at. percent each. The effect of additions of Mn, Rh 'and M0 at various levels of Re is shown in Table V.
  • the present invention provides a different kind of alloy which is particularly useful in the formation of articles having improved high temperature properties as a result of the combination of the balance of elements and the processing to provide aligned cellular dendrites in the articles microstructure.
  • Ordinary nickel-base superalloys include carbon which is then available for the formation of various types of carbides.
  • the strength mechanism and microstructure of such ordinary alloy heavily involves carbide formation and accumulation at various points in the microstucture.
  • the literature in respect to nickel-base superalloys includes very complete discussions of this type of microstructure and its problems and benefits based on carbides.
  • NiAl which is sometimes called beta phase
  • beta phase is dramatically destructive toward stress rupture properties; the gamma-gamma p'rime eutectic tends to lower incipient melting temperature and hence it is to be maintained at as low a level as is practical.
  • the type of alloy involved with the present invention must include significantly larger or different alloying additions to strengthen both the gamma prime intermetallic precipitate as well as the gamma matrix while removing the tendency toward NiAl formation and reducing the gamma-gamma prime eutectic formation.
  • the present invention adds as much Al and Cr as possbile while maintaining such stability and balancing the alloys stability with other alloying additions to avoid the formation of NiAl.
  • the cast article of the present invention is characterized not only by its aligned cellular dendritic structure and the absence of carbides and NiAl, but also by the fact that it does not include alloying additions of Ti, Zr and B normally added to nickel-base superalloys. In addition, it includes ralatively large amounts of Re which has been found to provide improved strength both for the gamma matrix as well as for the gamma prime precipitate. Because the alloy has a narrower solidusliquidus range, it is easier to process by unidirectional solidification and therefore such processing can be conducted at higher rates. lts improved stress rupture properties are attained without a sacrifice of tensile properties which are as good or better than ordinary superalloy tensile strength and ductilities.
  • a cast Ni-base superalloy article the microstructure of which comprises aligned cellular dendrites and is characterized by the substantial absence of NiAl, carbon, carbides and Ti, the superalloy consisting, in atomic percent, essentially of 4-1 l Cr, 5-16 A1, about 0.5-5 Re, up to about 10 V, up to about 15 Co, up to about 5 Ta, up to about 5 W, up to about 1 Mo, up to about 2.5 Mn, up to about 2.5 Rh, with the balance essentially nickel and incidental impurities.
  • the article of claim 1 in which the superalloy consists, in atomic percent, essentially of 3-8 Co, 4-9 Cr, 8-14 Al, 1-4 Ta, 1-7 V, 0.5-5 Re, up to about 2 W, up to about 1 Mo, up to about 1 Mn, up to about 1 Rh, with the balance essentially nickel and incidental impurities.
  • a cast Ni base superalloy characterized by the substantial absence of NiAl, carbon, carbides and Ti and consisting, in atomic percent, essentially of 4-11 Cr, 5-16 Al, about 0.5-5 Re, up to about 10 V, up to about 15 Co, up to about 5 Ta, up to about 5 W, up to about 1 Mo, up to about 2.5 Mn, up to about 2.5 Rh, with the balance essentially nickel and incidental impurities.
  • the alloy of claim 5 consisting, in atomic percent, essentially of 3-8 Co, 4-9 Cr, 8-14 Al, l-4 Ta, 1-7 V, 0.5-5 Re, up to about 2 W, up to about 1 Mo, up to about 1 Mn, up to about 1 Rh, with the balance essentially nickel and incidental impurities.
  • the alloy of claim 7 consisting, in atomic percent, essentially of 3-4 Co, 5-9 Cr, 11-13 Al, l-3 Ta, 5-6 V, 0.5-2 Re, up to 1.5 W, up to 1 Mo, up to 0.5 Mn, with the balance nickel and incidental impurities.

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)
  • Manufacture And Refinement Of Metals (AREA)
US426092A 1973-12-18 1973-12-18 Nickel-base superalloy cast article Expired - Lifetime US3887363A (en)

Priority Applications (8)

Application Number Priority Date Filing Date Title
US426092A US3887363A (en) 1973-12-18 1973-12-18 Nickel-base superalloy cast article
GB2991674A GB1473134A (fr) 1973-12-18 1974-07-05
CA215,680A CA1053482A (fr) 1973-12-18 1974-12-09 Article coule en superalliage a base de nickel
DE19742458540 DE2458540A1 (de) 1973-12-18 1974-12-11 Gegossener artikel aus einer superlegierung auf nickelbasis
IT30578/74A IT1027700B (it) 1973-12-18 1974-12-16 Perfezionato articolo in getto di superlega a base di nichel
JP49144123A JPS5095122A (fr) 1973-12-18 1974-12-17
BE151573A BE823437A (fr) 1973-12-18 1974-12-17 Super-alliage a base de nickel
FR7441455A FR2254651B1 (fr) 1973-12-18 1974-12-17

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US426092A US3887363A (en) 1973-12-18 1973-12-18 Nickel-base superalloy cast article

Publications (1)

Publication Number Publication Date
US3887363A true US3887363A (en) 1975-06-03

Family

ID=23689251

Family Applications (1)

Application Number Title Priority Date Filing Date
US426092A Expired - Lifetime US3887363A (en) 1973-12-18 1973-12-18 Nickel-base superalloy cast article

Country Status (8)

Country Link
US (1) US3887363A (fr)
JP (1) JPS5095122A (fr)
BE (1) BE823437A (fr)
CA (1) CA1053482A (fr)
DE (1) DE2458540A1 (fr)
FR (1) FR2254651B1 (fr)
GB (1) GB1473134A (fr)
IT (1) IT1027700B (fr)

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2406001A1 (fr) * 1977-10-17 1979-05-11 Gen Electric Alliage perfectionne a base de nickel et piece coulee obtenue a partir de cet alliage
US4169742A (en) * 1976-12-16 1979-10-02 General Electric Company Cast nickel-base alloy article
US4765850A (en) * 1984-01-10 1988-08-23 Allied-Signal Inc. Single crystal nickel-base super alloy
US4935072A (en) * 1986-05-13 1990-06-19 Allied-Signal, Inc. Phase stable single crystal materials
US6468368B1 (en) * 2000-03-20 2002-10-22 Honeywell International, Inc. High strength powder metallurgy nickel base alloy
US20050281704A1 (en) * 2004-06-21 2005-12-22 Siemens Westinghouse Power Corporation Boron free joint for superalloy component
US20100196191A1 (en) * 2009-02-05 2010-08-05 Honeywell International Inc. Nickel-base superalloys
KR20150044879A (ko) 2012-08-09 2015-04-27 도쿠리츠교세이호징 붓시쯔 자이료 겐큐키코 Ni기 단결정 초합금

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1979000343A1 (fr) * 1977-12-05 1979-06-14 Secr Defence Ameliorations aux alliages a base de nickel cobalt et fer, ou s'y rapportant
SE452633B (sv) * 1978-03-03 1987-12-07 Johnson Matthey Co Ltd Nickelbaslegering med gammaprimfasmatris
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
US4313760A (en) * 1979-05-29 1982-02-02 Howmet Turbine Components Corporation Superalloy coating composition
US4339509A (en) 1979-05-29 1982-07-13 Howmet Turbine Components Corporation Superalloy coating composition with oxidation and/or sulfidation resistance
JP5146867B2 (ja) * 2006-08-18 2013-02-20 独立行政法人物質・材料研究機構 高温耐久性に優れた耐熱部材

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3526499A (en) * 1967-08-22 1970-09-01 Trw Inc Nickel base alloy having improved stress rupture properties

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3526499A (en) * 1967-08-22 1970-09-01 Trw Inc Nickel base alloy having improved stress rupture properties

Cited By (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4169742A (en) * 1976-12-16 1979-10-02 General Electric Company Cast nickel-base alloy article
FR2406001A1 (fr) * 1977-10-17 1979-05-11 Gen Electric Alliage perfectionne a base de nickel et piece coulee obtenue a partir de cet alliage
US4765850A (en) * 1984-01-10 1988-08-23 Allied-Signal Inc. Single crystal nickel-base super alloy
US4935072A (en) * 1986-05-13 1990-06-19 Allied-Signal, Inc. Phase stable single crystal materials
US6468368B1 (en) * 2000-03-20 2002-10-22 Honeywell International, Inc. High strength powder metallurgy nickel base alloy
US20050281704A1 (en) * 2004-06-21 2005-12-22 Siemens Westinghouse Power Corporation Boron free joint for superalloy component
US7641985B2 (en) * 2004-06-21 2010-01-05 Siemens Energy, Inc. Boron free joint for superalloy component
US20100196191A1 (en) * 2009-02-05 2010-08-05 Honeywell International Inc. Nickel-base superalloys
US8216509B2 (en) 2009-02-05 2012-07-10 Honeywell International Inc. Nickel-base superalloys
KR20150044879A (ko) 2012-08-09 2015-04-27 도쿠리츠교세이호징 붓시쯔 자이료 겐큐키코 Ni기 단결정 초합금
US9816161B2 (en) 2012-08-09 2017-11-14 Mitsubishi Hitachi Power Systems, Ltd. Ni-based single crystal superalloy

Also Published As

Publication number Publication date
JPS5095122A (fr) 1975-07-29
DE2458540A1 (de) 1975-06-19
CA1053482A (fr) 1979-05-01
FR2254651B1 (fr) 1977-07-08
GB1473134A (fr) 1977-05-11
BE823437A (fr) 1975-04-16
IT1027700B (it) 1978-12-20
FR2254651A1 (fr) 1975-07-11

Similar Documents

Publication Publication Date Title
US3887363A (en) Nickel-base superalloy cast article
US5154884A (en) Single crystal nickel-base superalloy article and method for making
US8226886B2 (en) Nickel-based superalloys and articles
JP2881626B2 (ja) 単結晶ニッケル・ベース超合金
US4388124A (en) Cyclic oxidation-hot corrosion resistant nickel-base superalloys
US5104614A (en) Superalloy compositions with a nickel base
US3869284A (en) High temperature alloys
US3904402A (en) Composite eutectic alloy and article
USRE29920E (en) High temperature alloys
US3164465A (en) Nickel-base alloys
JPWO2006059805A1 (ja) 耐熱超合金
US6054096A (en) Stable heat treatable nickel superalloy single crystal articles and compositions
JPH0323613B2 (fr)
US3567526A (en) Limitation of carbon in single crystal or columnar-grained nickel base superalloys
US3030206A (en) High temperature chromiummolybdenum alloy
US3293030A (en) Nickel-base alloys
US4284430A (en) Cyclic oxidation resistant transverse ductile fiber reinforced eutectic nickel-base superalloys
US5516380A (en) NiAl intermetallic alloy and article with improved high temperature strength
EP0593824A1 (fr) Alliages monocristallins à base d'aluminure de nickel et méthode
US4126495A (en) Nickel-base superalloy
US3937628A (en) Solid-solution strengthened austenitic alloys
US5330711A (en) Nickel base alloys for castings
USRE28681E (en) High temperature alloys
US3793012A (en) Nickel-base tantalum carbide eutectic alloys
US4684505A (en) Heat resistant alloys with low strategic alloy content