EP2913417B1 - Article et procédé de formation d'un article - Google Patents

Article et procédé de formation d'un article Download PDF

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Publication number
EP2913417B1
EP2913417B1 EP15156338.4A EP15156338A EP2913417B1 EP 2913417 B1 EP2913417 B1 EP 2913417B1 EP 15156338 A EP15156338 A EP 15156338A EP 2913417 B1 EP2913417 B1 EP 2913417B1
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EP
European Patent Office
Prior art keywords
article
composition
hafnium
chromium
rhenium
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EP15156338.4A
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German (de)
English (en)
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EP2913417A1 (fr
Inventor
Ganjiang Feng
Michael Douglas Arnett
Shan Liu
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General Electric Co
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General Electric Co
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Priority to PL15156338T priority Critical patent/PL2913417T3/pl
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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
    • 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%
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22D—CASTING OF METALS; CASTING OF OTHER SUBSTANCES BY THE SAME PROCESSES OR DEVICES
    • B22D18/00—Pressure casting; Vacuum casting
    • B22D18/04—Low pressure casting, i.e. making use of pressures up to a few bars to fill the mould
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22D—CASTING OF METALS; CASTING OF OTHER SUBSTANCES BY THE SAME PROCESSES OR DEVICES
    • B22D21/00—Casting non-ferrous metals or metallic compounds so far as their metallurgical properties are of importance for the casting procedure; Selection of compositions therefor
    • B22D21/02—Casting exceedingly oxidisable non-ferrous metals, e.g. in inert atmosphere
    • B22D21/025—Casting heavy metals with high melting point, i.e. 1000 - 1600 degrees C, e.g. Co 1490 degrees C, Ni 1450 degrees C, Mn 1240 degrees C, Cu 1083 degrees C
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22D—CASTING OF METALS; CASTING OF OTHER SUBSTANCES BY THE SAME PROCESSES OR DEVICES
    • B22D25/00—Special casting characterised by the nature of the product
    • B22D25/02—Special casting characterised by the nature of the product by its peculiarity of shape; of works of art
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22F—CHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS AND NON-FERROUS ALLOYS
    • C22F1/00—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
    • C22F1/10—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of nickel or cobalt or alloys based thereon
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/005—Selecting particular materials
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • F01D5/282—Selecting composite materials, e.g. blades with reinforcing filaments

Definitions

  • the present invention is directed to an article and a method for forming an article. More specifically, the present invention is directed to an article and a method for forming an article including an equiaxed grain structure and a composition.
  • Hot gas path components of gas turbines and aviation engines operate at elevated temperatures, often in excess of 2,000 °F.
  • the superalloy compositions used to form hot gas path components are often single-crystal compositions incorporating significant amounts of rhenium (Re) due to the elevated temperatures and other operating conditions components are exposed to in the first stage.
  • Such superalloy compositions typically contain one to three percent, by weight, rhenium (Re), and some may incorporate up to six percent, by weight, rhenium (Re).
  • N2Re includes, by weight percent, 6.0% to 9.0% aluminum (Al), up to 0.5% titanium (Ti), 4.0% to 6.0% tantalum (Ta), 12.5% to 15.0% chromium (Cr), 3.0% to 10.0% cobalt (Co), up to 0.25% molybdenum (Mo), 2.0% to 5.0% tungsten (W), up to 1.0% silicon (Si), up to 0.2% hafnium (Hf), 1.0% to 3.0% rhenium (Re), and balance nickel (Ni) and incidental impurities.
  • N2Re may also include up to 0.01% boron (B), up to 0.07% carbon (C), up to 0.03% zirconium (Zr), and up to 0.1% lanthanum (La).
  • B boron
  • C carbon
  • Zr zirconium
  • La lanthanum
  • One example of a composition that falls within the ranges of N2Re may include the alloy commercially unavailable under the trade name "René N2" (available from General Electric Company).
  • Document EP 0 684 321 A1 describes a hot corrosion resistant single crystal nickel-based superalloy comprising among others, by weight percent, 11.5% to 13.5% chromium (Cr), 3.4% -3.8% aluminium (Al), 4.0% to 4.4% titanium (Ti) and 4.5% to 5.8% tantalum (Ta), further comprising 0-0.25% rhenium (Re), and having a phasial stability number N V3B less than about 2.45.
  • Cr chromium
  • Al aluminium
  • Ti titanium
  • Ta tantalum
  • Re rhenium
  • R108 includes, by weight percent, 5.25% to 5.75% Aluminum (Al), 0.6% to 0.9% Titanium (Ti), 2.8% to 3.3% Tantalum (Ta), 8.0% to 8.7% Chromium (Cr), 9.0% to 10.0% Cobalt (Co), 0.4% to 0.6% Molybdenum (Mo), 9.3% to 9.7% Tungsten (W), up to 0.12% Silicon (Si), 1.3% to 1.7% Hafnium (Hf), 0.01% to 0.02% Boron (B), up to 0.1% Carbon (C), 0.005% to 0.02% Zirconium (Zr), up to 0.2% Iron (Fe), up to 0.1% Manganese (Mn), up to 0.1% Copper (Cu), up to 0.01% Phosphorous (P), up to 0.004% Sulfur (S), up to 0.1% Niobium (Nb), and balance of nickel (N
  • compositions that falls within the ranges of R108 may include the alloy commercially unavailable under the trade name "René 108." Under testing conditions of 2,000 °F in a burner rig, an article formed from R108 forms an unstable oxide scale on the surface due to the low content of chromium.
  • R108 and N2Re have comparable high temperature mechanical properties, but R108 has significantly inferior hot corrosion resistance and oxidation resistance in comparison with N2Re. As a result, R108 is unsuitable for making first stage hot gas path components for either heavy duty gas turbine or aviation engines.
  • Single-crystal superalloys incorporating rhenium (Re), such as René N5, René N6 and René N2 may provide highly desirable properties for gas turbine or aviation engine applications, including good strength, ductility, creep lifetime, low-cycle fatigue lifetime, oxidation resistance and hot corrosion resistance under gas turbine or aviation engine operating conditions.
  • rhenium (Re) is among the most expensive of metals and the processing of single-crystal parts is typically time-consuming and costly, making rhenium (Re)-containing single-crystal superalloys economically undesirable.
  • the invention encompasses an article made of an alloy which includes an equiaxed grain structure and a composition, wherein the composition includes, by weight percent, 6.0% to 9.0% aluminum (Al), up to 0.5% titanium (Ti), 2.5% to 4.5% tantalum (Ta), 10.0% to 12.5% chromium (Cr), 5.0% to 10.0% cobalt (Co), 0.30% to 0.80% molybdenum (Mo), 2.0% to 5.0% tungsten (W), up to 1.0% silicon (Si), 0.35% to 0.60% hafnium (Hf), 0.005% to 0.010% boron (B), 0.06% to 0.10% carbon (C), up to 0.02% zirconium (Zr), up to 0.1% lanthanum (La), up to 0.03% yttrium (Y), and balance nickel (Ni) and incidental impurities, and wherein rhenium (Re), if present, is a trace element in an amount of less than 0.01%, by weight, of the composition.
  • the invention further encompasses a method for forming an article which includes providing a composition and forming the article.
  • the composition includes, by weight percent, 6.0% to about 9.0% aluminum (Al), up to 0.5% titanium (Ti), 2.5% to 4.5% tantalum (Ta), 10.0% to 12.5% chromium (Cr), 5.0% to 10.0% cobalt (Co), 0.30% to 0.80% molybdenum (Mo), 2.0% to 5.0% tungsten (W), up to 1.0% silicon (Si), 0.35% to 0.60% hafnium (Hf), 0.005% to 0.010% boron (B), 0.06% to 0.10% carbon (C), up to 0.02% zirconium (Zr), up to 0.1% lanthanum (La), up to 0.03% yttrium (Y), up to 0.01% rhenium (Re), and balance nickel (Ni) and incidental impurities.
  • the article includes an equiaxed grain structure.
  • Embodiments of the present disclosure in comparison to methods and articles not using one or more of the features disclosed herein, increase corrosion resistance, increase oxidation resistance, lengthen low-cycle fatigue lifetime, increase creep lifetime, improve castability, increase phase stability at elevated temperatures, decrease cost, or a combination thereof.
  • Embodiments of the present disclosure enable the fabrication of hot gas path components of gas turbines and aviation engines with rhenium (Re)-free nicked-based superalloys having at least as advantageous properties at elevated temperatures as rhenium (Re)-containing nicked-based superalloys, as well as having an equiaxed grain structure.
  • the invention concerns an article made from an alloy which includes an equiaxed grain structure and a composition.
  • the composition includes, by weight percent, 6.0% to 9.0% aluminum (Al), up to 0.5% titanium (Ti), 2.5% to 4.5% tantalum (Ta), 10.0% to 12.5% chromium (Cr), 5.0% to 10.0% cobalt (Co), 0.30% to 0.80% molybdenum (Mo), 2.0% to 5.0% tungsten (W), up to 1.0% silicon (Si), 0.35% to 0.60% hafnium (Hf), 0.005% to 0.010% boron (B), 0.06% to 0.10% carbon (C), up to 0.02% zirconium (Zr), up to 0.1% lanthanum (La), up to 0.03% yttrium (Y), and balance nickel (Ni) and incidental impurities.
  • the composition is devoid of rhenium (Re) or includes rhenium (Re) as a trace element in an amount of less than 0.01%, by
  • the 2.5% to 4.5% tantalum (Ta) in the composition is completely or partially replaced by niobium (Nb) on a 1:1 molar basis. This substitution does not have any material effect on the castability or service properties of the article, but reduces the cost of the composition.
  • the composition includes, by weight percent: 6.2% to 6.5% aluminum (Al), up to 0.04% titanium (Ti), 3.9% to 4.3% tantalum (Ta), 12.0% to 12.5% chromium (Cr), 7.0% to 8.0% cobalt (Co), 0.40% to 0.75% molybdenum (Mo), 4.7% to 5.0% tungsten (W), 0.08% to 0.12% silicon (Si), 0.47% to 0.53% hafnium (Hf), 0.005% to 0.010% boron (B), 0.06% to 0.10% carbon (C), up to 0.02% zirconium (Zr), up to 0.1% lanthanum (La), up to 0.03% yttrium (Y), up to 0.01% rhenium (Re), and balance nickel (Ni) and incidental impurities.
  • Al aluminum
  • Ti titanium
  • Ta 3.9% to 4.3% tantalum
  • Cr 12.0% to 12.5%
  • Cr chromium
  • Co cobalt
  • Mo molybdenum
  • the article is a hot gas path component of a gas turbine or an aviation engine.
  • the hot gas path component is subjected to temperatures of at least about 2,000 °F.
  • the hot gas path component is selected from the group consisting of a blade, a vane, a nozzle, a seal and a stationary shroud.
  • the method for forming the article includes providing the composition and forming the article from the composition.
  • forming the article from the composition includes any suitable technique, including, but not limited to, casting, powder metallurgy and three-dimensional additive machining.
  • casting includes precision investment casting with variable pressure control.
  • precision investment casting with variable pressure control means a casting process described as follows. An ingot is heated by induction coils in a melting chamber to surface re-melting under a surface re-melting pressure. An inert gas is introduced into the melting chamber until a casting pressure is reached. The temperature is adjusted until a melt temperature is reached. When the ingot is fully converted into a melt, the melt is poured into a mold cavity under the inert gas at the casting pressure. The inert gas is maintained at the casting pressure until an article being cast solidifies. Other steps in a typical industrial casting process, such as pattern making, mold preparation and post-pour solidification, remain unchanged in precision investment casting with variable pressure control.
  • the precision investment casting with variable pressure control includes a surface re-melting pressure of 10 -3 atmospheres and an inert gas casting pressure of about 10 -2 atmospheres to about 10 -1 atmospheres.
  • the inert gas is argon (Ar).
  • precision investment casting with variable pressure control minimizes the loss of chromium (Cr) during melting and casting.
  • the operation of a hot gas path component of a gas turbine or an aviation engine at a temperature of at least about 2,000 °F typically requires a chromium (Cr) content, by weight, of at least about 12.0% in order to maintain hot corrosion resistance and oxidation resistance.
  • the composition is highly castable.
  • “highly castable” indicates that during casting of the composition into the article there is no lack of feeding on any fine structural features, such as surface enhancement dimples or thin ribs, solidification shrinkage is within acceptable parameters, and the article is essentially free of mold/metal or core/metal reactions.
  • the composition provides sufficiently high internal integrity such that the composition may be cast into a hot gas path component of a gas turbine or an aviation engine subjected to temperatures of at least about 2,000 °F without requiring the use of hot isostatic pressing.
  • Hot isostatic pressing is widely used in order to close the solidification shrinkage porosities inside a cast article and to improve the mechanical properties to meet requirements of a hot gas path component of a gas turbine or an aviation engine subjected to temperatures of at least about 2,000 °F. Eliminating a processing step of subjecting a cast article to hot isostatic pressing reduces the cost of producing the cast article.
  • the surface of an article formed from the composition according to the present disclosure forms a stable aluminum oxide-rich scale hot under operating conditions for the hot gas path of a gas turbine or an aviation engine.
  • the stable aluminum oxide-rich scale retards the diffusion of reactive species in the oxidative environment and improves the oxidation and hot corrosion capabilities of the composition according to the present disclosure.
  • the composition according to the present disclosure includes, by weight percent, 6.25% aluminum (Al), 4.0% tantalum (Ta), 12.5% chromium (Cr), 7.5% cobalt (Co), 0.5% molybdenum (Mo), 5.0% tungsten (W), 0.5% hafnium (Hf), 0.0075% Boron (B), 0.08% carbon (C), and balance nickel (Ni) and incidental impurities.
  • the high castability of the composition relative to R108 is exemplified by the comparison that an article formed from RNX according to the present disclosure undergoes 50% less solidification shrinkage during casting than does a corresponding article formed from R108.
  • the high castability of the composition is demonstrated by an article formed from RNX according to the present disclosure by precision investment casting with variable pressure control, wherein the article is a hot gas path component of a gas turbine, specifically a 48-pound nozzle.
  • the nozzle includes a plurality of very small dimples having complicated geometry, wherein the nozzle includes more than about 400 dimples per square inch on a curved internal surface.
  • the dimples are formed with a high degree of precision suitable for use under operating conditions.
  • the tensile properties, including yield strength, ultimate strength and ductility, of an article formed from RNX according to the present disclosure are at least comparable to the tensile properties of a corresponding article formed from N2Re.
  • an article formed from RNX according to the present disclosure has a low-cycle fatigue lifetime 20% greater, alternatively 18% to 22% greater, than a corresponding low-cycle fatigue lifetime exhibited by a corresponding article formed from N2Re, and 54% greater, alternatively 50% to 58% greater, than a corresponding low-cycle fatigue lifetime exhibited by a corresponding article formed from R108, under testing conditions of 1,800 °F and 0.6% strain with two minutes of hold time.
  • an article formed from RNX according to the present disclosure has a creep lifetime about 2.3 times greater, alternatively 2.0 to 2.6 times greater, than a corresponding creep lifetime exhibited by a corresponding article formed from N2Re, and28% greater, alternatively 25% to 31% greater, than a corresponding creep lifetime exhibited by a corresponding article formed from R108, under testing conditions of 1,800 °F and 20 ksi.
  • an article formed from RNX according to the present disclosure has an oxidation resistance about the same as a corresponding oxidation resistance exhibited by a corresponding article formed from N2Re, and 3 times greater, alternately 2.7 to 3.3 times greater, than a corresponding oxidation resistance exhibited by a corresponding article formed from R108.
  • an article formed from RNX according to the present disclosure has a hot corrosion resistance about the same as a corresponding hot corrosion resistance exhibited by a corresponding article formed from N2Re, and 2 times greater, alternately 1.8 to 3.2 times greater, than a corresponding hot corrosion resistance exhibited by a corresponding article formed from R108.
  • FIG. 4 a comparison is shown of the oxidation layer depth for an article formed from RNX according to the present disclosure and a corresponding article formed from R108 under testing conditions of 2,000 °F for up to 4,000 hours in a burner rig.
  • an article formed from RNX according to the present disclosure includes a composition depletion depth 502, and a corresponding article formed from R108 ( FIG. 6 ) having an equiaxed grain structure includes an R108 depletion depth 602.
  • the article formed from RNX undergoes surface depletion at about one-half the rate, alternatively about one-quarter to about three-quarters, of the corresponding article formed from R108.
  • depletion means the disappearance of a coherent strengthening phase gamma prime ( ⁇ ').
  • the chemical formula for ⁇ ' is Ni 3 (Al,Ti,Ta).
  • the RNX includes a weakened matrix resulting in a significantly reduced load-bearing capability.
  • the significantly reduced load-bearing capability may lead to premature failures when an article is subjected to operating conditions. Therefore, narrowed depletion zone for an article formed from RNX according to the present disclosure represents a remarkable improvement as compared to a corresponding articled formed from R108 when the article is a hot gas path component of a gas turbine or an aviation engine.
  • hafnium (Hf) is highly reactive with oxygen, and the higher concentration of hafnium (Hf) in R108 as compared to RNX (approximately 3-fold higher) promotes hafnium (Hf) segregation during solidification of an article in a casting process, which results in more severe pitting in articles formed from alloys with higher concentrations of hafnium (Hf) (such as R108) as compared to RNX.

Claims (12)

  1. Article comprenant une structure de grain équiaxe et une composition, la composition comprenant, en pourcent en poids :
    6,0 % à 9,0 % d'aluminium (Al) ;
    jusqu'à 0,5 % de titane (Ti) ;
    2,5 % à 4,5 % de tantale (Ta), qui en option est remplacé en totalité ou en partie par le niobium (Nb) sur une base 1:1 en moles ;
    10,0 % à 12,5 % de chrome (Cr) ;
    5,0 % à 10,0 % de cobalt (Co) ;
    0,30 % à 0,80 % de molybdène (Mo) ;
    2,0 % à 5,0 % de tungstène (W) ;
    jusqu'à 1,0 % de silicium (Si) ;
    0,35 % à 0,60 % de hafnium (Hf) ;
    0,005 % à 0,010 % de bore (B) ;
    0,06 % à 0,10 % de carbone (C) ;
    jusqu'à 0,02 % de zirconium (Zr) ;
    jusqu'à 0,1 % de lanthane (La) ;
    jusqu'à 0,03 % d'yttrium (Y) ; et
    le reste étant constitué de nickel (Ni) et des impuretés inévitables, et
    dans lequel le rhénium (Re), s'il est présent, est un élément-trace en une quantité inférieure à 0,01 % en poids par rapport à la composition.
  2. Article selon la revendication 1, dans lequel la composition comprend, en pourcent en poids :
    6,2 % à 6,5 % d'aluminium (Al) ;
    jusqu'à 0,04 % de titane (Ti) ;
    3,9 % à 4,3 % de tantale (Ta) qui en option est en totalité ou en partie remplacé par le niobium (Nb) sur une base 1:1 en moles ;
    12,0 % à 12,5 % de chrome (Cr) ;
    7,0 % à 8,0 % de cobalt (Co) ;
    0,40 % à 0,75 % de molybdène (Mo) ;
    4,7 % à 5,0 % de tungstène (W) ;
    0,08 % à 0,12 % de silicium (Si) ;
    0,47 % à 0,53 % de hafnium (Hf) ;
    0,005 % à 0,010 % de bore (B) ;
    0,06 % à 0,10 % de carbone (C) ;
    jusqu'à 0,02 % de zirconium (Zr) ;
    jusqu'à 0,1 % de lanthane (La) ;
    jusqu'à 0,03 % d'yttrium (Y) ;
    jusqu'à 0,01 % de rhénium (Re) ; et
    le reste étant constitué de nickel (Ni) et des impuretés inévitables.
  3. Article selon l'une quelconque des revendications précédentes, l'article étant un composant pour la trajectoire des gaz chauds d'une turbine à gaz ou d'un moteur d'aviation.
  4. Article selon la revendication 3, le composant pour la trajectoire des gaz chauds étant choisie dans le groupe consistant en une pale, une aube, un joint et un carénage fixe.
  5. Article selon l'une quelconque des revendications précédentes, dans lequel la composition de l'article possède une résistance à l'oxydation, la résistance à l'oxydation étant 2 à 4 fois plus grande qu'une résistance à l'oxydation correspondante présentée par une composition correspondante de R108, R108 comprenant, en pourcent en poids, 5,25 % à 5,75 % d'aluminium (Al), 0,6 % à 0,9 % de titane (Ti), 2,8 % à 3,3 % de tantale (Ta), 8,0 % à 8,7 % de chrome (Cr), 9,0 % à 10,0 % de cobalt (Co), 0,4 % à 0,6 % de molybdène (Mo), 9,3 % à 9,7 % de tungstène (W), jusqu'à 0,12 % de silicium (Si), 1,3 % à 1,7 % de hafnium (Hf), 0,01 % à 0,02 % de bore (B), jusqu'à 0,1 % de carbone (C), 0,005 % à 0,02 % de zirconium (Zr), jusqu'à 0,2 % de fer (Fe), jusqu'à 0,1 % de manganèse (Mn), jusqu'à 0,1 % de cuivre (Cu), jusqu'à 0,01 % de phosphore (P), jusqu'à 0,004 % de soufre (S), jusqu'à 0,1 % de niobium (Nb), et le reste étant constitué de nickel (Ni) et des impuretés inévitables ; et/ou
    la composition de l'article ayant une durée de vie en fatigue oligocyclique, la durée de vie en fatigue oligocyclique étant de 18 % à 22 % plus grande qu'une durée de vie en fatigue oligocyclique correspondante présentée par une composition correspondante de N2Re, N2Re comprenant, en pourcent en poids, 6,0 % à 9,0 % d'aluminium (Al), jusqu'à 0,5 % de titane (Ti), 4,0 % à 6,0 % de tantale (Ta), 12,5 % à 15,0 % de chrome (Cr), 3,0 % à 10,0 % de cobalt (Co), jusqu'à 0,25 % de molybdène (Mo), 2,0 % à 5,0 % de tungstène (W), jusqu'à 1,0 % de silicium (Si), jusqu'à 0,2 % de hafnium (Hf), 1,0 % à 3,0 % de rhénium (Re), jusqu'à 0,01 % de bore (B), jusqu'à 0,07 % de carbone (C), jusqu'à 0,03 % de zirconium (Zr), et jusqu'à 0,1 % de lanthane (La), et le reste étant constitué de nickel (Ni) et des impuretés inévitables ; et/ou
    la composition de l'article ayant une durée de vie en fluage, la durée de vie en fluage étant de 2,0 à 2,5 fois plus grande qu'une durée de vie en fluage correspondante présentée par une composition correspondante dudit N2Re ; et/ou
    la composition de l'article ayant une résistance à la corrosion à chaud, la résistance à la corrosion à chaud étant de 1,5 à 2,5 fois plus grande qu'une résistance à la corrosion à chaud correspondante présentée par une composition correspondante dudit R108.
  6. Procédé de formation d'un article, comprenant :
    la fourniture d'une composition comprenant, en pourcent en poids
    6,0 % à 9,0 % d'aluminium (Al) ;
    jusqu'à 0,5 % de titane (Ti) ;
    2,5 % à 4,5 % de tantale (Ta), qui en option est remplacé en totalité ou en partie par le niobium (Nb) sur une base 1:1 en moles ;
    10,0 % à 12,5 % de chrome (Cr) ;
    5,0 % à 10,0 % de cobalt (Co) ;
    0,30 % à 0,80 % de molybdène (Mo) ;
    2,0 % à 5,0 % de tungstène (W) ;
    jusqu'à 1,0 % de silicium (Si) ;
    0,35 % à 0,60 % de hafnium (Hf) ;
    0,005 % à 0,010 % de bore (B) ;
    0,06 % à 0,10 % de carbone (C) ;
    jusqu'à 0,02 % de zirconium (Zr) ;
    jusqu'à 0,1 % de lanthane (La) ;
    jusqu'à 0,03 % d'yttrium (Y) ;
    jusqu'à 0,01 % de rhénium (Re) ; et
    le reste étant constitué de nickel (Ni) et des impuretés inévitables ; et
    le façonnage de l'article pour obtenir un article qui comprend une structure de grain équiaxe.
  7. Procédé selon la revendication 6, dans lequel la composition comprend, en pourcent en poids :
    6,2 % à 6,5 % d'aluminium (Al) ;
    jusqu'à 0,04 % de titane (Ti) ;
    3,9 % à 4,3 % de tantale (Ta);
    12,0 % à 12,5 % de chrome (Cr) ;
    7,0 % à 8,0 % de cobalt (Co) ;
    0,40 % à 0,75 % de molybdène (Mo) ;
    4,7 % à 5,0 % de tungstène (W) ;
    0,08 % à 0,12 % de silicium (Si) ;
    0,47 % à 0,53 % de hafnium (Hf) ;
    0,005 % à 0,010 % de bore (B) ;
    0,06 % à 0,10 % de carbone (C) ;
    jusqu'à 0,02 % de zirconium (Zr) ;
    jusqu'à 0,1 % de lanthane (La) ;
    jusqu'à 0,03 % d'yttrium (Y) ;
    jusqu'à 0,01 % de rhénium (Re) ; et
    le reste étant constitué de nickel (Ni) et des impuretés inévitables.
  8. Procédé selon la revendication 6 ou la revendication 7, dans lequel l'article est un composant pour la trajectoire des gaz chauds d'une turbine à gaz ou d'un moteur d'aviation.
  9. Procédé selon la revendication 8, dans lequel le composant pour la trajectoire des gaz chauds est choisi dans le groupe consistant en une pale, une aube, une buse, un joint et un carénage fixe.
  10. Procédé selon l'une quelconque des revendications 6 à 9, dans lequel le façonnage de l'article comprend la coulée, la métallurgie des poudres et l'usinage additif tridimensionnel.
  11. Procédé selon la revendication 10, dans lequel la coulée comprend une coulée de haute précision à régulation variable de la pression.
  12. Procédé selon la revendication 11, dans lequel la coulée de haute précision avec régulation variable de la pression comprend :
    une pression de re-fusion en surface de 10-3 atmosphères ; et
    une pression de coulée sous gaz inerte d'environ 10-2 atmosphères à environ 10-1 atmosphères.
EP15156338.4A 2014-02-28 2015-02-24 Article et procédé de formation d'un article Active EP2913417B1 (fr)

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JP (1) JP6699989B2 (fr)
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US11739398B2 (en) * 2021-02-11 2023-08-29 General Electric Company Nickel-based superalloy

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US3832167A (en) 1971-02-23 1974-08-27 Int Nickel Co Nickel alloy with good stress-rupture strength
US4152488A (en) 1977-05-03 1979-05-01 United Technologies Corporation Gas turbine blade tip alloy and composite
EP0683239A1 (fr) 1994-05-20 1995-11-22 United Technologies Corporation Superalliage à base de nickel résistant à l'oxydation
EP0684321A1 (fr) 1994-05-03 1995-11-29 Cannon-Muskegon Corporation Superalliage monocristallin à base de nickel résistant à la corrosion à haute température
US5523170A (en) 1994-12-28 1996-06-04 General Electric Company Repaired article and material and method for making
EP1076118A1 (fr) 1999-08-13 2001-02-14 ABB (Schweiz) AG Procédé et appareillage pour mouler une pièce à solidification directionnelle
EP1201778A2 (fr) 2000-10-30 2002-05-02 United Technologies Corporation Matériaux en superalliage résistant à l'oxydation et de faible densité capables de retenir un revêtement de barrière thermique sans couche de liaison
EP1375033A1 (fr) 2002-06-27 2004-01-02 Howmet Research Corporation Procédé de coulée de précision sous pression
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US3677747A (en) 1971-06-28 1972-07-18 Martin Marietta Corp High temperature castable alloys and castings
US4152488A (en) 1977-05-03 1979-05-01 United Technologies Corporation Gas turbine blade tip alloy and composite
EP0684321A1 (fr) 1994-05-03 1995-11-29 Cannon-Muskegon Corporation Superalliage monocristallin à base de nickel résistant à la corrosion à haute température
EP0683239A1 (fr) 1994-05-20 1995-11-22 United Technologies Corporation Superalliage à base de nickel résistant à l'oxydation
US5523170A (en) 1994-12-28 1996-06-04 General Electric Company Repaired article and material and method for making
EP1076118A1 (fr) 1999-08-13 2001-02-14 ABB (Schweiz) AG Procédé et appareillage pour mouler une pièce à solidification directionnelle
EP1201778A2 (fr) 2000-10-30 2002-05-02 United Technologies Corporation Matériaux en superalliage résistant à l'oxydation et de faible densité capables de retenir un revêtement de barrière thermique sans couche de liaison
EP1375033A1 (fr) 2002-06-27 2004-01-02 Howmet Research Corporation Procédé de coulée de précision sous pression
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B. GEDDES, ET AL.: "Superalloys - Alloying and Performance", November 2010, pages: 28, 29, 62 - 80, XP055431321

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US20150247220A1 (en) 2015-09-03
JP2015165048A (ja) 2015-09-17
JP6699989B2 (ja) 2020-05-27
EP2913417A1 (fr) 2015-09-02
HUE032320T2 (en) 2017-09-28
PL2913417T3 (pl) 2017-07-31

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