EP1319729B1 - High temperature resistant part, made of single-crystal or polycrystalline nickel-base superalloy - Google Patents

High temperature resistant part, made of single-crystal or polycrystalline nickel-base superalloy Download PDF

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Publication number
EP1319729B1
EP1319729B1 EP01129743A EP01129743A EP1319729B1 EP 1319729 B1 EP1319729 B1 EP 1319729B1 EP 01129743 A EP01129743 A EP 01129743A EP 01129743 A EP01129743 A EP 01129743A EP 1319729 B1 EP1319729 B1 EP 1319729B1
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Prior art keywords
component
weight
superalloy
rhenium
ruthenium
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EP01129743A
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German (de)
French (fr)
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EP1319729A1 (en
EP1319729A8 (en
Inventor
Ralf Prof. Buergel
Winfried Dr. Esser
Joern Dr. Grossmann
Wolfgang Dr. Hermann
Hael Prof. Mughrabi
Juergen Preuhs
Florian Pyczak
Alfred Dr. Scholz
Robert Prof. Singer
Andreas Volek
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Siemens AG
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Siemens AG
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Priority to DE50112339T priority Critical patent/DE50112339D1/en
Priority to EP01129743A priority patent/EP1319729B1/en
Priority to JP2002356858A priority patent/JP2003193161A/en
Priority to CA 2414019 priority patent/CA2414019A1/en
Publication of EP1319729A1 publication Critical patent/EP1319729A1/en
Publication of EP1319729A8 publication Critical patent/EP1319729A8/en
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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
    • C22C19/057—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W with the maximum Cr content being less 10%
    • 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%
    • 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

Definitions

  • US-PS-5,611,670 discloses a blade for a gas turbine.
  • the blade has a single crystal platform region and a single crystalline airfoil.
  • An attachment region of the blade is designed with a directionally solidified structure.
  • the blade is cast from a superalloy having in percent by weight the following composition: up to 0.2% carbon, 5-14% chromium, 4-7% aluminum, 2-15% tungsten, 0.5-5% titanium, bis to 3% niobium, up to 6% molybdenum, up to 12% tantalum, up to 10.5% cobalt, up to 2% hafnium, up to 4% rhenium, up to 0.035% boron, up to 0.035% zirconium and the rest Nickel.
  • These broad ranges are intended to indicate alloy compositions that are generally suitable for the proposed gas turbine blade, but do not exhibit a compositional range suitable for particular oxidation and corrosion resistance or strength.
  • US Pat. No. 5,122,206 discloses a nickel-base superalloy which has a particularly narrow coexistence zone for the solid and liquid phases and is therefore particularly suitable for a single crystal casting process.
  • the alloy has the following composition in weight percent: 10-30% chromium, 0.1-5% niobium, 0.1-8% titanium, 0.1-8% aluminum, 0.05-0.5% copper or instead Copper 0.1-3% tantalum, in the former case optionally also hafnium or rhenium with a content of 0.05-3% may be present and in the second case, instead of rhenium or hafnium 0.05-0.5% copper. Furthermore, optionally 0.05-3% molybdenum or tungsten may be provided.

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  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Crystals, And After-Treatments Of Crystals (AREA)

Description

Die Erfindung betrifft ein hochtemperaturbeständiges Bauteil aus einer Nickel-Basis-Superlegierung.The invention relates to a high temperature resistant component made of a nickel-based superalloy.

In der DE 23 33 775 B2 ist ein Verfahren zur Wärmebehandlung einer Nickellegierung beschrieben. Die Nickellegierung besteht aus bis zu 0,3 % Kohlenstoff, 11-15 % Chrom, 8-12 % Kobalt, 1-2,5 % Molybdän, 3-10 % Wolfram, 3,5-10 % Tantal, 3,5-4,5 % Titan, 3-4 % Aluminium, 0,005-0,025 % Bor, 0,05-0,4 % Zirkon und den Rest Nickel. Weiterhin sind 0,01-3 % Hafnium zusätzlich in der Legierung enthalten, wobei durch eine geeignete Wärmebehandlung eine blockartige Carbid-Ausbildung und eine feindisperse Ausscheidung einer Ni3(Al,Ti)-Phase. Ein Zusatz von Rhenium oder Ruthenium wird nicht angesprochen.In DE 23 33 775 B2 a process for the heat treatment of a nickel alloy is described. The nickel alloy consists of up to 0.3% carbon, 11-15% chromium, 8-12% cobalt, 1-2.5% molybdenum, 3-10% tungsten, 3.5-10% tantalum, 3.5- 4.5% titanium, 3-4% aluminum, 0.005-0.025% boron, 0.05-0.4% zirconium and the balance nickel. Further, 0.01-3% of hafnium is additionally contained in the alloy, and by a suitable heat treatment, a block-like carbide formation and a finely dispersed precipitation of a Ni 3 (Al, Ti) phase. An addition of rhenium or ruthenium is not addressed.

Die US-PS-5,611,670 offenbart eine Laufschaufel für eine Gasturbine. Die Laufschaufel weist einen einkristallinen Plattformbereich und ein einkristallines Schaufelblatt auf. Ein Befestigungsbereich der Schaufel ist mit einer gerichtet erstarrten Struktur ausgeführt. Die Schaufel ist aus einer Superlegierung gegossen, die in Gewichtsprozent folgende Zusammensetzung aufweist: bis zu 0,2 % Kohlenstoff, 5-14 % Chrom, 4-7 % Aluminium, 2-15 %Wolfram, 0,5-5 % Titan, bis zu 3 % Niob, bis zu 6 % Molybdän, bis zu 12 % Tantal, bis zu 10,5 % Kobalt, bis zu 2 % Hafnium, bis zu 4 % Rhenium, bis 0,035 % Bor, bis zu 0,035 % Zirkon und den Rest Nickel. Diese weiten Bereichsangaben dienen der Angabe von Legierungszusammensetzungen, die grundsätzlich für die vorgeschlagene Gasturbinenschaufel geeignet sind, zeigen aber keinen hinsichtlich einer besonderen Oxidations- undKorrosionsbeständigkeit oder Festigkeit geeigneten Zusammensetzungsbereich auf.US-PS-5,611,670 discloses a blade for a gas turbine. The blade has a single crystal platform region and a single crystalline airfoil. An attachment region of the blade is designed with a directionally solidified structure. The blade is cast from a superalloy having in percent by weight the following composition: up to 0.2% carbon, 5-14% chromium, 4-7% aluminum, 2-15% tungsten, 0.5-5% titanium, bis to 3% niobium, up to 6% molybdenum, up to 12% tantalum, up to 10.5% cobalt, up to 2% hafnium, up to 4% rhenium, up to 0.035% boron, up to 0.035% zirconium and the rest Nickel. These broad ranges are intended to indicate alloy compositions that are generally suitable for the proposed gas turbine blade, but do not exhibit a compositional range suitable for particular oxidation and corrosion resistance or strength.

In der EP 0 297 785 B1 ist eine Nickel-Basis-Superlegierung für Einkristalle offenbart. Die Superlegierung weist in Gewichtsprozent folgende Zusammensetzung auf: 6-15 % Chrom, 5-12 % Wolfram, 0,01-4 % Rhenium, 3-9 % Tantal, 0,5-2 % Titan, 4-7 % Aluminium und optional 0,5-3 % Molybdän. Mit dieser Superlegierung wird sowohl eine Hochtemperaturrissfestigkeit als auch eine Korrosionsbeständigkeit erreicht. Um die Korrosionsbeständigkeit nicht zu beeinträchtigen, darf der Titangehalt zwei Gewichtsprozent nicht überschreiten.EP 0 297 785 B1 discloses a nickel-base superalloy for single crystals. The superalloy has the following composition in weight percent: 6-15% chromium, 5-12% tungsten, 0.01-4% rhenium, 3-9% tantalum, 0.5-2% titanium, 4-7% aluminum, and optional 0.5-3% molybdenum. This superalloy achieves both high temperature crack resistance and corrosion resistance. In order not to affect the corrosion resistance, the titanium content must not exceed two percent by weight.

In der US-PS-5,122,206 ist eine Nickel-Basis-Superlegierung angegeben, die eine besonders schmale Koexistenzzone für die feste und flüssige Phase aufweist und damit besonders für einen Einkristallgießprozess geeignet ist. Die Legierung weist in Gewichtsprozent folgende Zusammensetzung auf: 10-30 % Chrom, 0,1-5 % Niob, 0,1-8 % Titan, 0,1-8 % Aluminium, 0,05-0,5 % Kupfer oder statt Kupfer 0,1-3 % Tantal, wobei im erstgenannten Fall optional auch Hafnium oder Rhenium mit einem Gehalt von 0,05-3 % vorhanden sein kann und im zweiten Fall auch statt Rhenium oder Hafnium 0,05-0,5 % Kupfer. Weiterhin können optional 0,05-3 % Molybdän oder Wolfram vorgesehen sein.US Pat. No. 5,122,206 discloses a nickel-base superalloy which has a particularly narrow coexistence zone for the solid and liquid phases and is therefore particularly suitable for a single crystal casting process. The alloy has the following composition in weight percent: 10-30% chromium, 0.1-5% niobium, 0.1-8% titanium, 0.1-8% aluminum, 0.05-0.5% copper or instead Copper 0.1-3% tantalum, in the former case optionally also hafnium or rhenium with a content of 0.05-3% may be present and in the second case, instead of rhenium or hafnium 0.05-0.5% copper. Furthermore, optionally 0.05-3% molybdenum or tungsten may be provided.

Die WO 01/09403 A1 zeigt eine Nickelbasislegierung mit 11 -13 % Chrom, 3 - 5% Wolfram, 0,5-2,5% Molybdän, 3 - 5% Aluminium 3 - 5 % Titan, 3 - 7% Tantal, 0 - 12 % Kobalt, 0 - 1% Niob 0 - 2 % Hafnium, 0 - 1% Zirkon, 0 - 0.05% Bor, 0 - 0.2 % Kohlenstoff, 1 - 5% Rhenium, 0 - 5% Ruthenium, Rest Nickel. Die durch Rhenium geförderte Bildung versprödender intermetallischer Phasen (Cr- und/ oder Re-haltige Ausscheidungen) führt zu einer Reduzierung der Lebensdauer, weil die Sprödphasen die Rissbildung fördern.WO 01/09403 A1 shows a nickel-based alloy with 11-13% chromium, 3-5% tungsten, 0.5-2.5% molybdenum, 3-5% aluminum 3-5% titanium, 3-7% tantalum. 0 - 12% cobalt, 0 - 1% niobium 0 - 2% hafnium, 0 - 1% zirconium, 0 - 0.05% boron, 0 - 0.2% carbon, 1 - 5% rhenium, 0 - 5% ruthenium, balance nickel. The rhenium-promoted formation of embrittling intermetallic phases (Cr- and / or Re-containing precipitates) leads to a reduction in the service life, because the brittle phases promote the formation of cracks.

Der Erfindung liegt die Aufgabe zugrunde, ein Bauteil aus einer Nickel-Basis-Superlegierung anzugeben, das besonders günstige Eigenschaften hinsichtlich einer Hochtemperaturfestigkeit, Oxidations- und Korrosionsbeständigkeit und Stabilität gegen duktilitätsmindernde Bildung intermetallischer Phasen über eine lange Lebensdauer aufweist.The invention has for its object to provide a component of a nickel-based superalloy, which has particularly favorable properties in terms of high temperature strength, oxidation and corrosion resistance and stability against ductility-reducing formation of intermetallic phases over a long life.

Erfindungsgemäß wird die auf ein Bauteil gerichtete Aufgabe gelöst durch Angabe eines hochtemperaturbeständigen Bauteils aus einer Nickel-Basis-Superlegierung gemäß Anspruch 1.According to the invention, the object directed to a component is achieved by specifying a high-temperature-resistant component made of a nickel-based superalloy according to claim 1.

Die Superlegierung-des angegebenen Bauteils ist in ihrer Zusammensetzung erstmalig so spezifiziert, daß für das Bauteil besonders günstige Eigenschaften hinsichtlich seiner Hochtemperaturfestigkeit, seiner Oxidations- und Korrosionsbeständigkeit und hinsichtlich einer Stabilität gegen die Bildung duktilitätsmindernder intermetallischer Phasen besteht. Über umfangreiche Versuche, die der Erfindung vorausgingen, konnte die angegebene spezielle Zusammensetzung ermittelt werden, mit der die gewünschten, oben genannten Eigenschaften in überraschend hohem Maße erfüllt werden. Insbesondere geht die Erfindung dabei von einer chromreichen Superlegierung aus, die eine erhöhte Festigkeit durch den Zusatz von Rhenium erhält. Die durch Rhenium geförderte Bildung versprödender intermetallischer Phasen (Cr- und/oder Re-haltige Ausscheidungen) wird durch einen Chromgehalt gemäß Anspruch 1 kontrolliert.For the first time, the superalloy of the specified component is specified in such a way that the component has particularly favorable properties with regard to its high-temperature strength, its oxidation and corrosion resistance and stability against the formation of ductile reducing intermetallic phases. Extensive experiments which preceded the invention, the specific composition specified could be determined, with which the desired properties mentioned above are met to a surprisingly high degree. In particular, the invention is based on a chromium-rich superalloy which obtains increased strength through the addition of rhenium. The rhenium-promoted formation of embrittling intermetallic phases (Cr- and / or Re-containing precipitates) is controlled by a chromium content according to claim 1.

Vorzugsweise beträgt der Rheniumgehalt mindestens zwei Gewichtsprozent.Preferably, the rhenium content is at least two percent by weight.

Bevorzugt enthält die Super-Legierung Ruthenium. Durch die Zugabe von Ruthenium kann insbesondere die Tendenz zur Ausbildung versprödender intermetallischer Phasen weiter verringert werden. Gerade bei einem Rheniumgehalt oberhalb von zwei Gewichtsprozent erweist sich die Zugabe von Ruthenium als günstig. Vorzugsweise ist dabei der maximale Rutheniumgehalt drei Gewichtsprozent und der minimale Rutheniumgehalt 0,1 Gewichtsprozent Gewichtsprozent. Bevorzugtermassen liegt der Kobaltgehalt der Superlegierung bei bis zu 12 Gewichtsprozent.The super alloy preferably contains ruthenium. In particular, the tendency to form embrittling intermetallic phases can be further reduced by the addition of ruthenium. Especially with a rhenium content above two percent by weight, the addition of ruthenium proves to be favorable. Preferably, the maximum ruthenium content is three weight percent and the minimum ruthenium content is 0.1 weight percent weight percent. The cobalt content of the superalloy is preferably up to 12 percent by weight.

Vorzugsweise enthält die Superlegierung höchstens ein Gewichtsprozent Niob.Preferably, the superalloy contains at most one weight percent niobium.

In der Superlegierung sind optional mindestens eines der folgenden Elemente enthalten:
0-2 Gew.-% Hafnium,
0-1 Gew.-% Zirkon,
0-0,05 Gew.-% Bor,
0-0,2 Gew.-% Kohlenstoff.The superalloy optionally contains at least one of the following elements:
0-2% by weight hafnium,
0-1 wt% zircon,
0-0.05 wt% boron,
0-0.2% by weight of carbon.

Überraschenderweise läßt sich auch durch Zugabe von Ruthenium und ohne einen Rheniumgehalt eine besonders hohe Hochtemperaturfestigkeit erreichen, wobei in der angegebenen Zusammensetzung gleichzeitig die Oxidations-/Korrosionsbeständigkeit ebenfalls hoch ist.Surprisingly, a particularly high high-temperature strength can also be achieved by addition of ruthenium and without a rhenium content, wherein the oxidation / corrosion resistance is also high in the specified composition at the same time.

Der Kobaltgehalt der Superlegierung ist geringer als 12 Gewichtsprozent, während der Niobgehalt bei höchstens einem Gewichtsprozent liegt. In der Superlegierung sind 0-2 Gewichtsprozent Hafnium und/oder 0-1 Gewichtsprozent Zirkon und/oder 0-0,05 Gewichtsprozent Bor und/oder 0-0,2 Gewichtsprozent Kohlenstoff enthalten.The cobalt content of the superalloy is less than 12 weight percent, while the niobium content is at most one weight percent. The superalloy contains 0-2% by weight of hafnium and / or 0-1% by weight of zirconium and / or 0-0.05% by weight of boron and / or 0-0.2% by weight of carbon.

Vorzugsweise weist das Bauteil eine gerichtet erstarrte Kornstruktur auf. In einer solchen gerichtet erstarrten Struktur sind die Korngrenzen im wesentlichen entlang einer Achse ausgerichtet. Damit ergibt sich eine besonders hohe Festigkeit entlang dieser Achse.Preferably, the component has a directionally solidified grain structure. In such a directionally solidified structure, the grain boundaries are aligned substantially along an axis. This results in a particularly high strength along this axis.

Bevorzugtermassen weist das Bauteil eine einkristalline Struktur auf. Durch die einkristalline Struktur werden festigkeitsmindernde Korngrenzen im Bauteil vermieden und es ergibt sich eine besonders hohe Festigkeit.Preferably, the component has a monocrystalline structure. Due to the monocrystalline structure strength-reducing grain boundaries are avoided in the component and there is a particularly high strength.

Vorzugsweise ist das Bauteil als eine Gasturbinenschaufel ausgebildet. Gerade eine Gasturbinenschaufel ist besonders hohen Anforderungen hinsichtlich einer Hochtemperaturfestigkeit und einer Oxidations-/Korrosionsbeständigkeit ausgesetzt.Preferably, the component is designed as a gas turbine blade. Especially a gas turbine blade is exposed to particularly high demands in terms of high temperature resistance and oxidation / corrosion resistance.

Die Erfindung wird in einem Ausführungsbeispiel näher erläutert.The invention will be explained in more detail in an embodiment.

Ein Ausführungsbeispiel der Erfindung ist ein hochtemperaturbeständiges Bauteil, ausgeführt als Gasturbinenschaufel. Die Gasturbinenschaufel weist ein Schaufelblatt, eine Plattform und einen Befestigungsbereich auf. Die Gasturbinenschaufel ist in einem Gießprozeß gerichtet erstarrt hergestellt, wodurch sich entlang einer Schaufelachse gerichtete Korngrenzen ergeben.An embodiment of the invention is a high temperature resistant component designed as a gas turbine blade. The gas turbine blade has an airfoil, a platform and a mounting area. The gas turbine blade is made directionally solidified in a casting process, resulting in grain boundaries along a blade axis.

Die Gasturbinenschaufel ist aus einer Nickel-Basis-Superlegierung gefertigt, die eine der vorteilhaften Zusammensetzungen aufweist.
Insbesondere ist ein Anteil von Cobalt zwischen 6 und 10% und ein Gehalt von Zirkonium zwischen 0 und 0.1% von Vorteil.The gas turbine blade is made of a nickel-base superalloy having one of the advantageous compositions.
In particular, a proportion of cobalt between 6 and 10% and a content of zirconium between 0 and 0.1% is advantageous.

Vorteilhafte Zusammensetzungen sind beispielsweise gegeben durch:

  • Cr: 10.25%, Mo: 1.85%, W:4.70, Co: 6.50%, Ti: 3.75%, Ta: 3.9%, Al: 3.3%, B: 0.0125%, Zr: 0.008%, Hf: <0.01%, Re: 1.5%, Rest Ni.
  • Cr: 9.00%, Mo: 1.85%, W:4.70, Co: 6.50%, Ti: 3.75%, Ta: 3.9%, Al: 3.3%, B: 0.0125%, Zr: 0.008%, Hf: <0.01%, Re: 3.5%, Rest Ni.
  • Cr: 10.75%, Mo: 1.85%, W:4.70, Co: 6.50%, Ti: 3.75%, Ta: 3.9%, Al: 3.3%, B: 0.0125%, Zr: 0.008%, Hf: <0.01%, Re: 1.5%, Ru: 2.0% Rest Ni.
  • Cr: 10.25%, Mo: 1.85%, W:4.70, Co: 8.50%, Ti: 3.75%, Ta: 3.9%, Al: 3.3%, B: 0.0125%, Zr: 0.008%, Hf: <0.01%, Ru: 1.5%, Rest Ni.
  • Cr: 10.75%, Mo: 1.85%, W:4.70, Co: 8.50%, Ti: 3.75%, Ta: 3.9%, Al: 3.3%, B: 0.0125%, Zr: 0.008%, Hf: <0.01%, Ru: 3.75%, Rest Ni.
  • Cr: 10.25%, Mo: 1.85%, W:4.70, Co: 8.50%, Ti: 3.75%, Ta: 3.9%, Al: 3.3%, B: 0.0125%, Zr: 0.008%, Hf: <0.01%, Re: 2.00%, Ru: 2.5, Rest Ni.
Advantageous compositions are given for example by:
  • Cr: 10.25%, Mo: 1.85%, W: 4.70, Co: 6.50%, Ti: 3.75%, Ta: 3.9%, Al: 3.3%, B: 0.0125%, Zr: 0.008%, Hf: <0.01%, Re: 1.5%, balance Ni.
  • Cr: 9.00%, Mo: 1.85%, W: 4.70, Co: 6.50%, Ti: 3.75%, Ta: 3.9%, Al: 3.3%, B: 0.0125%, Zr: 0.008%, Hf: <0.01%, Re: 3.5%, balance Ni.
  • Cr: 10.75%, Mo: 1.85%, W: 4.70, Co: 6.50%, Ti: 3.75%, Ta: 3.9%, Al: 3.3%, B: 0.0125%, Zr: 0.008%, Hf: <0.01%, Re: 1.5%, Ru: 2.0% rest Ni.
  • Cr: 10.25%, Mo: 1.85%, W: 4.70, Co: 8.50%, Ti: 3.75%, Ta: 3.9%, Al: 3.3%, B: 0.0125%, Zr: 0.008%, Hf: <0.01%, Ru: 1.5%, balance Ni.
  • Cr: 10.75%, Mo: 1.85%, W: 4.70, Co: 8.50%, Ti: 3.75%, Ta: 3.9%, Al: 3.3%, B: 0.0125%, Zr: 0.008%, Hf: <0.01%, Ru: 3.75%, balance Ni.
  • Cr: 10.25%, Mo: 1.85%, W: 4.70, Co: 8.50%, Ti: 3.75%, Ta: 3.9%, Al: 3.3%, B: 0.0125%, Zr: 0.008%, Hf: <0.01%, Re: 2.00%, Ru: 2.5, rest Ni.

Claims (8)

  1. High-temperature-resistant component (1) made from a nickel-base superalloy, the composition of which comprises the following elements, in percent by weight:
    9 - 10.75% of chromium
    3 - 5% of tungsten
    0.5 - 2.5% of molybdenum
    3 - 5% of aluminium
    3 - 5% of titanium
    3 - 7% of tantalum
    0 - 12% of cobalt
    0 - 1% of niobium
    0 - 2% of hafnium
    0 - 1% of zirconium
    0 - 0.05% of boron
    0 - 0.2% of carbon
    at least one element selected from the group consisting of rhenium, ruthenium, in which 1 - 5% rhenium and/or 0.1 to 5% ruthenium is used,
    remainder Ni and impurities.
  2. Component (1) according to Claim 1, in which the rhenium content is at least 2% by weight.
  3. Component (1) according to Claim 1, having a maximum ruthenium content of 3% by weight in the superalloy.
  4. Component (1) according to Claim 1 or 3, having a minimum ruthenium content of 0.1% by weight, in particular 0.5% by weight, in the superalloy.
  5. Component (1) according to one of the preceding claims, which has a directionally solidified grain structure (9).
  6. Component (1) according to one of Claims 1 to 4, which has a single-crystalline structure.
  7. Component (1) according to one of Claims 1 to 4, which has an isotropic distribution of the orientations of the grain structure.
  8. Component (1) according to one of the preceding claims, which is designed as a gas turbine blade or vane.
EP01129743A 2001-12-13 2001-12-13 High temperature resistant part, made of single-crystal or polycrystalline nickel-base superalloy Expired - Lifetime EP1319729B1 (en)

Priority Applications (4)

Application Number Priority Date Filing Date Title
DE50112339T DE50112339D1 (en) 2001-12-13 2001-12-13 High-temperature resistant component made of monocrystalline or polycrystalline nickel-based superalloy
EP01129743A EP1319729B1 (en) 2001-12-13 2001-12-13 High temperature resistant part, made of single-crystal or polycrystalline nickel-base superalloy
JP2002356858A JP2003193161A (en) 2001-12-13 2002-12-09 High temperature resistant structural member
CA 2414019 CA2414019A1 (en) 2001-12-13 2002-12-13 High temperature-resistant component

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EP01129743A EP1319729B1 (en) 2001-12-13 2001-12-13 High temperature resistant part, made of single-crystal or polycrystalline nickel-base superalloy

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EP1319729A1 EP1319729A1 (en) 2003-06-18
EP1319729A8 EP1319729A8 (en) 2003-10-15
EP1319729B1 true EP1319729B1 (en) 2007-04-11

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