EP1029100B1 - Product with a layer system for protecting against a hot aggressive gas - Google Patents

Product with a layer system for protecting against a hot aggressive gas Download PDF

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Publication number
EP1029100B1
EP1029100B1 EP98959748A EP98959748A EP1029100B1 EP 1029100 B1 EP1029100 B1 EP 1029100B1 EP 98959748 A EP98959748 A EP 98959748A EP 98959748 A EP98959748 A EP 98959748A EP 1029100 B1 EP1029100 B1 EP 1029100B1
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EP
European Patent Office
Prior art keywords
product
lanthanum
hafnium
yttrium
chromium
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Expired - Lifetime
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EP98959748A
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German (de)
French (fr)
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EP1029100A1 (en
Inventor
Wolfram Beele
Beate Heimberg
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Siemens AG
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Siemens AG
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Classifications

    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C28/00—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D
    • C23C28/30—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer
    • C23C28/32—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer
    • C23C28/321—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer with at least one metal alloy layer
    • C23C28/3215—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer with at least one metal alloy layer at least one MCrAlX layer
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C28/00—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C28/00—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D
    • C23C28/30—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer
    • C23C28/34—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one inorganic non-metallic material layer, e.g. metal carbide, nitride, boride, silicide layer and their mixtures, enamels, phosphates and sulphates
    • C23C28/345—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one inorganic non-metallic material layer, e.g. metal carbide, nitride, boride, silicide layer and their mixtures, enamels, phosphates and sulphates with at least one oxide layer
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C28/00—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D
    • C23C28/30—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer
    • C23C28/34—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one inorganic non-metallic material layer, e.g. metal carbide, nitride, boride, silicide layer and their mixtures, enamels, phosphates and sulphates
    • C23C28/345—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one inorganic non-metallic material layer, e.g. metal carbide, nitride, boride, silicide layer and their mixtures, enamels, phosphates and sulphates with at least one oxide layer
    • C23C28/3455—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one inorganic non-metallic material layer, e.g. metal carbide, nitride, boride, silicide layer and their mixtures, enamels, phosphates and sulphates with at least one oxide layer with a refractory ceramic layer, e.g. refractory metal oxide, ZrO2, rare earth oxides or a thermal barrier system comprising at least one refractory oxide layer
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/12—All metal or with adjacent metals
    • Y10T428/12493—Composite; i.e., plural, adjacent, spatially distinct metal components [e.g., layers, joint, etc.]
    • Y10T428/12535—Composite; i.e., plural, adjacent, spatially distinct metal components [e.g., layers, joint, etc.] with additional, spatially distinct nonmetal component
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/12—All metal or with adjacent metals
    • Y10T428/12493—Composite; i.e., plural, adjacent, spatially distinct metal components [e.g., layers, joint, etc.]
    • Y10T428/12535—Composite; i.e., plural, adjacent, spatially distinct metal components [e.g., layers, joint, etc.] with additional, spatially distinct nonmetal component
    • Y10T428/12611—Oxide-containing component
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/12—All metal or with adjacent metals
    • Y10T428/12493—Composite; i.e., plural, adjacent, spatially distinct metal components [e.g., layers, joint, etc.]
    • Y10T428/12535—Composite; i.e., plural, adjacent, spatially distinct metal components [e.g., layers, joint, etc.] with additional, spatially distinct nonmetal component
    • Y10T428/12611—Oxide-containing component
    • Y10T428/12618—Plural oxides

Definitions

  • the invention relates to a product with a metallic base body and a layer system thereon to protect the base body against a hot aggressive gas, with an adhesive layer made of an alloy of the type MCrAlY.
  • M stands for one or more elements from the group iron, cobalt and nickel, Cr for chromium, Al for aluminum and Y for yttrium and / or a rare earth element.
  • EP 0 486 489 B1 specifies a corrosion-resistant protective coating for medium and high temperatures up to approximately 1050 ° C. for a gas turbine part made of a nickel-based or cobalt-based alloy.
  • the protective coating has in percent by weight 25 to 40% nickel, 28 to 32% chromium, 7 to 9% aluminum, 1 to 2% silicon and 0.3 to 1% of at least one reactive element of the rare earths, at least 5% cobalt and optionally 0 up to 15% of at least one of the elements from the group consisting of rhenium, platinum, palladium, zircon, manganese, tungsten, titanium, molybdenum, niobium, iron, hafnium, tantalum.
  • the protective coating has only the elements nickel, chromium, aluminum, silicon, yttrium and additionally rhenium in a range from 1 to 15% and a remainder made of cobalt.
  • the addition of rhenium significantly improves the corrosion properties.
  • US Pat. No. 4,321,310 describes a gas turbine component which has a base body made of a nickel-based superalloy MAR-M-200.
  • a layer of an MCrAlY alloy, in particular a NiCOCrAlY alloy with 18% chromium, 23% cobalt, 12.5% aluminum, 0.3% yttrium and a remainder made of nickel is applied to the base material.
  • This layer of the MCrAlY alloy has a polished Surface on which an aluminum oxide layer is applied.
  • a ceramic thermal barrier coating is applied to this aluminum oxide layer, which has a stem-shaped structure.
  • US Pat. No. 4,585,481 also specifies protective layers for protecting a metallic substrate made of a superalloy against high-temperature oxidation and corrosion.
  • MCrAlY alloys are used for the protective layers. Here are 5 to 40% chromium, 8 to 35% aluminum, 0.1 to 2% of an oxygen-active element from group IIIb of the periodic table including the lanthanides and actinides and mixtures thereof, 0.1 to 7% silicon, 0.1 to 3% hafnium and a remainder comprising nickel and / or cobalt.
  • the corresponding protective layers made of MCrAlY alloys are applied according to US Pat. No. 4,585,481 by means of a plasma spraying process.
  • US Pat. No. 4,339,509 also relates to the application of a protective layer to a superalloy for protection against oxidation and sulfidation.
  • the protective layer is again of the MCrAlY type with 10 to 35% chromium, 5 to 15% aluminum, 0.1 to 10% magnesium, up to 8% tantalum, up to 5% tungsten, up to 12% silicon, up to 10% hafnium and 5 up to 35% cobalt and a remainder made of nickel.
  • the alloy has 15 to 40% chromium, 3 to 13% aluminum, 0.1 to 10% magnesium, up to 5% tantalum, up to 2% tungsten, up to 12% silicon, up to 10% hafnium and a balance of cobalt.
  • the alloy can at most have a single element from the group lanthanum, yttrium or other rare earths up to 15%.
  • the only specifically disclosed embodiment of the alloy of the protective layer has yttrium alone or yttrium with an addition of tungsten and tantalum.
  • Alloys containing lanthanum have at least a further proportion of tantalum, magnesium or titanium in addition to a proportion of nickel, cobalt, chromium and aluminum.
  • WO 96/3582 A1 specifies a thermal barrier coating for a turbine blade made of a superalloy which is exposed to a hot gas.
  • the thermal insulation layer has a ceramic protective layer which is bonded to an adhesion promoter layer made of an aluminide or an alloy of the MCrAlY type.
  • the nickel-based alloy with a proportion of hafnium Mar-M247 and the cobalt-based alloy Mar-M509 with a proportion of zircon are specified as superalloys.
  • a MCrAlY alloy with a proportion of 10 to 35% chromium, 5 to 15% aluminum and 0.01 to 1% of one of the elements yttrium, hafnium or lanthanum is indicated on this.
  • Oxidation of aluminum in the adhesion promoter layer creates an aluminum oxide layer, which enables the ceramic protective layer to be bonded to the adhesion promoter layer.
  • Partially stabilized zirconium oxide is used as the ceramic protective layer, the stabilization being able to be carried out using calcium oxide, magnesium oxide, cerium oxide or yttrium oxide.
  • the object of the invention is to provide a product with a metallic base body and a layer system located thereon, which has an adhesive layer with an alloy for connecting a thermal insulation layer, in particular with a ternary oxide.
  • the object is achieved by a product according to claims 1 and 4, in which the adhesive layer correspondingly contains an alloy (details in the following each in percent by weight) with 3 to 50% chromium, 3 to 20% aluminum, 0 to 0.5% yttrium and / or a rare earth element, 0.1 to 10% lanthanum, 0 to 10% hafnium, 0 to 10 % Magnesium, 0 to 2% silicon and one or more elements from the group comprising iron, cobalt and nickel.
  • an alloy tails in the following each in percent by weight
  • the adhesive layer correspondingly contains an alloy (details in the following each in percent by weight) with 3 to 50% chromium, 3 to 20% aluminum, 0 to 0.5% yttrium and / or a rare earth element, 0.1 to 10% lanthanum, 0 to 10% hafnium, 0 to 10 %
  • Magnesium 0 to 2% silicon and one or more elements from the group comprising iron, cobalt and nickel.
  • the alloy of the adhesive layer corresponds to an MCrAlY alloy with an addition of 0.1% to 10% lanthanum and at least 0.01 to 0.5% yttrium and / or at least 0.1 to 10% hafnium.
  • the adhesive layer is not only suitable, common thermal insulation layers, especially ceramic thermal insulation layers, with zirconium oxide, e.g. partially stabilized with yttrium oxide, to be attached to the body. It is also suitable for connecting ceramic thermal insulation layers with ternary oxides.
  • Such ternary oxides contain oxygen as the third element and preferably nickel, magnesium or cobalt as the first element and aluminum or chromium as the second element.
  • the first element of the ternary oxide is calcium or lanthanum and the second element is aluminum, zirconium or hafnium.
  • the adhesive layer enables the production of a chemically suitable interface composite.
  • This good connection to a thermal insulation layer made of a ternary oxide is achieved by lanthanum oxide formed due to oxidation of the adhesive layer and optionally additional hafnium oxide formed. Oxidation of the lanthanum-containing adhesive layer can result in a thermally grown intermediate layer of lanthanum-containing bonding oxides on the surface of the adhesive layer facing away from the base body, to which the thermal insulation layer bonds well.
  • An intermediate layer also referred to as a bonding layer, can contain aluminum oxide (Al 2 O 3 ), chromium oxide (Cr 2 O 3 ) and / or hafnium oxide (HfO 2 ) in addition to lanthanum oxide (La 2 O 3 ).
  • An intermediate layer can be produced separately as a separate layer using coating processes.
  • a preferred alloy of the adhesive layer has 15 to 25% chromium, 10 to 20% aluminum, 0.01 to 0.3% yttrium, 0 to 33% cobalt and 0.1% to 2% lanthanum, 0.1 to 2% hafnium apart from production-related impurities, no magnesium and no silicon, and a remainder made of nickel.
  • the proportion of lanthanum can be 0.1 to 5%, the proportion of hafnium 0 to 2%, the proportion of magnesium 0.1 to 2% and the proportion of silicon 0 to 2%.
  • the alloy of the adhesive layer has 3 to 15% chromium, 3 to 10% aluminum, 0.5 to 10% lanthanum, 0 to 10% hafnium, 0 to 2% magnesium, 0.01 to 0.3% Yttrium, except for production-related impurities, no silicon, 0 to 33% cobalt and a remainder made of nickel. It is also possible here that a further rare earth element, scandium or an element of the lanthanides, such as cerium, is used instead of or in addition to yttrium. If necessary, an element of the actinides can also be added.
  • the alloy preferably has a combination of lanthanum, hafnium and yttrium in the ranges of lanthanum 0.5 to 10%, hafnium 0.5 to 10% and yttrium 0.1 to 0.5%.
  • the alloy has cobalt between 0 and 33%, chromium between 15 and 25%, aluminum 10 to 20%, hafnium 0.5 to 2%, yttrium 0.01 to 0.3%, lanthanum 0.5 up to 2% and essentially no magnesium and no silicon and a remainder of nickel.
  • the proportion of lanthanum is between 0.5 and 5%, of magnesium between 0.1 and 2% and of silicon up to 2%.
  • the proportion of chromium is 3 to 15%, of aluminum 3 to 10%, of lanthanum 0.5 to 10%, of hafnium 0.5 to 10%, of yttrium 0.01 to 0.3%, of magnesium 0 to 2%, of cobalt to 33% and a remainder of nickel, essentially no silicon being contained.
  • the lanthanum content is over 5%, preferably between 5 and 10%.
  • the proportion of chromium is between 3 and 15%, aluminum between 3 and 10%, hafnium between 2 and 10%, magnesium between 0 and 10%, yttrium between 0.01 and 0.5%, silicon between 0 and 2% and a remainder made of cobalt, nickel or a mixture thereof.
  • the alloy of the adhesive layer preferably has the elements lanthanum, hafnium and yttrium and optionally other elements of the rare earths with a total weight fraction of more than 2%. Up to a total of these elements of less than 5%, at least two of the elements mentioned are present in the alloy at the same time.
  • the alloys, in which at least two of the components lanthanum, hafnium and yttrium are always present, as well as the alloy with a weight fraction of more than 5% lanthanum are, in addition to the connection of a ternary oxide, also preferred for the connection of conventional zirconium oxide-based thermal insulation systems.
  • the product is preferably a component of a gas turbine, in particular a moving blade, a guide blade or a heat shield element.
  • the base body preferably consists of a nickel-based or cobalt-based alloy.
  • the gas turbine blade 1 shown in FIG. 1 has a metallic base body 2 made of a nickel-based or cobalt-based superalloy.
  • an adhesive layer 7 made of an alloy comprising chromium, aluminum, yttrium, lanthanum, hafnium, magnesium, silicon and a remainder composed of one or more elements from the group comprising iron, cobalt and nickel is applied to the base body 2.
  • a thermal insulation layer 5 made of a ternary oxide is applied to this adhesive layer 7.
  • a bonding layer 8 made of lanthanum-containing bonding oxides is formed, in particular by oxidation of the bonding layer 7. This results in a good connection of the thermal insulation layer to the metallic base body 2 via the adhesive layer 7.
  • the invention is characterized by an adhesive layer made of an alloy of the type MCrAlY with the addition of lanthanum, whereby the connection of a ternary oxide, in particular comprising lanthanum, is given in particular.

Description

Die Erfindung betrifft ein Erzeugnis mit einem metallischen Grundkörper und einem darauf befindlichen Schichtsystem zum Schutz des Grundkörpers gegen ein heißes aggressives Gas, mit einer Haftschicht aus einer Legierung der Art MCrAlY. Hierbei steht M für ein Element oder mehrere Elemente aus der Gruppe Eisen, Kobalt und Nickel, Cr für Chrom, Al für Aluminium und Y für Yttrium und/oder ein Element der Seltenen Erden.The invention relates to a product with a metallic base body and a layer system thereon to protect the base body against a hot aggressive gas, with an adhesive layer made of an alloy of the type MCrAlY. Here M stands for one or more elements from the group iron, cobalt and nickel, Cr for chromium, Al for aluminum and Y for yttrium and / or a rare earth element.

Aus der EP 0 486 489 B1 ist eine korrosionsfeste Schutzbeschichtung für mittlere und hohe Temperaturen bis etwa 1050 °C für ein Gasturbinenteil aus einer Nickel-Basis- oder Kobalt-Basislegierung angegeben. Die Schutzbeschichtung weist in Gewichtsprozent 25 bis 40% Nickel, 28 bis 32% Chrom, 7 bis 9 % Aluminum, 1 bis 2 % Silizium und 0,3 bis 1 % wenigstens eines reaktiven Elements der Seltenen Erden, mindestens 5% Kobalt sowie wahlweise 0 bis 15% wenigstens eines der Elemente aus der Gruppe bestehend aus Rhenium, Platin, Palladium, Zirkon, Mangan, Wolfram, Titan, Molybdän, Niob, Eisen, Hafnium, Tantal auf. In den angegebenen konkreten Ausführungsformen weist die Schutzbeschichtung lediglich die Elemente Nickel, Chrom, Aluminium, Silizium, Yttrium und zusätzlich Rhenium in einem Bereich von 1 bis 15% sowie einen Rest aus Kobalt auf. Durch die Zugabe des Rheniums werden die Korrosionseigenschaften deutlich verbessert.EP 0 486 489 B1 specifies a corrosion-resistant protective coating for medium and high temperatures up to approximately 1050 ° C. for a gas turbine part made of a nickel-based or cobalt-based alloy. The protective coating has in percent by weight 25 to 40% nickel, 28 to 32% chromium, 7 to 9% aluminum, 1 to 2% silicon and 0.3 to 1% of at least one reactive element of the rare earths, at least 5% cobalt and optionally 0 up to 15% of at least one of the elements from the group consisting of rhenium, platinum, palladium, zircon, manganese, tungsten, titanium, molybdenum, niobium, iron, hafnium, tantalum. In the specified specific embodiments, the protective coating has only the elements nickel, chromium, aluminum, silicon, yttrium and additionally rhenium in a range from 1 to 15% and a remainder made of cobalt. The addition of rhenium significantly improves the corrosion properties.

In der US-PS 4,321,310 ist eine Gasturbinenkomponente beschrieben, die einen Grundkörper aus einer Nickel-Basis-Superlegierung MAR-M-200 aufweist. Auf den Grundwerkstoff ist eine Schicht aus einer MCrAlY-Legierung, insbesondere einer NiCOCrAlY-Legierung mit 18% Chrom, 23% Kobalt, 12,5% Aluminium, 0,3% Yttrium und einem Rest aus Nickel aufgebracht. Diese Schicht aus der MCrAlY-Legierung weist eine polierte Oberfläche auf, auf die eine Aluminiumoxidschicht aufgebracht ist. An diese Aluminiumoxidschicht ist eine keramische Wärmedämmschicht aufgebracht, welche eine stengelförmige Struktur aufweist.US Pat. No. 4,321,310 describes a gas turbine component which has a base body made of a nickel-based superalloy MAR-M-200. A layer of an MCrAlY alloy, in particular a NiCOCrAlY alloy with 18% chromium, 23% cobalt, 12.5% aluminum, 0.3% yttrium and a remainder made of nickel is applied to the base material. This layer of the MCrAlY alloy has a polished Surface on which an aluminum oxide layer is applied. A ceramic thermal barrier coating is applied to this aluminum oxide layer, which has a stem-shaped structure.

In der US-PS 4,585,481 sind ebenfalls Schutzschichten zum Schutz eines metallischen Substrats aus einer Superlegierung gegen Hochtemperatur-Oxidation und -Korrosion angegeben. Für die Schutzschichten finden MCrAlY-Legierungen Anwendung. Hierbei sind 5 bis 40% Chrom, 8 bis 35% Aluminium, 0,1 bis 2% eines sauerstoffaktiven Elements aus der Gruppe IIIb des Periodensystems einschließlich der Lanthanide und Aktinide sowie Mischungen davon, 0,1 bis 7% Silizium, 0,1 bis 3% Hafnium sowie einem Rest umfassend Nickel und/oder Kobalt angegeben. Die entsprechenden Schutzschichten aus MCrAlY-Legierungen werden gemäß der US-PS 4,585,481 mittels eines Plasmaspritzverfahrens aufgebracht.US Pat. No. 4,585,481 also specifies protective layers for protecting a metallic substrate made of a superalloy against high-temperature oxidation and corrosion. MCrAlY alloys are used for the protective layers. Here are 5 to 40% chromium, 8 to 35% aluminum, 0.1 to 2% of an oxygen-active element from group IIIb of the periodic table including the lanthanides and actinides and mixtures thereof, 0.1 to 7% silicon, 0.1 to 3% hafnium and a remainder comprising nickel and / or cobalt. The corresponding protective layers made of MCrAlY alloys are applied according to US Pat. No. 4,585,481 by means of a plasma spraying process.

Weiterhin ist es aus dem Artikel "Application of Ion-Beamed Treatment in Turbine Blade Production Technology" von Yu.D. Yagodkin et al in Surface and Coatings Technology 84, (1996), Seiten 590 - 592 bekannt, Schutzschichten der Art NiCrAlY oder NiCoCrAlY mittels Ionenbestrahlung mit Bor oder Lanthan zu dotieren. Die Schutzschichten sind hierbei auf eine Nikkelbasis-Superlegierung aufgebracht. Über die Höhe der möglichen Dotierungsgrade gibt obiger Artikel keine Auskunft.Furthermore, it is from the article "Application of Ion-Beamed Treatment in Turbine Blade Production Technology" by Yu.D. Yagodkin et al in Surface and Coatings Technology 84, (1996), pages 590-592 discloses doping protective layers of the type NiCrAlY or NiCoCrAlY by means of ion irradiation with boron or lanthanum. The protective layers are applied to a nickel base superalloy. The above article does not provide any information about the level of possible doping levels.

Die US-PS 4,339,509 betrifft ebenfalls das Aufbringen einer Schutzschicht auf eine Superlegierung zum Schutz vor Oxidation und Sulfidation. Die Schutzschicht ist wiederum von der Art MCrAlY mit 10 bis 35% Chrom, 5 bis 15% Aluminium, 0,1 bis 10% Magnesium, bis 8% Tantal, bis 5% Wolfram, bis 12% Silizium, bis 10% Hafnium sowie 5 bis 35% Kobalt und einem Rest aus Nickel. Alternativ weist die Legierung 15 bis 40% Chrom, 3 bis 13% Aluminium, 0,1 bis 10% Magnesium, bis 5% Tantal, bis 2% Wolfram, bis 12% Silizium, bis 10% Hafnium und einen Rest aus Kobalt auf. Grundsätzlich kann die Legierung höchstens ein einzelnes Element aus der Gruppe Lanthan, Yttrium oder weiterer Seltener Erden bis 15% aufweisen. Die einzig konkret offenbarte Ausführungsform der Legierung der Schutzschicht weist neben Kobalt, Nickel, Chrom und Aluminium Yttrium alleine oder Yttrium mit einem Zusatz an Wolfram und Tantal auf. Legierungen, die Lanthan aufweisen, besitzen neben einem Anteil an Nickel, Kobalt, Chrom und Aluminium zumindest einen weiteren Anteil an Tantal, Magnesium oder Titan.US Pat. No. 4,339,509 also relates to the application of a protective layer to a superalloy for protection against oxidation and sulfidation. The protective layer is again of the MCrAlY type with 10 to 35% chromium, 5 to 15% aluminum, 0.1 to 10% magnesium, up to 8% tantalum, up to 5% tungsten, up to 12% silicon, up to 10% hafnium and 5 up to 35% cobalt and a remainder made of nickel. Alternatively, the alloy has 15 to 40% chromium, 3 to 13% aluminum, 0.1 to 10% magnesium, up to 5% tantalum, up to 2% tungsten, up to 12% silicon, up to 10% hafnium and a balance of cobalt. Basically, the alloy can at most have a single element from the group lanthanum, yttrium or other rare earths up to 15%. In addition to cobalt, nickel, chromium and aluminum, the only specifically disclosed embodiment of the alloy of the protective layer has yttrium alone or yttrium with an addition of tungsten and tantalum. Alloys containing lanthanum have at least a further proportion of tantalum, magnesium or titanium in addition to a proportion of nickel, cobalt, chromium and aluminum.

In der WO 96/3582 A1 ist eine Wärmedämmschicht für eine Turbinenschaufel aus einer Superlegierung, welche einem Heißgas ausgesetzt ist, angegeben. Die Wärmedämmschicht weist hierbei eine keramische Schutzschicht auf, die an eine Haftvermittlerschicht aus einem Aluminid oder einer Legierung der Art MCrAlY angebunden ist. Als Superlegierung wird einerseits die Nickelbasislegierung mit einem Anteil an Hafnium Mar-M247 sowie die Kobaltbasislegierung Mar-M509 mit einem Anteil an Zirkon angegeben. Hierauf ist eine MCrAlY-Legierung mit einem Anteil von 10 bis 35% Chrom, 5 bis 15% Aluminium sowie 0,01 bis 1% eines der Elemente Yttrium, Hafnium oder Lanthan angegeben. Durch eine Oxidation von Aluminium in der Haftvermittlerschicht entsteht eine Aluminiumoxidschicht, welche ein Anbindung der keramischen Schutzschicht an die Haftvermittlerschicht ermöglicht. Als keramische Schutzschicht wird hierbei teilstabilisiertes Zirkonoxid verwendet, wobei die Stabilisierung durch Kalziumoxid, Magnesiumoxid, Zeroxid oder Yttriumoxid erfolgen kann.WO 96/3582 A1 specifies a thermal barrier coating for a turbine blade made of a superalloy which is exposed to a hot gas. The thermal insulation layer has a ceramic protective layer which is bonded to an adhesion promoter layer made of an aluminide or an alloy of the MCrAlY type. On the one hand, the nickel-based alloy with a proportion of hafnium Mar-M247 and the cobalt-based alloy Mar-M509 with a proportion of zircon are specified as superalloys. A MCrAlY alloy with a proportion of 10 to 35% chromium, 5 to 15% aluminum and 0.01 to 1% of one of the elements yttrium, hafnium or lanthanum is indicated on this. Oxidation of aluminum in the adhesion promoter layer creates an aluminum oxide layer, which enables the ceramic protective layer to be bonded to the adhesion promoter layer. Partially stabilized zirconium oxide is used as the ceramic protective layer, the stabilization being able to be carried out using calcium oxide, magnesium oxide, cerium oxide or yttrium oxide.

Aufgabe der Erfindung ist es, ein Erzeugnis mit einem metallischen Grundkörper und einem darauf befindlichen Schichtsystem anzugeben, welches eine Haftschicht mit einer Legierung zur Anbindung einer Wärmedämmschicht, insbesondere mit einem ternären Oxid, aufweist.The object of the invention is to provide a product with a metallic base body and a layer system located thereon, which has an adhesive layer with an alloy for connecting a thermal insulation layer, in particular with a ternary oxide.

Erfindungsgemäß wird die Aufgabe durch ein Erzeugnis gemäß den Ansprüchen 1 und 4 gelöst, bei dem die Haftschicht entsprechend eine Legierung (Angaben im folgenden jeweils in Gewichtsprozent) mit 3 bis 50% Chrom, 3 bis 20% Aluminium, 0 bis 0,5% Yttrium und/oder einem Element der Seltenen Erden, 0,1 bis 10% Lanthan, 0 bis 10% Hafnium, 0 bis 10% Magnesium, 0 bis 2% Silizium sowie einem Element oder mehrere Elemente aus der Gruppe umfassend Eisen, Kobalt und Nickel aufweist.According to the invention the object is achieved by a product according to claims 1 and 4, in which the adhesive layer correspondingly contains an alloy (details in the following each in percent by weight) with 3 to 50% chromium, 3 to 20% aluminum, 0 to 0.5% yttrium and / or a rare earth element, 0.1 to 10% lanthanum, 0 to 10% hafnium, 0 to 10 % Magnesium, 0 to 2% silicon and one or more elements from the group comprising iron, cobalt and nickel.

Die Legierung der Haftschicht entspricht hierbei einer MCrAlY-Legierung mit einem Zusatz von 0,1% bis 10% Lanthan und zumindest 0,01 bis 0,5% Yttrium und/oder zumindest 0,1 bis 10% Hafnium. Durch den Zusatz von Lanthan ist die Haftschicht nicht nur geeignet, geläufige Wärmedämmschichten, insbesondere keramische Wärmedämmschichten, mit Zirkonoxid, z.B. teilstabilisiert mit Yttriumoxid, an den Grundkörper anzubinden. Sie ist auch geeignet, keramische Wärmedämmschichten mit ternären Oxiden anzubinden.The alloy of the adhesive layer corresponds to an MCrAlY alloy with an addition of 0.1% to 10% lanthanum and at least 0.01 to 0.5% yttrium and / or at least 0.1 to 10% hafnium. By adding lanthanum, the adhesive layer is not only suitable, common thermal insulation layers, especially ceramic thermal insulation layers, with zirconium oxide, e.g. partially stabilized with yttrium oxide, to be attached to the body. It is also suitable for connecting ceramic thermal insulation layers with ternary oxides.

Solche ternäre Oxide enthalten als drittes Element Sauerstoff sowie vorzugsweise als erstes Element Nickel, Magnesium oder Kobalt und als zweites Element Aluminium oder Chrom. In einer alternativen Ausgestaltung ist das erste Element des ternären Oxides Calcium oder Lanthan und das zweite Element Aluminium, Zirkon oder Hafnium.Such ternary oxides contain oxygen as the third element and preferably nickel, magnesium or cobalt as the first element and aluminum or chromium as the second element. In an alternative embodiment, the first element of the ternary oxide is calcium or lanthanum and the second element is aluminum, zirconium or hafnium.

Bei solchen ternären Oxiden ermöglicht die Haftschicht die Herstellung eines chemisch geeigneten Interface-Verbundes. Diese gute Anbindung an eine Wärmedämmschicht aus einem ternären Oxid wird durch aufgrund von Oxidation der Haftschicht entstehendem Lanthanoxid und gegebenenfalls zusätzlich entstehendem Hafniumoxid erreicht. Durch Oxidation der Lanthan-haltigen Haftschicht kann an der dem Grundkörper abgewandten Oberfläche der Haftschicht eine thermisch gewachsene Zwischenschicht aus Lanthan-haltigen Anbindungsoxiden entstehen, an der die Wärmedämmschicht gut anbindet. Eine Zwischenschicht, auch als Anbindungsschicht bezeichnet, kann neben Lanthanoxid (La2O3) auch Aluminiumoxid (Al2O3), Chromoxid (Cr2O3) und/oder Hafniumoxid (HfO2) aufweisen. Eine Zwischenschicht kann separat als eigene Schicht durch Beschichtungsverfahren hergestellt werden.In the case of such ternary oxides, the adhesive layer enables the production of a chemically suitable interface composite. This good connection to a thermal insulation layer made of a ternary oxide is achieved by lanthanum oxide formed due to oxidation of the adhesive layer and optionally additional hafnium oxide formed. Oxidation of the lanthanum-containing adhesive layer can result in a thermally grown intermediate layer of lanthanum-containing bonding oxides on the surface of the adhesive layer facing away from the base body, to which the thermal insulation layer bonds well. An intermediate layer, also referred to as a bonding layer, can contain aluminum oxide (Al 2 O 3 ), chromium oxide (Cr 2 O 3 ) and / or hafnium oxide (HfO 2 ) in addition to lanthanum oxide (La 2 O 3 ). An intermediate layer can be produced separately as a separate layer using coating processes.

Eine bevorzugte Legierung der Haftschicht weist 15 bis 25% Chrom, 10 bis 20% Aluminium, 0,01 bis 0,3% Yttrium, 0 bis 33% Kobalt sowie 0,1% bis 2% Lanthan, 0,1 bis 2% Hafnium bis auf herstellungsbedingte Verunreinigungen kein Magnesium und kein Silizium sowie einen Rest aus Nickel auf. Alternativ hierzu kann der Anteil an Lanthan 0,1 bis 5%, der Anteil an Hafnium 0 bis 2%, der Anteil an Magnesium 0,1 bis 2% und der Anteil an Silizium 0 bis 2% betragen.A preferred alloy of the adhesive layer has 15 to 25% chromium, 10 to 20% aluminum, 0.01 to 0.3% yttrium, 0 to 33% cobalt and 0.1% to 2% lanthanum, 0.1 to 2% hafnium apart from production-related impurities, no magnesium and no silicon, and a remainder made of nickel. Alternatively, the proportion of lanthanum can be 0.1 to 5%, the proportion of hafnium 0 to 2%, the proportion of magnesium 0.1 to 2% and the proportion of silicon 0 to 2%.

In einer alternativen bevorzugten Ausführungsform weist die Legierung der Haftschicht 3 bis 15% Chrom, 3 bis 10% Aluminium, 0,5 bis 10% Lanthan, 0 bis 10% Hafnium, 0 bis 2% Magnesium, 0,01 bis 0,3% Yttrium, bis auf herstellungsbedingte Verunreinigungen kein Silizium, 0 bis 33% Kobalt und einen Rest aus Nickel auf. Es ist hierbei ebenfalls möglich, daß anstatt oder neben Yttrium ein weiteres Element der Seltenen Erden, Scandium oder ein Element der Lanthaniden, wie Cer, verwendet wird. Gegebenenfalls kann auch ein Element der Aktiniden zulegiert sein.In an alternative preferred embodiment, the alloy of the adhesive layer has 3 to 15% chromium, 3 to 10% aluminum, 0.5 to 10% lanthanum, 0 to 10% hafnium, 0 to 2% magnesium, 0.01 to 0.3% Yttrium, except for production-related impurities, no silicon, 0 to 33% cobalt and a remainder made of nickel. It is also possible here that a further rare earth element, scandium or an element of the lanthanides, such as cerium, is used instead of or in addition to yttrium. If necessary, an element of the actinides can also be added.

Vorzugsweise weist die Legierung eine Kombination aus Lanthan, Hafnium und Yttrium in den Bereichen Lanthan 0,5 bis 10%, Hafnium 0,5 bis 10% und Yttrium 0,1 bis 0,5%.The alloy preferably has a combination of lanthanum, hafnium and yttrium in the ranges of lanthanum 0.5 to 10%, hafnium 0.5 to 10% and yttrium 0.1 to 0.5%.

In einer weiterhin bevorzugten Ausführungsform weist die Legierung Kobalt zwischen 0 und 33%, Chrom zwischen 15 und 25%, Aluminium 10 bis 20%, Hafnium 0,5 bis 2%, Yttrium 0,01 bis 0,3%, Lanthan 0,5 bis 2% sowie im wesentlichen kein Magnesium und kein Silizium und einen Rest an Nickel auf. Alternativ hierzu liegt in einer weiteren Ausführungsform der Anteil an Lanthan zwischen 0,5 und 5%, an Magnesium zwischen 0,1 bis 2% und an Silizium bis 2%.In a further preferred embodiment, the alloy has cobalt between 0 and 33%, chromium between 15 and 25%, aluminum 10 to 20%, hafnium 0.5 to 2%, yttrium 0.01 to 0.3%, lanthanum 0.5 up to 2% and essentially no magnesium and no silicon and a remainder of nickel. As an alternative to this, in a further embodiment the proportion of lanthanum is between 0.5 and 5%, of magnesium between 0.1 and 2% and of silicon up to 2%.

In einer weiteren Ausführungsform beträgt der Anteil an Chrom 3 bis 15%, an Aluminium 3 bis 10%, an Lanthan 0,5 bis 10%, an Hafnium 0,5 bis 10%, an Yttrium 0,01 bis 0,3%, an Magnesium 0 bis 2%, , an Kobalt bis 33% und einem Rest aus Nickel, wobei im wesentlichen kein Silizium enthalten ist.In a further embodiment, the proportion of chromium is 3 to 15%, of aluminum 3 to 10%, of lanthanum 0.5 to 10%, of hafnium 0.5 to 10%, of yttrium 0.01 to 0.3%, of magnesium 0 to 2%, of cobalt to 33% and a remainder of nickel, essentially no silicon being contained.

In einer weiteren alternativen Ausführungsform liegt der Lanthangehalt bei über 5%, vorzugsweise zwischen 5 und 10%. Der Anteil an Chrom liegt hierbei zwischen 3 und 15%, an Aluminium zwischen 3 und 10%, an Hafnium zwischen 2 und 10%, an Magnesium zwischen 0 und 10%, an Yttrium zwischen 0,01 und 0,5%, an Silizium zwischen 0 und 2% sowie einem Rest aus Kobalt, Nickel oder einer Mischung daraus.In a further alternative embodiment, the lanthanum content is over 5%, preferably between 5 and 10%. The proportion of chromium is between 3 and 15%, aluminum between 3 and 10%, hafnium between 2 and 10%, magnesium between 0 and 10%, yttrium between 0.01 and 0.5%, silicon between 0 and 2% and a remainder made of cobalt, nickel or a mixture thereof.

Vorzugsweise weist die Legierung der Haftschicht die Elemente Lanthan, Hafnium und Yttrium sowie gegebenenfalls andere Elemente der Seltenen Erden mit einem Gewichtsanteil von in Summe über 2% auf. Bis zu einem Anteil dieser Elemente in Summe betrachtet von unter 5% liegen zumindest zwei der genannten Elemente gleichzeitig in der Legierung vor. Die Legierungen, bei denen immer zumindest zwei der Komponenten Lanthan, Hafnium und Yttrium vorliegen, sowie die Legierung mit einem Gewichtsanteil von über 5% Lanthan eignen sich neben der Anbindung eines ternären Oxides auch bevorzugt für die Anbindung von konventionellen Zirkonoxid-basierten Wärmedämmsystemen.The alloy of the adhesive layer preferably has the elements lanthanum, hafnium and yttrium and optionally other elements of the rare earths with a total weight fraction of more than 2%. Up to a total of these elements of less than 5%, at least two of the elements mentioned are present in the alloy at the same time. The alloys, in which at least two of the components lanthanum, hafnium and yttrium are always present, as well as the alloy with a weight fraction of more than 5% lanthanum are, in addition to the connection of a ternary oxide, also preferred for the connection of conventional zirconium oxide-based thermal insulation systems.

Das Erzeugnis ist vorzugsweise ein Bauteil einer Gasturbine, insbesondere eine Laufschaufel, eine Leitschaufel oder ein Hitzeschildelement. Der Grundkörper besteht vorzugsweise aus einer Nickelbasis- oder Kobaltbasis-Legierung.The product is preferably a component of a gas turbine, in particular a moving blade, a guide blade or a heat shield element. The base body preferably consists of a nickel-based or cobalt-based alloy.

Anhand der in der Zeichnung dargestellten Ausführungsbeispiele wird das Erzeugnis mit dem Schichtsystem näher erläutert.The product with the layer system is explained in more detail with the aid of the exemplary embodiments shown in the drawing.

Es zeigen in teilweise schematischer und nicht maßstäblicher Darstellung

FIG 1
eine perspektivische Darstellung einer GasturbinenLaufschaufel und
FIG 2
einen Schnitt durch Grundkörper und Schicht der Gasturbinen-Laufschaufel gemäß Figur 1.
They show a partially schematic and not to scale representation
FIG. 1
a perspective view of a gas turbine blade and
FIG 2
2 shows a section through the base body and layer of the gas turbine rotor blade according to FIG. 1.

Die in Figur 1 dargestellte Gasturbinenlaufschaufel 1 weist einen metallischen Grundkörper 2 aus einer Nickelbasis- oder Kobaltbasis-Superlegierung auf. Auf den Grundkörper 2 ist gemäß Figur 2 eine Haftschicht 7 aus einer Legierung umfassend Chrom, Aluminium, Yttrium, Lanthan, Hafnium, Magnesium, Silizium sowie einem Rest aus einem Element oder mehreren Elementen aus der Gruppe umfassend Eisen, Kobalt und Nickel aufgebracht. Auf diese Haftschicht 7 ist eine Wärmedämmschicht 5 aus einem ternären Oxid aufgebracht. Zwischen der Haftschicht 7 und der Wärmedämmschicht 5 ist eine Anbindungsschicht 8 aus Lanthan-haltigen Anbindungsoxiden, insbesondere durch Oxidation der Haftschicht 7, gebildet. Hierdurch erfolgt eine gute Anbindung der Wärmedämmschicht über die Haftschicht 7 an den metallischen Grundkörper 2. An einer äußeren Oberfläche 6 der Wärmedämmschicht 5 strömt bei einem Einsatz der Gasturbinenschaufel 1 in einer nicht dargestellten Gasturbine ein heißes aggressives Gas 4 vorbei, welches durch das Schichtsystem 3 aus Wärmedämmschicht 5 und Haftschicht 7 wirksam von dem metallischen Grundkörper 2 physikalisch und chemisch ferngehalten wird. Hierdurch wird eine deutliche Lebensdauersteigerung der Gasturbinenschaufel 1 erreicht.The gas turbine blade 1 shown in FIG. 1 has a metallic base body 2 made of a nickel-based or cobalt-based superalloy. According to FIG. 2, an adhesive layer 7 made of an alloy comprising chromium, aluminum, yttrium, lanthanum, hafnium, magnesium, silicon and a remainder composed of one or more elements from the group comprising iron, cobalt and nickel is applied to the base body 2. A thermal insulation layer 5 made of a ternary oxide is applied to this adhesive layer 7. Between the adhesive layer 7 and the heat insulation layer 5, a bonding layer 8 made of lanthanum-containing bonding oxides is formed, in particular by oxidation of the bonding layer 7. This results in a good connection of the thermal insulation layer to the metallic base body 2 via the adhesive layer 7. When the gas turbine blade 1 is used in a gas turbine (not shown), a hot aggressive gas 4 flows past an outer surface 6 of the thermal insulation layer 1 and flows out through the layer system 3 Thermal insulation layer 5 and adhesive layer 7 is effectively kept physically and chemically away from the metallic base body 2. In this way, a significant increase in the service life of the gas turbine blade 1 is achieved.

Die Erfindung zeichnet sich durch eine Haftschicht aus einer Legierung der Art MCrAlY mit einem Zusatz von Lanthan aus, wodurch besonders die Anbindung eines ternären Oxides, insbesondere umfassend Lanthan, gegeben ist.The invention is characterized by an adhesive layer made of an alloy of the type MCrAlY with the addition of lanthanum, whereby the connection of a ternary oxide, in particular comprising lanthanum, is given in particular.

Claims (17)

  1. Product (1) having a metallic base body (2) and a layer system (3) located thereon for protecting the base body (2) against a hot aggressive gas (4), having a ceramic thermal insulation layer (5) with an outer surface (6) which can be exposed to the gas (4), and having a bonding layer (7) which is arranged between the thermal insulation layer (5) and the base body (2), made of an alloy comprising the following elements (the numbers given are percentages by weight): 3% - 50% chromium 3% - 20% aluminium 0.01% - 0.5% yttrium and/or a rare-earth element 0.1% - 10% lanthanum 0% - 10% hafnium 0% - 10% magnesium 0% - 2% silicon
    and one element or a plurality of elements from the group comprising iron, cobalt and nickel.
  2. Product (1) according to Claim 1, containing 15% - 25% chromium 10% - 20% aluminium 0.01% - 0.3% yttrium 0.1% - 5% lanthanum 0% - 2% hafnium 0.1% - 2.0% magnesium 0% - 33% cobalt.
  3. Product (1) according to Claim 1, containing 3% - 15% chromium 3% - 10% aluminium 0.01% - 0.3% yttrium 0.5% - 10% lanthanum 0% - 10% hafnium 0% - 2% magnesium 0% - 33% cobalt.
  4. Product (1) having a metallic base body (2) and a layer system (3) located thereon for protecting the base body (2) against a hot aggressive gas (4), having a ceramic thermal insulation layer (5) with an outer surface (6) which can be exposed to the gas (4), and having a bonding layer (7) which is arranged between the thermal insulation layer (5) and the base body (2),made of an alloy comprising the following elements (the numbers given are percentages by weight): 3% - 50% chromium 3% - 20% aluminium 0% - 0.5% yttrium and/or a rare-earth element 0.1% - 10% lanthanum 0.1% - 10% hafnium 0% - 10% magnesium 0% - 2% silicon
    and one element or a plurality of elements from the group comprising iron, cobalt and nickel.
  5. Product (1) according to Claim 4, containing 15% - 25% chromium 10% - 20% aluminium 0.01% - 0.3% yttrium 0.1% - 2% lanthanum 0.1% - 2% hafnium 0% - 33% cobalt.
  6. Product (1) according to one of the preceding claims, the proportion of the sum of yttrium, lanthanum and hafnium and, where appropriate, further rare-earth elements being in excess of 2%.
  7. Product (1) according to Claim 1, 5 or 6, containing 0.1% - 0.5% yttrium 0.5% - 10% lanthanum 0.5% - 10% hafnium 0% - 10% magnesium.
  8. Product (1) according to Claim 7, containing 15% - 25% chromium 10% - 20% aluminium 0.01% - 0.3% yttrium 0.5% - 2% lanthanum 0.5% - 2% hafnium 0% - 33% cobalt.
  9. Product (1) according to Claim 7, containing 15% - 25% chromium 10% - 20% aluminium 0.01% - 0.3% yttrium 0.5% - 5% lanthanum 0.5% - 2% hafnium 0.1% - 2% magnesium 0% - 33% cobalt.
  10. Product (1) according to Claim 7, containing 3% - 15% chromium 3% - 10% aluminium 0.01% - 0.3% yttrium 0.5% - 10% lanthanum 0.5% - 10% hafnium 0% - 2% magnesium 0% - 33% cobalt.
  11. Product (1) according to Claim 4, containing 3% - 15% chromium 3% - 10% aluminium 0.01% - 0.5% yttrium 5% - 10% lanthanum 2% - 10% hafnium.
  12. Product (1) according to one of the preceding claims, in which the thermal insulation layer (5) comprises a ternary oxide with oxygen as the third element.
  13. Product (1) according to Claim 12, in which the first element of the ternary oxide is nickel, magnesium or cobalt and the second element of the ternary oxide is aluminium or chromium.
  14. Product (1) according to Claim 13, in which the first element of the ternary oxide is calcium or lanthanum, and the second element of the ternary oxide is aluminium, zirconium or hafnium.
  15. Product (1) according to one of Claims 12 to 14, having a binding layer (8) between the thermal insulation layer (5) and the bonding layer (7), the binding layer (8) comprising lanthanum oxide, in particular in combination with aluminium oxide, chromium oxide and/or hafnium oxide.
  16. Product (1) according to one of the preceding claims which is a component of a gas turbine, in particular a rotor blade, a guide vane or a heat shield element.
  17. Product (1) according to one of the preceding claims, in which the base body (2) consists of a nickel-based or cobalt-based alloy.
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DE59801544D1 (en) 2001-10-25
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US6416882B1 (en) 2002-07-09
EP1029100A1 (en) 2000-08-23

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