EP1029100B1 - Produit pourvu d'un systeme stratifie pour la protection contre un gaz chaud agressif - Google Patents

Produit pourvu d'un systeme stratifie pour la protection contre un gaz chaud agressif 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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Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Lifetime
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EP98959748A
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German (de)
English (en)
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EP1029100A1 (fr
Inventor
Wolfram Beele
Beate Heimberg
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Siemens AG
Siemens Corp
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Siemens AG
Siemens Corp
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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.

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  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Inorganic Chemistry (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Ceramic Engineering (AREA)
  • Other Surface Treatments For Metallic Materials (AREA)
  • Laminated Bodies (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Claims (17)

  1. Produit (1) ayant un corps (2) de base métallique et un système (3) stratifié se trouvant dessus, destiné à protéger le corps (2) de base d'un gaz (4) agressif chaud et comprenant une couche (5) calorifuge en céramique ayant une surface (6) extérieure pouvant être soumise au gaz (4), ainsi qu'une couche (7) d'accrochage, interposée entre la couche (5) calorifuge et le corps (2) de base, en un alliage comprenant les éléments suivants (exprimés en pourcentage en poids) : de 3% à 50% de chrome de 3% à 20% d'aluminium de 0,01% à 0,5% d'yttrium et/ou d'un élément des terres rares de 0,1% à 10% de lanthane de 0% à 10% d'hafnium de 0% à 10% de magnésium de 0% à 2% de silicium
    ainsi qu'un élément ou que plusieurs éléments du groupe comprenant le fer, le cobalt et le nickel.
  2. Produit (1) suivant la revendication 1, contenant de 15% à 25% de chrome de 10% à 20% d'aluminium de 0,01% à 0,3% d'yttrium de 0,1% à 5% de lanthane de 0% à 2% d'hafnium de 0,1% à 2% de magnésium de 0% à 33% de cobalt.
  3. Produit (1) suivant la revendication 1, contenant de 3% à 15% de chrome de 3% à 10% d'aluminium de 0,01% à 0,3% d'yttrium de 0,5% à 10% de lanthane de 0% à 10% d'hafnium de 0% à 2% de magnésium de 0% à 33% de cobalt.
  4. Produit (1) comprenant un corps (2) de base métallique et un système (3) stratifié se trouvant dessus, destiné à protéger le corps (2) de base d'un gaz (4) agressif chaud et comprenant une couche (5) calorifuge en céramique ayant une surface (6) extérieure pouvant être soumise au gaz (4), ainsi qu'une couche (7) d'accrochage, interposée entre la couche (5) calorifuge et le corps (2) de base, en un alliage comprenant les éléments suivants (exprimés en pourcentage en poids) : de 3% à 50% de chrome de 3% à 20% d'aluminium de 0% à 0,5% d'yttrium et/ou d'un élément des terres rares de 0,1% à 10% de lanthane de 0,1% à 10% d'hafnium de 0% à 10% de magnésium de 0% à 2% de silicium
    ainsi qu'un élément ou que plusieurs éléments du groupe comprenant le fer, le cobalt et le nickel.
  5. Produit (1) suivant la revendication 4, contenant de 15% à 25% de chrome de 10% à 20% d'aluminium de 0,01% à 0,3% d'yttrium de 0,1% à 2% de lanthane de 0,1% à 2% d'hafnium de 0% à 33% de cobalt.
  6. Produit (1) suivant l'une des revendications précédentes, dans lequel la proportion de la somme de l'yttrium, du lanthane et de l'hafnium et le cas échéant d'autres éléments des terres rares, dépasse 2%.
  7. Produit (1) suivant la revendication 1, 5 ou 6, contenant de 0,1% à 0,5% d'yttrium de 0,5% à 10% de lanthane de 0,5% à 10% d'hafnium de 0% à 10% de magnésium.
  8. Produit (1) suivant la revendication 7, contenant de 15% à 25% de chrome de 10% à 20% d'aluminium de 0,01% à 0,3% d'yttrium de 0,5% à 2% de lanthane de 0,5% à 2% d'hafnium de 0% à 33% de cobalt.
  9. Produit (1) suivant la revendication 7, contenant de 15% à 25% de chrome de 10% à 20% d'aluminium de 0,01% à 0,3% d'yttrium de 0,5% à 5% de lanthane de 0,5% à 2% d'hafnium de 0,1% à 2% de magnésium de 0% à 33% de cobalt.
  10. Produit (1) suivant la revendication 7, contenant de 3% à 15% de chrome de 3% à 10% d'aluminium de 0,01% à 0,3% d'yttrium de 0,5% à 10% de lanthane de 0,5% à 10% d'hafnium de 0% à 2% de magnésium de 0% à 33% de cobalt.
  11. Produit (1) suivant la revendication 4, contenant de 3% à 15% de chrome de 3% à 10% d'aluminium de 0,01% à 0,5% d'yttrium de 5% à 10% de lanthane de 2% à 10% d'hafnium.
  12. Produit (1) suivant l'une des revendications précédentes, dans lequel la couche (5) calorifuge comporte un oxyde ternaire ayant de l'oxygène en tant que troisième élément.
  13. Produit (1) suivant la revendication 12, dans lequel le premier élément de l'oxyde ternaire est le nickel, le magnésium ou le cobalt et le deuxième élément de l'oxyde ternaire est l'aluminium ou le chrome.
  14. Produit (1) suivant la revendication 12, dans lequel le premier élément de l'oxyde ternaire est le calcium ou le lanthane et le deuxième élément de l'oxyde ternaire est l'aluminium, le zirconium ou l'hafnium.
  15. Produit (1) suivant l'une des revendications 12 à 14, comprenant une couche (8) de liaison entre la couche (5) calorifuge et la couche (7) d'accrochage, la couche (8) de liaison comportant de l'oxyde de lanthane, notamment en combinaison avec de l'oxyde d'aluminium, de l'oxyde de chrome et/ou de l'oxyde d'hafnium.
  16. Produit (1) suivant l'une des revendications précédentes, qui est un élément constitutif d'une turbine à gaz, notamment une aube mobile, une aube directrice ou un élément formant bouclier thermique.
  17. Produit (1) suivant l'une des revendications précédentes, dans lequel le corps (2) de base est en un alliage à base de nickel ou à base de cobalt.
EP98959748A 1997-11-03 1998-10-21 Produit pourvu d'un systeme stratifie pour la protection contre un gaz chaud agressif Expired - Lifetime EP1029100B1 (fr)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
DE19748506 1997-11-03
DE19748506 1997-11-03
PCT/DE1998/003092 WO1999023270A1 (fr) 1997-11-03 1998-10-21 Produit pourvu d'un systeme stratifie pour la protection contre un gaz chaud agressif

Publications (2)

Publication Number Publication Date
EP1029100A1 EP1029100A1 (fr) 2000-08-23
EP1029100B1 true EP1029100B1 (fr) 2001-09-19

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US (1) US6416882B1 (fr)
EP (1) EP1029100B1 (fr)
JP (1) JP2001521987A (fr)
DE (1) DE59801544D1 (fr)
WO (1) WO1999023270A1 (fr)

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Also Published As

Publication number Publication date
EP1029100A1 (fr) 2000-08-23
US6416882B1 (en) 2002-07-09
JP2001521987A (ja) 2001-11-13
DE59801544D1 (de) 2001-10-25
WO1999023270A1 (fr) 1999-05-14

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