EP1937863A2 - Systemes constitues de plusieurs couches d'isolation thermique et procede de fabrication - Google Patents

Systemes constitues de plusieurs couches d'isolation thermique et procede de fabrication

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Publication number
EP1937863A2
EP1937863A2 EP06818021A EP06818021A EP1937863A2 EP 1937863 A2 EP1937863 A2 EP 1937863A2 EP 06818021 A EP06818021 A EP 06818021A EP 06818021 A EP06818021 A EP 06818021A EP 1937863 A2 EP1937863 A2 EP 1937863A2
Authority
EP
European Patent Office
Prior art keywords
layer
glass
gas
component
tight
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Withdrawn
Application number
EP06818021A
Other languages
German (de)
English (en)
Inventor
Daniel Emil Mack
Sonja-Michaela Gross
Robert Vassen
Detlev STÖVER
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Forschungszentrum Juelich GmbH
Original Assignee
Forschungszentrum Juelich GmbH
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Forschungszentrum Juelich GmbH filed Critical Forschungszentrum Juelich GmbH
Publication of EP1937863A2 publication Critical patent/EP1937863A2/fr
Withdrawn legal-status Critical Current

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Classifications

    • C—CHEMISTRY; METALLURGY
    • C03—GLASS; MINERAL OR SLAG WOOL
    • C03C—CHEMICAL COMPOSITION OF GLASSES, GLAZES OR VITREOUS ENAMELS; SURFACE TREATMENT OF GLASS; SURFACE TREATMENT OF FIBRES OR FILAMENTS MADE FROM GLASS, MINERALS OR SLAGS; JOINING GLASS TO GLASS OR OTHER MATERIALS
    • C03C8/00—Enamels; Glazes; Fusion seal compositions being frit compositions having non-frit additions
    • C03C8/02—Frit compositions, i.e. in a powdered or comminuted form
    • C—CHEMISTRY; METALLURGY
    • C03—GLASS; MINERAL OR SLAG WOOL
    • C03C—CHEMICAL COMPOSITION OF GLASSES, GLAZES OR VITREOUS ENAMELS; SURFACE TREATMENT OF GLASS; SURFACE TREATMENT OF FIBRES OR FILAMENTS MADE FROM GLASS, MINERALS OR SLAGS; JOINING GLASS TO GLASS OR OTHER MATERIALS
    • C03C8/00—Enamels; Glazes; Fusion seal compositions being frit compositions having non-frit additions
    • C03C8/14—Glass frit mixtures having non-frit additions, e.g. opacifiers, colorants, mill-additions
    • C03C8/18—Glass frit mixtures having non-frit additions, e.g. opacifiers, colorants, mill-additions containing free metals
    • 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
    • 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
    • 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
    • C23C28/36—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including layers graded in composition or physical properties
    • 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
    • C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
    • C23C4/04—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge characterised by the coating material
    • C23C4/06—Metallic material
    • C23C4/067—Metallic material containing free particles of non-metal elements, e.g. carbon, silicon, boron, phosphorus or arsenic
    • 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
    • C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
    • C23C4/04—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge characterised by the coating material
    • C23C4/06—Metallic material
    • C23C4/08—Metallic material containing only metal elements
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/14—Casings modified therefor
    • F01D25/145—Thermally insulated casings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • F01D5/288—Protective coatings for blades
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/24—Heat or noise insulation
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/78—Other construction of jet pipes
    • F02K1/82—Jet pipe walls, e.g. liners
    • F02K1/822—Heat insulating structures or liners, cooling arrangements, e.g. post combustion liners; Infrared radiation suppressors
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/10—Metals, alloys or intermetallic compounds
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/20—Oxide or non-oxide ceramics
    • F05D2300/21—Oxide ceramics
    • F05D2300/2102—Glass
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/603—Composites; e.g. fibre-reinforced
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23M—CASINGS, LININGS, WALLS OR DOORS SPECIALLY ADAPTED FOR COMBUSTION CHAMBERS, e.g. FIREBRIDGES; DEVICES FOR DEFLECTING AIR, FLAMES OR COMBUSTION PRODUCTS IN COMBUSTION CHAMBERS; SAFETY ARRANGEMENTS SPECIALLY ADAPTED FOR COMBUSTION APPARATUS; DETAILS OF COMBUSTION CHAMBERS, NOT OTHERWISE PROVIDED FOR
    • F23M2900/00—Special features of, or arrangements for combustion chambers
    • F23M2900/05004—Special materials for walls or lining
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/00005—Preventing fatigue failures or reducing mechanical stress in gas turbine components
    • 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
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
    • 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
    • Y10T428/249921—Web or sheet containing structurally defined element or component
    • Y10T428/249953—Composite having voids in a component [e.g., porous, cellular, etc.]

Definitions

  • Multi-layer thermal barrier coating systems and methods of manufacture are Multi-layer thermal barrier coating systems and methods of manufacture.
  • the invention relates to multilayer thermal barrier coating systems and a process for their preparation.
  • thermal barrier coatings which usually consist of yttrium-stabilized zirconium oxide (YSZ).
  • porous ceramics are permeable to oxygen.
  • An MCrAlY alloy adhesion promoter layer using iron, cobalt or nickel as metal M or an aluminide protects the substrate from oxidation while improving the adhesion of the ceramic layer.
  • surface temperatures of the components up to 1200 0 C can be realized today.
  • Thermal barrier coating systems often fail near the primer layer, where stresses are locally enhanced by particular geometric conditions due to boundary layer roughness. This effect is intensified if an oxide layer with a plasticity and a drastically reduced plasticity is formed between the bonding agent layer and the thermal barrier coating. When the critical oxide layer thickness is reached, this leads to the ceramic thermal insulation layer flaking off.
  • thermal barrier coatings are essential.
  • these composites are much more thermally conductive than about YSZ, so that to achieve a corresponding thermal insulation, a significantly larger layer thickness is required.
  • a thermal barrier coating which consists of a composite of YSZ or a glass-metal composite layer of 50-100 ⁇ m thickness and an overlying further layer with significantly lower thermal conductivity and higher temperature stability.
  • the disadvantage is the liability within this network insufficient.
  • the layers fail first at the interface between the composite layer and the overlying layer. However, they can also fail within the composite layer.
  • the object of the invention is to provide a method with which thermal barrier coatings can be produced with a better service life at high operating temperatures than in the prior art.
  • the object of the invention is also to provide a component with a temperature and aging resistant thermal barrier coating available.
  • an improved method for producing a thermal barrier coating on a component has been developed.
  • a gas-tight first layer is applied to the component.
  • the material for the gas-tight layer in particular, a glass-metal composite is suitable, wherein the gas-tightness is mainly caused by the glass.
  • the gas-tight layer is removed in an oxidizing atmosphere. Thereafter, a portion of the gas-tight layer is removed.
  • a second, porous layer is applied to the gas-tight layer.
  • a material for the porous layer in particular a ceramic, for example yttrium-stabilized zirconium oxide, is suitable. Such ceramics have a particularly low thermal conductivity, so that the second layer as actual thermal barrier coating must have only a small thickness.
  • thermal barrier coatings which combine the advantages of a glass-metal composite material and a ceramic.
  • the gas-tight composite protects the substrate from oxidation.
  • the porous ceramic has a significantly lower thermal conductivity than the composite material and requires a much smaller layer thickness than a thermal composite consisting of pure composite material. Due to the porous ceramic, the underlying composite material is additionally protected against corrosion and aging under conditions of use by reducing the temperature within the substrate-cooled layer system. This applies in particular when operating in oxidising atmospheres and at temperatures above 1000 ° C.
  • an alkali silicate glass is suitable and here in particular a glass of the composition: R 2 O - 5-30 wt .-%, TO - 5-30 wt .-%, Al 2 O 3 - 0-20
  • R represents one or more elements from the series Li, Na, K, Rb, Cs and T for one or more elements from the series Mg, Ca, Sr, Ba.
  • Such glasses have a particularly low thermal conductivity.
  • the thermal expansion coefficient of the lower region can be set in a wide range of 11-10 " 6K " 1 to 13 -10 " 6K " 1 .
  • thermal stresses between the lower region and the component, or between the lower and upper regions of the thermal barrier coating can be reduced. Such stresses could cause the entire thermal barrier coating to flake off the component, or cause the upper portion of the thermal barrier coating to flake off its lower portion. In places with a small radius of curvature, the voltage responsible for the chipping can be reduced.
  • alkali-free base glass in particular base glasses with 25-55 wt .-% SiO 2 , 0-25 wt -.% CaO and / or MgO, 0-15 wt .-% Al 2 O 3 , 0-50 wt .-% BaO and in total 0-15 wt .-% admixtures of, for example, B 2 O 3 , La 2 O 3 and MnO, are suitable as glass.
  • the use of alkali-free base glasses is suitable for increasing the risk of formation of critical corrosion of the metallic layers in combination with sulfur-containing hot gas minimize.
  • a glass-metal composite material containing an alloy of the composition MCrAlY with iron, cobalt or nickel as metal M is selected as the material for the gas-tight layer.
  • This composite material adheres particularly well to superalloys, from which, for example, turbine components are produced.
  • the aging takes place at temperatures above
  • the swapping follows at lower temperatures of less than 1000 0 C, preferably below 850 0 C. This may be necessary, for example when made with the thermal barrier coating is to be provided components of a non-highly heat-resistant material. Examples of such components are components of steam turbines, internal combustion engines and steel pipes, which are intended for the passage of hot gases.
  • the material composition should in this case be chosen so that the corroded layer to be removed forms as quickly as possible despite the reduced aging temperature.
  • the gas-tight layer must at least be removed so far that their corroded part is completely removed.
  • the depth at which the gas-tight layer corrodes during the removal depends on its exact composition as well as on the process parameters of the removal process.
  • the authoritative expert can estimate the depth of the corrosion or determine it with suitable measuring methods, for example by microscopic observation of a cross section. However, it can also determine the required depth to which the gas-tight layer must be removed in a reasonable number of tests. As a rule, it is to be expected that the gas-tight layer will corrode at least to a depth of 30 ⁇ m; Therefore, at least 30 ⁇ m of the gas-tight layer should be removed.
  • the removal can be done for example by mechanical processing.
  • proven techniques that can also be used in mass production are available.
  • the removal takes place by irradiation of the surface with particles.
  • a roughness of 4 .mu.m or more is introduced into the surface of the gas-tight layer prior to the application of the porous layer.
  • the adhesion between the gas-tight layer and the porous layer is further increased. This is particularly important if the porous layer is to be applied by means of a thermal spraying process.
  • Spray processes require a minimum of roughness on the surface to be coated.
  • an adhesion promoter layer may optionally be applied to the component prior to the production of the thermal barrier coating. This reduces the risk that the thermal barrier coating will generally flake off the component.
  • an aluminum-containing adhesion promoter layer and here in particular a layer of the composition MCrAlY with iron, cobalt or nickel as metal M, or else an aluminide layer are suitable. Such layers adhere particularly well to metals, in particular to the superalloys, from which turbine components and similar high temperature loaded components are produced.
  • an aluminum-impermeable barrier layer is introduced between the adhesion promoter layer and the gas-tight layer.
  • Such aluminum depletion has the consequence that the adhesion promoter layer is irreversibly weakened and is therefore to be kept as small as possible.
  • a barrier layer of alumina is selected.
  • a barrier layer can be produced particularly easily, since the adhesion promoter layer already contains the starting material aluminum.
  • the barrier layer can be produced by outsourcing the adhesion promoter layer in an oxidizing atmosphere. This type of production is particularly suitable since, in addition to the already existing air, no further reagents are needed.
  • the retrieval of the adhesive layer is preferably carried out at temperatures above 1000 0 C.
  • thermal barrier coating on the surface of a component with novel structural features has a better service life at high operating temperatures than thermal barrier coatings according to the prior art.
  • a thermal barrier coating which can be produced, for example, by the aforementioned method, comprises a lower and an upper region, the lower region being located between the component and the upper region.
  • the lower area consists entirely or predominantly of a composite material, which consists of glass with metal or glass ceramic with metal.
  • the glass is in particular a silicate glass or a alkali-free base glass, as a glass ceramic, in particular a glass ceramic based on the components BaO, CaO,
  • the upper part consists of a material that has a lower thermal conductivity than the material in the lower part.
  • the upper area can be designed by choosing a suitable material so that it acts as the actual thermal barrier coating.
  • the upper porous region can in particular also be configured as a graded layer or as a multilayered layer.
  • the adhesion between the lower region and the upper region can be significantly improved by the near-surface volume of the lower region facing the upper region (Limiting volume) is configured at least partially crystalline.
  • the amorphous portion of the lower portion should be between 5 and 60 volume percent.
  • the upper region can then advantageously consist of a porous ceramic, which would tend to adhere only very poorly on the lower region.
  • the ceramic may be in particular yttrium-stabilized zirconium oxide.
  • the partial crystallization reduces the aging of the glass / glass-ceramic-metal layer and thus improves the adhesion of the upper region to the lower region.
  • the at least semicrystalline boundary volume makes it possible to combine the advantages of the composite material and the ceramic in the thermal barrier coating.
  • the gas-tight composite material protects the substrate from oxidation.
  • the porous ceramic has a significantly lower thermal conductivity than the composite material. It requires a considerably smaller layer thickness than a thermal composite layer consisting of pure composite material and also protects the composite material against aging and temperature-assisted corrosion under conditions of use by reducing the temperature in the lower region of the substrate-side cooled component. This applies in particular when operating in oxidizing atmospheres and at surface temperatures above 1000 ° C.
  • the composite material contains an alloy of the composition MCrAlY with iron, cobalt or nickel as metal M.
  • the interface between the lower and the upper region has a roughness greater than 4 microns.
  • the adhesion between the upper and lower regions is further increased, in particular if the upper region is applied by means of a thermal spraying process.
  • Such spraying methods require a minimum of roughness on the surface to be coated.
  • the roughness can be introduced, for example, by mechanical processing or by irradiation of the interface with particles in the interface. Alternatively, even in the production of the lower region, the roughness can be adjusted, for example by using a thermal spraying process to produce this region. When applying layers by means of thermal spray processes, the resulting roughness can be controlled particularly well via the process parameters.
  • the composite material in the lower region may contain an alkali silicate glass and here in particular a glass of the composition: R 2 O - 5-30 wt .-%, TO - 5-30 wt .-%, Al 2 O 3 - 0-20
  • R represents one or more elements from the series Li, Na, K, Rb, Cs and T for one or more elements from the series Mg, Ca, Sr, Ba.
  • Silicate glasses, in particular in the aforementioned composition have a particularly low thermal conductivity.
  • the coefficient of thermal expansion of the lower region can be varied over a wide range 11-10 "6 K " 1 to 13-10 “6 K “ 1 can be set.
  • thermal stresses between the lower region and the component or between the lower and upper region which could cause the heat insulation layer to flake off, can be reduced in regions with a small radius of curvature.
  • the composite material can also be a glass ceramic, in particular based on the components BaO, CaO, Al 2 O 3 and SiO 2 , or an alkali-free base glass, in particular a base glass with 25-55 wt .-% SiO 2 , 0-25 wt .-% CaO, 0-15% by weight Al 2 O 3 , 0-50% by weight BaO and in total 0-15% by weight admixtures of, for example, B 2 O 3 , La 2 O 3 and MnO. Additions of ZnO, PbO and V 2 O 5 are also useful in the glass ceramic since they crystallize out and are therefore immobile. You can, for example, influence the crystallization properties of the glass ceramic.
  • the base glass or the glass ceramic contains 1% by weight Al 2 O 3 or less, in particular 0.5% by weight Al 2 O 3 or less.
  • crystallizing glasses have the advantage that they form a partially crystalline boundary volume particularly quickly, so that, under favorable circumstances, no corroded area arises which would have to be removed.
  • the thermal barrier coating may be on a primer layer which reduces the risk of the thermal barrier coating from flaking off the substrate.
  • the primer layer is advantageously aluminum-containing; In particular, it may be a layer of the composition MCrAlY with iron, cobalt or nickel as the metal M. such Layers have the advantage that they adhere particularly well to those alloys from which turbine components are made.
  • an aluminum-impermeable barrier layer is located between the adhesion promoter layer and the thermal barrier coating. This prevents aluminum from migrating from the primer layer into the composite material. Preventing this aluminum depletion prevents the primer layer from being further weakened over time by the mere presence of the composite material, especially at high operating temperatures.
  • the barrier layer is advantageously aluminum oxide, which is particularly easy to produce, for example by suitable aging of the bonding agent layer in air.
  • Method manufacturable thermal barrier coating has further advantages. It is also inexpensive to produce in quantities required for mass production with reproducible quality. There are also more materials and process parameters
  • the substrate consists of a superalloy IN738. Then a 50-200 micron thick MCrAlY alloy is applied as a bonding agent layer (bond coat).
  • metal M the elements cobalt and nickel were chosen here.
  • the alloy of the adhesion promoter layer consists of 33% by weight of cobalt, 27% by weight of chromium, 31% by weight of nickel, 8% by weight of aluminum, 0.5% by weight of yttrium and an admixture of 0.5% by weight of silicon.
  • the metal used is the alloy used in the adhesion promoter layer.
  • the glass is an alkali-lime-silica glass of 70 wt .-% SiO 2, 17 wt .-% Na 2 O, 8 wt .-% CaO, 2 wt .-% MgO and 3 wt .-% Al 2 O 3.
  • the gas-tight layer is first produced with a thickness of about 150-300 microns. Subsequently, the component is aged for 24-48 hours at 950 0 C in air.
  • Example 1 the procedure is as in Example 1. Subsequently, as a gas-tight layer with a metal-glass-ceramic composite layer
  • the metal used is again the alloy of the adhesion promoter layer.
  • the glass ceramic is an alkali-free base glass with 47 wt .-% SiO 2 , 16 wt .-% CaO, 37 wt .-% BaO and 0.5 wt .-% Al 2 O 3 .
  • the ceramic layer of YSZ is applied directly to the partially crystallized composite layer in a thickness of 250-350 ⁇ m without a corroded layer portion being removed beforehand.

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Abstract

L'invention concerne un procédé permettant de réaliser des couches d'isolation thermique adhérant mieux à des composants même en cas de températures élevées et souvent variables. Une couche de composite verre-métal étanche au gaz est appliquée sur le composant et vieillie. La partie attaquée par la corrosion de la couche étanche au gaz est ensuite retirée puis une seconde couche poreuse est appliquée. Cette dernière peut être composée d'une céramique, en particulier d'un oxyde de zirconium stabilisé à l'yttrium. Ladite invention concerne également une couche d'isolation thermique constituée d'un assemblage d'une couche de composite verre-métal étanche au gaz et d'une autre couche poreuse placée sur cette dernière. L'adhérence à l'intérieur de cet assemblage est améliorée de façon marquée par rapport à l'état de la technique, le volume à la limite entre la couche de composite et l'autre couche présentant une structure semi-cristalline. Ainsi, cette invention permet, en particulier, de réaliser un assemblage de couches de composite verre au silicate-métal et d'oxyde de zirconium stabilisé à l'yttrium, thermostables sur une longue durée. Un assemblage de ce type est particulièrement avantageux lorsqu'il est utilisé comme couche d'isolation thermique, puisque cet assemblage combine une bonne protection contre l'oxydation à une faible conductivité thermique et une faible sensibilité au vieillissement.
EP06818021A 2005-10-20 2006-10-17 Systemes constitues de plusieurs couches d'isolation thermique et procede de fabrication Withdrawn EP1937863A2 (fr)

Applications Claiming Priority (2)

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DE200510050661 DE102005050661A1 (de) 2005-10-20 2005-10-20 Mehrlagige Wärmedämmschichtsysteme und Verfahren zur Herstellung
PCT/DE2006/001837 WO2007045225A2 (fr) 2005-10-20 2006-10-17 Systemes constitues de plusieurs couches d'isolation thermique et procede de fabrication

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EP1937863A2 true EP1937863A2 (fr) 2008-07-02

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EP (1) EP1937863A2 (fr)
JP (1) JP5113068B2 (fr)
DE (1) DE102005050661A1 (fr)
WO (1) WO2007045225A2 (fr)

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US7915527B1 (en) 2006-08-23 2011-03-29 Rockwell Collins, Inc. Hermetic seal and hermetic connector reinforcement and repair with low temperature glass coatings
US8617913B2 (en) * 2006-08-23 2013-12-31 Rockwell Collins, Inc. Alkali silicate glass based coating and method for applying
US8581108B1 (en) 2006-08-23 2013-11-12 Rockwell Collins, Inc. Method for providing near-hermetically coated integrated circuit assemblies
US8084855B2 (en) 2006-08-23 2011-12-27 Rockwell Collins, Inc. Integrated circuit tampering protection and reverse engineering prevention coatings and methods
US8637980B1 (en) 2007-12-18 2014-01-28 Rockwell Collins, Inc. Adhesive applications using alkali silicate glass for electronics
US8076185B1 (en) 2006-08-23 2011-12-13 Rockwell Collins, Inc. Integrated circuit protection and ruggedization coatings and methods
CN101310969B (zh) * 2007-05-23 2011-11-16 中国科学院金属研究所 一种用于Ti-Al合金的Al/Al2O3/MCrAlY复合涂层及制备方法
RU2447361C2 (ru) * 2007-11-23 2012-04-10 Сименс Акциенгезелльшафт Элемент горелки и горелка с покрытием из оксида алюминия и способ покрытия элемента горелки
EP2112334A1 (fr) * 2008-04-21 2009-10-28 Siemens Aktiengesellschaft Boîtier extérieur pour une turbomachine
US8119040B2 (en) 2008-09-29 2012-02-21 Rockwell Collins, Inc. Glass thick film embedded passive material
DE102009058853A1 (de) * 2009-12-18 2011-06-22 Rolls-Royce Deutschland Ltd & Co KG, 15827 Turbinenschaufel
CN105568204A (zh) * 2015-12-10 2016-05-11 苏州市嘉明机械制造有限公司 一种基于等离子喷涂的耐热压绝缘镜板的制造方法
CN106746666B (zh) * 2016-12-05 2020-04-17 西北有色金属研究院 玻璃陶瓷复合热障涂层及涂层制备方法
CN111748761B (zh) * 2020-06-10 2022-04-22 北京工业大学 高韧性低导热的金属基-陶瓷复合涂层及其制备方法和应用
CN112876080B (zh) * 2021-02-04 2022-02-15 中国科学院合肥物质科学研究院 一种铅基反应堆泵叶轮用玻璃陶瓷涂层及其制备方法
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Publication number Publication date
US7998601B2 (en) 2011-08-16
WO2007045225A3 (fr) 2007-11-22
JP2009511752A (ja) 2009-03-19
WO2007045225A2 (fr) 2007-04-26
DE102005050661A1 (de) 2007-05-16
JP5113068B2 (ja) 2013-01-09
US20090110904A1 (en) 2009-04-30

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