EP2802677A1 - Ceramic thermally insulating layer system having an external aluminum-rich layer, and method - Google Patents

Ceramic thermally insulating layer system having an external aluminum-rich layer, and method

Info

Publication number
EP2802677A1
EP2802677A1 EP12808773.1A EP12808773A EP2802677A1 EP 2802677 A1 EP2802677 A1 EP 2802677A1 EP 12808773 A EP12808773 A EP 12808773A EP 2802677 A1 EP2802677 A1 EP 2802677A1
Authority
EP
European Patent Office
Prior art keywords
layer
aluminum
layer system
ceramic
thermally insulating
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Withdrawn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
EP12808773.1A
Other languages
German (de)
French (fr)
Inventor
Maria del Mar JUEZ LORENZO
Vladislav Kolarik
Veronica KUCHENREUTHER-HUMMEL
Werner Stamm
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.)
Fraunhofer Gesellschaft zur Forderung der Angewandten Forschung eV
Siemens AG
Original Assignee
Fraunhofer Gesellschaft zur Forderung der Angewandten Forschung eV
Siemens AG
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 Fraunhofer Gesellschaft zur Forderung der Angewandten Forschung eV, Siemens AG filed Critical Fraunhofer Gesellschaft zur Forderung der Angewandten Forschung eV
Priority to EP12808773.1A priority Critical patent/EP2802677A1/en
Publication of EP2802677A1 publication Critical patent/EP2802677A1/en
Withdrawn legal-status Critical Current

Links

Classifications

    • 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
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B15/00—Layered products comprising a layer of metal
    • B32B15/04—Layered products comprising a layer of metal comprising metal as the main or only constituent of a layer, which is next to another layer of the same or of a different material
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B15/00—Layered products comprising a layer of metal
    • B32B15/20—Layered products comprising a layer of metal comprising aluminium or copper
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B18/00—Layered products essentially comprising ceramics, e.g. refractory products
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B5/00—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts
    • B32B5/16—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by features of a layer formed of particles, e.g. chips, powder or granules
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B9/00—Layered products comprising a layer of a particular substance not covered by groups B32B11/00 - B32B29/00
    • B32B9/005—Layered products comprising a layer of a particular substance not covered by groups B32B11/00 - B32B29/00 comprising one layer of ceramic material, e.g. porcelain, ceramic tile
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B9/00—Layered products comprising a layer of a particular substance not covered by groups B32B11/00 - B32B29/00
    • B32B9/04—Layered products comprising a layer of a particular substance not covered by groups B32B11/00 - B32B29/00 comprising such particular substance as the main or only constituent of a layer, which is next to another layer of the same or of a different material
    • 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
    • C23C2/00—Hot-dipping or immersion processes for applying the coating material in the molten state without affecting the shape; Apparatus therefor
    • C23C2/04—Hot-dipping or immersion processes for applying the coating material in the molten state without affecting the shape; Apparatus therefor characterised by the coating material
    • C23C2/12—Aluminium or alloys based thereon
    • 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
    • C23C28/02—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 only coatings only including layers of metallic material
    • C23C28/021—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 only coatings only including layers of metallic material including at least one metal alloy 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
    • C23C28/32—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic 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
    • C23C30/00—Coating with metallic material characterised only by the composition of the metallic material, i.e. not characterised by the coating process
    • C23C30/005—Coating with metallic material characterised only by the composition of the metallic material, i.e. not characterised by the coating process on hard metal substrates
    • 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
    • C23C4/073—Metallic material containing MCrAl or MCrAlY alloys, where M is nickel, cobalt or iron, with or without non-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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2250/00—Layers arrangement
    • B32B2250/03—3 layers
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2264/00—Composition or properties of particles which form a particulate layer or are present as additives
    • B32B2264/10—Inorganic particles
    • B32B2264/105—Metal
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2603/00—Vanes, blades, propellers, rotors with blades
    • 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
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/231—Preventing heat transfer
    • 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
    • F05D2300/12—Light metals
    • F05D2300/121—Aluminium
    • 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
    • F05D2300/2112—Aluminium oxides
    • 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
    • F05D2300/2118—Zirconium oxides
    • 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

Definitions

  • the invention relates to a layer system with ceramic
  • thermal barrier coatings In gas turbine inspections, attacks on thermal barrier coatings are observed, especially in oil-fired turbines. Further investigations show that CMAS attacks were the trigger of layer damage, as has already been observed in aircraft turbines.
  • a compound of calcium, magnesium, aluminum and silicon or iron leads to low-melting eutectics on thermal barrier coatings in the temperature range around 1200 ° C - 1250 ° C or higher. These compounds dissolve the yttria required for stabilization from the thermal barrier coating. This leads to strong monoclinic phase transitions with temperature changes in the ceramic, which lead to the destruction of the thermal barrier coating.
  • the chemically very aggressi ⁇ ve CMAS compound reacts with the aluminum excess of anorthite. This is a high-fusing connection that eliminates or at least reduces CMAS attack.
  • a particular advantage of this coating ⁇ which is the ability of the repeated application even after installation of the component.
  • the building up anorthite layer protects to ⁇ additionally from the attack of CMAS connection.
  • the application of the aluminum-containing protective layer on the rotor and guide vane of a gas turbine can also take place in the installed state, wherein in particular a housing half of the gas turbine is open.
  • the coating is inexpensive (aluminum particles in egg ⁇ ner binder matrix) and easy to apply.
  • the additional protective layer system also enables the operator of a gas turbine to operate a cost-effective partially stabilized zirconium oxide system under CMAS attack.
  • FIG. 1 shows a layer system according to the invention
  • FIG. 2 shows a turbine blade
  • Figure 3 is a list of superalloys.
  • FIG. 1 shows a layer system 1 according to the invention.
  • the layer system 1 has a substrate 4.
  • the substrate 4 comprises, in particular consists of a nickel- or ko ⁇ baltbas fortunate superalloy, in particular according to FIG. 3
  • the layer system 1 furthermore has a ceramic layer 10.
  • the ceramic layer 10 may comprise zirconium oxide, partially stabilized zirconium oxide or two-layered ceramic systems of zirconium oxide and / or pyrochlore phase such as gadolinium hafnate or zirconate.
  • a metallic adhesion promoter layer and / or an aluminum oxide layer may be present. These may be aluminide layers or NiCoCrAlY layers that form the TGOs.
  • Ceramic thermal barrier coating systems as they are known in high-temperature components, especially in turbine blades or components of gas turbines, may be the starting point.
  • the layer of aluminum or Alumini ⁇ ump Preferably, the layer of aluminum or Alumini ⁇ ump
  • the particle size is preferably from 0.1 ⁇ to 50 ⁇ .
  • Aluminum always has an oxide layer.
  • the proportion of aluminum (AI) represents the largest share.
  • Layers 13 with compounds which have aluminum in the superstoichiometric ratio or have aluminum in excess can also be used, but preferably no aluminides (NiAl,%) Or MCrAlYs.
  • Possible methods for applying the layer 13 of an emulsion of the Al particles and binders are spraying (application by brush, application with a roller or immersion of the components in the emulsion.
  • FIG. 2 shows a perspective view of a rotor 120 or guide vane 130 of a turbomachine that extends along a longitudinal axis 121.
  • the turbomachine may be a gas turbine of an aircraft or a power plant for electricity generation, a steam turbine or a compressor.
  • the blade 120, 130 has along the longitudinal axis 121 to each other, a securing region 400, an adjoining blade or vane platform 403 and a blade 406 and a blade tip 415.
  • the vane 130 As a guide vane 130, the vane 130 having at its blade tip 415 have a further platform (not Darge ⁇ asserted).
  • a blade root 183 is formed, which serves for attachment of the blades 120, 130 to a shaft or a disc (not shown).
  • the blade root 183 is, for example, as a hammerhead out staltet ⁇ . Other designs as fir tree or Schissebwschwanzfuß are possible.
  • the blade 120, 130 has for a medium which flows past the scene ⁇ felblatt 406 on a leading edge 409 and a trailing edge 412th
  • massive metallic materials in particular superalloys, are used.
  • superalloys are known, for example, from EP 1 204 776 B1, EP 1 306 454, EP 1 319 729 A1, WO 99/67435 or WO 00/44949.
  • the blade 120, 130 can be made by a casting process, also by directional solidification, by a forging process, by a milling process or combinations thereof.
  • Such monocrystalline workpieces takes place e.g. by directed solidification from the melt.
  • These are casting processes in which the liquid metallic alloy is transformed into a monocrystalline structure, i. to the single-crystal workpiece, or directionally solidified.
  • dendritic crystals are aligned along the heat flow and form either a columnar grain structure (columnar, ie grains that run the entire length of the workpiece and here, in common parlance, referred to as directionally solidified) or a monocrystalline structure, ie the whole workpiece be ⁇ is made of a single crystal.
  • a columnar grain structure columnar, ie grains that run the entire length of the workpiece and here, in common parlance, referred to as directionally solidified
  • a monocrystalline structure ie the whole workpiece be ⁇ is made of a single crystal.
  • Structures are also called directionally solidified structures. Such methods are known from US Pat. No. 6,024,792 and EP 0 892 090 A1.
  • the blades 120, 130 may have coatings against corrosion or oxidation, e.g. B. (MCrAlX; M is at least one element of the group consisting of iron (Fe), cobalt (Co), Ni ⁇ ckel (Ni), X is an active element and stands for yttrium (Y) and / or silicon and / or at least one element the rare earth, or hafnium (Hf)).
  • M is at least one element of the group consisting of iron (Fe), cobalt (Co), Ni ⁇ ckel (Ni)
  • X is an active element and stands for yttrium (Y) and / or silicon and / or at least one element the rare earth, or hafnium (Hf)).
  • Such alloys are known from EP 0 486 489 B1, EP 0 786 017 B1, EP 0 412 397 B1 or EP 1 306 454 A1.
  • the density is preferably 95% of the theoretical log ⁇ te.
  • the layer composition comprises Co-30Ni-28Cr-8A1-0, 6Y-0, 7Si or Co-28Ni-24Cr-10Al-0, 6Y.
  • nickel-based protective layers such as Ni-10Cr-12Al-0.6Y-3Re or Ni-12Co-21Cr-IIAl-O, 4Y-2Re or Ni-25Co-17Cr-10A1-0, 4Y-1 are also preferably used , 5Re.
  • a thermal barrier coating which is preferably the outermost layer, and consists for example of Zr0 2 , Y2Ü3-Zr02, ie it is not, partially ⁇ or fully stabilized by yttria
  • the thermal barrier coating covers the entire MCrAlX layer.
  • Electron beam evaporation produces stalk-shaped grains in the thermal barrier coating.
  • the heat insulation layer may have ⁇ porous, micro- or macro-cracked compatible grains for better thermal shock resistance.
  • the Thermal insulation layer is therefore preferably more porous than the
  • Refurbishment means that components 120, 130 may need to be deprotected after use (e.g., by sandblasting). This is followed by removal of the corrosion and / or oxidation layers or products. Optionally, even cracks in the component 120, 130 are repaired. This is followed by a re-coating of the component 120, 130 and a renewed use of the component 120, 130.
  • the blade 120, 130 may be hollow or solid. If the blade 120, 130 is to be cooled, it is hollow and also has, if necessary, film cooling holes 418 (indicated by dashed lines) on.

Landscapes

  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Materials Engineering (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Ceramic Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Plasma & Fusion (AREA)
  • Life Sciences & Earth Sciences (AREA)
  • Wood Science & Technology (AREA)
  • Inorganic Chemistry (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Other Surface Treatments For Metallic Materials (AREA)

Abstract

As a result of applying particles of aluminum to an outermost layer, the ceramic layer (10) is better protected against what is known as CMAS attacks.

Description

Keramisches Wärmedämmschichtsystem mit äußerer aluminiumreicher Schicht und Verfahren  Ceramic thermal barrier coating system with outer aluminum rich layer and process
Die Erfindung betrifft ein Schichtsystem mit keramischerThe invention relates to a layer system with ceramic
Schicht, auf der eine aluminiumreiche äußere Schicht aufge¬ bracht ist und ein Verfahren. Layer on which an aluminum-rich outer layer is applied ¬ and a method.
Bei Inspektionen von Gasturbinen werden insbesondere bei mit in Öl befeuerten Turbinen Angriffe auf Wärmedämmschichten beobachtet. Nähere Untersuchungen zeigen, dass - wie auch schon in Flugturbinen beobachtet wurde - CMAS-Angriffe der Auslöser der Schichtschädigungen waren. Eine Verbindung von Kalzium, Magnesium, Aluminium und Silizium bzw. Eisen führt zu nieder- schmelzenden Eutektika auf Wärmedämmschichten im Temperaturbereich um 1200°C - 1250°C oder höher. Diese Verbindungen lösen das zur Stabilisierung benötigte Yttriumoxid aus der Wärmedämmschicht. Dies führt zu stark monoklinen Phasenübergängen bei Temperaturwechsel in der Keramik, die zur Zerstö- rung der Wärmedämmschicht führen. In gas turbine inspections, attacks on thermal barrier coatings are observed, especially in oil-fired turbines. Further investigations show that CMAS attacks were the trigger of layer damage, as has already been observed in aircraft turbines. A compound of calcium, magnesium, aluminum and silicon or iron leads to low-melting eutectics on thermal barrier coatings in the temperature range around 1200 ° C - 1250 ° C or higher. These compounds dissolve the yttria required for stabilization from the thermal barrier coating. This leads to strong monoclinic phase transitions with temperature changes in the ceramic, which lead to the destruction of the thermal barrier coating.
Bisher trat dieser Effekt in stationären Turbinen nur bedingt auf, da die Oberflächentemperaturen der eingesetzten Wärmedämmschicht die notwendigen Schmelztemperaturen von CMAS und Eisen nicht erreichten. Es war daher kein Schutz notwendig. Mit steigender Gastemperatur nimmt dieser Angriff im Umfang jedoch zu. So far, this effect was only limited in stationary turbines, since the surface temperatures of the thermal barrier coating used did not reach the necessary melting temperatures of CMAS and iron. Therefore, no protection was necessary. With increasing gas temperature, however, this attack increases in scope.
Es ist daher Aufgabe der Erfindung oben genanntes Problem zu lösen. It is therefore an object of the invention to solve the above-mentioned problem.
Die Aufgabe wird gelöst durch ein Schichtsystem gemäß An¬ spruch 1 und ein Verfahren gemäß Anspruch 6. In den Unteransprüchen sind weitere vorteilhafte Maßnahmen aufgelistet, die beliebig miteinander kombiniert werden kön¬ nen, um weitere Vorteile zu erzielen. Im Rahmen von Untersuchungen mit Kleinstpartikeln aus Aluminium konnte gezeigt werden, dass solche Partikel in Verbin¬ dung mit CMAS hochschmelzende Verbindungen bilden, wie zum Beispiel Anorthit. Diese Partikel in der Größenordnung von lOOnm bis 50ym lassen sich in eine Bindermatrix einbringen und mit einer Luftpistole leicht verspritzen. Diese Matrix wird auf eine Wärmedämmschichtoberfläche aufgebracht. Durch diese Kleinstpartikel hat man einerseits eine große aktive Fläche zur Verfügung, aber andererseits ist das System durch den lockeren Verbund sehr duktil. Die chemisch sehr aggressi¬ ve CMAS-Verbindung reagiert mit dem Aluminium-Überschuß zu Anorthit. Dies ist eine hochschmelzende Verbindung, die den CMAS-Angriff unterbindet oder zumindest reduziert. Ein beson¬ derer Vorteil dieser Beschichtung ist die Möglichkeit des wiederholten Aufbringens auch im eingebauten Zustand des Bauteils. Die sich aufbauende Anorthit-Schicht schützt zu¬ sätzlich vor dem Angriff der CMAS-Verbindung. The object is achieved by a layer system according to claim 1. ¬ and a method according to claim 6. In the subclaims further advantageous measures are listed, which are combined with each other Kgs ¬ nen to achieve further advantages. In the course of investigations with small particles of aluminum could be demonstrated that such particles form in Verbin ¬ extension with CMAS high melting compounds, such as anorthite. These particles of the order of 100 nm to 50 μm can be introduced into a binder matrix and easily splashed with an air gun. This matrix is applied to a thermal barrier coating surface. On the one hand, these small particles provide a large active area, but on the other hand, the system is very ductile due to the loose bond. The chemically very aggressi ¬ ve CMAS compound reacts with the aluminum excess of anorthite. This is a high-fusing connection that eliminates or at least reduces CMAS attack. A particular advantage of this coating ¬ which is the ability of the repeated application even after installation of the component. The building up anorthite layer protects to ¬ additionally from the attack of CMAS connection.
Die Aufbringung der aluminiumhaltigen Schutzschicht auf Lauf- und Leitschaufel einer Gasturbine kann auch im eingebauten Zustand erfolgen, wobei insbesondere eine Gehäusehälfte der Gasturbine geöffnet ist. The application of the aluminum-containing protective layer on the rotor and guide vane of a gas turbine can also take place in the installed state, wherein in particular a housing half of the gas turbine is open.
Die Beschichtung ist kostengünstig (Aluminiumpartikel in ei¬ ner Bindermatrix) und leicht aufzubringen. The coating is inexpensive (aluminum particles in egg ¬ ner binder matrix) and easy to apply.
Das zusätzliche Schutzschichtsystem ermöglich dem Betreiber einer Gasturbine auch ein kostengünstiges teilstabilisiertes Zirkonoxid-System unter CMAS-Angriff zu betreiben. The additional protective layer system also enables the operator of a gas turbine to operate a cost-effective partially stabilized zirconium oxide system under CMAS attack.
Es zeigen Show it
Figur 1 ein erfindungsgemäßes Schichtsystem, FIG. 1 shows a layer system according to the invention,
Figur 2 eine Turbinenschaufel, FIG. 2 shows a turbine blade,
Figur 3 eine Liste von Superlegierungen . Figure 3 is a list of superalloys.
Die Beschreibung und die Figuren stellen nur Ausführungsbeispiele der Erfindung dar. Figur 1 zeigt ein erfindungsgemäßes Schichtsystem 1. The description and the figures represent only embodiments of the invention. FIG. 1 shows a layer system 1 according to the invention.
Das Schichtsystem 1 weist ein Substrat 4 auf. Das Substrat 4 weist auf, insbesondere besteht aus einer nickel- oder ko¬ baltbasierten Superlegierung, insbesondere gemäß Figur 3. The layer system 1 has a substrate 4. The substrate 4 comprises, in particular consists of a nickel- or ko ¬ baltbasierten superalloy, in particular according to FIG. 3
Das Schichtsystem 1 weist weiterhin eine keramische Schicht 10 auf. Die keramische Schicht 10 kann Zirkonoxid, teilstabi lisiertes Zirkonoxid oder zweischichtige keramische Systeme aus Zirkonoxid und/oder Pyrochlorphase wie Gadoliniumhafnat oder -zirkonat aufweisen. The layer system 1 furthermore has a ceramic layer 10. The ceramic layer 10 may comprise zirconium oxide, partially stabilized zirconium oxide or two-layered ceramic systems of zirconium oxide and / or pyrochlore phase such as gadolinium hafnate or zirconate.
Zwischen der keramischen Schicht 10 und dem Substrat 4 kann eine metallische Haftvermittlerschicht und/oder eine Alumini umoxidschicht (TGO) vorhanden sein. Dies können Aluminid- schichten oder NiCoCrAlY-Schichten sein, die die TGO ausbilden . Between the ceramic layer 10 and the substrate 4, a metallic adhesion promoter layer and / or an aluminum oxide layer (TGO) may be present. These may be aluminide layers or NiCoCrAlY layers that form the TGOs.
Weitere keramische Wärmedämmschichtsysteme, wie sie bei Hoch temperaturbauteilen insbesondere bei Turbinenschaufeln oder Bauteilen von Gasturbinen bekannt sind, können die Ausgangsbasis sein.  Other ceramic thermal barrier coating systems, as they are known in high-temperature components, especially in turbine blades or components of gas turbines, may be the starting point.
Als äußerste Schicht 13 auf der keramischen Schicht 10, die einem Heißgas in einer Gasturbine ausgesetzt ist im Falle ei ner Turbinenschaufel, ist eine Schicht aus Aluminiumpartikel vorhanden . As the outermost layer 13 on the ceramic layer 10, which is exposed to a hot gas in a gas turbine in the case of a turbine blade, a layer of aluminum particles is present.
Vorzugsweise besteht die Schicht aus Aluminium oder Alumini¬ umpartikel . Preferably, the layer of aluminum or Alumini ¬ umpartikel.
Die Partikelgröße liegt dabei vorzugsweise bei 0,1μιη bis 50μιη.  The particle size is preferably from 0.1μιη to 50μιη.
Aluminium weist immer eine Oxidschicht auf.  Aluminum always has an oxide layer.
Insbesondere stellt der Anteil an Aluminium (AI) den größten Anteil dar.  In particular, the proportion of aluminum (AI) represents the largest share.
Auch Schichten 13 mit Verbindungen, die Aluminium im überstö chiometrischen Verhältnis aufweisen oder Aluminium im Über- schuss aufweisen, können verwendet werden, aber vorzugsweise keine Aluminide (NiAl , .. ) oder MCrAlY's. Mögliche Verfahren zum Aufbringen der Schicht 13 aus einer Emulsion aus den Al-Partikeln und Binder sind Sprühen (Auftragen mit Pinsel, Auftragen mit einer Rolle oder Eintauchen der Bauteile in die Emulsion. Layers 13 with compounds which have aluminum in the superstoichiometric ratio or have aluminum in excess can also be used, but preferably no aluminides (NiAl,...) Or MCrAlYs. Possible methods for applying the layer 13 of an emulsion of the Al particles and binders are spraying (application by brush, application with a roller or immersion of the components in the emulsion.
Weitere Aluminiumbeschichtungsarten sind möglich, wie Plattieren von Aluminium. Other aluminum coatings are possible, such as aluminum plating.
Die Figur 2 zeigt in perspektivischer Ansicht eine Laufschau- fei 120 oder Leitschaufel 130 einer Strömungsmaschine, die sich entlang einer Längsachse 121 erstreckt. FIG. 2 shows a perspective view of a rotor 120 or guide vane 130 of a turbomachine that extends along a longitudinal axis 121.
Die Strömungsmaschine kann eine Gasturbine eines Flugzeugs oder eines Kraftwerks zur Elektrizitätserzeugung, eine Dampf- turbine oder ein Kompressor sein. The turbomachine may be a gas turbine of an aircraft or a power plant for electricity generation, a steam turbine or a compressor.
Die Schaufel 120, 130 weist entlang der Längsachse 121 auf¬ einander folgend einen Befestigungsbereich 400, eine daran angrenzende Schaufelplattform 403 sowie ein Schaufelblatt 406 und eine Schaufelspitze 415 auf. The blade 120, 130 has along the longitudinal axis 121 to each other, a securing region 400, an adjoining blade or vane platform 403 and a blade 406 and a blade tip 415.
Als Leitschaufel 130 kann die Schaufel 130 an ihrer Schaufel¬ spitze 415 eine weitere Plattform aufweisen (nicht darge¬ stellt) . Im Befestigungsbereich 400 ist ein Schaufelfuß 183 gebildet, der zur Befestigung der Laufschaufeln 120, 130 an einer Welle oder einer Scheibe dient (nicht dargestellt) . As a guide vane 130, the vane 130 having at its blade tip 415 have a further platform (not Darge ¬ asserted). In the mounting region 400, a blade root 183 is formed, which serves for attachment of the blades 120, 130 to a shaft or a disc (not shown).
Der Schaufelfuß 183 ist beispielsweise als Hammerkopf ausge¬ staltet. Andere Ausgestaltungen als Tannenbaum- oder Schwal- benschwanzfuß sind möglich. The blade root 183 is, for example, as a hammerhead out staltet ¬. Other designs as fir tree or Schwäbwschwanzfuß are possible.
Die Schaufel 120, 130 weist für ein Medium, das an dem Schau¬ felblatt 406 vorbeiströmt, eine Anströmkante 409 und eine Ab¬ strömkante 412 auf. Bei herkömmlichen Schaufeln 120, 130 werden in allen Bereichen 400, 403, 406 der Schaufel 120, 130 beispielsweise mas¬ sive metallische Werkstoffe, insbesondere Superlegierungen verwendet . Solche Superlegierungen sind beispielsweise aus der EP 1 204 776 Bl, EP 1 306 454, EP 1 319 729 AI, WO 99/67435 oder WO 00/44949 bekannt. The blade 120, 130 has for a medium which flows past the scene ¬ felblatt 406 on a leading edge 409 and a trailing edge 412th In conventional blades 120, 130, in all regions 400, 403, 406 of the blade 120, 130, for example, massive metallic materials, in particular superalloys, are used. Such superalloys are known, for example, from EP 1 204 776 B1, EP 1 306 454, EP 1 319 729 A1, WO 99/67435 or WO 00/44949.
Die Schaufel 120, 130 kann hierbei durch ein Gussverfahren, auch mittels gerichteter Erstarrung, durch ein Schmiedeverfahren, durch ein Fräsverfahren oder Kombinationen daraus gefertigt sein.  The blade 120, 130 can be made by a casting process, also by directional solidification, by a forging process, by a milling process or combinations thereof.
Werkstücke mit einkristalliner Struktur oder Strukturen wer- den als Bauteile für Maschinen eingesetzt, die im Betrieb ho¬ hen mechanischen, thermischen und/oder chemischen Belastungen ausgesetzt sind. Workpieces with a single-crystal structure or structures advertising the used as components for machines which are exposed during operation ho ¬ hen mechanical, thermal and / or chemical stresses.
Die Fertigung von derartigen einkristallinen Werkstücken erfolgt z.B. durch gerichtetes Erstarren aus der Schmelze. Es handelt sich dabei um Gießverfahren, bei denen die flüssige metallische Legierung zur einkristallinen Struktur, d.h. zum einkristallinen Werkstück, oder gerichtet erstarrt.  The production of such monocrystalline workpieces takes place e.g. by directed solidification from the melt. These are casting processes in which the liquid metallic alloy is transformed into a monocrystalline structure, i. to the single-crystal workpiece, or directionally solidified.
Dabei werden dendritische Kristalle entlang dem Wärmefluss ausgerichtet und bilden entweder eine stängelkristalline Kornstruktur (kolumnar, d.h. Körner, die über die ganze Länge des Werkstückes verlaufen und hier, dem allgemeinen Sprachgebrauch nach, als gerichtet erstarrt bezeichnet werden) oder eine einkristalline Struktur, d.h. das ganze Werkstück be¬ steht aus einem einzigen Kristall. In diesen Verfahren muss man den Übergang zur globulitischen (polykristallinen) Erstarrung meiden, da sich durch ungerichtetes Wachstum notwendigerweise transversale und longitudinale Korngrenzen ausbil¬ den, welche die guten Eigenschaften des gerichtet erstarrten oder einkristallinen Bauteiles zunichte machen. Here, dendritic crystals are aligned along the heat flow and form either a columnar grain structure (columnar, ie grains that run the entire length of the workpiece and here, in common parlance, referred to as directionally solidified) or a monocrystalline structure, ie the whole workpiece be ¬ is made of a single crystal. In these methods, you have to avoid solidification transition to globular (polycrystalline), since non-directional growth inevitably forms transverse and longitudinal grain boundaries ¬ which make the good properties of the directionally solidified or single-crystal component naught.
Ist allgemein von gerichtet erstarrten Gefügen die Rede, so sind damit sowohl Einkristalle gemeint, die keine Korngrenzen oder höchstens Kleinwinkelkorngrenzen aufweisen, als auch Stängelkristallstrukturen, die wohl in longitudinaler Richtung verlaufende Korngrenzen, aber keine transversalen Korn- grenzen aufweisen. Bei diesen zweitgenannten kristallinenIf the term generally refers to directionally solidified structures, it means both single crystals that have no grain boundaries or at most small-angle grain boundaries, and stem crystal structures that have grain boundaries running in the longitudinal direction but no transverse grain boundaries. In these second-mentioned crystalline
Strukturen spricht man auch von gerichtet erstarrten Gefügen (directionally solidified structures) . Solche Verfahren sind aus der US-PS 6,024,792 und der EP 0 892 090 AI bekannt. Structures are also called directionally solidified structures. Such methods are known from US Pat. No. 6,024,792 and EP 0 892 090 A1.
Ebenso können die Schaufeln 120, 130 Beschichtungen gegen Korrosion oder Oxidation aufweisen, z. B. (MCrAlX; M ist zumindest ein Element der Gruppe Eisen (Fe) , Kobalt (Co) , Ni¬ ckel (Ni) , X ist ein Aktivelement und steht für Yttrium (Y) und/oder Silizium und/oder zumindest ein Element der Seltenen Erden, bzw. Hafnium (Hf) ) . Solche Legierungen sind bekannt aus der EP 0 486 489 Bl, EP 0 786 017 Bl, EP 0 412 397 Bl oder EP 1 306 454 AI. Likewise, the blades 120, 130 may have coatings against corrosion or oxidation, e.g. B. (MCrAlX; M is at least one element of the group consisting of iron (Fe), cobalt (Co), Ni ¬ ckel (Ni), X is an active element and stands for yttrium (Y) and / or silicon and / or at least one element the rare earth, or hafnium (Hf)). Such alloys are known from EP 0 486 489 B1, EP 0 786 017 B1, EP 0 412 397 B1 or EP 1 306 454 A1.
Die Dichte liegt vorzugsweise bei 95% der theoretischen Dich¬ te . The density is preferably 95% of the theoretical log ¬ te.
Auf der MCrAlX-Schicht (als Zwischenschicht oder als äußerste Schicht) bildet sich eine schützende Aluminiumoxidschicht (TGO = thermal grown oxide layer) .  A protective aluminum oxide layer (TGO = thermal grown oxide layer) is formed on the MCrAlX layer (as an intermediate layer or as the outermost layer).
Vorzugsweise weist die SchichtZusammensetzung Co-30Ni-28Cr- 8A1-0, 6Y-0, 7Si oder Co-28Ni-24Cr-10Al-0, 6Y auf. Neben diesen kobaltbasierten Schutzbeschichtungen werden auch vorzugsweise nickelbasierte Schutzschichten verwendet wie Ni-10Cr-12Al- 0,6Y-3Re oder Ni-12Co-21Cr-llAl-0, 4Y-2Re oder Ni-25Co-17Cr- 10A1-0, 4Y-1, 5Re . Auf der MCrAlX kann noch eine Wärmedämmschicht vorhanden sein, die vorzugsweise die äußerste Schicht ist, und besteht beispielsweise aus Zr02, Y2Ü3-Zr02, d.h. sie ist nicht, teil¬ weise oder vollständig stabilisiert durch Yttriumoxid Preferably, the layer composition comprises Co-30Ni-28Cr-8A1-0, 6Y-0, 7Si or Co-28Ni-24Cr-10Al-0, 6Y. Besides these cobalt-based protective coatings, nickel-based protective layers such as Ni-10Cr-12Al-0.6Y-3Re or Ni-12Co-21Cr-IIAl-O, 4Y-2Re or Ni-25Co-17Cr-10A1-0, 4Y-1 are also preferably used , 5Re. On the MCrAlX may still be present a thermal barrier coating, which is preferably the outermost layer, and consists for example of Zr0 2 , Y2Ü3-Zr02, ie it is not, partially ¬ or fully stabilized by yttria
und/oder Kalziumoxid und/oder Magnesiumoxid. and / or calcium oxide and / or magnesium oxide.
Die Wärmedämmschicht bedeckt die gesamte MCrAlX-Schicht. The thermal barrier coating covers the entire MCrAlX layer.
Durch geeignete Beschichtungsverfahren wie z.B. Elektronen- strahlverdampfen (EB-PVD) werden stängelförmige Körner in der Wärmedämmschicht erzeugt.  By suitable coating methods, e.g. Electron beam evaporation (EB-PVD) produces stalk-shaped grains in the thermal barrier coating.
Andere Beschichtungsverfahren sind denkbar, z.B. atmosphäri- sches Plasmaspritzen (APS), LPPS, VPS oder CVD. Die Wärme¬ dämmschicht kann poröse, mikro- oder makrorissbehaftete Kör¬ ner zur besseren Thermoschockbeständigkeit aufweisen. Die Wärmedämmschicht ist also vorzugsweise poröser als die Other coating methods are conceivable, for example atmospheric plasma spraying (APS), LPPS, VPS or CVD. The heat insulation layer may have ¬ porous, micro- or macro-cracked compatible grains for better thermal shock resistance. The Thermal insulation layer is therefore preferably more porous than the
MCrAlX-Schicht . MCrAlX layer.
Wiederaufarbeitung (Refurbishment ) bedeutet, dass Bauteile 120, 130 nach ihrem Einsatz gegebenenfalls von Schutzschichten befreit werden müssen (z.B. durch Sandstrahlen) . Danach erfolgt eine Entfernung der Korrosions- und/oder Oxidations- schichten bzw. -produkte. Gegebenenfalls werden auch noch Risse im Bauteil 120, 130 repariert. Danach erfolgt eine Wie- derbeschichtung des Bauteils 120, 130 und ein erneuter Einsatz des Bauteils 120, 130. Refurbishment means that components 120, 130 may need to be deprotected after use (e.g., by sandblasting). This is followed by removal of the corrosion and / or oxidation layers or products. Optionally, even cracks in the component 120, 130 are repaired. This is followed by a re-coating of the component 120, 130 and a renewed use of the component 120, 130.
Die Schaufel 120, 130 kann hohl oder massiv ausgeführt sein. Wenn die Schaufel 120, 130 gekühlt werden soll, ist sie hohl und weist ggf. noch Filmkühllöcher 418 (gestrichelt angedeu¬ tet) auf. The blade 120, 130 may be hollow or solid. If the blade 120, 130 is to be cooled, it is hollow and also has, if necessary, film cooling holes 418 (indicated by dashed lines) on.

Claims

Patentansprüche claims
1. Schichtsystem (1), 1st layer system (1),
das zumindest aufweist:  that at least has:
ein Substrat ( 4 ) ,  a substrate (4),
eine keramische Schicht (10) und  a ceramic layer (10) and
eine äußerste Schicht (13),  an outermost layer (13),
die (13) aluminiumreich ausgebildet ist,  which is (13) aluminum-rich,
insbesondere direkt auf der keramischen Schicht (10) und optional eine metallische Haftvermittlerschicht zwi¬ schen Substrat (4) und keramischer Schicht (10) . in particular, directly on the ceramic layer (10) and optionally a metallic adhesion promoter layer Zvi ¬'s substrate (4) and the ceramic layer (10).
2. Schichtsystem (1) nach Anspruch 1, Second layer system (1) according to claim 1,
bei dem die äußerste Schicht (13) Aluminiumpartikel auf¬ weist, in which the outermost layer (13) has aluminum particles ,
insbesondere mit einer Partikelgröße von lOOnm bis 50ym aufweist .  especially having a particle size of 100 nm to 50 μm.
3. Schichtsystem nach einem oder beiden der Ansprüche 1 oder 2, 3. Layer system according to one or both of claims 1 or 2,
bei dem die keramische Schicht Zirkonoxid aufweist, insbesondere mit Yttriumoxid stabilisiert ist.  in which the ceramic layer comprises zirconium oxide, in particular stabilized with yttrium oxide.
4. Schichtsystem nach einem oder mehreren der Ansprüche 1, 2 oder 3, 4. Layer system according to one or more of claims 1, 2 or 3,
bei dem die äußerste Schicht aus Aluminium (AI) besteht.  in which the outermost layer consists of aluminum (AI).
5. Schichtsystem nach einem oder mehreren der vorherigen Ansprüche, 5. Layer system according to one or more of the preceding claims,
das als Turbinenbauteil ausgebildet ist,  which is designed as a turbine component,
insbesondere als Turbinenschaufel (120, 130). in particular as a turbine blade (120, 130).
6. Verfahren zur Herstellung eines Schichtsystems (1) gemäß Anspruch 1, 2, 3, 4 oder 5, 6. A method for producing a layer system (1) according to claim 1, 2, 3, 4 or 5,
bei dem Aluminiumpartikel mittels Binder direkt auf eine keramische Schicht (10) aufgetragen werden.  in which aluminum particles are applied directly to a ceramic layer (10) by means of binders.
7. Verfahren nach Anspruch 6, 7. The method according to claim 6,
bei dem der Auftrag der aluminiumhaltigen Schicht (13) im eingebauten Zustand eines Bauteils,  in which the application of the aluminum-containing layer (13) in the installed state of a component,
das das Schichtsystem (1) darstellt,  which represents the layer system (1),
erfolgt .  he follows .
Verfahren einem oder beiden der Ansprüche 6 oder 7, das eine Partikelgröße für die Aluminiumpartikel von lOOnm bis 50ym aufweist. Process according to one or both of claims 6 or 7, which has a particle size for the aluminum particles of 100 nm to 50 μm.
Verfahren nach einem oder beiden der Ansprüche, Method according to one or both of the claims,
bei eine Emulsion aus Aluminium-Partikel und Binder durch Sprayen, Pinseln, Aufrollieren oder Eintauchen aufgetragen wird .  when applying an emulsion of aluminum particles and binder by spraying, brushing, rolling or dipping.
EP12808773.1A 2012-02-22 2012-12-13 Ceramic thermally insulating layer system having an external aluminum-rich layer, and method Withdrawn EP2802677A1 (en)

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