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US20160251971A1 - Two-ply ceramic layer with different microstructures - Google Patents

Two-ply ceramic layer with different microstructures Download PDF

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Publication number
US20160251971A1
US20160251971A1 US15/028,949 US201415028949A US2016251971A1 US 20160251971 A1 US20160251971 A1 US 20160251971A1 US 201415028949 A US201415028949 A US 201415028949A US 2016251971 A1 US2016251971 A1 US 2016251971A1
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Prior art keywords
layer
ceramic layer
ceramic
outermost
ply
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US15/028,949
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Jens Bay Düsterhöft
Claus Heuser
Matthias Richter
Werner Stamm
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Siemens AG
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Siemens AG
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Assigned to SIEMENS AKTIENGESELLSCHAFT reassignment SIEMENS AKTIENGESELLSCHAFT ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: STAMM, WERNER
Abandoned legal-status Critical Current

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    • 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
    • C23C4/10—Oxides, borides, carbides, nitrides or silicides; Mixtures thereof
    • 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
    • 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
    • C23C28/04—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 of inorganic non-metallic material
    • C23C28/042—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 of inorganic non-metallic material including a refractory ceramic layer, e.g. refractory metal oxides, ZrO2, rare earth oxides
    • 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
    • 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
    • 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
    • C23C4/10—Oxides, borides, carbides, nitrides or silicides; Mixtures thereof
    • C23C4/11—Oxides
    • 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
    • C23C4/12—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge characterised by the method of spraying
    • C23C4/134—Plasma spraying
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
    • F04D29/324—Blades
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/54—Fluid-guiding means, e.g. diffusers
    • F04D29/541—Specially adapted for elastic fluid pumps
    • F04D29/542—Bladed diffusers
    • 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
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/31—Application in turbines in steam turbines
    • 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
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • F05D2220/323—Application in turbines in gas turbines for aircraft propulsion, e.g. jet engines
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/30—Manufacture with deposition of material
    • F05D2230/31—Layer deposition
    • F05D2230/312—Layer deposition by plasma spraying
    • 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
    • F05D2300/50—Intrinsic material properties or characteristics
    • F05D2300/502—Thermal properties
    • F05D2300/5023—Thermal capacity
    • 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
    • F05D2300/611—Coating
    • 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 following relates to a ceramic layer which has a two-ply structure, with different microstructures being present in the layers.
  • Ceramic layers are used, in particular, as thermal barrier layers in turbine blades and have a porosity.
  • the advantages are good thermal insulation and good erosion resistance.
  • FIG. 1 is a working example of a layer system in accordance with embodiments of the invention.
  • FIG. 2 is a working example of a layer system in accordance with embodiments of the invention.
  • FIG. 3 is a working example of a layer system in accordance with embodiments of the invention.
  • FIG. 4 is a working example of a layer system in accordance with embodiments of the invention.
  • FIG. 5 a list of superalloys in accordance with embodiments of the invention.
  • FIG. 6 a turbine blade in accordance with embodiments of the invention.
  • FIG. 1 and FIGS. 2 to 4 in each case show a layer system 1 ′, 1 ′′, . . . which has at least one metallic substrate 4 .
  • the metallic substrate 4 comprises, in particular, a cobalt- or nickel-based superalloy, in particular as shown in FIG. 5 .
  • a metallic bonding layer 7 has preferably been applied to the substrate 4 ( FIGS. 1-4 ), very particularly preferably directly to the substrate 4 .
  • This metallic bonding layer 7 preferably comprises an alloy of the NiCoCrAl (X) type, on the surface of which a protective aluminum oxide layer (not shown) is formed during further coating or during operation (TGO).
  • a lower ceramic layer 10 ′ ( FIG. 1 ) of a two-ply, outermost ceramic thermal barrier layer 15 ′ is applied to the substrate 4 or the metallic bonding layer 7 .
  • the porosity is preferably reported in percent by volume.
  • An APS process is preferably used for the lower ceramic layer 10 ′ as per FIG. 1 and the lower ceramic layer 10 ′ of the two-ply, outermost ceramic thermal barrier layer 15 ′ preferably has a porosity of (12+/ ⁇ 4) %.
  • the lower ceramic layer 10 ′ preferably has a layer thickness of up to 1 mm.
  • the minimum thickness of the lower ceramic layer 10 ′ is at least 100 ⁇ m, very particularly preferably at least 150 ⁇ m ( FIGS. 1-4 ).
  • the outermost, ceramic layer 13 in FIGS. 1 to 4 has a layer which is dense compared to the lower layer 10 ′, . . . , 10 IV of the two-ply ceramic thermal barrier layers 15 ′, 15 ′′, . . . and through which cracks run vertically, i.e. the porosity is preferably ⁇ 8%.
  • the minimum layer thickness of the outermost ceramic layer 13 is 30 ⁇ m, in particular at least 50 ⁇ m ( FIGS. 1-4 ).
  • the maximum layer thickness of the outermost ceramic layer 13 is not more than 500 ⁇ m, in particular not more than 300 ⁇ m ( FIGS. 1-4 ).
  • the porosity of the segmented layers like that of the outermost ceramic layer 13 here corresponds to that from the known art.
  • FIG. 2 shows a further working example having a layer system 1 ′′.
  • the lower layer 10 ′′ of the ceramic thermal barrier layer 15 ′′ has a porosity of (15+/ ⁇ 4)%.
  • the lower ceramic layer 10 ′′ in FIG. 2 can likewise preferably have a layer thickness of up to 1.5 mm, in particular from >1 mm to 1.5 mm, and then have a porosity of (20+/ ⁇ 5)%.
  • the minimum layer thickness of the outermost, ceramic layer 13 is 30 ⁇ m, in particular at least 50 ⁇ m.
  • the porosity of the lower ceramic layer 10 ′′ in FIG. 2 can likewise preferably be increased further to (25+/ ⁇ 5)% and layer thicknesses of >1.5 mm are then preferably produced.
  • the minimum layer thickness of the outermost, ceramic layer 13 is 30 ⁇ m, in particular at least 50 ⁇ m.
  • FIG. 3 shows a further working example of a layer system 1 ′′′ according to embodiments of the invention.
  • the lower ceramic layer 10 ′′′ of the thermal barrier layer 15 ′′′ has a porosity of preferably greater than 15% and has been produced by means of an APS process. However, the pores have been produced by spraying a ceramic powder, preferably by means of polymers.
  • the lower ceramic layer 10 ′′′ can preferably have a layer thickness of a plurality of millimeters, in particular ⁇ 2 mm.
  • the minimum layer thickness of the outermost, ceramic layer 13 is 30 ⁇ m, in particular at least 50 ⁇ m.
  • FIG. 4 shows a further layer system 10 IV according to embodiments of the invention.
  • the lower ceramic layer 10 IV of the two-ply, ceramic thermal barrier layer 15 IV has been produced by the suspension plasma spraying (SPS) process and has a ductile columnar structure having a certain porosity of 4% and cracks up to ⁇ 8%.
  • SPS suspension plasma spraying
  • the outermost layer 13 in FIG. 4 is configured with the minimum layer thickness and structure and maximum layer thickness in FIGS. 1-3 .
  • Possible materials for the outermost, ceramic thermal barrier layers 15 ′, . . . 15 IV are yttrium oxide, partially stabilized zirconium oxide or thermal barrier layers composed of fully stabilized zirconium oxide.
  • pyrochlores such as gadolinium zirconate, gadolinium hafnate, lanthanum zirconate, gadolinium zirconate.
  • the materials for the lower, ceramic layer 10 ′, 10 ′′, . . . and the outermost layer 13 can be varied as a function of use conditions and production possibilities.
  • the two-ply outermost ceramic layer 15 is preferably the outermost layer of the layer system 1 ′, 1 ′′, . . . .
  • FIG. 6 shows a perspective view of a rotor blade 120 or guide blade 130 of a turbomachine, which extends along a longitudinal axis 121 .
  • the turbomachine can be a gas turbine of an aircraft or of a power station for generating electricity, a steam turbine or a compressor.
  • the blade 120 , 130 has, in succession along the longitudinal axis 121 , a fastening region 400 , a blade platform 403 adjoining this and also a blade leaf 406 and a blade tip 415 .
  • the blade 130 can have a further platform (not shown) at its blade tip 415 .
  • a blade foot 183 which serves for fastening the rotor blades 120 , 130 to a shaft or a disk (not shown).
  • the blade foot 183 is, for example, configured as a hammer head. Other configurations as Christmas tree foot or swallowtail foot are possible.
  • the blade 120 , 130 has a leading edge 409 and a trailing edge 412 for a medium flowing past the blade leaf 406 .
  • all regions 400 , 403 , 406 of the blade 120 , 130 are, for example, made of massive metallic materials, in particular superalloys.
  • 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 have been made by a casting process, including by means of directional solidification, by a forging process, by a milling process or combinations thereof.
  • Workpieces having a monocrystalline structure or structures are used as components for machines which are subjected to high mechanical, thermal and/or chemical stresses during operation.
  • the manufacture of such monocrystalline workpieces is carried out, for example, by directional solidification from the melt. This involves casting processes in which the liquid metallic alloy solidifies to form a monocrystalline structure, i.e. the monocrystalline workpiece, or directionally.
  • dendritic crystals are aligned along the heat flow and form either a columnar crystalline grain structure (i.e. grains which run over the entire length of the workpiece and here referred to, in keeping with general language usage, as directionally solidified) or a monocrystalline structure, i.e. the entire workpiece consists of a single crystal.
  • a columnar crystalline grain structure i.e. grains which run over the entire length of the workpiece and here referred to, in keeping with general language usage, as directionally solidified
  • a monocrystalline structure i.e. the entire workpiece consists of a single crystal.
  • directionally solidified microstructures encompasses both single crystals which have no grain boundaries or at most low-angle grain boundaries and also columnar crystal structures which do have grain boundaries running in the longitudinal direction but no transverse grain boundaries. These crystalline structures mentioned second are also referred to as directionally solidified microstructures.
  • the blades 120 , 130 can likewise have coatings to protect against corrosion or oxidation, e.g. (MCrAlX; M is at least one element from the group iron (Fe), cobalt (Co), nickel (Ni), X is an active element and is yttrium (Y) and/or silicon and/or at least one element of the rare earths, or hafnium (Hf)).
  • M is at least one element from the group iron (Fe), cobalt (Co), nickel (Ni)
  • X is an active element and is yttrium (Y) and/or silicon and/or at least one element of the rare earths, 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 density.
  • a protective aluminum oxide layer forms on the MCrAlX layer (as intermediate layer or as outermost layer).
  • the layer composition preferably comprises Co-30Ni-28Cr-8Al-0, 6Y-0.7Si or Co-28Ni-24Cr-10Al-0.6Y.
  • preference is also given to using nickel-based protective layers such as Ni-10Cr-12Al-0.6Y-3Re or Ni-12Co-21Cr-11Al-0.4Y-2Re or Ni-25Co-17Cr-10Al-0.4Y-1.5Re.
  • a thermal barrier layer can be additionally present on the MCrAlX and is preferably the outermost layer and consists, for example, of ZrO 2 , Y 2 O 3 —ZrO 2 , i.e. it is unstabilized, partially stabilized or fully stabilized by yttrium oxide and/or calcium oxide and/or magnesium oxide.
  • the thermal barrier layer covers the entire MCrAlX layer.
  • Columnar grains are produced in the thermal barrier layer by suitable treatment processes, e.g. electron beam vaporization (EB-PVD).
  • EB-PVD electron beam vaporization
  • the thermal barrier layer can have grains which are porous, have microcracks or have macrocracks for better thermal shock resistance.
  • the thermal barrier layer is thus preferably more porous than the MCrAlX layer.
  • Refurbishment means that components 120 , 130 have to be freed of any protective layers (e.g. by sand blasting) after they have been used. This is followed by removal of the corrosion and/or oxidation layers or products. Cracks in the component 120 , 130 are optionally also repaired. This is followed by recoating of the component 120 , 130 and renewed use of the component 120 , 130 .
  • any protective layers e.g. by sand blasting
  • the blade 120 , 130 can be hollow or solid. When the blade 120 , 130 is to be cooled, it is hollow and optionally has film cooling holes 418 (indicated by dashes).

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  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Materials Engineering (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Inorganic Chemistry (AREA)
  • Plasma & Fusion (AREA)
  • Physics & Mathematics (AREA)
  • General Engineering & Computer Science (AREA)
  • Ceramic Engineering (AREA)
  • Coating By Spraying Or Casting (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Laminated Bodies (AREA)

Abstract

A two-ply heat-insulating ceramic layer is provided with a highly porous crackfree lower ply and an outermost heat-insulating ply with vertical cracks in order to ensure both a high heat insulation as well as a high erosion resistance. In one aspect is a layer system having a two-ply, outermost ceramic layer, which has a lower ceramic layer and an outermost ceramic layer. The lower ceramic layer has a porosity of at least 5%, in particular at least 8%, very particularly preferably at least 10%, and barely any or no vertical cracks, in particular no vertical cracks running right through, and the outermost ceramic layer has a layer thickness of not more than 40%, in particular not more than 20%, very particularly preferably not more than 10% of the layer thickness of the lower ceramic layer.

Description

    CROSS-REFERENCE TO RELATED APPLICATIONS
  • This application claims priority to PCT Application No. PCT/EP2014/059738, having a filing date of May 13, 2014, based off of EP Application No. 13189688.8 having a filing date of Oct. 22, 2013, the entire contents of which are hereby incorporated by reference.
    • FIELD OF TECHNOLOGY
  • The following relates to a ceramic layer which has a two-ply structure, with different microstructures being present in the layers.
    • BACKGROUND
  • Ceramic layers are used, in particular, as thermal barrier layers in turbine blades and have a porosity.
  • Vertically segmented thermal barrier layers in which cracks are formed during coating by means of a subsequent treatment are likewise known.
  • However, there is the problem that when the porosity is increased to achieve greater thermal insulation, the erosion resistance of a thermal barrier layer, which is generally plasma-sprayed, is reduced.
    • SUMMARY
  • The advantages are good thermal insulation and good erosion resistance.
    • BRIEF DESCRIPTION
  • Some of the embodiments will be described in detail, with reference to the following figures, wherein like designations denote like members, wherein:
  • FIG. 1 is a working example of a layer system in accordance with embodiments of the invention;
  • FIG. 2 is a working example of a layer system in accordance with embodiments of the invention;
  • FIG. 3 is a working example of a layer system in accordance with embodiments of the invention;
  • FIG. 4 is a working example of a layer system in accordance with embodiments of the invention;
  • FIG. 5 a list of superalloys in accordance with embodiments of the invention; and
  • FIG. 6 a turbine blade in accordance with embodiments of the invention.
    •  DETAILED DESCRIPTION
  • The description and the figures represent only working examples of embodiments of the invention.
  • FIG. 1 and FIGS. 2 to 4 in each case show a layer system 1′, 1″, . . . which has at least one metallic substrate 4.
  • The metallic substrate 4 comprises, in particular, a cobalt- or nickel-based superalloy, in particular as shown in FIG. 5.
  • A metallic bonding layer 7 has preferably been applied to the substrate 4 (FIGS. 1-4), very particularly preferably directly to the substrate 4.
  • This metallic bonding layer 7 preferably comprises an alloy of the NiCoCrAl (X) type, on the surface of which a protective aluminum oxide layer (not shown) is formed during further coating or during operation (TGO).
  • A lower ceramic layer 10′ (FIG. 1) of a two-ply, outermost ceramic thermal barrier layer 15′ is applied to the substrate 4 or the metallic bonding layer 7.
  • The porosity is preferably reported in percent by volume.
  • An APS process is preferably used for the lower ceramic layer 10′ as per FIG. 1 and the lower ceramic layer 10′ of the two-ply, outermost ceramic thermal barrier layer 15′ preferably has a porosity of (12+/−4) %.
  • The lower ceramic layer 10′ preferably has a layer thickness of up to 1 mm.
  • The minimum thickness of the lower ceramic layer 10′ is at least 100 μm, very particularly preferably at least 150 μm (FIGS. 1-4).
  • The outermost, ceramic layer 13 in FIGS. 1 to 4 has a layer which is dense compared to the lower layer 10′, . . . , 10 IV of the two-ply ceramic thermal barrier layers 15′, 15″, . . . and through which cracks run vertically, i.e. the porosity is preferably <8%.
  • The minimum layer thickness of the outermost ceramic layer 13 is 30 μm, in particular at least 50 μm (FIGS. 1-4).
  • The maximum layer thickness of the outermost ceramic layer 13 is not more than 500 μm, in particular not more than 300 μm (FIGS. 1-4).
  • The porosity of the segmented layers like that of the outermost ceramic layer 13 here corresponds to that from the known art.
  • FIG. 2 shows a further working example having a layer system 1″.
  • In contrast to FIG. 1, the lower layer 10″ of the ceramic thermal barrier layer 15″ has a porosity of (15+/−4)%.
  • The lower ceramic layer 10″ in FIG. 2 can likewise preferably have a layer thickness of up to 1.5 mm, in particular from >1 mm to 1.5 mm, and then have a porosity of (20+/−5)%.
  • The minimum layer thickness of the outermost, ceramic layer 13 is 30 μm, in particular at least 50 μm.
  • The porosity of the lower ceramic layer 10″ in FIG. 2 can likewise preferably be increased further to (25+/−5)% and layer thicknesses of >1.5 mm are then preferably produced.
  • The minimum layer thickness of the outermost, ceramic layer 13 is 30 μm, in particular at least 50 μm.
  • FIG. 3 shows a further working example of a layer system 1′″ according to embodiments of the invention.
  • The lower ceramic layer 10′″ of the thermal barrier layer 15′″ has a porosity of preferably greater than 15% and has been produced by means of an APS process. However, the pores have been produced by spraying a ceramic powder, preferably by means of polymers.
  • This gives a characteristic microstructure of the pores.
  • The lower ceramic layer 10′″ can preferably have a layer thickness of a plurality of millimeters, in particular ≧2 mm.
  • The minimum layer thickness of the outermost, ceramic layer 13 is 30 μm, in particular at least 50 μm.
  • FIG. 4 shows a further layer system 10 IV according to embodiments of the invention.
  • The lower ceramic layer 10 IV of the two-ply, ceramic thermal barrier layer 15 IV has been produced by the suspension plasma spraying (SPS) process and has a ductile columnar structure having a certain porosity of 4% and cracks up to <8%.
  • The outermost layer 13 in FIG. 4 is configured with the minimum layer thickness and structure and maximum layer thickness in FIGS. 1-3.
  • Possible materials for the outermost, ceramic thermal barrier layers 15′, . . . 15 IV are yttrium oxide, partially stabilized zirconium oxide or thermal barrier layers composed of fully stabilized zirconium oxide.
  • It is likewise possible to use pyrochlores such as gadolinium zirconate, gadolinium hafnate, lanthanum zirconate, gadolinium zirconate.
  • Here, the materials for the lower, ceramic layer 10′, 10″, . . . and the outermost layer 13 can be varied as a function of use conditions and production possibilities.
  • The two-ply outermost ceramic layer 15 is preferably the outermost layer of the layer system 1′, 1″, . . . .
  • FIG. 6 shows a perspective view of a rotor blade 120 or guide blade 130 of a turbomachine, which extends along a longitudinal axis 121.
  • The turbomachine can be a gas turbine of an aircraft or of a power station for generating electricity, a steam turbine or a compressor.
  • The blade 120, 130 has, in succession along the longitudinal axis 121, a fastening region 400, a blade platform 403 adjoining this and also a blade leaf 406 and a blade tip 415. As guide blade 130, the blade 130 can have a further platform (not shown) at its blade tip 415.
  • In the fastening region 400, there is a blade foot 183 which serves for fastening the rotor blades 120, 130 to a shaft or a disk (not shown).
  • The blade foot 183 is, for example, configured as a hammer head. Other configurations as Christmas tree foot or swallowtail foot are possible.
  • The blade 120, 130 has a leading edge 409 and a trailing edge 412 for a medium flowing past the blade leaf 406.
  • In the case of conventional blades 120, 130, all regions 400, 403, 406 of the blade 120, 130 are, for example, made of massive metallic materials, in particular superalloys. 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.
  • The blade 120, 130 can have been made by a casting process, including by means of directional solidification, by a forging process, by a milling process or combinations thereof.
  • Workpieces having a monocrystalline structure or structures are used as components for machines which are subjected to high mechanical, thermal and/or chemical stresses during operation.
  • The manufacture of such monocrystalline workpieces is carried out, for example, by directional solidification from the melt. This involves casting processes in which the liquid metallic alloy solidifies to form a monocrystalline structure, i.e. the monocrystalline workpiece, or directionally.
  • Here, dendritic crystals are aligned along the heat flow and form either a columnar crystalline grain structure (i.e. grains which run over the entire length of the workpiece and here referred to, in keeping with general language usage, as directionally solidified) or a monocrystalline structure, i.e. the entire workpiece consists of a single crystal. In these processes, the transition to globulitic (polycrystalline) solidification has to be avoided since transverse and longitudinal grain boundaries are necessarily formed by nondirectional growth and these nullify the good properties of the directionally solidified or monocrystalline component.
  • If general reference is made to directionally solidified microstructures, this encompasses both single crystals which have no grain boundaries or at most low-angle grain boundaries and also columnar crystal structures which do have grain boundaries running in the longitudinal direction but no transverse grain boundaries. These crystalline structures mentioned second are also referred to as directionally solidified microstructures.
  • Such processes are known from U.S. Pat. No. 6,024,792 and EP 0 892 090 A1.
  • The blades 120, 130 can likewise have coatings to protect against corrosion or oxidation, e.g. (MCrAlX; M is at least one element from the group iron (Fe), cobalt (Co), nickel (Ni), X is an active element and is yttrium (Y) and/or silicon and/or at least one element of the rare earths, 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 density.
  • A protective aluminum oxide layer (TGO=thermally grown oxide layer) forms on the MCrAlX layer (as intermediate layer or as outermost layer).
  • The layer composition preferably comprises Co-30Ni-28Cr-8Al-0, 6Y-0.7Si or Co-28Ni-24Cr-10Al-0.6Y. Apart from these cobalt-based protective coatings, preference is also given to using nickel-based protective layers such as Ni-10Cr-12Al-0.6Y-3Re or Ni-12Co-21Cr-11Al-0.4Y-2Re or Ni-25Co-17Cr-10Al-0.4Y-1.5Re.
  • A thermal barrier layer can be additionally present on the MCrAlX and is preferably the outermost layer and consists, for example, of ZrO2, Y2O3—ZrO2, i.e. it is unstabilized, partially stabilized or fully stabilized by yttrium oxide and/or calcium oxide and/or magnesium oxide.
  • The thermal barrier layer covers the entire MCrAlX layer. Columnar grains are produced in the thermal barrier layer by suitable treatment processes, e.g. electron beam vaporization (EB-PVD).
  • Other coating processes are conceivable, e.g. atmospheric plasma spraying (APS), LPPS, VPS or CVD. The thermal barrier layer can have grains which are porous, have microcracks or have macrocracks for better thermal shock resistance. The thermal barrier layer is thus preferably more porous than the MCrAlX layer.
  • Refurbishment means that components 120, 130 have to be freed of any protective layers (e.g. by sand blasting) after they have been used. This is followed by removal of the corrosion and/or oxidation layers or products. Cracks in the component 120, 130 are optionally also repaired. This is followed by recoating of the component 120, 130 and renewed use of the component 120, 130.
  • The blade 120, 130 can be hollow or solid. When the blade 120, 130 is to be cooled, it is hollow and optionally has film cooling holes 418 (indicated by dashes).
  • Although the present invention has been disclosed in the form of preferred embodiments and variations thereon, it will be understood that numerous additional modifications and variations could be made thereto without departing from the scope of the invention.
  • For the sake of clarity, it is to be understood that the use of ‘a’ or ‘an’ throughout this application does not exclude a plurality, and ‘comprising’ does not exclude other steps or elements.

Claims (17)

1. A layer system
having a two-ply, outermost ceramic layer,
which has a lower ceramic layer and
an outermost ceramic layer,
wherein the lower ceramic layer has a porosity of at least 5%,
and
is substantially free of vertical cracks running therethrough,
and the outermost ceramic layer has a layer thickness of not more than 40%,
of the layer thickness of the lower ceramic layer.
2. The layer system as claimed in claim 1, wherein the outermost ceramic layer has a minimum layer thickness of 30 μm.
3. The layer system as claimed in claim 1, wherein the outermost ceramic layer has a maximum layer thickness of 500 μm.
4. The layer system as claimed in claim 1, wherein the lower ceramic layer of the two-ply ceramic layer has a porosity of 12+ or −4% and in particular has a layer thickness of up to 1 mm.
5. The layer system as claimed in claim 1, wherein the lower ceramic layer of the two-ply ceramic layer has a porosity of 15+ or −4% and in particular has a layer thickness of up to 1 mm.
6. The layer system as claimed in claim 1, wherein the lower ceramic layer of the two-ply ceramic layer has a porosity of 20+ or −4% and has a layer thickness of up to 1.5 mm.
7. The layer system as claimed in claim 1, wherein the lower ceramic layer of the ceramic layer has a porosity of 25+ or −5% and has a layer thickness of >1.5 mm.
8. The layer system as claimed in claim 1, wherein the lower ceramic layer has a porosity of >15%.
9. The layer system as claimed in claim 1, wherein the lower ceramic layer of the thermal barrier layer has a ductile columnar structure.
10. The layer system as claimed in claim 1, wherein the lower ceramic layer of the two-ply ceramic thermal barrier layer has been produced by an APS process.
11. The layer system as claimed in claim 1, wherein the lower ceramic layer of the two-ply ceramic thermal barrier layer has been produced by spraying of ceramic powders with polymers.
12. The layer system as claimed in claim 1, wherein the lower ceramic layer of the two-ply, ceramic thermal barrier layer has been produced by suspension plasma spraying.
13. The layer system as claimed in claim 1, wherein the materials for the lower ceramic layer and of the outermost ceramic layer are selected from among: zirconium oxide, partially stabilized or fully stabilized, and pyrochlores.
14. The layer system as claimed in claim 1, wherein the two-ply ceramic layer is the outermost layer.
15. The layer system as claimed in claim 1, wherein the lower ceramic layer has a minimum thickness of at least 100 μm.
16. The layer system as claimed in claim 1, wherein the outermost ceramic layer is dense and has a porosity of less than 8%.
17. The layer system as claimed in claim 1, wherein the outermost ceramic layer has cracks running vertically through it.
US15/028,949 2013-10-22 2014-05-13 Two-ply ceramic layer with different microstructures Abandoned US20160251971A1 (en)

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EP20130189688 EP2865781A1 (en) 2013-10-22 2013-10-22 Two layer ceramic layer having different microstructures
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Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10094232B2 (en) * 2015-08-13 2018-10-09 United Technologies Corporation Self crystalline orientation for increased compliance
US10662787B2 (en) 2015-11-27 2020-05-26 Siemens Aktiengesellschaft Local two-layer thermal barrier coating
US10808308B2 (en) * 2016-06-08 2020-10-20 Mitsubishi Heavy Industries, Ltd. Thermal barrier coating, turbine member, and gas turbine
US20220083158A1 (en) * 2020-08-25 2022-03-17 Steven Chrisopher Welch High Precision Trackpad and Methods of Manufacture
US20220154592A1 (en) * 2019-03-22 2022-05-19 Siemens Energy Global GmbH & Co. KG Fully stabilized zirconia in a seal system
US20220371967A1 (en) * 2021-05-18 2022-11-24 Rolls-Royce Corporation Cmas-resistant environmental barrier coating system

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102014222686A1 (en) * 2014-11-06 2016-05-12 Siemens Aktiengesellschaft Double-layered thermal barrier coating by different coating methods
EP3153602A1 (en) * 2015-10-07 2017-04-12 Siemens Aktiengesellschaft Dvc-ceramic layer with underlying porous ceramic sublayer
JP7516293B2 (en) * 2021-03-03 2024-07-16 株式会社東芝 Heat-resistant components and power generation systems

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20060147699A1 (en) * 2002-10-03 2006-07-06 Alberta Research Council Inc. Protective ceramic coating
US20120027635A1 (en) * 2010-08-02 2012-02-02 Yoji Takezaki Method for producing fluid dynamic pressure bearing

Family Cites Families (25)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE58908611D1 (en) 1989-08-10 1994-12-08 Siemens Ag HIGH-TEMPERATURE-RESISTANT CORROSION PROTECTION COATING, IN PARTICULAR FOR GAS TURBINE COMPONENTS.
DE3926479A1 (en) 1989-08-10 1991-02-14 Siemens Ag RHENIUM-PROTECTIVE COATING, WITH GREAT CORROSION AND / OR OXIDATION RESISTANCE
JPH07243018A (en) * 1994-03-08 1995-09-19 Mitsubishi Heavy Ind Ltd Surface modification method for heat insulating film
JP3370676B2 (en) * 1994-10-14 2003-01-27 シーメンス アクチエンゲゼルシヤフト Protective layer for protecting members against corrosion, oxidation and thermal overload, and method of manufacturing the same
EP0861927A1 (en) 1997-02-24 1998-09-02 Sulzer Innotec Ag Method for manufacturing single crystal structures
EP0892090B1 (en) 1997-02-24 2008-04-23 Sulzer Innotec Ag Method for manufacturing single crystal structures
WO1999067435A1 (en) 1998-06-23 1999-12-29 Siemens Aktiengesellschaft Directionally solidified casting with improved transverse stress rupture strength
US6231692B1 (en) 1999-01-28 2001-05-15 Howmet Research Corporation Nickel base superalloy with improved machinability and method of making thereof
DE50006694D1 (en) 1999-07-29 2004-07-08 Siemens Ag HIGH-TEMPERATURE-RESISTANT COMPONENT AND METHOD FOR PRODUCING THE HIGH-TEMPERATURE-RESISTANT COMPONENT
US6730413B2 (en) * 2001-07-31 2004-05-04 General Electric Company Thermal barrier coating
DE50104022D1 (en) 2001-10-24 2004-11-11 Siemens Ag Protective layer containing rhenium to protect a component against corrosion and oxidation at high temperatures
DE50112339D1 (en) 2001-12-13 2007-05-24 Siemens Ag High-temperature resistant component made of monocrystalline or polycrystalline nickel-based superalloy
US7416788B2 (en) * 2005-06-30 2008-08-26 Honeywell International Inc. Thermal barrier coating resistant to penetration by environmental contaminants
US20080145694A1 (en) * 2006-12-19 2008-06-19 David Vincent Bucci Thermal barrier coating system and method for coating a component
ES2368005T3 (en) * 2007-05-07 2011-11-11 Siemens Aktiengesellschaft CERAMIC POWDER, CERAMIC COAT AND LAYER SYSTEM WITH PIROCLORO AND OXIDE PHASES.
DE102008007870A1 (en) * 2008-02-06 2009-08-13 Forschungszentrum Jülich GmbH Thermal barrier coating system and process for its preparation
US20100124616A1 (en) * 2008-11-19 2010-05-20 General Electric Company Method of forming an abradable coating
EP2230329A1 (en) * 2009-03-18 2010-09-22 Siemens Aktiengesellschaft Dual layer porous coating system with pyrochlorine phase
JP5075880B2 (en) * 2009-06-30 2012-11-21 株式会社日立製作所 Heat-resistant parts and high-temperature parts for gas turbines
US20110151219A1 (en) * 2009-12-21 2011-06-23 Bangalore Nagaraj Coating Systems for Protection of Substrates Exposed to Hot and Harsh Environments and Coated Articles
JP5561733B2 (en) * 2010-12-28 2014-07-30 株式会社日立製作所 Gas turbine component having thermal barrier coating and gas turbine using the same
US8617698B2 (en) * 2011-04-27 2013-12-31 Siemens Energy, Inc. Damage resistant thermal barrier coating and method
US20130224453A1 (en) * 2012-02-29 2013-08-29 United Technologies Corporation Spallation-Resistant Thermal Barrier Coating
EP2644824A1 (en) * 2012-03-28 2013-10-02 Siemens Aktiengesellschaft Method for producing and restoring of ceramic thermal barrier coatings in gas turbines and related gas turbine
JP5657048B2 (en) * 2013-03-19 2015-01-21 三菱重工業株式会社 High temperature resistant member and gas turbine

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20060147699A1 (en) * 2002-10-03 2006-07-06 Alberta Research Council Inc. Protective ceramic coating
US20120027635A1 (en) * 2010-08-02 2012-02-02 Yoji Takezaki Method for producing fluid dynamic pressure bearing

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10094232B2 (en) * 2015-08-13 2018-10-09 United Technologies Corporation Self crystalline orientation for increased compliance
US10662787B2 (en) 2015-11-27 2020-05-26 Siemens Aktiengesellschaft Local two-layer thermal barrier coating
US10808308B2 (en) * 2016-06-08 2020-10-20 Mitsubishi Heavy Industries, Ltd. Thermal barrier coating, turbine member, and gas turbine
US20220154592A1 (en) * 2019-03-22 2022-05-19 Siemens Energy Global GmbH & Co. KG Fully stabilized zirconia in a seal system
US20220083158A1 (en) * 2020-08-25 2022-03-17 Steven Chrisopher Welch High Precision Trackpad and Methods of Manufacture
US20220371967A1 (en) * 2021-05-18 2022-11-24 Rolls-Royce Corporation Cmas-resistant environmental barrier coating system

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