EP1891249A1 - Systeme de couches conçu pour un composant comprenant une couche d'isolation thermique et une couche metallique anti-erosion, procede de production dudit composant, et procede pour faire fonctionner une turbine a vapeur - Google Patents

Systeme de couches conçu pour un composant comprenant une couche d'isolation thermique et une couche metallique anti-erosion, procede de production dudit composant, et procede pour faire fonctionner une turbine a vapeur

Info

Publication number
EP1891249A1
EP1891249A1 EP06725133A EP06725133A EP1891249A1 EP 1891249 A1 EP1891249 A1 EP 1891249A1 EP 06725133 A EP06725133 A EP 06725133A EP 06725133 A EP06725133 A EP 06725133A EP 1891249 A1 EP1891249 A1 EP 1891249A1
Authority
EP
European Patent Office
Prior art keywords
layer
layer system
barrier coating
thermal barrier
erosion protection
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Withdrawn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
EP06725133A
Other languages
German (de)
English (en)
Inventor
Jochen Barnikel
Friedhelm Schmitz
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.)
Siemens AG
Original Assignee
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 Siemens AG filed Critical Siemens AG
Priority to EP06725133A priority Critical patent/EP1891249A1/fr
Publication of EP1891249A1 publication Critical patent/EP1891249A1/fr
Withdrawn legal-status Critical Current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
    • 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
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C28/00—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D
    • C23C28/30—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer
    • C23C28/32—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer
    • C23C28/321—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer with at least one metal alloy layer
    • C23C28/3215—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer with at least one metal alloy layer at least one MCrAlX layer
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C28/00—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D
    • C23C28/30—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer
    • C23C28/34—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one inorganic non-metallic material layer, e.g. metal carbide, nitride, boride, silicide layer and their mixtures, enamels, phosphates and sulphates
    • C23C28/345—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one inorganic non-metallic material layer, e.g. metal carbide, nitride, boride, silicide layer and their mixtures, enamels, phosphates and sulphates with at least one oxide layer
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C28/00—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D
    • C23C28/30—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer
    • C23C28/34—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one inorganic non-metallic material layer, e.g. metal carbide, nitride, boride, silicide layer and their mixtures, enamels, phosphates and sulphates
    • C23C28/345—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one inorganic non-metallic material layer, e.g. metal carbide, nitride, boride, silicide layer and their mixtures, enamels, phosphates and sulphates with at least one oxide layer
    • C23C28/3455—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one inorganic non-metallic material layer, e.g. metal carbide, nitride, boride, silicide layer and their mixtures, enamels, phosphates and sulphates with at least one oxide layer with a refractory ceramic layer, e.g. refractory metal oxide, ZrO2, rare earth oxides or a thermal barrier system comprising at least one refractory oxide layer
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C28/00—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D
    • C23C28/30—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer
    • C23C28/34—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
    • C23C28/347—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 layers adapted for cutting tools or wear applications
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C28/00—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D
    • C23C28/30—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer
    • C23C28/36—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including layers graded in composition or physical properties
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
    • C23C4/02—Pretreatment of the material to be coated, e.g. for coating on selected surface areas
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/007—Preventing corrosion
    • 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
    • F01D5/286—Particular treatment of blades, e.g. to increase durability or resistance against corrosion or erosion
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05C—INDEXING SCHEME RELATING TO MATERIALS, MATERIAL PROPERTIES OR MATERIAL CHARACTERISTICS FOR MACHINES, ENGINES OR PUMPS OTHER THAN NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES
    • F05C2201/00—Metals
    • F05C2201/04—Heavy metals
    • F05C2201/0433—Iron group; Ferrous alloys, e.g. steel
    • F05C2201/0466—Nickel
    • 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
    • F05D2250/00—Geometry
    • F05D2250/50—Inlet or outlet
    • F05D2250/51—Inlet
    • 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
    • F05D2300/10—Metals, alloys or intermetallic compounds
    • F05D2300/13—Refractory metals, i.e. Ti, V, Cr, Zr, Nb, Mo, Hf, Ta, W
    • F05D2300/132—Chromium
    • 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
    • F05D2300/22—Non-oxide ceramics
    • F05D2300/222—Silicon
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/12—All metal or with adjacent metals
    • Y10T428/12479—Porous [e.g., foamed, spongy, cracked, etc.]
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/12—All metal or with adjacent metals
    • Y10T428/12493—Composite; i.e., plural, adjacent, spatially distinct metal components [e.g., layers, joint, etc.]
    • Y10T428/12535—Composite; i.e., plural, adjacent, spatially distinct metal components [e.g., layers, joint, etc.] with additional, spatially distinct nonmetal component
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/12—All metal or with adjacent metals
    • Y10T428/12493—Composite; i.e., plural, adjacent, spatially distinct metal components [e.g., layers, joint, etc.]
    • Y10T428/12535—Composite; i.e., plural, adjacent, spatially distinct metal components [e.g., layers, joint, etc.] with additional, spatially distinct nonmetal component
    • Y10T428/12611—Oxide-containing component

Definitions

  • Coating system for a component with a thermal barrier coating and a metal erosion protection layer method for the production and method for operating a steam turbine
  • the invention relates to a component with a thermal barrier coating and a metal erosion control layer according to claim 1, a method for the production according to claim 31 and a method for operating a steam turbine according to claim 32.
  • Thermal barrier coatings applied to components are known in the gas turbine art such as e.g. in EP 1 029 115 are described.
  • Thermal barrier coatings allow components to be used at higher temperatures than the base material allows, or to extend service life.
  • Known base materials (substrates) for gas turbines allow operating temperatures of a maximum of 1000 0 C to 1100 0 C, whereas a coating with a thermal barrier coating allows operating temperatures of up to 1350 ° C.
  • US 2003/0152814 A1 discloses a thermal barrier coating system comprising a substrate of a superalloy, an aluminum oxide layer on the substrate and a ceramic as an outer ceramic thermal barrier coating.
  • EP 0 783 043 A1 discloses an erosion protection layer consisting of aluminum oxide or silicon carbide on a ceramic thermal barrier coating.
  • US Patent 5,683,226 discloses a component of a steam turbine whose erosion resistance is improved.
  • US 4,405,284 discloses an outer metallic layer which is significantly more porous than the underlying ceramic thermal barrier coating.
  • EP 0 783 043 A1 discloses in the discussion of the state of the art that an erosion-resistant coating is built up in two layers, namely an inner metallic layer and an outer ceramic layer.
  • US 5,740,515 discloses a ceramic thermal barrier coating on which is applied an outer hard ceramic silicide coating.
  • WO 00/70190 discloses a component in which an outer metallic layer is applied, which comprises aluminum, which serves to increase the oxidation resistance of the component.
  • the object is achieved by a component according to claim 1, by a method according to claim 31 and by a method according to claim 32.
  • a metallic erosion control layer is of particular advantage because it is elastically and plastically deformable due to its ductility.
  • the thermal barrier coating does not necessarily serve only the
  • thermo-mechanical stresses can be avoided or at least reduced.
  • Figure 6, 7, 8 further embodiments of a trained component according to the invention.
  • FIG. 1 shows a first exemplary embodiment of a layer system 1 designed according to the invention for a component.
  • layer system 1 and component are used interchangeably when the component has the layer system 1.
  • the component 1 is preferably a component of a gas or steam turbine 300, 303 (FIG. 4), in particular a steam inflow region 333 of a steam turbine 300, a turbine blade 342, 354, 357 (FIG. 4) or a housing part 334, 335, 366 (Fig. 4, 5) and consists of a substrate 4 (support structure) and a heat insulating layer applied thereto 7 and an outer metallic erosion protection layer 13 on the thermal barrier coating 7. Between the substrate 4 and the thermal barrier coating 7 at least one metallic bonding layer 10 is arranged , The bonding layer 10 serves to protect against corrosion and / or oxidation of the substrate 4 and / or for better bonding of the thermal barrier coating 7 to the substrate 4. This is the case in particular if the thermal barrier coating 7 is made of ceramic and the substrate 4 is made of a metal consists.
  • the erosion protection layer 13 consists of a metal or a metal alloy and protects the component from erosion and / or wear, as is the case in particular with steam turbines 300, 303 ( Figure 4), which are subject to scaling, is the case and in which average flow velocities of about 50 m / s (ie 20 m / s - 100 m / s) and pressures of 350 to 400 bar occur.
  • the density of the thermal barrier coating 7 is preferably 80% - 95% of the theoretical density, wherein the density p of the metallic erosion control layer 13 is preferably at least 96%, preferably 98% of the theoretical density.
  • metal is meant not only elemental metals, but also alloys, mixed crystals or intermetallic compounds.
  • the bonding layer 10 and the erosion protection layer 13 according to the invention have the same or similar composition.
  • both layers 10, 13 have the same elements in the same proportions (identity), preferably of an MCrAlX alloy or of SC 21, SC 23 or SC 24.
  • identity preferably of an MCrAlX alloy or of SC 21, SC 23 or SC 24.
  • Similar composition means that both layers 10, 13 have the same elements, but with slightly different proportions, ie differences of at most 3% per element (for example, layer 10 has chromium content of 30%, the layer 13 can have chromium contents of at least 27% (30-3) or at most 33% (30 + 3) and up to at least one additional element can be present up to at least 1% by weight.
  • the SC 21 consists of (in wt%) 29% - 31% nickel, 27% - 29% chromium, 7% - 8% aluminum, 0.5% - 0.7% yttrium, 0.3% - 0.7 % Silicon and balance cobalt.
  • the SC 23 consists of (in wt%) 11% - 13% cobalt, 20% - 22% chromium, 10.5% - 11.5% aluminum, 0.3% - 0.5% yttrium, 1.5% - 2.5% rhenium and the rest nickel.
  • the SC 24 consists of (in wt%) 24% - 26% cobalt, 16% - 18% chromium, 9.5% - 11% aluminum, 0.3% - 0.5% yttrium, 1.0% - 1 , 8% rhenium and the rest nickel.
  • the wear / erosion protection layer 13 preferably consists of alloys based on iron, chromium, nickel and / or cobalt or, for example, NiCr 80/20 or NiCrSiB with admixtures of boron (B) and silicon (Si) or NiAl (for example: Ni: 95wt%, Al 5wt%).
  • a metallic erosion protection layer 13 in steam turbines 300, 303 can be used since the operating temperatures in steam turbines in the steam inflow region 333 are at 450 ° C., 550 ° C., 650 ° C., 750 ° C. or 850 ° C.
  • a temperature of 750 ° C is used.
  • Metallic erosion protection layers 13 in gas turbines on a ceramic thermal barrier coating 7 within the first stage of the turbine or within the combustion chamber do not executed, since metallic erosion protection layers 13 as an outer layer, the service temperatures of up to 1350 0 C can not stand.
  • the bonding layer 10 for protecting a substrate 4 against corrosion and oxidation at a high temperature has, for example, substantially the following elements (parts by weight percentage wt%): 11.5% to 20.0% chromium, 0.3% to 1 , 5% silicon, 0.0% to 1.0% aluminum,
  • the metallic bonding layer 10 consists of 12.5% to 14.0% chromium, 0.5% to 1.0% silicon, 0.1% to 0.5% aluminum,
  • the composition of the iron-based attachment layer 10 exhibits particularly good properties, so that the attachment layer 10 is outstandingly suitable for application to ferritic substrates 4.
  • the thermal expansion coefficients of the iron-based attachment layer 10 exhibits particularly good properties, so that the attachment layer 10 is outstandingly suitable for application to ferritic substrates 4.
  • Substrate 4 and bonding layer 10 can be matched to each other very well (only up to 10% difference) or even equal, so that there is no thermal stress induced Construction between substrate 4 and bonding layer 10 comes (thermal mismatch), which could cause a spalling of the bonding layer 10.
  • the composition of the outer erosion control layer 13 is selected to have a high ductility.
  • High ductility in this context means that elongation at break of 5% (an elongation of 5% leads to the formation of cracks) at the service temperature.
  • Such an erosion protection layer 13 with such a ductility can be present directly on a substrate 4 or on a ceramic thermal barrier coating 7, wherein the composition of the bonding layer 10 then no longer plays a role.
  • the heat-insulating layer 7 is in particular a ceramic layer, which, for example, consists at least partially of zirconium oxide (partially stabilized or fully stabilized by yttrium oxide and / or magnesium oxide) and / or at least partially of titanium oxide and, for example, is thicker than 0.1 mm.
  • thermal barrier coatings 7 which consist of 100% either zirconium oxide or titanium oxide can be used.
  • the ceramic layer 7 can be applied by known coating methods such as atmospheric plasma spraying (APS), vacuum plasma spraying (VPS), low-pressure plasma spraying (LPPS) and by chemical or physical coating methods (CVD, PVD).
  • the substrate 4 is preferably a steel or other iron-based alloy (for example 1% CrMoV or 10-12% chromium steels) or a nickel- or cobalt-based superalloy.
  • the substrate 4 is a ferritic base alloy, a steel or a nickel or cobalt-based superalloy, in particular a 1% CrMoV steel or a 10 to 12% chromium steel.
  • ferritic substrates 4 of the layer system 1 consist of a
  • the thermal barrier coating 7 at least partially has a certain open and / or closed porosity.
  • the erosion protection layer 13 preferably has a higher density than the thermal barrier coating 7, so that it 13 has a higher erosion resistance.
  • the metallic erosion protection layer 13 has a very low porosity and in particular has a lower roughness, so that a good resistance to erosive erosion is achieved.
  • the lower porosity and roughness of the metallic erosion control layer can be achieved by various techniques:
  • the bonding layer 10, which is located between the substrate and the thermal barrier coating is designed to have a sufficiently high roughness with undercuts to achieve good bond strength of the thermal barrier coating to the tie layer 10.
  • a substantially coarser powder can be used during the injection process.
  • FIG. 2 shows a porous thermal insulation layer 7 with a gradient of porosity.
  • the layer 7 can be used in the region of greater porosity for thermal insulation and, where appropriate, for erosion protection in the area of lower porosity.
  • the bonding layer 10 preferably has a greater porosity than in the region of an outer surface or the contact surface with the erosion protection layer 13.
  • the erosion protection layer 13 is preferably applied only locally and preferably there on the component 1, where the angle of impact of eroding particles on the component 1 between 60 ° and 120 °, preferably between 70 ° and 110 ° or preferably by 80 ° and 100 °. It is particularly useful to coat the sites that have an angle of incidence of 90 ° +/- 2 ° of the eroding particles. In this almost vertical impact of eroding particles on the surface of a component 1, a metallic erosion protection layer 13 offers the best
  • the vertical on the surface of the component 1 represents the axis 90 °.
  • FIG. 4 shows by way of example a steam turbine 300, 303 with a turbine shaft 309 extending along a rotation axis 306.
  • the steam turbine has a high-pressure turbine section 300 and a medium-pressure turbine section 303, each having an inner housing 312 and an outer housing 315 enclosing this.
  • the high-pressure turbine part 300 is designed, for example, in Topfbauart.
  • the medium-pressure turbine section 303 is double-flow. It is also possible for the medium-pressure turbine section 303 to be single-flow.
  • a bearing 318 is arranged between the high-pressure turbine section 300 and the medium-pressure turbine section 303, wherein the turbine shaft 309 in the bearing 318 a Storage area 321 has.
  • the turbine shaft 309 is supported on another bearing 324 adjacent to the high pressure turbine sub 300.
  • the high-pressure turbine section 300 has a shaft seal 345.
  • the turbine shaft 309 is sealed off from the outer housing 315 of the medium-pressure turbine section 303 by two further shaft seals 345.
  • the turbine shaft 309 in the high-pressure turbine section 300 has the high-pressure impeller blading 354, 357.
  • the middle-pressure blast turbine 303 has a central steam inflow region 333.
  • the turbine shaft 309 Associated with the steam inflow region 333, the turbine shaft 309 has a radially symmetrical shaft shield 363, a cover plate, on the one hand for dividing the steam flow into the two flows of the medium-pressure turbine section 303 and for preventing direct contact of the hot steam with the turbine shaft 309.
  • the turbine shaft 309 has in the medium-pressure turbine section 303 a second blading area 366 with the medium-pressure blades 354, 342.
  • the hot steam flowing through the second blading area 366 flows out of the medium-pressure turbine section 303 from a discharge connection 369 to a downstream low-pressure turbine, not shown.
  • the turbine shaft 309 is composed of two sub-turbine shafts 309a and 309b, which are fixedly connected to one another in the region of the bearing 318.
  • FIG. 5 shows an enlarged view of a region of the steam turbine 300, 303.
  • the steam turbine 300, 303 is in the region of the inflow region 333 of an outer housing 334, abut the temperatures between 250 ° to 350 0 C.
  • Erosion protection layer 13 applied on the inside 336 (on the outside 337, for example, not).
  • the thermal barrier coating 7 is present locally only on the inner housing 335 (and not in the blading area 366, for example).
  • the heat input into the inner housing 335 is reduced, so that the thermal expansion behavior is influenced.
  • the entire deformation behavior of the inner housing 335 and the Dampfeinström Anlagens 333 can be controlled. This can be done by a variation of the thickness of the thermal barrier coating 7 or the application of different materials at different locations on the surface of the inner housing 335.
  • the porosity at different locations of the inner housing 335 may be different.
  • the thermal barrier coating 7 may be applied locally, for example in the inner housing 335 in the region of the inflow region 333.
  • the thermal barrier coating 7 can be applied locally only in the blading region 366 (FIG. 6). Especially in the inflow region 333, the use of an erosion protective layer 13 is required.
  • thermal barrier coating 7 TBC with erosion protection layer 13 is present in the inflow region 333, a Thermal insulation layer 7 without erosion protection layer in the blading area 366 and / or the turbine blades be present.
  • FIG. 7 shows a further exemplary embodiment of a component 1 according to the invention.
  • the thickness of the thermal barrier coating 7 in the inflow region 333 is made thicker than in the blading region 366 of the steam turbine 300, 303.
  • the heat input and thus the thermal expansion and thus the expansion behavior of the inner housing 334, consisting of the inflow region 333 and the blading region 366, are adjusted in a controlled manner.
  • thermal barrier coating 7 is applied here in the entire hot region, ie globally, and has the erosion protection layer 13.
  • FIG. 8 shows a further example of application for the use of a thermal barrier coating 7.
  • the component 1, in particular a housing part, is here a valve housing 31, into which a hot steam flows through an inlet channel 46.
  • the inflow passage 46 causes a mechanical weakening of the valve housing.
  • the valve housing 31 consists for example of a pot-shaped housing part 34 and a lid 37.
  • a valve consisting of a valve plug 40 and a spindle 43 is present.
  • the valve housing 31 would expand axially more strongly in the region of the channel 46, so that tilting of the cover with the spindle 43 occurs, as shown by dashed lines indicated.
  • the valve cone 34 no longer sits properly, so that the tightness of the valve is reduced.
  • thermal barrier coating 7 serves to control the deformation behavior and thus to ensure the tightness of the valve.
  • the thermal barrier coating 7 in turn has the erosion protection layer 13.

Landscapes

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

Abstract

L'invention concerne des composants (333, 366) d'une turbine à vapeur (300, 303) comprenant une couche d'isolation thermique (7) ainsi qu'une couche métallique anti-érosion (13) qui recouvre ladite couche d'isolation thermique (7). Selon l'invention, la couche anti-érosion (13) comprend le même matériau qu'une couche de liaison métallique (10).
EP06725133A 2005-06-13 2006-03-17 Systeme de couches conçu pour un composant comprenant une couche d'isolation thermique et une couche metallique anti-erosion, procede de production dudit composant, et procede pour faire fonctionner une turbine a vapeur Withdrawn EP1891249A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP06725133A EP1891249A1 (fr) 2005-06-13 2006-03-17 Systeme de couches conçu pour un composant comprenant une couche d'isolation thermique et une couche metallique anti-erosion, procede de production dudit composant, et procede pour faire fonctionner une turbine a vapeur

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
EP05012633A EP1734145A1 (fr) 2005-06-13 2005-06-13 Composant ayant un revêtement avec une barrière thermique et une couche resistante à l'erosion, procéde de manufacture et méthode pour son utilisation
PCT/EP2006/060835 WO2006133980A1 (fr) 2005-06-13 2006-03-17 Systeme de couches conçu pour un composant comprenant une couche d'isolation thermique et une couche metallique anti-erosion, procede de production dudit composant, et procede pour faire fonctionner une turbine a vapeur
EP06725133A EP1891249A1 (fr) 2005-06-13 2006-03-17 Systeme de couches conçu pour un composant comprenant une couche d'isolation thermique et une couche metallique anti-erosion, procede de production dudit composant, et procede pour faire fonctionner une turbine a vapeur

Publications (1)

Publication Number Publication Date
EP1891249A1 true EP1891249A1 (fr) 2008-02-27

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EP05012633A Withdrawn EP1734145A1 (fr) 2005-06-13 2005-06-13 Composant ayant un revêtement avec une barrière thermique et une couche resistante à l'erosion, procéde de manufacture et méthode pour son utilisation
EP06725133A Withdrawn EP1891249A1 (fr) 2005-06-13 2006-03-17 Systeme de couches conçu pour un composant comprenant une couche d'isolation thermique et une couche metallique anti-erosion, procede de production dudit composant, et procede pour faire fonctionner une turbine a vapeur

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EP05012633A Withdrawn EP1734145A1 (fr) 2005-06-13 2005-06-13 Composant ayant un revêtement avec une barrière thermique et une couche resistante à l'erosion, procéde de manufacture et méthode pour son utilisation

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US (1) US8047775B2 (fr)
EP (2) EP1734145A1 (fr)
JP (1) JP4749467B2 (fr)
CN (1) CN101198713B (fr)
WO (1) WO2006133980A1 (fr)

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Also Published As

Publication number Publication date
CN101198713B (zh) 2010-08-18
US20090053069A1 (en) 2009-02-26
JP4749467B2 (ja) 2011-08-17
WO2006133980A1 (fr) 2006-12-21
JP2008544127A (ja) 2008-12-04
US8047775B2 (en) 2011-11-01
EP1734145A1 (fr) 2006-12-20
CN101198713A (zh) 2008-06-11

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