EP1973860A1 - Composant compact en ceramique, couche ceramique a tres forte porosite, utilisation de cette couche et composant la contenant - Google Patents

Composant compact en ceramique, couche ceramique a tres forte porosite, utilisation de cette couche et composant la contenant

Info

Publication number
EP1973860A1
EP1973860A1 EP06830829A EP06830829A EP1973860A1 EP 1973860 A1 EP1973860 A1 EP 1973860A1 EP 06830829 A EP06830829 A EP 06830829A EP 06830829 A EP06830829 A EP 06830829A EP 1973860 A1 EP1973860 A1 EP 1973860A1
Authority
EP
European Patent Office
Prior art keywords
ceramic
layer
component
solid
ceramic layer
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.)
Ceased
Application number
EP06830829A
Other languages
German (de)
English (en)
Inventor
Stefan Lampenscherf
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.)
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 EP06830829A priority Critical patent/EP1973860A1/fr
Priority to EP20100013498 priority patent/EP2341165A1/fr
Publication of EP1973860A1 publication Critical patent/EP1973860A1/fr
Ceased legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/002—Wall structures
    • C—CHEMISTRY; METALLURGY
    • C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
    • C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
    • C04B38/00—Porous mortars, concrete, artificial stone or ceramic ware; Preparation thereof
    • C04B38/007—Porous mortars, concrete, artificial stone or ceramic ware; Preparation thereof characterised by the pore distribution, e.g. inhomogeneous distribution of pores
    • C04B38/0074—Porous mortars, concrete, artificial stone or ceramic ware; Preparation thereof characterised by the pore distribution, e.g. inhomogeneous distribution of pores expressed as porosity percentage
    • 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
    • C23C30/00—Coating with metallic material characterised only by the composition of the metallic material, i.e. not characterised by the coating process
    • 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
    • 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
    • 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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
    • 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
    • F01D5/284—Selection of ceramic materials
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • F01D5/288—Protective coatings for blades
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
    • F02C7/045—Air intakes for gas-turbine plants or jet-propulsion plants having provisions for noise suppression
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/24—Heat or noise insulation
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23M—CASINGS, LININGS, WALLS OR DOORS SPECIALLY ADAPTED FOR COMBUSTION CHAMBERS, e.g. FIREBRIDGES; DEVICES FOR DEFLECTING AIR, FLAMES OR COMBUSTION PRODUCTS IN COMBUSTION CHAMBERS; SAFETY ARRANGEMENTS SPECIALLY ADAPTED FOR COMBUSTION APPARATUS; DETAILS OF COMBUSTION CHAMBERS, NOT OTHERWISE PROVIDED FOR
    • F23M5/00—Casings; Linings; Walls
    • C—CHEMISTRY; METALLURGY
    • C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
    • C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
    • C04B2111/00—Mortars, concrete or artificial stone or mixtures to prepare them, characterised by specific function, property or use
    • C04B2111/00474—Uses not provided for elsewhere in C04B2111/00
    • C04B2111/00482—Coating or impregnation materials
    • C04B2111/00525—Coating or impregnation materials for metallic surfaces
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23M—CASINGS, LININGS, WALLS OR DOORS SPECIALLY ADAPTED FOR COMBUSTION CHAMBERS, e.g. FIREBRIDGES; DEVICES FOR DEFLECTING AIR, FLAMES OR COMBUSTION PRODUCTS IN COMBUSTION CHAMBERS; SAFETY ARRANGEMENTS SPECIALLY ADAPTED FOR COMBUSTION APPARATUS; DETAILS OF COMBUSTION CHAMBERS, NOT OTHERWISE PROVIDED FOR
    • F23M2900/00—Special features of, or arrangements for combustion chambers
    • F23M2900/05001—Preventing corrosion by using special lining materials or other techniques
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23M—CASINGS, LININGS, WALLS OR DOORS SPECIALLY ADAPTED FOR COMBUSTION CHAMBERS, e.g. FIREBRIDGES; DEVICES FOR DEFLECTING AIR, FLAMES OR COMBUSTION PRODUCTS IN COMBUSTION CHAMBERS; SAFETY ARRANGEMENTS SPECIALLY ADAPTED FOR COMBUSTION APPARATUS; DETAILS OF COMBUSTION CHAMBERS, NOT OTHERWISE PROVIDED FOR
    • F23M2900/00—Special features of, or arrangements for combustion chambers
    • F23M2900/05004—Special materials for walls or lining
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/249921—Web or sheet containing structurally defined element or component
    • Y10T428/249953—Composite having voids in a component [e.g., porous, cellular, etc.]
    • Y10T428/249967—Inorganic matrix in void-containing component
    • Y10T428/249969—Of silicon-containing material [e.g., glass, etc.]

Definitions

  • Ceramic solid component, ceramic layer with high porosity, use of this layer and a component with this layer are ceramic solid component, ceramic layer with high porosity, use of this layer and a component with this layer
  • the invention relates to a solid ceramic component, a ceramic layer with high porosity, the use of this layer at very high temperatures and a component with this layer.
  • Ceramic layers are often used for thermal insulation of components that could not be used without a protective layer at high temperatures. These are e.g. Turbine blades for gas turbines or steam turbines. In this case, a ceramic thermal insulation layer is applied to a substrate with a metallic bonding layer.
  • the ceramic porous layers known hitherto show, in particular with large layer thicknesses, too low a stretching tolerance.
  • the object is achieved by a solid ceramic component, a ceramic layer according to claim 1 or 2, by a Use according to claim 11 and by a component according to claim 12.
  • FIG. 1 shows a layer system
  • FIG. 2 shows a micrograph of a ceramic layer according to the prior art
  • FIG. 3 shows a micrograph of a ceramic layer according to the invention
  • FIG. 4 shows a gas turbine
  • Figure 5 is a perspective view of a turbine blade
  • Figure 6 is a perspective view of a combustion chamber.
  • FIG. 1 shows a layer system 1 according to the invention.
  • the layer system 1 consists of a substrate 4, which in particular when used for high temperatures such.
  • a substrate 4 which in particular when used for high temperatures such.
  • nickel- or cobalt-based superalloys exist in gas turbine engines 100 (FIG. 4).
  • iron-based superalloys can also be used.
  • a metallic bonding layer 7 is preferably present, which represents an alloy of the type MCrAlX.
  • a ceramic layer 10 according to the invention with high porosity is present on this metallic bonding layer 7 or on the substrate 4. Particularly at very high temperatures, as occur, for example, for coatings inside the combustion chamber (FIG. 6) ( ⁇ 1100 ° C.), a specific adjustment of the porosity is necessary in order to achieve a sufficient expansion tolerance.
  • FIG. 2 shows a micrograph of a ceramic thermal barrier layer with pores and their pore cross sections according to the prior art.
  • a pore in the ceramic layer is cut during the production of the cut and, in this sectional plane, has a specific pore cross-section, which represents the area of the pore in the plane of the micrograph. Every other microsection gives similar values for the pore cross sections.
  • the porosity analysis gives pores in the range of O ⁇ m 2 - 3000 ⁇ m 2 for the microsection of the prior art and also pore cross sections in the range of> 3000 ⁇ m 2 - 6000 ⁇ m 2 , but no pore cross-sections lying above it.
  • FIG. 3 shows a micrograph of an inventive ceramic thermal insulation layer 10 with pores and their pore cross-sections.
  • the following table discloses a distribution of pore cross sections.
  • the inventive ceramic layer 10 also has pore cross sections with values between> 6000 ⁇ m 2 and 9000 ⁇ m 2 (FIG. 3).
  • pore cross sections of> 9000 ⁇ m 2 - 12000 ⁇ m 2 are also present.
  • no pore cross sections ⁇ 12000 ⁇ m 2 are present.
  • the higher porosity is not achieved by a uniform enlargement of the pores according to the prior art, but by deliberate introduction of a few larger pores, ie a broadening of the pore cross-sectional distribution, which then leads to low hardness values for a ceramic layer.
  • the porosity is 22vol% to 28vol%. Preferably, values around 24vol% or 26vol% are used.
  • the hardness of the layer measured with HV 0 , 3 amounts to 630.
  • the layer thickness of the ceramic layer 10 is between 200 .mu.m and 2400 .mu.m, in particular between 100 .mu.m and 1200 .mu.m. Preferably, the layer thickness can also be large 1500 ⁇ m.
  • the strain tolerance of this inventive layer 10 with a layer thickness of HOO ⁇ m amounts to 1300 0 C just 0.15%. Comparable standard layers have values ⁇ 0.1%. This results in a significant increase in the expansion tolerance for the inventive layer 10 at high temperatures. At low temperatures (around 1100 ° C), the strain tolerance values of the standard layers and the new layers are comparable.
  • the layer 10 is preferably produced by plasma spraying with plastic particles. Due to the high proportion of plastic to be used, larger voids are formed (percolation effect, i.e., the voids overlap).
  • microstructure of a solid porous ceramic component corresponds to the microstructure of the layer.
  • Such components are preferably used as combustion stones for a combustion chamber 110.
  • FIG. 4 shows by way of example a gas turbine 100 in a long partial section.
  • the gas turbine 100 has inside a rotatably mounted about a rotation axis 102 rotor 103 with a shaft 101, which is also referred to as a turbine runner.
  • a compressor 105 for example, a toroidal combustion chamber 110, in particular annular combustion chamber, with a plurality of coaxially arranged burners 107, a turbine 108 and the exhaust gas housing 109.
  • the annular combustion chamber 110 communicates with an example ring-shaped hot gas channel 111th
  • four turbine stages 112 connected in series form the turbine 108.
  • Each turbine stage 112 is formed, for example, from two blade rings. In flow direction of a working medium
  • a row 125 formed of rotor blades 120 follows.
  • the guide vanes 130 are fastened to an inner housing 138 of a stator 143, whereas the rotor blades 120 of a row 125 are attached to the rotor 103 by means of a turbine disk 133, for example.
  • air 105 is sucked in and compressed by the compressor 105 through the intake housing 104.
  • the compressed air provided at the turbine-side end of the compressor 105 is supplied to the burners 107 where it is mixed with a fuel.
  • the mixture is then burned to form the working fluid 113 in the combustion chamber 110.
  • the working medium 113 flows along the hot gas channel 111 past the guide vanes 130 and the blades 120.
  • the working medium 113 expands in a pulse-transmitting manner, so that the blades 120 drive the rotor 103 and this drives the machine coupled to it.
  • the components exposed to the hot working medium 113 are subject to thermal loads during the operation of the gas turbine 100.
  • the guide vanes 130 and rotor blades 120 of the first turbine stage 112, viewed in the direction of flow of the working medium 113, are subjected to the greatest thermal stress in addition to the heat shield elements lining the annular combustion chamber 110.
  • substrates of the components may have a directional structure, i. they are monocrystalline (SX structure) or have only slow grains (DS structure).
  • SX structure monocrystalline
  • DS structure slow grains
  • iron-, nickel- or cobalt-based superalloys are used as the material for the components, in particular for the turbine blade 120, 130 and components of the combustion chamber 110.
  • 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; These documents are part of the disclosure regarding the chemical composition of the alloys.
  • the blades 120, 130 may be anti-corrosion coatings (MCrAlX; M is at least one element of the group iron (Fe), cobalt (Co), nickel (Ni), X is an active element and is yttrium (Y) and / or silicon , Scandium (Sc) and / or at least one element of the rare earth or hafnium).
  • M is at least one element of the group iron (Fe), cobalt (Co), nickel (Ni)
  • X is an active element and is yttrium (Y) and / or silicon , Scandium (Sc) and / or at least one element of the rare earth or hafnium.
  • 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, which should be part of this disclosure with regard to the chemical composition.
  • a heat-insulating layer 10 may also be present, and consists for example of Zr ⁇ 2, Y2Ü3-Zr ⁇ 2, ie it is not, partially or fully ⁇ dig stabilized by yttria and / or calcium oxide and / or magnesium oxide.
  • Electron Beam Evaporation produces proton grains in the thermal insulation layer.
  • the vane 130 has a Leitschaufelfuß facing the mecanical exhauste 138 of the turbine 108 (not shown here) and a Leitschaufelfuß opposite
  • the vane head faces the rotor 103 and fixed to a mounting ring 140 of the stator 143.
  • FIG. 5 shows a perspective view of a moving blade 120 or guide blade 130 of a flow machine, which extends along a longitudinal axis 121.
  • the flow machine may be a gas turbine of an aircraft or a power plant for power generation, a steam turbine or a compressor.
  • the blade 120, 130 has, along the longitudinal axis 121, a fastening area 400, an adjacent blade platform 403, and an airfoil 406 and a blade tip 415.
  • the blade 130 may have another platform at its blade tip 415 (not shown).
  • 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 designed, for example, as a hammer head. Other designs as Christmas tree or Schwalbenschwanzfuß are possible.
  • the blade 120, 130 has a flow-on edge 409 and a downstream edge 412 for a medium that flows past the blade 406.
  • blades 120, 130 for example, solid metallic materials, in particular superalloys, are used in all regions 400, 403, 406 of the blade 120, 130.
  • 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; These documents are part of the disclosure regarding the chemical composition of the alloy.
  • the blade 120, 130 can hereby be produced by a casting process, also by directional solidification, by a forging process, by a milling process or combinations thereof.
  • Single-crystalline structures or structures are used as components for machines that are subject to high mechanical, thermal and / or chemical stresses during operation.
  • Such monocrystalline workpieces for example, by directed solidification from the melt. These are casting processes in which the liquid metallic alloy solidifies to a monocrystalline structure, ie to a single-crystalline workpiece, or directionally.
  • dendritic crystals are aligned along the warm flow and form either a prismatic crystalline grain structure (columnar, ie grains that run the entire length of the workpiece and here, in common usage, are referred to as directionally solidified) or a monocrystalline structure, ie the whole
  • the work consists of a single crystal.
  • the blades 120, 130 may have coatings against corrosion or oxidation, e.g. B. (MCrAlX; M is at least one element of the group iron (Fe), cobalt (Co),
  • Nickel (Ni), X is an active element and stands for 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, which should be part of this disclosure with regard to the chemical composition of the alloy.
  • the density is preferably 95% of the theoretical density.
  • Warmedamm- layer 10 is present, which is preferably the outermost layer, and consists for example of Zr ⁇ 2, Y2 ⁇ 3 ⁇ Zr ⁇ 2, ie it is not, partially or completely stabilized by yttria and / or calcium oxide and / or magnesium oxide ,
  • the thermal insulation layer covers the entire MCrAlX layer. Suitable coating processes, such as electron beam evaporation (EB-PVD), are used to produce protuberant grains in the thermal insulation layer. Other coating methods are conceivable, for example atmospheric plasma spraying (APS), LPPS, VPS or CVD.
  • the thermal barrier layer can have porous, micro- or macro-cracked grains for better thermal shock resistance.
  • the thermal insulation layer is therefore preferably more porous than the MCrAlX layer.
  • Refurbishment means that components 120, 130 may need to be stripped of protective layers 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 possibly still has film cooling holes 418 (indicated by dashed lines).
  • FIG. 6 shows a combustion chamber 110 of a gas turbine.
  • the combustion chamber 110 is designed, for example, as a so-called annular combustion chamber, in which a multiplicity of burners 107 arranged in the circumferential direction around a rotation axis 102 pass into a common combustion chamber space 154, which produce flames 156.
  • the combustion chamber 110 is configured in its entirety as an annular structure, which is positioned around the axis of rotation 102 around.
  • the combustion chamber 110 is designed for a comparatively high temperature of the working medium M of about 1000 ° C. to 1600 ° C.
  • the combustion chamber wall 153 is located on its Dium M facing side provided with an inner lining formed from heat shield elements 155.
  • Each heat shield element 155 made of an alloy is equipped on the working fluid side with a particularly heat-resistant protective layer (MCrAlX layer and / or ceramic coating) or is made of high-temperature-resistant material (solid ceramic blocks).
  • M is at least one element of the group iron (Fe), cobalt (Co), nickel (Ni), X is an active element and stands for yttrium (Y) and / or silicon and / or at least one element of the rare earths, or hafnium (Hf).
  • MCrAlX means: M is at least one element of the group iron (Fe), cobalt (Co), nickel (Ni), X is an active element and stands for 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, which should be part of this disclosure with regard to the chemical composition of the alloy.
  • ceramic maintenance can medamm harsh, consisting for example of ZrO 2, Y 2 O 3 -ZrO 2, DH is not partially full text or ⁇ stabilized dig by yttrium oxide and / or calcium and / or magnesium oxide.
  • Electron Beam Evaporation produces proton grains in the thermal insulation layer.
  • thermal insulation layer may have porous, micro- or macro-cracked grains for better thermal shock resistance.
  • Refurbishment means that heat shield elements 155 may have to be freed of protective layers after their use (eg by sandblasting). This is followed by removal of the corrosion and / or oxidation layers or products. If necessary, cracks in the heat shield element 155 are also repaired. Thereafter, a recoating of the heat shield element takes place. 155 and a renewed use of the heat shield elements 155.
  • a cooling system can additionally be provided for the heat shield elements 155 or for their holding elements.
  • the heat shield elements 155 are then, for example, hollow and possibly still have cooler holes (not shown) which still touch the combustion chamber space 154.

Landscapes

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

Abstract

Des couches céramiques sont souvent utilisées en isolation thermique dans un système de couches. Elles présentent alors une très grande porosité. L'invention concerne une couche isolante thermiquement, en céramique, présentant une répartition particulière de la grandeur des pores, de manière à présenter, lors de températures supérieures à 1200°C une grande tolérance à l'expansion.
EP06830829A 2006-01-09 2006-12-28 Composant compact en ceramique, couche ceramique a tres forte porosite, utilisation de cette couche et composant la contenant Ceased EP1973860A1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP06830829A EP1973860A1 (fr) 2006-01-09 2006-12-28 Composant compact en ceramique, couche ceramique a tres forte porosite, utilisation de cette couche et composant la contenant
EP20100013498 EP2341165A1 (fr) 2006-01-09 2006-12-28 Élément de construction ceramique, massique ou revêmtement céramique ayant une haute porositée, leur utilisation et élément de construction comportant ladite revêtement

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
EP20060000338 EP1806430A1 (fr) 2006-01-09 2006-01-09 Revêmtement céramique ayant une haute porositée, utilisation de celle-ci revêtement et composant comprenant telle revêtement
EP06830829A EP1973860A1 (fr) 2006-01-09 2006-12-28 Composant compact en ceramique, couche ceramique a tres forte porosite, utilisation de cette couche et composant la contenant
PCT/EP2006/070233 WO2007080058A1 (fr) 2006-01-09 2006-12-28 Composant compact en ceramique, couche ceramique a tres forte porosite, utilisation de cette couche et composant la contenant

Publications (1)

Publication Number Publication Date
EP1973860A1 true EP1973860A1 (fr) 2008-10-01

Family

ID=35840556

Family Applications (3)

Application Number Title Priority Date Filing Date
EP20060000338 Withdrawn EP1806430A1 (fr) 2006-01-09 2006-01-09 Revêmtement céramique ayant une haute porositée, utilisation de celle-ci revêtement et composant comprenant telle revêtement
EP06830829A Ceased EP1973860A1 (fr) 2006-01-09 2006-12-28 Composant compact en ceramique, couche ceramique a tres forte porosite, utilisation de cette couche et composant la contenant
EP20100013498 Withdrawn EP2341165A1 (fr) 2006-01-09 2006-12-28 Élément de construction ceramique, massique ou revêmtement céramique ayant une haute porositée, leur utilisation et élément de construction comportant ladite revêtement

Family Applications Before (1)

Application Number Title Priority Date Filing Date
EP20060000338 Withdrawn EP1806430A1 (fr) 2006-01-09 2006-01-09 Revêmtement céramique ayant une haute porositée, utilisation de celle-ci revêtement et composant comprenant telle revêtement

Family Applications After (1)

Application Number Title Priority Date Filing Date
EP20100013498 Withdrawn EP2341165A1 (fr) 2006-01-09 2006-12-28 Élément de construction ceramique, massique ou revêmtement céramique ayant une haute porositée, leur utilisation et élément de construction comportant ladite revêtement

Country Status (4)

Country Link
US (1) US20090081445A1 (fr)
EP (3) EP1806430A1 (fr)
CN (1) CN101356137A (fr)
WO (1) WO2007080058A1 (fr)

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2339119A1 (fr) * 2009-12-23 2011-06-29 Siemens Aktiengesellschaft Revêtement de barrière thermique ayant une faible conductivité thermique
EP2644824A1 (fr) 2012-03-28 2013-10-02 Siemens Aktiengesellschaft Procédé de production et reproduction de rêvetements de barrières thermiques en céramique dans des turbines à gaz et turbine à gaz associée
EP2882939B1 (fr) * 2012-10-05 2020-01-08 Siemens Aktiengesellschaft Procédé de reconditionnement d'une aube de turbine à gaz ainsi que l'usage d'une turbine à gaz pourvue d'une telle aube

Family Cites Families (19)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4764089A (en) * 1986-08-07 1988-08-16 Allied-Signal Inc. Abradable strain-tolerant ceramic coated turbine shroud
DE3926479A1 (de) 1989-08-10 1991-02-14 Siemens Ag Rheniumhaltige schutzbeschichtung, mit grosser korrosions- und/oder oxidationsbestaendigkeit
EP0486489B1 (fr) 1989-08-10 1994-11-02 Siemens Aktiengesellschaft Revetement anticorrosion resistant aux temperatures elevees, notamment pour elements de turbines a gaz
FR2668145B1 (fr) * 1990-10-17 1993-01-22 Ceramiques Composites Corps fritte en carbure de silicium notamment pour garniture mecanique et garniture comportant un tel corps fritte.
US5834108A (en) * 1992-12-29 1998-11-10 Toshiba Ceramics Co., Ltd. Multi-layered ceramic porous body
JP3370676B2 (ja) 1994-10-14 2003-01-27 シーメンス アクチエンゲゼルシヤフト 腐食・酸化及び熱的過負荷に対して部材を保護するための保護層並びにその製造方法
EP0892090B1 (fr) 1997-02-24 2008-04-23 Sulzer Innotec Ag Procédé de fabrication de structure monocristallines
EP0861927A1 (fr) 1997-02-24 1998-09-02 Sulzer Innotec Ag Procédé de fabrication de structures monocristallines
EP0897019B1 (fr) * 1997-07-18 2002-12-11 ANSALDO RICERCHE S.r.l. Procédé et appareil pour la formation de revêtements céramiques poreux, en particulier revêtements de barrières thermiques, sur des substrats métalliques
US6057047A (en) * 1997-11-18 2000-05-02 United Technologies Corporation Ceramic coatings containing layered porosity
EP1306454B1 (fr) 2001-10-24 2004-10-06 Siemens Aktiengesellschaft Revêtement protecteur contenant du rhénium pour la protection d'un élément contre l'oxydation et la corrosion aux températures élevées
WO1999067435A1 (fr) 1998-06-23 1999-12-29 Siemens Aktiengesellschaft Alliage a solidification directionnelle a resistance transversale a la rupture amelioree
US6231692B1 (en) 1999-01-28 2001-05-15 Howmet Research Corporation Nickel base superalloy with improved machinability and method of making thereof
DE50006694D1 (de) 1999-07-29 2004-07-08 Siemens Ag Hochtemperaturbeständiges bauteil und verfahren zur herstellung des hochtemperaturbeständigen bauteils
DE10013378A1 (de) * 2000-03-17 2001-10-04 Dornier Gmbh Poröse Keramik
DE50112339D1 (de) 2001-12-13 2007-05-24 Siemens Ag Hochtemperaturbeständiges Bauteil aus einkristalliner oder polykristalliner Nickel-Basis-Superlegierung
EP1362933A1 (fr) * 2002-05-15 2003-11-19 Siemens Aktiengesellschaft Revêtement de barrière thermique
DK177002B1 (da) * 2003-09-29 2010-11-15 Niras As Indretning til beskyttelse mod eksplosion
EP1959099B1 (fr) * 2004-12-14 2011-06-15 Mitsubishi Heavy Industries, Ltd. Procédé de fabrication d'un élément revêtu avec une barrière thermique

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See references of WO2007080058A1 *

Also Published As

Publication number Publication date
CN101356137A (zh) 2009-01-28
WO2007080058A8 (fr) 2008-11-27
US20090081445A1 (en) 2009-03-26
WO2007080058A1 (fr) 2007-07-19
EP2341165A1 (fr) 2011-07-06
EP1806430A1 (fr) 2007-07-11

Similar Documents

Publication Publication Date Title
EP2097616B1 (fr) Élément structurel ayant dans sa surface des évidements s'étendant en oblique, et procédé d'exploitation d'une turbine
WO2006061267A1 (fr) Systeme stratifie, utilisation et procede de realisation d'un systeme stratifie
EP2593582B1 (fr) Système stratifié céramique poreux
EP2695971A1 (fr) Système de couche à double couche poreux doté d'une phase pyrochlore
WO2010040746A1 (fr) Broche métallique pour procédé de coulée de précision et moule de coulée en céramique
EP1835045A1 (fr) Procédé d'obtention d'une pièce revêtue
EP1816316B1 (fr) Procédé de réparation de composants
EP2904211A1 (fr) Surface modifiée autour d'un trou
WO2012062546A1 (fr) Système à couches poreux, muni d'une couche interne poreuse
EP2373824A1 (fr) Procédé pour recouvrir un composant pourvu de trous de refroidissement pelliculaire et composant
WO2008049460A1 (fr) PROCÉDÉ POUR RÉGLER LA RUGOSITÉ de surface LORS D'UNE OPÉRATION DE REVÊTEMENT À BASSE TEMPÉRATURE, ET ÉLÉMENT DE CONSTRUCTION
EP2882939A1 (fr) Procédé de reconditionnement d'une aube de turbine à gaz ainsi que turbine à gaz pourvue d'une telle aube
WO2008087084A1 (fr) Mélange poudreux comprenant de la poudre en blocs, procédé d'utilisation du mélange poudreux et éléments de construction
WO2006103125A1 (fr) Systeme de couches et procede pour realiser un systeme de couches
EP1973860A1 (fr) Composant compact en ceramique, couche ceramique a tres forte porosite, utilisation de cette couche et composant la contenant
WO2006069822A1 (fr) Procede de creation d'un trou
EP1967615A1 (fr) Procédé destiné à l'application d'une couche d'isolation thermique et pièce de turbine dotée d'une couche d'isolation thermique
EP2082076A1 (fr) Procédé d'optimisation de revêtement par un coupon et composant avec coupon
EP1681374A1 (fr) Système de revêtement comprenant une couche barrière et procédé de fabrication
WO2013060499A1 (fr) Surface pourvue de dépressions spécialement formées et élément
EP1930115A1 (fr) Fil, son utilisation et procédé de soudage
WO2007144217A1 (fr) Procédé d'application d'un matériau sur un composant
WO2007082793A1 (fr) Composant dote d'un revetement et procede de preparation d'un revetement
EP1918063A1 (fr) Poudre de brasage composite comprenant un noyau et un revêtement métallique pour le brasage de pièces de turbine
EP1811055A1 (fr) Methode pour fabriquer un composant avec des orifices

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

17P Request for examination filed

Effective date: 20080516

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HU IE IS IT LI LT LU LV MC NL PL PT RO SE SI SK TR

17Q First examination report despatched

Effective date: 20081009

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE APPLICATION HAS BEEN REFUSED

18R Application refused

Effective date: 20101230