US20190301291A9 - Masking method for producing a combination of blade tip hardfacing and erosion-protection coating - Google Patents
Masking method for producing a combination of blade tip hardfacing and erosion-protection coating Download PDFInfo
- Publication number
- US20190301291A9 US20190301291A9 US15/152,671 US201615152671A US2019301291A9 US 20190301291 A9 US20190301291 A9 US 20190301291A9 US 201615152671 A US201615152671 A US 201615152671A US 2019301291 A9 US2019301291 A9 US 2019301291A9
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- US
- United States
- Prior art keywords
- erosion
- hardfacing
- blade
- protection coating
- tip
- Prior art date
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- 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
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
- B23K1/00—Soldering, e.g. brazing, or unsoldering
- B23K1/0008—Soldering, e.g. brazing, or unsoldering specially adapted for particular articles or work
- B23K1/0018—Brazing of turbine parts
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
- B23K1/00—Soldering, e.g. brazing, or unsoldering
- B23K1/19—Soldering, e.g. brazing, or unsoldering taking account of the properties of the materials to be soldered
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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
- C23C14/00—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material
- C23C14/04—Coating on selected surface areas, e.g. using masks
- C23C14/042—Coating on selected surface areas, e.g. using masks using masks
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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
- C23C14/00—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material
- C23C14/04—Coating on selected surface areas, e.g. using masks
- C23C14/042—Coating on selected surface areas, e.g. using masks using masks
- C23C14/044—Coating on selected surface areas, e.g. using masks using masks using masks to redistribute rather than totally prevent coating, e.g. producing thickness gradient
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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
- C23C14/00—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material
- C23C14/06—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material characterised by the coating material
- C23C14/0641—Nitrides
- C23C14/0647—Boron nitride
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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
- C23C14/00—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material
- C23C14/06—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material characterised by the coating material
- C23C14/14—Metallic material, boron or silicon
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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
- C23C14/00—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material
- C23C14/22—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material characterised by the process of coating
- C23C14/34—Sputtering
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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
- C23C14/00—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material
- C23C14/22—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material characterised by the process of coating
- C23C14/34—Sputtering
- C23C14/35—Sputtering by application of a magnetic field, e.g. magnetron sputtering
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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
- 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
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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
- 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
- C23C28/324—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 matrix material layer comprising a mixture of at least two metals or metal phases or a metal-matrix material with hard embedded particles, e.g. WC-Me
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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
- 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
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- C—CHEMISTRY; METALLURGY
- C25—ELECTROLYTIC OR ELECTROPHORETIC PROCESSES; APPARATUS THEREFOR
- C25D—PROCESSES FOR THE ELECTROLYTIC OR ELECTROPHORETIC PRODUCTION OF COATINGS; ELECTROFORMING; APPARATUS THEREFOR
- C25D3/00—Electroplating: Baths therefor
- C25D3/02—Electroplating: Baths therefor from solutions
- C25D3/12—Electroplating: Baths therefor from solutions of nickel or cobalt
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- C—CHEMISTRY; METALLURGY
- C25—ELECTROLYTIC OR ELECTROPHORETIC PROCESSES; APPARATUS THEREFOR
- C25D—PROCESSES FOR THE ELECTROLYTIC OR ELECTROPHORETIC PRODUCTION OF COATINGS; ELECTROFORMING; APPARATUS THEREFOR
- C25D7/00—Electroplating characterised by the article coated
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- C—CHEMISTRY; METALLURGY
- C25—ELECTROLYTIC OR ELECTROPHORETIC PROCESSES; APPARATUS THEREFOR
- C25D—PROCESSES FOR THE ELECTROLYTIC OR ELECTROPHORETIC PRODUCTION OF COATINGS; ELECTROFORMING; APPARATUS THEREFOR
- C25D9/00—Electrolytic coating other than with metals
- C25D9/04—Electrolytic coating other than with metals with inorganic materials
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- 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
- F01D11/122—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 with erodable or abradable material
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- 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
- F01D5/14—Form or construction
- F01D5/147—Construction, i.e. structural features, e.g. of weight-saving hollow blades
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- 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
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
- B23K2101/00—Articles made by soldering, welding or cutting
- B23K2101/34—Coated articles, e.g. plated or painted; Surface treated articles
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
- B23K2103/00—Materials to be soldered, welded or cut
- B23K2103/16—Composite materials, e.g. fibre reinforced
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- B23K2203/16—
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- 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
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- 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
- F05D2230/313—Layer deposition by physical vapour deposition
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- 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
- F05D2240/00—Components
- F05D2240/20—Rotors
- F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
- F05D2240/307—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor related to the tip of a rotor blade
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- 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
- F05D2300/16—Other metals not provided for in groups F05D2300/11 - F05D2300/15
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- 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
- F05D2300/228—Nitrides
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- 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
- F05D2300/506—Hardness
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- 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
Definitions
- the present invention relates to a method for manufacturing a blade for a turbomachine, the blade having a hardfacing on its tip and an erosion-protection coating at least on its airfoil.
- the present invention also relates to a corresponding blade for a turbomachine such as, for example, a stationary gas turbine or an aircraft engine.
- Turbomachines such as stationary gas turbines or aircraft engines, include, inter alia, a plurality of blades rotatably mounted on a rotor so as to either compress the fluid flowing through the turbomachine or to be driven into rotation by the fluid.
- the gap between the blade tips at the radial ends of the blades and the flow duct boundary must be as small as possible in order that as little fluid as possible may flow through the gap between the flow duct boundary and the blades.
- blade tip hardfacings have particles of hard material embedded in a metal matrix, which are intended to cut the groove for the labyrinth seal into the opposite sealing material of the flow duct boundary and to protect the blade tip from wear.
- blades of turbomachines also include protective coatings, such as erosion-protection coatings, on the airfoil to also protect the blade material in the airfoil region from wear caused, for example, by erosion.
- protective coatings such as erosion-protection coatings
- a blade of a turbomachine must be provided with different coatings adjacent to one another, such as, for example, a hardfacing on the tip and an erosion-protection coating on the airfoil.
- care must be taken that none of the coatings, especially the blade tip hardfacing, becomes covered by the other coating, namely the erosion-protection coating, because the covered coating; i.e., for example, the blade tip hardfacing, is otherwise unable to perform its function in the desired manner.
- the blade in the event of a failure of the cutting function of the blade tip hardfacing, the blade can be massively damaged by excessive thermal and mechanical loading.
- the individual coatings must be suitably applied one after another while preventing unwanted mutual coverage of the coatings.
- DE 10 2010 049 398 A1 describes a wear- and oxidation resistant turbine blade including an oxidation-resistant metallic coating, in particular an MCrAlY coating, in which M is a metal, in particular nickel, cobalt, or a combination thereof, and which, in addition, may have a ceramic thermal barrier coating.
- a protective coating of abrasive material and binder material is applied to the blade tip by laser metal forming. Initially, the oxidation-resistant protective coating in the form of the MCrAlY coating is applied to the blade over the entire surface thereof. Then, the MCrAlY coating is mechanically removed in the region of the blade tip, and subsequently the wear-resistant protective coating is applied to the blade tip in the blade tip region by laser metal forming.
- This method is complex and error-prone because the protective coating may be further damaged during removal of the oxidation-resistant protective coating in the region of the blade tip. Moreover, the oxidation-resistant protective coating may become damaged or covered during the laser metal forming process.
- a method for manufacturing a blade for a turbomachine it is proposed in accordance with the present invention to initially apply a blade tip hardfacing to the blade tip and to subsequently position a mask in the region of the blade tip hardfacing, which mask covers the blade tip hardfacing during the subsequent deposition of an erosion-protection coating, so that at least the thickness of the coating deposited in the region of the blade tip hardfacing is reduced to such an extent that it does not have any adverse properties with respect to the functioning of the blade tip hardfacing.
- the mask is positioned at a distance from the blade tip hardfacing, so that, during deposition of the erosion-protection coating, no transition is produced between the erosion-protection coating contacting the blade and the erosion-protection coating formed on the mask.
- This makes it possible to prevent the erosion-protection coating from being damaged during subsequent removal of the mask, and especially from becoming detached outside of the areas of the mask, which would result in unprotected areas on the blade.
- the mask at a distance from the blade tip hardfacing, and thus from the blade as a whole, a smooth transition is obtained in the erosion-protection coating from the airfoil to the blade tip hardfacing.
- the blade tip hardfacing may be at least partially covered by the erosion-protection coating.
- the thickness of the erosion-protection coating in the region of the blade tip hardfacing is significantly reduced, so that the effect of the blade tip hardfacing can fully manifest itself, at least after a short period of use during which the thin erosion-protection coating is removed in the region of the blade tip hardfacing.
- the smooth transition from a thick erosion-protection coating in the region of the airfoil to a thin erosion-protection coating in the region of the blade tip hardfacing ensures that no unprotected areas are present on the blade.
- the thickness of the erosion-protection coating may also tend towards zero.
- the smooth transition and the associated decrease in the thickness of the erosion-protection coating toward the blade tip hardfacing also ensures adhesion of the erosion-protection coating, while at the same time ensuring that the function of the blade tip hardfacing is maintained.
- the relative terms used in connection with the erosion-protection coating refer to a comparison between the respective areas of the erosion-protection coating in the region of the airfoil and in the region of the blade tip, respectively blade tip hardfacing, so that the expression “thick erosion-protection coating in the region of the airfoil” merely indicates that the coating thickness in this region is greater than in the region of the blade tip hardfacing.
- the shape of the mask used for masking the blade tip hardfacing may be selected to replicate, or correspond to, the shape of blade tip, respectively the top surface or top side of the blade tip, respectively of the blade tip hardfacing.
- the replica can be both two-dimensional and three-dimensional.
- a two-dimensional replica may be produced by projecting the surface shape of the blade tip, respectively the blade tip hardfacing, onto a plane.
- the shape and/or dimensioning of the mask may be selected such that the mask partially or completely overhangs the region of the blade tip hardfacing, respectively the blade tip.
- the mask may also be selected to be smaller in order to achieve a larger overlapping region of the blade tip hardfacing and the erosion-protection coating. It is also possible to vary the distance at which the mask is positioned from the blade tip hardfacing, respectively the blade tip, in order to control the thickness of the deposited erosion-protection coating in the region of the blade tip hardfacing and/or the transition of the erosion-protection coating from the airfoil to the blade tip.
- the mask may be supported in the region of the leading edge and/or trailing edge of the blade by suitable holding elements, such as posts. Furthermore, the mask may be manufactured using an additive manufacturing technique in which the mask and/or corresponding holding elements are manufactured layer by layer from powder material, such as by selective laser melting, selective electron beam melting, or the like, in order to enable simple manufacture of a sophisticated structure.
- the mask, and particularly the thickness thereof, may be dimensioned such that the mask has sufficient stability, especially with respect to the effects occurring during the subsequent deposition of the erosion-protection coating, and in particular such that it is not deformed by temperature effects and resulting temperature changes or the like.
- the mask may be dimensioned and/or positioned such that the erosion-protection coating in the region of the blade tip hardfacing has a maximum or average thickness less than half, preferably less than or equal to one-third, in particular less than or equal to 10%, of the average thickness of the remaining erosion-protection coating, in particular the erosion-protection coating in the region of the airfoil.
- the blade tip hardfacing may be applied using any suitable technique, such as by electrodeposition of, for example, a nickel matrix with embedded particles of hard material, such as boron nitride particles, or build-up brazing or deposition of a slurry coating.
- the erosion-protection coating may be deposited by physical vapor deposition (PVD)
- PVD physical vapor deposition
- thermal evaporation, arc evaporation, electron-beam evaporation, sputtering and/or magnetron sputtering it is possible to use, in particular, thermal evaporation, arc evaporation, electron-beam evaporation, sputtering and/or magnetron sputtering.
- FIG. 1 a perspective view of a blade, such as may be used in turbomachines, with a mask for the deposition of an erosion-protection coating;
- FIG. 2 a top view showing the airfoil of the blade of FIG. 1 without the blade root, but with the mask positioned thereabove, and in
- FIG. 3 a portion of a turbine blade after various steps of the inventive method as illustrated in subfigures a) through e).
- FIG. 1 shows, in a purely schematic perspective view, a blade as may be used in a turbomachine, such as, for example, a stationary gas turbine or an aircraft engine.
- Blade 1 has a blade root 2 which may be inserted into a disk which rotates with a shaft of the turbomachine.
- Blade 1 further has an airfoil 3 which is disposed in the flow duct of the turbomachine and which either compresses the fluid flowing through the turbomachine or is driven by the passing fluid.
- the blade tip 4 Located at the radially outer end of blade 1 is the blade tip 4 , which, in order to prevent flow losses, lies as closely adjacent as possible to a surrounding flow duct casing or even cuts into the same.
- blade tip 4 is provided with a blade tip hardfacing (see FIG.
- the blade tip hardfacing may be formed by, for example, a coating containing a nickel matrix 6 with cubic boron nitride particles 7 embedded therein.
- Airfoil 3 also has a coating for protecting blade 1 , this coating being an erosion-protection coating intended to protect the material of blade 1 from erosive wear.
- an erosion-protection coating may be composed of a multi-layer coating which may be formed by a plurality of alternately deposited hard and soft layers, in particular ceramic layers and metal layers.
- FIG. 1 further shows that, for applying an erosion-protection coating that is to be deposited mainly on the airfoil as well as on leading edge 8 and trailing edge 9 of the blade, the region of blade tip 4 is masked by a mask 10 which is held by two posts 11 , 12 located in the region of leading edge 8 and trailing edge 9 .
- mask 10 is positioned at a distance from blade tip 4 . This distance may be selected to be very small.
- Mask 10 is shaped to correspond to the shape of blade tip 4 and, accordingly, also has a curved shape, as shown in the embodiment of FIG. 1 .
- FIG. 2 shows the blade of FIG. 1 in a top view in which only the airfoil is shown by a dashed line and which illustrates the arrangement of mask 10 from above.
- mask 10 corresponds to the shape of blade tip 4 , and in particular of the top surface thereof, in terms of its dimensions and its shape in a plane transverse to the radial direction of the blade 1 .
- mask 10 has the same banana-shaped configuration as the top surface of blade tip 4 .
- mask 10 is configured with a small overhang, making it slightly larger than the top surface of blade tip 4 .
- mask 10 may also be dimensioned slightly smaller than the top surface of blade tip 4 , depending on the desired amount of coverage of blade tip hardfacing 5 with erosion-protection coating 13 , 14 . For this purpose, it is also possible to vary the distance at which mask 10 is positioned from blade tip 4 . In the extreme case, mask 10 may also rest directly on blade tip 4 .
- FIG. 3 illustrates in subfigures a) through e) the various stages during the manufacture of a blade having a blade tip hardfacing on blade tip 4 and an erosion-protection coating on airfoil 3 .
- Subfigure a) of FIG. 3 shows a portion of a blade 1 including airfoil 3 and blade tip 4 .
- a blade tip hardfacing 5 is applied to blade tip 4 , the hardfacing being composed of a nickel matrix 6 and cubic boron nitride particles 7 embedded therein.
- the application of blade tip hardfacing 5 is accomplished, for example, by electrodeposition of nickel matrix 6 in which the cubic boron nitride particles are embedded.
- the blade tip hardfacing may also be accomplished in any other suitable manner.
- mask 10 is positioned so that erosion-protection coating 13 , 14 can be applied (see FIG. 3 c )).
- Erosion-protection coating 13 , 14 can be deposited by physical vapor deposition (PVD) and, more specifically, by depositing the respective sub-layers of the multi-layer erosion-protection coating using various techniques of thermal evaporation or sputter deposition.
- PVD physical vapor deposition
- blade 1 is coated over its entire surface both on airfoil 3 and on blade tip 4 on top of blade tip hardfacing 5 .
- mask 10 reduces the deposition of the erosion-protection coating in the region of blade tip 4 , so that the erosion-protection coating 14 obtained is thinner compared to the thicker erosion-protection coating 13 in the region of airfoil 3 (see FIG. 3 d )).
- the thickness of erosion-protection coating 14 in the region of blade tip 4 is so small that the particles of hard material in the form of boron nitride particles 7 which are embedded in the tip hardfacing project out of erosion-protection coating 14 .
- the thin erosion-protection coating 14 in the region of blade tip 4 , respectively blade tip hardfacing 5 is so thin that it does not impair the cutting effect of the particles of hard material, respectively BN particles 7 .
- erosion-protection coating 13 , 14 Following the deposition of erosion-protection coating 13 , 14 , mask 10 and its supporting posts 11 , 12 are removed, leaving a blade 1 which has a thicker erosion-protection coating 13 in the region of the airfoil and a thinner erosion-protection coating 14 in the region of the blade tip, respectively blade tip hardfacing 5 .
- the relative terms “thicker” and “thinner” each refer to the respective other portion of erosion-protection coating 13 , 14 .
- Blade tip hardfacing 5 is embedded in and surrounded by the adjoining erosion-protection coating 13 without the erosion-protection coating excessively covering the abrasive surface of blade tip hardfacing 5 that is in contact with a sealing material located opposite thereto.
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Abstract
Description
- This claims the benefit of German Patent Application DE102015208783.2, filed May 12, 2015 and hereby incorporated by reference herein.
- The present invention relates to a method for manufacturing a blade for a turbomachine, the blade having a hardfacing on its tip and an erosion-protection coating at least on its airfoil. The present invention also relates to a corresponding blade for a turbomachine such as, for example, a stationary gas turbine or an aircraft engine.
- Turbomachines, such as stationary gas turbines or aircraft engines, include, inter alia, a plurality of blades rotatably mounted on a rotor so as to either compress the fluid flowing through the turbomachine or to be driven into rotation by the fluid.
- In order to minimize flow losses between the rotating blades and a surrounding flow duct boundary, the gap between the blade tips at the radial ends of the blades and the flow duct boundary must be as small as possible in order that as little fluid as possible may flow through the gap between the flow duct boundary and the blades.
- For this reason, in known turbomachines, so-called labyrinth seals are provided for sealing between the blade tips and the flow duct boundary. In such labyrinth seals, the blade tips move in a groove which is formed by the blade tips cutting into a sealing material on the flow duct boundary during operation of the turbomachine. In this connection, it is also known to provide the blade tips with so-called blade tip hardfacings. Blade tip hardfacings have particles of hard material embedded in a metal matrix, which are intended to cut the groove for the labyrinth seal into the opposite sealing material of the flow duct boundary and to protect the blade tip from wear.
- Moreover, blades of turbomachines also include protective coatings, such as erosion-protection coatings, on the airfoil to also protect the blade material in the airfoil region from wear caused, for example, by erosion.
- Accordingly, a blade of a turbomachine must be provided with different coatings adjacent to one another, such as, for example, a hardfacing on the tip and an erosion-protection coating on the airfoil. However, care must be taken that none of the coatings, especially the blade tip hardfacing, becomes covered by the other coating, namely the erosion-protection coating, because the covered coating; i.e., for example, the blade tip hardfacing, is otherwise unable to perform its function in the desired manner. In fact, in the event of a failure of the cutting function of the blade tip hardfacing, the blade can be massively damaged by excessive thermal and mechanical loading.
- Accordingly, the individual coatings must be suitably applied one after another while preventing unwanted mutual coverage of the coatings.
- DE 10 2010 049 398 A1 describes a wear- and oxidation resistant turbine blade including an oxidation-resistant metallic coating, in particular an MCrAlY coating, in which M is a metal, in particular nickel, cobalt, or a combination thereof, and which, in addition, may have a ceramic thermal barrier coating. In addition to this oxidation-resistant protective coating, a protective coating of abrasive material and binder material is applied to the blade tip by laser metal forming. Initially, the oxidation-resistant protective coating in the form of the MCrAlY coating is applied to the blade over the entire surface thereof. Then, the MCrAlY coating is mechanically removed in the region of the blade tip, and subsequently the wear-resistant protective coating is applied to the blade tip in the blade tip region by laser metal forming.
- This method is complex and error-prone because the protective coating may be further damaged during removal of the oxidation-resistant protective coating in the region of the blade tip. Moreover, the oxidation-resistant protective coating may become damaged or covered during the laser metal forming process.
- It is an object of the present invention to provide a method for manufacturing a blade for a turbomachine, where at least two different coatings can be provided on the blade in a simple and reliable manner without mutual impairment of the function and quality of the individual coatings. More specifically, it is an object to apply a blade tip hardfacing and an erosion-protection coating adjacent to each other to a blade of a turbomachine in an efficient manner while preventing the erosion-protection coating in particular from covering the blade tip hardfacing and thus impairing the functioning of the blade tip hardfacing. Another object of the present invention is to provide a corresponding blade for a turbomachine such as, for example, a stationary gas turbine or an aircraft engine.
- In a method for manufacturing a blade for a turbomachine, it is proposed in accordance with the present invention to initially apply a blade tip hardfacing to the blade tip and to subsequently position a mask in the region of the blade tip hardfacing, which mask covers the blade tip hardfacing during the subsequent deposition of an erosion-protection coating, so that at least the thickness of the coating deposited in the region of the blade tip hardfacing is reduced to such an extent that it does not have any adverse properties with respect to the functioning of the blade tip hardfacing.
- Preferably, the mask is positioned at a distance from the blade tip hardfacing, so that, during deposition of the erosion-protection coating, no transition is produced between the erosion-protection coating contacting the blade and the erosion-protection coating formed on the mask. This makes it possible to prevent the erosion-protection coating from being damaged during subsequent removal of the mask, and especially from becoming detached outside of the areas of the mask, which would result in unprotected areas on the blade. In contrast, by positioning the mask at a distance from the blade tip hardfacing, and thus from the blade as a whole, a smooth transition is obtained in the erosion-protection coating from the airfoil to the blade tip hardfacing. In the process, the blade tip hardfacing may be at least partially covered by the erosion-protection coating. However, due to the masking of the blade tip hardfacing during the deposition of the erosion-protection coating, the thickness of the erosion-protection coating in the region of the blade tip hardfacing is significantly reduced, so that the effect of the blade tip hardfacing can fully manifest itself, at least after a short period of use during which the thin erosion-protection coating is removed in the region of the blade tip hardfacing. Thus, the smooth transition from a thick erosion-protection coating in the region of the airfoil to a thin erosion-protection coating in the region of the blade tip hardfacing ensures that no unprotected areas are present on the blade. In the region of the blade tip hardfacing, the thickness of the erosion-protection coating may also tend towards zero. In addition, the smooth transition and the associated decrease in the thickness of the erosion-protection coating toward the blade tip hardfacing also ensures adhesion of the erosion-protection coating, while at the same time ensuring that the function of the blade tip hardfacing is maintained.
- The relative terms used in connection with the erosion-protection coating, such as “thin,” “thick,” “thinner,” and “thicker” in each instance refer to a comparison between the respective areas of the erosion-protection coating in the region of the airfoil and in the region of the blade tip, respectively blade tip hardfacing, so that the expression “thick erosion-protection coating in the region of the airfoil” merely indicates that the coating thickness in this region is greater than in the region of the blade tip hardfacing.
- The shape of the mask used for masking the blade tip hardfacing may be selected to replicate, or correspond to, the shape of blade tip, respectively the top surface or top side of the blade tip, respectively of the blade tip hardfacing. The replica can be both two-dimensional and three-dimensional. A two-dimensional replica may be produced by projecting the surface shape of the blade tip, respectively the blade tip hardfacing, onto a plane.
- The shape and/or dimensioning of the mask may be selected such that the mask partially or completely overhangs the region of the blade tip hardfacing, respectively the blade tip. The mask may also be selected to be smaller in order to achieve a larger overlapping region of the blade tip hardfacing and the erosion-protection coating. It is also possible to vary the distance at which the mask is positioned from the blade tip hardfacing, respectively the blade tip, in order to control the thickness of the deposited erosion-protection coating in the region of the blade tip hardfacing and/or the transition of the erosion-protection coating from the airfoil to the blade tip.
- The mask may be supported in the region of the leading edge and/or trailing edge of the blade by suitable holding elements, such as posts. Furthermore, the mask may be manufactured using an additive manufacturing technique in which the mask and/or corresponding holding elements are manufactured layer by layer from powder material, such as by selective laser melting, selective electron beam melting, or the like, in order to enable simple manufacture of a sophisticated structure.
- The mask, and particularly the thickness thereof, may be dimensioned such that the mask has sufficient stability, especially with respect to the effects occurring during the subsequent deposition of the erosion-protection coating, and in particular such that it is not deformed by temperature effects and resulting temperature changes or the like.
- The mask may be dimensioned and/or positioned such that the erosion-protection coating in the region of the blade tip hardfacing has a maximum or average thickness less than half, preferably less than or equal to one-third, in particular less than or equal to 10%, of the average thickness of the remaining erosion-protection coating, in particular the erosion-protection coating in the region of the airfoil.
- The blade tip hardfacing may be applied using any suitable technique, such as by electrodeposition of, for example, a nickel matrix with embedded particles of hard material, such as boron nitride particles, or build-up brazing or deposition of a slurry coating.
- The erosion-protection coating may be deposited by physical vapor deposition (PVD) In this connection, it is possible to use, in particular, thermal evaporation, arc evaporation, electron-beam evaporation, sputtering and/or magnetron sputtering.
- The accompanying drawings show purely schematically in
-
FIG. 1 : a perspective view of a blade, such as may be used in turbomachines, with a mask for the deposition of an erosion-protection coating; -
FIG. 2 : a top view showing the airfoil of the blade ofFIG. 1 without the blade root, but with the mask positioned thereabove, and in -
FIG. 3 : a portion of a turbine blade after various steps of the inventive method as illustrated in subfigures a) through e). - Other advantages, characteristics and features of the present invention will become apparent from the following detailed description of exemplary embodiments. However, the present invention is not limited to such exemplary embodiments.
-
FIG. 1 shows, in a purely schematic perspective view, a blade as may be used in a turbomachine, such as, for example, a stationary gas turbine or an aircraft engine.Blade 1 has ablade root 2 which may be inserted into a disk which rotates with a shaft of the turbomachine.Blade 1 further has anairfoil 3 which is disposed in the flow duct of the turbomachine and which either compresses the fluid flowing through the turbomachine or is driven by the passing fluid. Located at the radially outer end ofblade 1 is theblade tip 4, which, in order to prevent flow losses, lies as closely adjacent as possible to a surrounding flow duct casing or even cuts into the same. To this end,blade tip 4 is provided with a blade tip hardfacing (seeFIG. 3 ) which also has a cutting function, allowingblade tip 4 to cut into a surrounding flow duct casing, respectively into sealing material attached thereto. The blade tip hardfacing may be formed by, for example, a coating containing anickel matrix 6 with cubicboron nitride particles 7 embedded therein. - Airfoil 3 also has a coating for protecting
blade 1, this coating being an erosion-protection coating intended to protect the material ofblade 1 from erosive wear. Such an erosion-protection coating may be composed of a multi-layer coating which may be formed by a plurality of alternately deposited hard and soft layers, in particular ceramic layers and metal layers. -
FIG. 1 further shows that, for applying an erosion-protection coating that is to be deposited mainly on the airfoil as well as on leadingedge 8 and trailing edge 9 of the blade, the region ofblade tip 4 is masked by amask 10 which is held by twoposts edge 8 and trailing edge 9. - As shown in the schematic view of
FIG. 1 ,mask 10 is positioned at a distance fromblade tip 4. This distance may be selected to be very small. -
Mask 10 is shaped to correspond to the shape ofblade tip 4 and, accordingly, also has a curved shape, as shown in the embodiment ofFIG. 1 . -
FIG. 2 shows the blade ofFIG. 1 in a top view in which only the airfoil is shown by a dashed line and which illustrates the arrangement ofmask 10 from above. It is clear thatmask 10 corresponds to the shape ofblade tip 4, and in particular of the top surface thereof, in terms of its dimensions and its shape in a plane transverse to the radial direction of theblade 1. As can clearly be seen inFIG. 2 ,mask 10 has the same banana-shaped configuration as the top surface ofblade tip 4. In the view ofFIG. 2 ,mask 10 is configured with a small overhang, making it slightly larger than the top surface ofblade tip 4. However, instead of being oversized,mask 10 may also be dimensioned slightly smaller than the top surface ofblade tip 4, depending on the desired amount of coverage ofblade tip hardfacing 5 with erosion-protection coating blade tip 4. In the extreme case,mask 10 may also rest directly onblade tip 4. -
FIG. 3 illustrates in subfigures a) through e) the various stages during the manufacture of a blade having a blade tip hardfacing onblade tip 4 and an erosion-protection coating onairfoil 3. Subfigure a) ofFIG. 3 shows a portion of ablade 1 includingairfoil 3 andblade tip 4. - As shown in
FIG. 3b ), ablade tip hardfacing 5 is applied toblade tip 4, the hardfacing being composed of anickel matrix 6 and cubicboron nitride particles 7 embedded therein. The application ofblade tip hardfacing 5 is accomplished, for example, by electrodeposition ofnickel matrix 6 in which the cubic boron nitride particles are embedded. However, the blade tip hardfacing may also be accomplished in any other suitable manner. - After
blade tip hardfacing 5 is completed,mask 10 is positioned so that erosion-protection coating FIG. 3c )). - Erosion-
protection coating blade 1 is coated over its entire surface both onairfoil 3 and onblade tip 4 on top ofblade tip hardfacing 5. However,mask 10 reduces the deposition of the erosion-protection coating in the region ofblade tip 4, so that the erosion-protection coating 14 obtained is thinner compared to the thicker erosion-protection coating 13 in the region of airfoil 3 (seeFIG. 3d )). In particular, the thickness of erosion-protection coating 14 in the region ofblade tip 4 is so small that the particles of hard material in the form ofboron nitride particles 7 which are embedded in the tip hardfacing project out of erosion-protection coating 14. In any case, the thin erosion-protection coating 14 in the region ofblade tip 4, respectivelyblade tip hardfacing 5, is so thin that it does not impair the cutting effect of the particles of hard material, respectivelyBN particles 7. - Following the deposition of erosion-
protection coating mask 10 and its supportingposts blade 1 which has a thicker erosion-protection coating 13 in the region of the airfoil and a thinner erosion-protection coating 14 in the region of the blade tip, respectivelyblade tip hardfacing 5. In this connection, the relative terms “thicker” and “thinner” each refer to the respective other portion of erosion-protection coating -
Blade tip hardfacing 5 is embedded in and surrounded by the adjoining erosion-protection coating 13 without the erosion-protection coating excessively covering the abrasive surface ofblade tip hardfacing 5 that is in contact with a sealing material located opposite thereto. - Although the present invention has been described in detail with reference to the above exemplary embodiments, it is not limited to such exemplary embodiments. Rather, various modifications may be made by omitting individual features or by combining features in different ways, without departing from the protective scope of the appended claims.
-
- 1 blade
- 2 blade root
- 3 airfoil
- 4 blade tip
- 5 blade tip hardfacing
- 6 Ni matrix
- 7 BN particle
- 8 leading edge
- 9 trailing edge
- 10 mask
- 11,13 post
- 13 erosion-protection coating on the airfoil
- 14 erosion-protection coating in the region of the blade tip
Claims (21)
Applications Claiming Priority (4)
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DE102015208783.2A DE102015208783A1 (en) | 2015-05-12 | 2015-05-12 | Covering method for producing a combination of blade tip armor and erosion protection layer |
EPDE102015208783.2 | 2015-05-12 | ||
DE102015208783.2 | 2015-05-12 | ||
DE102015208783 | 2015-05-12 |
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US10415400B2 US10415400B2 (en) | 2019-09-17 |
US20190301291A9 true US20190301291A9 (en) | 2019-10-03 |
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US15/152,671 Active 2037-07-07 US10415400B2 (en) | 2015-05-12 | 2016-05-12 | Masking method for producing a combination of blade tip hardfacing and erosion-protection coating |
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US11795295B2 (en) * | 2017-11-06 | 2023-10-24 | Rtx Corporation | Wear resistant coating, method of manufacture thereof and articles comprising the same |
US20190194799A1 (en) | 2017-12-22 | 2019-06-27 | United Technologies Corporation | Line-of-sight coating fixture and apparatus |
RU2718877C2 (en) * | 2018-02-26 | 2020-04-15 | Федеральное государственное бюджетное образовательное учреждение высшего образования "Ухтинский государственный технический университет" | Method of applying a functionally oriented wear-resistant coating on a gas turbine blade |
DE102019213545A1 (en) | 2019-09-05 | 2021-03-11 | Robert Bosch Gmbh | Housing of an electric drive |
US11299993B2 (en) * | 2019-10-28 | 2022-04-12 | Honeywell International Inc. | Rotor assembly for in-machine grinding of shroud member and methods of using the same |
US11286794B2 (en) * | 2019-12-17 | 2022-03-29 | Rolls-Royce North American Technologies, Inc. | Erosion-resistant coating with patterned leading edge |
DE102020206202A1 (en) | 2020-05-18 | 2021-11-18 | MTU Aero Engines AG | Blade for a turbomachine with blade tip armor and anti-erosion layer and method for producing the same |
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US4610698A (en) * | 1984-06-25 | 1986-09-09 | United Technologies Corporation | Abrasive surface coating process for superalloys |
US4863538A (en) * | 1986-10-17 | 1989-09-05 | Board Of Regents, The University Of Texas System | Method and apparatus for producing parts by selective sintering |
US5603603A (en) * | 1993-12-08 | 1997-02-18 | United Technologies Corporation | Abrasive blade tip |
US5565035A (en) * | 1996-03-14 | 1996-10-15 | United Technologies Corporation | Fixture for masking a portion of an airfoil during application of a coating |
US5704759A (en) * | 1996-10-21 | 1998-01-06 | Alliedsignal Inc. | Abrasive tip/abradable shroud system and method for gas turbine compressor clearance control |
US5952110A (en) * | 1996-12-24 | 1999-09-14 | General Electric Company | Abrasive ceramic matrix turbine blade tip and method for forming |
US5803971A (en) * | 1997-01-13 | 1998-09-08 | United Technologies Corporation | Modular coating fixture |
US6224337B1 (en) * | 1999-09-17 | 2001-05-01 | General Electric Company | Thermal barrier coated squealer tip cavity |
US6434876B1 (en) * | 2000-09-26 | 2002-08-20 | General Electric Company | Method of applying a particle-embedded coating to a substrate |
JP2003148103A (en) * | 2001-11-09 | 2003-05-21 | Mitsubishi Heavy Ind Ltd | Turbine and its manufacturing method |
EP1352988A1 (en) * | 2002-04-10 | 2003-10-15 | Siemens Aktiengesellschaft | Method for coating an object |
US7473072B2 (en) * | 2005-02-01 | 2009-01-06 | Honeywell International Inc. | Turbine blade tip and shroud clearance control coating system |
US7510370B2 (en) * | 2005-02-01 | 2009-03-31 | Honeywell International Inc. | Turbine blade tip and shroud clearance control coating system |
DE102005060712A1 (en) * | 2005-12-20 | 2007-06-21 | Mtu Aero Engines Gmbh | Production of gas turbine blade tip casing involving positioning of mask in region of blade tip and thermal plasma spraying of base material on tip, involves introduction of the powdered base material into the plasma jet |
US7980820B2 (en) * | 2007-08-27 | 2011-07-19 | United Technologies Corporation | Turbine engine blade cooling |
CA2719273C (en) | 2009-11-02 | 2017-03-28 | Alstom Technology Ltd. | Wear-resistant and oxidation-resistant turbine blade |
DE102010049399A1 (en) * | 2009-11-02 | 2011-05-26 | Alstom Technology Ltd. | Abrasive monocrystalline turbine blade |
US20110116912A1 (en) * | 2009-11-13 | 2011-05-19 | Mccall Thomas | Zoned discontinuous coating for high pressure turbine component |
US9145775B2 (en) * | 2012-03-02 | 2015-09-29 | United Technologies Corporation | Tapered thermal coating for airfoil |
EP2929065A4 (en) * | 2013-02-12 | 2016-06-01 | United Technologies Corp | Metallic coating fixed stator tip treatment |
US10151245B2 (en) * | 2013-03-06 | 2018-12-11 | United Technologies Corporation | Fixturing for thermal spray coating of gas turbine components |
DE102013224568A1 (en) * | 2013-11-29 | 2015-06-03 | Siemens Aktiengesellschaft | Method for producing a chamfer, component with chamfer and device |
DE102013224566A1 (en) * | 2013-11-29 | 2015-06-03 | Siemens Aktiengesellschaft | Tungsten alloy masking mask and a tungsten alloy |
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EP3093372B1 (en) | 2020-04-29 |
EP3093372A2 (en) | 2016-11-16 |
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