WO2005068784A1 - Turbomaschinenschaufel und verfahren zur herstellung einer schaufelspitzenpanzerung an turbomaschinenschaufeln - Google Patents
Turbomaschinenschaufel und verfahren zur herstellung einer schaufelspitzenpanzerung an turbomaschinenschaufeln Download PDFInfo
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- WO2005068784A1 WO2005068784A1 PCT/DE2004/002795 DE2004002795W WO2005068784A1 WO 2005068784 A1 WO2005068784 A1 WO 2005068784A1 DE 2004002795 W DE2004002795 W DE 2004002795W WO 2005068784 A1 WO2005068784 A1 WO 2005068784A1
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- blade tip
- molybdenum
- laser
- blade
- intermediate layer
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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
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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
- B23K26/00—Working by laser beam, e.g. welding, cutting or boring
- B23K26/20—Bonding
- B23K26/32—Bonding taking account of the properties of the material involved
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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
- B23K26/00—Working by laser beam, e.g. welding, cutting or boring
- B23K26/34—Laser welding for purposes other than joining
- B23K26/342—Build-up welding
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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
- B23K35/00—Rods, electrodes, materials, or media, for use in soldering, welding, or cutting
- B23K35/001—Interlayers, transition pieces for metallurgical bonding of workpieces
- B23K35/004—Interlayers, transition pieces for metallurgical bonding of workpieces at least one of the workpieces being of a metal of the iron group
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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
- B23K35/00—Rods, electrodes, materials, or media, for use in soldering, welding, or cutting
- B23K35/001—Interlayers, transition pieces for metallurgical bonding of workpieces
- B23K35/005—Interlayers, transition pieces for metallurgical bonding of workpieces at least one of the workpieces being of a refractory metal
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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
- B23K35/00—Rods, electrodes, materials, or media, for use in soldering, welding, or cutting
- B23K35/22—Rods, electrodes, materials, or media, for use in soldering, welding, or cutting characterised by the composition or nature of the material
- B23K35/24—Selection of soldering or welding materials proper
- B23K35/32—Selection of soldering or welding materials proper with the principal constituent melting at more than 1550 degrees C
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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
- B23K35/00—Rods, electrodes, materials, or media, for use in soldering, welding, or cutting
- B23K35/22—Rods, electrodes, materials, or media, for use in soldering, welding, or cutting characterised by the composition or nature of the material
- B23K35/36—Selection of non-metallic compositions, e.g. coatings, fluxes; Selection of soldering or welding materials, conjoint with selection of non-metallic compositions, both selections being of interest
- B23K35/3601—Selection of non-metallic compositions, e.g. coatings, fluxes; Selection of soldering or welding materials, conjoint with selection of non-metallic compositions, both selections being of interest with inorganic compounds as principal constituents
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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
- B23K35/00—Rods, electrodes, materials, or media, for use in soldering, welding, or cutting
- B23K35/22—Rods, electrodes, materials, or media, for use in soldering, welding, or cutting characterised by the composition or nature of the material
- B23K35/36—Selection of non-metallic compositions, e.g. coatings, fluxes; Selection of soldering or welding materials, conjoint with selection of non-metallic compositions, both selections being of interest
- B23K35/3601—Selection of non-metallic compositions, e.g. coatings, fluxes; Selection of soldering or welding materials, conjoint with selection of non-metallic compositions, both selections being of interest with inorganic compounds as principal constituents
- B23K35/3608—Titania or titanates
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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
- B23K35/00—Rods, electrodes, materials, or media, for use in soldering, welding, or cutting
- B23K35/22—Rods, electrodes, materials, or media, for use in soldering, welding, or cutting characterised by the composition or nature of the material
- B23K35/36—Selection of non-metallic compositions, e.g. coatings, fluxes; Selection of soldering or welding materials, conjoint with selection of non-metallic compositions, both selections being of interest
- B23K35/3601—Selection of non-metallic compositions, e.g. coatings, fluxes; Selection of soldering or welding materials, conjoint with selection of non-metallic compositions, both selections being of interest with inorganic compounds as principal constituents
- B23K35/361—Alumina or aluminates
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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
- C23C24/00—Coating starting from inorganic powder
- C23C24/08—Coating starting from inorganic powder by application of heat or pressure and heat
- C23C24/10—Coating starting from inorganic powder by application of heat or pressure and heat with intermediate formation of a liquid phase in the layer
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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
- C23C26/00—Coating not provided for in groups C23C2/00 - C23C24/00
- C23C26/02—Coating not provided for in groups C23C2/00 - C23C24/00 applying molten material to the substrate
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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
- C23C28/322—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer only coatings of metal elements only
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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
- 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
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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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- 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
- B23K2103/08—Non-ferrous metals or alloys
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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
- B23K2103/18—Dissimilar materials
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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
- B23K2103/18—Dissimilar materials
- B23K2103/26—Alloys of Nickel and Cobalt and Chromium
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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
- B23K2103/50—Inorganic material, e.g. metals, not provided for in B23K2103/02 – B23K2103/26
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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
- B23K2103/50—Inorganic material, e.g. metals, not provided for in B23K2103/02 – B23K2103/26
- B23K2103/52—Ceramics
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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
- F05D2230/20—Manufacture essentially without removing material
- F05D2230/23—Manufacture essentially without removing material by permanently joining parts together
- F05D2230/232—Manufacture essentially without removing material by permanently joining parts together by welding
- F05D2230/234—Laser welding
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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
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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
- F05D2230/90—Coating; Surface treatment
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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
- F05D2300/13—Refractory metals, i.e. Ti, V, Cr, Zr, Nb, Mo, Hf, Ta, W
- F05D2300/131—Molybdenum
Definitions
- the invention relates to a turbomachine blade, in particular a gas turbine blade, according to the preamble of claim 1. Furthermore, the invention relates to a method for producing blade tip armor on turbomachine blades, in particular on gas turbine blades, according to the preamble of patent claim 6.
- Turbomachines such as aircraft engines, typically comprise several stages with rotating blades and fixed guide vanes, the rotor blades rotating together with a rotor, and the rotor blades and guide vanes being enclosed by a fixed housing of the gas turbine.
- This also includes the so-called sealing systems in aircraft engines. Maintaining a minimal gap between the rotating blades and the fixed housing of a high-pressure compressor and between the fixed guide vanes and a rotating rotor shaft is particularly problematic in aircraft engines.
- high-pressure compressors the highest temperatures and temperature gradients occur, which makes it difficult to maintain gaps.
- shrouds such as those used in turbines are dispensed with in the case of compressor rotor blades and compressor guide vanes.
- the guide vanes and the rotor blades have no shroud in the compressor.
- the ends or tips of the rotating blades are therefore exposed to a direct frictional contact with the housing when they are rubbed into the fixed housing.
- the free ends or tips of the guide vanes are exposed to direct frictional contact with the rotor shaft. Such a rubbing of the blade tips is caused by manufacturing tolerances when a minimal radial gap is set.
- the present invention is based on the problem of creating a novel turbomachine blade and a novel method for producing blade tip armor on turbomachine blades.
- an adhesion-promoting intermediate layer made of molybdenum is arranged between the blade tip and the blade tip armor made of a ceramic covering.
- the intermediate layer made of molybdenum and the blade tip armor made of the ceramic covering are preferably applied by laser powder cladding.
- Laser powder cladding is also referred to as laser beam cladding or laser beam generation.
- Fig. 1 is a schematic representation of a gas turbine blades in perspective
- FIG. 2 shows a schematic cross section through a gas turbine blade according to the invention with a blade tip armor
- Fig. 3 is a schematic representation to illustrate the invention
- Fig. 4 is a schematic representation to illustrate an alternative of the inventive method.
- FIG. 1 shows, as a turbomachine blade, a moving blade 10 of a gas turbine, namely an aircraft engine, the rotating blade 10 having an airfoil 11 and a blade root 12 adjoining the airfoil 11.
- a blade tip 13 of the blade 1 1 is provided with a blade tip armor 14 made of a ceramic covering.
- an adhesion-promoting intermediate layer 15 made of molybdenum is arranged between the blade tip 13 of the moving blade 10 and the blade tip armor 14 made of the ceramic covering.
- 2 shows a partial cross section through the area of the metallic blade tip 13, the ceramic blade tip armor 14 and the intermediate layer 15 made of molybdenum arranged between the blade tip 13 and the blade tip armor 14. 2 is only a schematic illustration. The thickness ratios of the layer thicknesses shown in FIG. 2 of the intermediate layer 15 and blade tip armor 14 do not correspond to the actual circumstances.
- the rotor blade 10 and thus the airfoil 11 and the blade tip 13 are made from a titanium-based alloy.
- the intermediate layer 15 made of molybdenum is applied to such a blade tip 13 made of a titanium-based alloy, and a blade tip armor 14 made of an Al 2 O 3 -TiO 2 ceramic material is then applied to the intermediate layer 15.
- the Combining a blade 10 made of a titanium-based alloy with such an aluminum oxide ceramic is particularly advantageous.
- the blade 10 and the blade 1 1 and the blade tip 13 of a nickel-based alloy or Rail ⁇ is made sisleg réelle.
- the intermediate layer 15 made of molybdenum is then in turn applied to such a blade tip 13 made of a nickel-based alloy or an iron-based alloy, and a blade tip armor 14 made of a Zr0 2 -Y 2 0 3 ceramic material is applied to the intermediate layer 15.
- the combination of a blade made of a nickel-based alloy or an iron-based alloy with a zirconium oxide ceramic is also particularly advantageous.
- a common feature of the above-described turbomachine blades or rotor blades 10 of a gas turbine is that a blade tip armor 14 made of oxide ceramic is applied to a metallic blade, an intermediate layer 15 made of molybdenum being applied between the metallic blade tip 13 and the blade tip armor 14 made of oxide oxide.
- the intermediate layer 15 made of molybdenum improves the adhesion of the oxide ceramic to the tip of the blade.
- the blade tip armor 15 made of oxide ceramic is therefore not applied directly to the blade tip 13, but rather with the intermediate layer 15 made of molybdenum.
- the intermediate layer 15 made of molybdenum and the blade tip armor 14 made of the ceramic material to the blade tip 13 or the intermediate layer 15 by laser powder deposition welding.
- the details of the method according to the invention for producing a blade tip armor on turbomachine blades are discussed in greater detail below.
- a C0 2 laser is used for laser powder build-up welding of the intermediate layer 15 made of molybdenum and the blade tip armor 14 made of the ceramic material used.
- a C0 2 laser with a nominal output of 6000 W and a wavelength of 10.6 ⁇ m is preferably used.
- the adhesion-promoting intermediate layer 15 made of molybdenum is first applied to the metallic blade tip 13 to be armored by laser powder deposition welding in a first step of the method according to the invention.
- This adhesion-promoting intermediate layer 15 made of molybdenum is applied for blades made of a titanium-based alloy or nickel-based alloy or iron-based alloy using the same process parameters.
- the laser is operated with a laser beam intensity of 1 * 10 to 3 * 10 5 W / cm 3 , in particular with a laser beam intensity of 1.6 * 10 5 to 2 * 10 5 W / cm 3 .
- the feed rate of the laser for applying the intermediate layer 15 made of molybdenum is between 1000 and 1800 mm / min, in particular in the order of 1200 to 1600 mm / min.
- a feed rate of the CO 2 laser when applying the molybdenum intermediate layer of 1400 mm / min is particularly preferred.
- the molybdenum material or the molybdenum powder is preferably conveyed in the direction of the laser with a powder amount of 3 to 6 g / min, in particular with a powder amount of 4 to 5 g / min.
- a molybdenum output of 4.5 g / min is particularly preferred.
- Argon is used as the conveying gas to convey the molybdenum towards the laser.
- the blade tip armor 14 made of the ceramic coating namely an oxide ceramic
- a molybdenum intermediate layer 15 applied using the above process parameters.
- a blade tip 13 which consists of a titanium-based alloy
- an Al 2 0 3 -Ti0 2 ceramic material is used
- a Zr0 2 - Y 2 0 3 ceramic material is applied.
- the CO 2 laser is used with a laser beam intensity of 2 * 10 4 to 4 * 10 4 , preferably with a laser beam intensity of 2.9 * 10 4 to 3.2 * 10 4 W / cm 3 operated.
- the feed rate of the laser during laser powder build-up welding of the ceramic layer is between 50 to 400 mm / min, preferably between 100 and 350 mm / min.
- the ceramic powder is conveyed towards the laser with an appropriate delivery rate.
- the delivery rate is 3 to 5 g / min
- the Zr0 2 N 2 ⁇ 3 ceramic powder the powder amount is 3 to 9 g / min.
- Helium is used as the conveying gas to convey the ceramic powder.
- an intermediate layer of molybdenum to the blade tip to be armored and only then to coat the blade tip armor from the oxide ceramic.
- Both the molybdenum intermediate layer and the blade tip armor made of oxide ceramics are applied using laser powder cladding.
- the adhesion of the applied layers, in particular the applied oxide ceramic is based on adhesive mechanisms such as chemical interaction (diffusion) and chemical adsorption.
- the existence of the molybdenum intermediate layer favors the formation of a diffusion zone between the base material, i.e. the titanium-based alloy or nickel-based alloy or iron-based alloy, the blade to be armored and the ceramic material of the actual blade tip armor.
- the laser powder deposition welding of the molybdenum intermediate layer 15 and the blade tip armor 1 made of the ceramic material takes place either in the sense of FIG. 3 in the variant of a coaxial powder supply of the material currently to be applied or in the sense of FIG. 4 in the variant of a lateral powder supply of the material to be applied.
- 3 and 4 each show the application of the molybdenum intermediate layer 15 on the blade tip 13 to be armored, a laser beam 17 generated by a laser source 16 being focused in each case onto the surface to be coated.
- a separately configured feed device 18 is used, with the coaxial feed according to FIG. 3, the feed device 18 is integrated into the laser arrangement 16. It is particularly preferred to apply the intermediate molybdenum layer and the oxide ceramic after the so-called laser powder deposition welding in mold. Details of this process are familiar to the expert addressed here.
- a non-porous and low-crack blade tip armor with good adhesion to the metallic base material of the blade to be armored can be provided.
- the adhesive strength of the blade tip armor to the metallic base material is optimized due to the use of a molybdenum intermediate layer.
- the structure of the blade tip armor made of oxide ceramics is very fine, the thermal insulation is extremely good.
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- Materials Engineering (AREA)
- Optics & Photonics (AREA)
- Chemical Kinetics & Catalysis (AREA)
- Physics & Mathematics (AREA)
- Metallurgy (AREA)
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Abstract
Description
Claims
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE102004001722A DE102004001722A1 (de) | 2004-01-13 | 2004-01-13 | Turbomaschinenschaufel und Verfahren zur Herstellung einer Schaufelspitzenpanzerung an Turbomaschinenschaufeln |
DE102004001722.0 | 2004-01-13 |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2005068784A1 true WO2005068784A1 (de) | 2005-07-28 |
Family
ID=34716489
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/DE2004/002795 WO2005068784A1 (de) | 2004-01-13 | 2004-12-22 | Turbomaschinenschaufel und verfahren zur herstellung einer schaufelspitzenpanzerung an turbomaschinenschaufeln |
Country Status (2)
Country | Link |
---|---|
DE (1) | DE102004001722A1 (de) |
WO (1) | WO2005068784A1 (de) |
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2006094481A1 (de) * | 2005-03-10 | 2006-09-14 | Mtu Aero Engines Gmbh | Bauteil, insbesondere gasturbinenbauteil |
EP3061850A1 (de) * | 2015-02-25 | 2016-08-31 | United Technologies Corporation | Hartphasenlose metallbeschichtung für verdichterschaufelspitze |
CN114150256A (zh) * | 2021-12-14 | 2022-03-08 | 中国航发南方工业有限公司 | 航空发动机小尺寸涡轮工作叶片的耐高温热腐蚀涂层 |
Families Citing this family (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2893268B1 (fr) * | 2005-11-15 | 2008-02-08 | Snecma Sa | Procede de realisation d'un rebord situe a l'extremite libre d'une aube, aube obtenue par ce procede et turbomachine equipee de cette aube |
EP1865258A1 (de) * | 2006-06-06 | 2007-12-12 | Siemens Aktiengesellschaft | Gepanzerte Maschinenkomponente und Gasturbine |
EP2068082A1 (de) * | 2007-12-04 | 2009-06-10 | Siemens Aktiengesellschaft | Maschinenkomponente und Gasturbine |
DE102009032564A1 (de) * | 2009-07-10 | 2011-01-13 | Mtu Aero Engines Gmbh | Verfahren zur Panzerung von Bauteilen aus einem TiAI-Basiswerkstoff, sowie entsprechende Bauteile |
DE102009050563A1 (de) * | 2009-10-23 | 2011-01-27 | Mtu Aero Engines Gmbh | Nickelbasislegierung und Verfahren zur generativen Herstellung und/oder Reparatur von Bauteilen |
US20170145554A1 (en) * | 2014-06-26 | 2017-05-25 | Shell Oil Company | Coating method and coated substrate |
DE102017129793A1 (de) * | 2017-12-13 | 2019-06-13 | BENTELER Lightweight Protection GmbH & Co. KG | Panzerungsbauteil und Verfahren zur Herstellung eines Panzerungsbauteils |
Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP0305113A2 (de) * | 1987-08-27 | 1989-03-01 | Imi Titanium Limited | Rotierende oder bewegende metallische Komponenten und Verfahren zur Herstellung solcher Komponenten |
US5554837A (en) * | 1993-09-03 | 1996-09-10 | Chromalloy Gas Turbine Corporation | Interactive laser welding at elevated temperatures of superalloy articles |
EP0919699A2 (de) * | 1997-11-26 | 1999-06-02 | United Technologies Corporation | Schleifmittelbeschichtung aus stengelförmigem Zirkonoxid für eine Gasturbinendichtung |
DE19920567A1 (de) * | 1999-05-03 | 2000-11-16 | Fraunhofer Ges Forschung | Bauteil aus Titan oder einer Titanlegierung und Verfahren zu seiner Beschichtung |
-
2004
- 2004-01-13 DE DE102004001722A patent/DE102004001722A1/de not_active Withdrawn
- 2004-12-22 WO PCT/DE2004/002795 patent/WO2005068784A1/de active Application Filing
Patent Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP0305113A2 (de) * | 1987-08-27 | 1989-03-01 | Imi Titanium Limited | Rotierende oder bewegende metallische Komponenten und Verfahren zur Herstellung solcher Komponenten |
US5554837A (en) * | 1993-09-03 | 1996-09-10 | Chromalloy Gas Turbine Corporation | Interactive laser welding at elevated temperatures of superalloy articles |
EP0919699A2 (de) * | 1997-11-26 | 1999-06-02 | United Technologies Corporation | Schleifmittelbeschichtung aus stengelförmigem Zirkonoxid für eine Gasturbinendichtung |
DE19920567A1 (de) * | 1999-05-03 | 2000-11-16 | Fraunhofer Ges Forschung | Bauteil aus Titan oder einer Titanlegierung und Verfahren zu seiner Beschichtung |
Cited By (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2006094481A1 (de) * | 2005-03-10 | 2006-09-14 | Mtu Aero Engines Gmbh | Bauteil, insbesondere gasturbinenbauteil |
EP3061850A1 (de) * | 2015-02-25 | 2016-08-31 | United Technologies Corporation | Hartphasenlose metallbeschichtung für verdichterschaufelspitze |
CN114150256A (zh) * | 2021-12-14 | 2022-03-08 | 中国航发南方工业有限公司 | 航空发动机小尺寸涡轮工作叶片的耐高温热腐蚀涂层 |
CN114150256B (zh) * | 2021-12-14 | 2023-11-03 | 中国航发南方工业有限公司 | 航空发动机小尺寸涡轮工作叶片的耐高温热腐蚀涂层 |
Also Published As
Publication number | Publication date |
---|---|
DE102004001722A1 (de) | 2005-08-04 |
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