WO2010054633A2 - REVÊTEMENT ANTI-USURE POUR TiAL - Google Patents

REVÊTEMENT ANTI-USURE POUR TiAL Download PDF

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Publication number
WO2010054633A2
WO2010054633A2 PCT/DE2009/001580 DE2009001580W WO2010054633A2 WO 2010054633 A2 WO2010054633 A2 WO 2010054633A2 DE 2009001580 W DE2009001580 W DE 2009001580W WO 2010054633 A2 WO2010054633 A2 WO 2010054633A2
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WO
WIPO (PCT)
Prior art keywords
hard material
layer
noble metal
component according
particles
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Ceased
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PCT/DE2009/001580
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German (de)
English (en)
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WO2010054633A3 (fr
Inventor
Erwin Bayer
Wilfried Smarsly
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MTU Aero Engines AG
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MTU Aero Engines GmbH
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Publication of WO2010054633A2 publication Critical patent/WO2010054633A2/fr
Publication of WO2010054633A3 publication Critical patent/WO2010054633A3/fr
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

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    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C18/00—Chemical coating by decomposition of either liquid compounds or solutions of the coating forming compounds, without leaving reaction products of surface material in the coating; Contact plating
    • C23C18/02—Chemical coating by decomposition of either liquid compounds or solutions of the coating forming compounds, without leaving reaction products of surface material in the coating; Contact plating by thermal decomposition
    • 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
    • C23C18/00—Chemical coating by decomposition of either liquid compounds or solutions of the coating forming compounds, without leaving reaction products of surface material in the coating; Contact plating
    • C23C18/02—Chemical coating by decomposition of either liquid compounds or solutions of the coating forming compounds, without leaving reaction products of surface material in the coating; Contact plating by thermal decomposition
    • C23C18/08—Chemical coating by decomposition of either liquid compounds or solutions of the coating forming compounds, without leaving reaction products of surface material in the coating; Contact plating by thermal decomposition characterised by the deposition of metallic material
    • 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
    • C23C28/02—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D only coatings only including layers of metallic material
    • C23C28/021—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D only coatings only including layers of metallic material including at least one metal alloy layer
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C28/00—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D
    • C23C28/02—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D only coatings only including layers of metallic material
    • C23C28/023—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D only coatings only including layers of metallic material only coatings of metal elements only
    • 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
    • C23C28/02—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D only coatings only including layers of metallic material
    • C23C28/027—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D only coatings only including layers of metallic material including at least one metal matrix material comprising a mixture of at least two metals or metal phases or metal matrix composites, e.g. metal matrix with embedded inorganic hard particles, CERMET, MMC.
    • 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
    • C23C28/02—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D only coatings only including layers of metallic material
    • C23C28/028—Including graded layers in composition or in physical properties, e.g. density, porosity, grain size
    • 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
    • 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
    • F05D2260/00—Function
    • F05D2260/95—Preventing corrosion
    • 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
    • F05D2300/211—Silica
    • 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
    • F05D2300/2112—Aluminium oxides
    • 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
    • F05D2300/2118—Zirconium oxides
    • 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
    • F05D2300/224—Carbon, e.g. graphite
    • 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
    • F05D2300/226—Carbides
    • F05D2300/2261—Carbides of silicon
    • 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
    • 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
    • F05D2300/2284—Nitrides of titanium
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • the present invention relates to a wear-resistant component made of a TiAl material for high-temperature applications with a two-layer protective layer and a method for its production and the corresponding application in a Turbinenschau- fei.
  • TiAl materials ie materials based on ⁇ -titanium aluminide, Ot 2 -Ti 3 Al, and corresponding alloys are of interest for use in the construction of gas or aviation turbines.
  • turbine blades are often designed such that they seal with their free ends against sealing surfaces, so-called sealing fins, wherein the ends of the turbine blades grind in order to produce a good sealing effect, so that abrasive wear can occur at the ends of the turbine blades .
  • sealing fins wherein the ends of the turbine blades grind in order to produce a good sealing effect, so that abrasive wear can occur at the ends of the turbine blades .
  • DE 37 88 116 T2 EP 0 166 676 A2 and CA 2 411 156 A1 describe abrasive materials for turbine blade ends.
  • there are temperature or corrosion protection layers as described in US 5,413,871 or JP 2003269105 A.
  • a TiAl component or a corresponding protective system for a TiAl material and a method for its production is to be provided which, in high-temperature applications, offers reliable protection against wear of the most varied types, for example. Erosion, fretting, or wear in connection with corrosion phenomena prevented, the protective layer should be safe and easy to produce during operation.
  • a wear-protected component with the features of claim 1, a method for producing a corresponding component having the features of claim 15 and in particular a turbine blade having the features of claim 20.
  • Advantageous embodiments are the subject of the dependent claims.
  • the invention is characterized in that on an TiAl material, ie a material based on the intermetallic phases ⁇ -TiAl, Ot 2 -Ti 3 Al and alloys thereof, an at least two-layer or two-layer protective layer system is provided which comprises a first diffusion barrier layer comprising a noble metal and a second hard material layer with hard material particles, wherein the hard material particles are embedded in a noble metal matrix.
  • Such a two-layered layer system offers the possibility of preventing diffusion of components of the protective layer, ie in particular of the elements of the hard material particles, into the TiAl, at the same time preventing or at least hindering the ductile noble metal from crack growth, so that the mechanical properties and in particular the vibration resistance of the component not be affected.
  • the hard material particles which are embedded in the noble metal matrix in the hard material layer, provide the necessary hardness and resistance to, for example, erosion or abrasive wear and the like, the incorporation of the hard material particles into a noble metal matrix or the coating of the individual particles by noble metal, the risk of Crack formation and growth and thus reduce or avoid negative effects on the mechanical properties of the entire coating or on the entire composite material.
  • the term of the TiAl material used here generally includes the intermetallic phases of the TiAl, ie in particular ⁇ -Titanalumind or Ot 2 -Ti 3 Al and also corresponding alloys, for example with niobium or the like.
  • the corresponding materials may include companion elements such as nitrogen, carbon, oxygen, hydrogen, and the like.
  • the noble metals for the diffusion barrier layer or the precious metal matrix include the platinum metals, gold, silver, mercury and rhenium, ie in particular ruthenium, rhodium, palladium, silver, rhenium, osmium, iridium, platinum, gold and mercury, in particular the use of palladium, silver , Osmium, platinum and gold come into question.
  • the hard material particles of the hard material layer may in particular be nanoscale in order to avoid the formation of cracks or crack growth due to their size.
  • the hard material particles of the hard material layer can have an average or maximum particle size of 500 nm or less, in particular 250 nm or less, preferably 100 nm or less.
  • the hard material particles may be of a ceramic material or other hard material, such as, in particular, alumina, zirconia, diamond, diamond-like carbon, boron nitride, cubic boron nitride (CBN), titanium nitride, titanium-aluminum nitride, silicon oxide, especially silicon dioxide and silicon carbide and the like.
  • the protective layer may in particular be limited to the above-described, basically two-layered or two-layered structure, wherein the diffusion barrier layer as well as the hard material layer per se may be formed in a plurality of layers or different partial layers.
  • the diffusion barrier layer can be arranged directly on the TiAl material and / or the hard material layer can be formed as a surface layer.
  • the diffusion barrier layer may have a thickness of 0.5 .mu.m to 10 .mu.m, in particular 1 .mu.m to 3 .mu.m, preferably about 1 .mu.m to 2 .mu.m, while the hard material layer has a thickness of 0.1 .mu.m to 100 .mu.m, preferably 0.1 .mu.m to 10 microns, most preferably 0.2 to 0.8 microns, in particular about 0.5 microns may have.
  • the protective layer can be adapted in particular by adapting the hard material layer to different conditions of use.
  • the chemical composition of the hard material particles used, the size of the hard material particles and / or their proportions in the hard material layer can be varied.
  • this variation can be given along the thickness of the hard material layer, so that the protective layer and in particular the hard material layer can be formed in the form of a gradient layer.
  • discrete regions with different configurations of the hard material layer are arranged on one component. In addition, these areas can also merge continuously.
  • the corresponding layers can be deposited on the TiAl material in any suitable manner.
  • an organic precious metal Bond can be used, which can be applied with or without solvent on the TiAl material.
  • organometallic compounds which contain noble metals are mentioned, for example, in EP 0 456 908 A.
  • the solvents present in the applied layer can be vaporized by the effect of temperature.
  • the organic noble metal compound can be cracked, so that correspondingly volatile components are formed and only the noble metal remains on the treated surface. This can be formed in a very simple manner, a thin diffusion barrier layer of a noble metal.
  • the hard material particles In the same way can thereby form a hard material layer.
  • the hard material particles In this case, only the organic precious metal compound or to the mixture of organic noble metal compound and solvent, the hard material particles must be dispersed so that the hard material particles remain in the deposited noble metal layer after the temperature treatment.
  • solvent used here can be any solvent with which the organic noble metal compound can form a solution, for example water.
  • the proportion of solvent can accordingly also vary in order to influence the properties of the deposited noble metal layer or of the noble metal layer with dispersed hard material particles.
  • the diffusion barrier layer and the hard material layer can be applied separately in succession or pass through parts of the treatment, such as the temperature treatment together.
  • the corresponding organic noble metal compounds can be applied successively in liquid form with or without solvent and once with the corresponding hard material particles in liquid form on the material and subsequently swept together by temperature treatment in corresponding metal layers überbowt.
  • the liquid to be applied is so thin that the dispersed particles of hard material can not be reliably held in the corresponding liquid film, it is advisable to apply it completely separate and in succession.
  • a corresponding turbine blade can have a protective layer according to the invention throughout, but the protective layer can be adapted for the various fields of use.
  • the proportion as well as the size of the hard material particles in the hard material layer can be increased. Accordingly, such a layer can be applied with a lower proportion of solvent. In comparison, the remaining areas can be provided with smaller and less hard particles or be deposited with a larger proportion of solvent.
  • FIG. 1 shows a sectional view through the layer structure of a component according to the invention
  • FIG. 2 is an illustration of the processing sequence for producing a protective layer according to the invention
  • FIG. 3 is a perspective view of a turbine blade according to the invention.
  • Figure 1 shows in a partial sectional view of the surface region of a TiAl component 1, wherein the base material, for example, from ⁇ -TiAl or a corresponding alloy based on ⁇ -TiAl with additions of niobium or accompanying elements such as oxygen, nitrogen, carbon, silicon, hydrogen and may be formed.
  • the base material for example, from ⁇ -TiAl or a corresponding alloy based on ⁇ -TiAl with additions of niobium or accompanying elements such as oxygen, nitrogen, carbon, silicon, hydrogen and may be formed.
  • Such components made of titanium aluminides are used due to their light weight, for example in aircraft turbines in the range of low operating temperatures.
  • a two-day protective layer 4 is arranged on the surface of the TiAl material 1, which consists of the partial layers 2 and 3.
  • the sub-layer 2 is a diffusion barrier layer formed of a noble metal.
  • the noble metals here include ruthenium, rhodium, palladium, silver, rhenium, osmium, iridium, platinum, silver and mercury, in particular palladium, silver, platinum, osmium and gold come into question.
  • a hard material layer 3 which comprises a plurality of hard material particles 6 in a noble metal matrix 5.
  • the noble metal matrix 5 can be formed from the same noble metal as the diffusion barrier layer 2 or from a different noble metal.
  • the hard material particles may be formed as nanoparticles, ie have an average or maximum size of 500 nm, in particular 250 nm, preferably 100 nm. Due to the small size of the hard material particles, cracking and / or crack growth is suppressed or impeded, which improves the mechanical properties of the protective layer 4 or of the entire composite material. In addition, the ductile matrix of a precious metal contributes to the fact that no crack formation can take place.
  • the diffusion barrier layer 2 prevents the diffusion of constituents of the protective layer 4 or in particular of the hard material layer 3 and here again of elements of the hard material particles 6 in the TiAl base material, so that an undesirable change of the TiAl base material can be avoided.
  • the hard material particles may be formed from ceramic materials and in particular comprise one or more components selected from aluminum oxide, zirconium oxide, diamond, diamond-like carbon, boron nitride, cubic boron nitride, titanium nitride, titanium-aluminum nitride or silicon dioxide.
  • the distribution of the hard material particles 6 in the noble metal matrix 5, in particular with regard to the size of the hard material particles and / or the proportion of the hard material particles 6 in the metal matrix 5 and the chemical composition of the hard material particles 6 can vary in the various dimensions of the hard material layer, ie both in the thickness direction perpendicular to the surface of the TiAl material 1 and in the independent spatial directions parallel to the surface of the component.
  • the hard material layer can be applied in multiple layers and / or separated according to different areas.
  • FIG. 2 shows a schematic representation of a production process with which a corresponding protective layer 4 can be produced on a TiAl material 1.
  • FIG. 2 shows that a container contains a mixture of an organic precious metal compound and a solvent 11, which is applied to a TiAl substrate via brushes or brushes 13 or the like, to form a liquid film 12 on the surface of the TiAl substrate to build.
  • the suitably prepared material is introduced into a furnace 14, in which a heating device 15 is provided, so that the liquid film 12 can be heated together with the substrate 10. This leads to evaporation of the solvent and to a decomposition of the organic noble metal compound and also evaporation of the volatile components, which is represented schematically by the vapor 16.
  • a heating device 15 is provided, so that the liquid film 12 can be heated together with the substrate 10.
  • the noble metal component of the organic noble metal compound Back on the TiAl substrate 10 remains the noble metal component of the organic noble metal compound, so that a noble metal layer 20 is formed, the thickness is very small and is in the micrometer range.
  • the pretreated TiAl substrate provided with a diffusion barrier layer is also painted with a mixture of an organic noble metal compound, a solvent, and hard material particles dispersed therein by brush or brush, so that a liquid film 18 is formed on the previously deposited noble metal layer 20.
  • the thus treated TiAl substrate 10 is again introduced into the corresponding furnace 14 and heated by the heater 15 so that the solvent of the mixture 17 of organic noble metal compound, solvent and hard material particles dispersed therein evaporates.
  • the organic noble metal compound is in turn decomposed, wherein the volatile components also evaporate and are in the gas phase 16, which can be removed by appropriate suction devices (not shown) and disposed of properly.
  • the application method shown represents only one possibility, and even here modifications and additions are possible.
  • the mixture 11 or the mixture 17 with other coating technologies, such as spraying or the like are applied.
  • the temperature treatment can also be carried out in another suitable manner.
  • the two different partial layers namely the diffusion barrier layer 20 and the hard material layer 30, are applied in such a way that first the liquid films 12 and 18 are arranged one above the other and only then the temperature treatment takes place.
  • FIG. 3 is a perspective view of a turbine blade 40 to which the present invention can be applied.
  • the turbine blade 40 includes a foot portion 41 which may be inserted into a corresponding rotor of a gas turbine. This foot region may cause signs of wear, as the turbine blade root 41 rubs against the rotor, which is often made of nickel or a nickel-based alloy. In connection with the present corrosion conditions it can come here to fretting appearances.
  • the airfoil 42 may be erosion, for example, when used in air turbines in sandy or dusty areas.
  • the end portion 43 of the turbine blade is often subjected to abrasive wear to achieve a good seal against the housing.
  • the protective layer 4 may correspond to the fields of application, ie the application in the foot region 41, in the airfoil region 42 or be modified according to the end portion 43, for example, as regards the chemical composition of the hard material particles, the size and distribution and the proportion of hard material particles in the hard material layer as well as the method of application.
  • the end portion 43 of the turbine blade which is exposed to high abrasive wear, have a higher concentration of hard material particles, which may also be formed with their average particle size or maximum particle size larger than in the remaining area of the turbine blade 40.
  • the layers are reduced via an organic noble metal compound with solvents, the solvent concentration. Similar adjustments can be made in other areas of the turbine blade 40.

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  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Materials Engineering (AREA)
  • Organic Chemistry (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Metallurgy (AREA)
  • General Chemical & Material Sciences (AREA)
  • Thermal Sciences (AREA)
  • Physics & Mathematics (AREA)
  • Composite Materials (AREA)
  • Inorganic Chemistry (AREA)
  • General Engineering & Computer Science (AREA)
  • Other Surface Treatments For Metallic Materials (AREA)

Abstract

L'invention concerne une pièce à protection anti-usure pour des utilisations à haute température, composée d'un matériau TiAl, en particulier une aube de turbine, comprenant un revêtement protecteur (4) composé d'au moins deux couches, à savoir une première couche (2) formant barrière de diffusion, en métal noble, et une seconde couche (3) en matériau dur contenant des particules de matériau dur prises dans une matrice de métal noble, lesquelles couches sont appliquées sur le matériau TiAl (1) pour former un revêtement protecteur. L'invention porte également sur un procédé de fabrication correspondant.
PCT/DE2009/001580 2008-11-11 2009-11-07 REVÊTEMENT ANTI-USURE POUR TiAL Ceased WO2010054633A2 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102008056741.8 2008-11-11
DE102008056741A DE102008056741A1 (de) 2008-11-11 2008-11-11 Verschleissschutzschicht für Tial

Publications (2)

Publication Number Publication Date
WO2010054633A2 true WO2010054633A2 (fr) 2010-05-20
WO2010054633A3 WO2010054633A3 (fr) 2010-12-29

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ID=42096482

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/DE2009/001580 Ceased WO2010054633A2 (fr) 2008-11-11 2009-11-07 REVÊTEMENT ANTI-USURE POUR TiAL

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Country Link
DE (1) DE102008056741A1 (fr)
WO (1) WO2010054633A2 (fr)

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WO2010054633A3 (fr) 2010-12-29
DE102008056741A1 (de) 2010-05-12

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