CN108431290A - 涡轮间隙控制涂层和方法 - Google Patents

涡轮间隙控制涂层和方法 Download PDF

Info

Publication number
CN108431290A
CN108431290A CN201680077542.6A CN201680077542A CN108431290A CN 108431290 A CN108431290 A CN 108431290A CN 201680077542 A CN201680077542 A CN 201680077542A CN 108431290 A CN108431290 A CN 108431290A
Authority
CN
China
Prior art keywords
blade
coating
pvd
abradable
coatings
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
CN201680077542.6A
Other languages
English (en)
Other versions
CN108431290B (zh
Inventor
S·威尔逊
康耐特·阿克格茨·多罗金
F·罗维尔
O·雅里
M·内斯特勒
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Oerlikon Surface Solutions AG Pfaeffikon
Original Assignee
Oerlikon Surface Solutions AG Truebbach
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Oerlikon Surface Solutions AG Truebbach filed Critical Oerlikon Surface Solutions AG Truebbach
Publication of CN108431290A publication Critical patent/CN108431290A/zh
Application granted granted Critical
Publication of CN108431290B publication Critical patent/CN108431290B/zh
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • F01D5/288—Protective coatings for blades
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • 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
    • 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
    • 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
    • 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
    • C23C14/0676—Oxynitrides
    • 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
    • C23C14/0688—Cermets, e.g. mixtures of metal and one or more of carbides, nitrides, oxides or borides
    • 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
    • C23C14/08—Oxides
    • C23C14/083—Oxides of refractory metals or yttrium
    • 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
    • C23C14/12—Organic 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
    • 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
    • C23C14/3485—Sputtering using pulsed power to the target
    • 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
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C30/00—Coating with metallic material characterised only by the composition of the metallic material, i.e. not characterised by the coating process
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C30/00—Coating with metallic material characterised only by the composition of the metallic material, i.e. not characterised by the coating process
    • C23C30/005—Coating with metallic material characterised only by the composition of the metallic material, i.e. not characterised by the coating process on hard metal substrates
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/20—Specially-shaped blade tips to seal space between tips and stator
    • 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
    • F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
    • 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
    • F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
    • F01D5/225—Blade-to-blade connections, e.g. for damping vibrations by shrouding
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • F01D5/286—Particular treatment of blades, e.g. to increase durability or resistance against corrosion or erosion
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • 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
    • 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
    • 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
    • F05D2240/10—Stators
    • F05D2240/14—Casings or housings protecting or supporting assemblies within
    • 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
    • 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
    • F05D2300/2281—Nitrides of aluminium
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/20—Oxide or non-oxide ceramics
    • F05D2300/22—Non-oxide ceramics
    • F05D2300/228—Nitrides
    • F05D2300/2282—Nitrides of boron
    • 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
    • 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
    • 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
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/12—All metal or with adjacent metals
    • Y10T428/12493—Composite; i.e., plural, adjacent, spatially distinct metal components [e.g., layers, joint, etc.]
    • Y10T428/12535—Composite; i.e., plural, adjacent, spatially distinct metal components [e.g., layers, joint, etc.] with additional, spatially distinct nonmetal component
    • Y10T428/12556—Organic component
    • Y10T428/12569—Synthetic resin
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/12—All metal or with adjacent metals
    • Y10T428/12493—Composite; i.e., plural, adjacent, spatially distinct metal components [e.g., layers, joint, etc.]
    • Y10T428/12535—Composite; i.e., plural, adjacent, spatially distinct metal components [e.g., layers, joint, etc.] with additional, spatially distinct nonmetal component
    • Y10T428/12576—Boride, carbide or nitride component
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/12—All metal or with adjacent metals
    • Y10T428/12493—Composite; i.e., plural, adjacent, spatially distinct metal components [e.g., layers, joint, etc.]
    • Y10T428/12535—Composite; i.e., plural, adjacent, spatially distinct metal components [e.g., layers, joint, etc.] with additional, spatially distinct nonmetal component
    • Y10T428/12597—Noncrystalline silica or noncrystalline plural-oxide component [e.g., glass, etc.]
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/12—All metal or with adjacent metals
    • Y10T428/12493—Composite; i.e., plural, adjacent, spatially distinct metal components [e.g., layers, joint, etc.]
    • Y10T428/12535—Composite; i.e., plural, adjacent, spatially distinct metal components [e.g., layers, joint, etc.] with additional, spatially distinct nonmetal component
    • Y10T428/12611—Oxide-containing component
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/12—All metal or with adjacent metals
    • Y10T428/12493—Composite; i.e., plural, adjacent, spatially distinct metal components [e.g., layers, joint, etc.]
    • Y10T428/12535—Composite; i.e., plural, adjacent, spatially distinct metal components [e.g., layers, joint, etc.] with additional, spatially distinct nonmetal component
    • Y10T428/12611—Oxide-containing component
    • Y10T428/12618—Plural oxides
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/24—Structurally defined web or sheet [e.g., overall dimension, etc.]
    • Y10T428/24942—Structurally defined web or sheet [e.g., overall dimension, etc.] including components having same physical characteristic in differing degree
    • Y10T428/2495—Thickness [relative or absolute]
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/24—Structurally defined web or sheet [e.g., overall dimension, etc.]
    • Y10T428/24942—Structurally defined web or sheet [e.g., overall dimension, etc.] including components having same physical characteristic in differing degree
    • Y10T428/2495—Thickness [relative or absolute]
    • Y10T428/24959—Thickness [relative or absolute] of adhesive layers
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/24—Structurally defined web or sheet [e.g., overall dimension, etc.]
    • Y10T428/24942—Structurally defined web or sheet [e.g., overall dimension, etc.] including components having same physical characteristic in differing degree
    • Y10T428/2495—Thickness [relative or absolute]
    • Y10T428/24967—Absolute thicknesses specified
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/24—Structurally defined web or sheet [e.g., overall dimension, etc.]
    • Y10T428/24942—Structurally defined web or sheet [e.g., overall dimension, etc.] including components having same physical characteristic in differing degree
    • Y10T428/24983—Hardness
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/26—Web or sheet containing structurally defined element or component, the element or component having a specified physical dimension
    • Y10T428/263—Coating layer not in excess of 5 mils thick or equivalent
    • Y10T428/264—Up to 3 mils
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/26—Web or sheet containing structurally defined element or component, the element or component having a specified physical dimension
    • Y10T428/263—Coating layer not in excess of 5 mils thick or equivalent
    • Y10T428/264—Up to 3 mils
    • Y10T428/265—1 mil or less

Abstract

本发明披露了一种至少具有高压涡轮段和低压涡轮段的涡轮发动机，包括壳体和至少一个可转动地安装在壳体内的涡轮叶片，其中，该壳体的内表面的至少一部分覆盖有作为可磨耗材料的覆材以便在所述内表面与所述至少一个叶片的叶顶之间提供间隙控制，其中，所述叶片叶顶涂覆有硬PVD涂层，其特征是，所述至少高压段和/或低压段的覆材包括多孔陶瓷基材料，在所述叶片叶顶上的硬PVD涂层实质上由无液滴的氮化物涂层构成。

Description

涡轮间隙控制涂层和方法
本发明涉及用于气体涡轮发动机的叶片以及气体涡轮发动机。根据本发明的第一实施例，所披露的叶片包括用于切削和成形用于涡轮密封应用的间隙控制涂层的物理气相沉积(PVD)薄膜硬涂层。该涂层提高了叶片耐磨性，所述叶片在摩擦侵蚀期间接触到热喷涂的CoNiCrAlY-氮化硼、NiCrAl膨润土和NiCrAl-氮化硼间隙控制涂层。
背景技术
典型地，涡轮发动机带有轴装涡轮叶片，其在周向上被限制在涡轮壳体或外壳内。通常，在叶片叶顶近侧的涡轮壳体衬有多种可磨耗覆材(涂层)，例如由高耐热性和耐蚀性的金属材料/陶瓷材料构成。在许多情况下，可磨耗的表面材料本身在一定程度上有磨蚀作用。因此保持叶片叶顶间隙G，以避免这两个对置部件相互接触，这种接触可能造成叶片叶顶提前磨损。
图1示出设计原理，示出涡轮壳体1、带有叶片5的转子盘3，叶片5包括叶片根部7和叶片叶顶9。还示出了可磨耗的密封11和在可磨耗的密封11与叶片叶顶9之间的叶顶间隙G。
为了尽可能减小在高压叶片侧和低压叶片侧之间的叶片叶顶气流泄漏，叶片叶顶间隙G需要被选择成实践上可行的尽可能的小。
为了实现这样的具有极小叶片叶顶间隙G的系统，在现有技术中已知的是采用所谓的凹槽叶顶。WO2015/041787披露了这种带有凹槽叶顶的叶片。为了运行目的，在初次使用时这些叶顶接触到壳体或外壳的可磨耗涂层，由此实现最小化的间隙G。为了形成这样的凹槽叶顶，WO2015/041787披露了一种特定的几何结构，其被选择成容许涡轮叶片叶顶表现得类似切削刀具，切入可磨耗基材并由此使之成形。不幸的是，仍然存在磨损损伤问题，因为这些具有特定几何结构的叶顶倾向于在接触可磨耗基材时遭到磨损，通常在叶片叶顶速度与叶片叶顶对可磨耗覆材的侵蚀率的特定组合情况下。如果采用特殊可磨耗材料例如像热喷涂的CoNiCrAlY-氮化硼、NiCrAl膨润土和NiCrAl-氮化硼，情况尤其如此。
另一种很相似的做法在US5756217A中被披露，其中，图案化条带涂层被用作磨蚀性涂层来对抗可磨耗涂层，针对与上述相同的目的。所用涂层材料选自氧化锆、氧化钇和/或氧化铝的组，且该材料通过热喷涂借助已被附接至待涂覆的结构表面的开孔掩模来施加。尽管US5756217A提到了此过程将避免沉积后的成形或机加工，所提出的工艺过程的操作工夫相当可观，且相对于上述可磨耗材料的磨损仍是严重问题。
在US20150075327A1中，Linska等人披露了通过电解沉积在叶片叶顶上产生的耐磨涂层。这些电解沉积涂层似乎加强了叶片叶顶，因此有效发挥作用，但需要附加制造步骤。电解沉积防磨保护层的另一缺点是以下事实，即只有导电材料可以被电镀沉积。这将这种涂层限制到相对厚(如300-500微米)的金属层或合金层，其在许多情况下并不足够耐磨。
在US20150368786A1中披露了一种叶顶涂覆方法，其利用机械掩模来仅使叶顶区域暴露至PVD涂层下。所披露的钨铬钴合金、碳化物或氮化物涂层的厚度据说在25.4-127μm之间，其应该保证了针对可磨耗方的期望叶片厚度公差。作为最优选的且唯一的耐磨涂层的例子，立方氮化硼被披露为在运行中不会磨损且可保护叶片结构完整性的材料。立方氮化硼的使用是可预期到的，因为其具有众所周知的极高的硬度、耐磨性和高达1300℃的抗氧化性。但是，在工程基材上的沉积可能是相当有挑战性的，因为在大多数情况下观察到六方氮化硼的存在。通常的PVD涂层的高应力(出现在生长期间内)也可能严重限制所需涂层厚度并且使得大多数PVD涂覆的碳化物或氮化物不可被用于像叶片上的耐磨层这样的应用。
因此，在现有技术中需要具有如下叶片叶顶的叶片，其就与上述可磨耗基材的接触而言显示出耐磨性。
发明目的
根据本发明，叶片叶顶涂覆有物理气相沉积的薄膜涂层，就像例如针对切削刀具应用所知道的那样。
已知在涡轮叶片上采用PVD涂层以防腐蚀以及防止夹带到气体涡轮发动机的压气机中的固体颗粒的侵蚀。例如EP0674020B1描述了一种防止这种颗粒侵蚀的多层耐蚀涂层。
但根据本发明，PVD涂层被用于加强叶片叶顶，防止因与可磨耗基材相互作用而引起的磨损。在涡轮内的严重摩擦侵蚀条件下和/或如果可磨耗涂层热喷涂为过高的宏观硬度条件下，叶片材料的过度摩擦生热会产生严重的磨损。所观察到的机理是叶片材料变热时软化、极度的宏观塑性变形和破裂以及叶片材料转移至定子覆材。叶片材料(大多局限于钛合金)的燃烧也可能出现，伴随出现发动机严重损伤的结果。叶片材料开裂的发生是源于对具有高于规定硬度的可磨耗覆材的低效切削而产生的极大叶片切削力。
本文的焦点在于应对上述叶片材料的两种主体磨蚀磨损的措施，所述磨损由所指定的CoNiCrAlY-hBN、NiCrAl-膨润土、NiCrFeAl-hBN和NiCrAl-hBN可磨耗涂层中的一种或多种金属合金或金属合金氧化物材料成分造成，其中，hBN被用作六方氮化硼的缩写。
在转子叶片之间的相对于定子(覆材)的侵蚀摩擦事件可能源于许多起因，例如：
·转子件和定子件之间的不同热膨胀作用，
·发动机状况或负载的快速变化，例如飞机硬着陆或喘振，
·“超温”运行条件，
·快速发动机关停，
·因壳体不圆导致的变形相关因素，
·轴承间隙和源于不稳定性的转子振动。
在叶片叶顶速度和叶片侵入定子(覆材)的侵蚀率的特定转子侵蚀情况下，可能出现叶片叶顶磨损。此外，如果间隙(可磨耗)涂层被喷涂到高于其规定硬度的硬度或密度，则在广泛范围的侵蚀条件下可能出现本不会发生的更严重的叶片磨损。
应该注意，由上述事件引起的磨损的类型截然不同于腐蚀冲击损伤，腐蚀冲击损伤出现在当颗粒如沙粒或灰尘夹杂在气流中且进入涡轮，撞击叶片时。
因此，本发明的目的是消除由上述事件引起的在例如下述物体上的磨损：
·钛合金压气机叶片，
·镍合金压气机叶片，
·不锈钢压气机叶片。
附图说明
图1是工业涡轮机或航空涡轮机的示意图，包括在转子盘3上的至少一个叶片5，具有叶片根部7和叶片叶顶9以及可磨耗密封11，可磨耗密封11位于涡轮机壳体1之内、在叶片叶顶9的相对侧并与其以间隙G间隔。
图2是在涂覆后的叶片叶顶区域9上和周围的同质涂层厚度分布的示意图。
根据本发明，这是通过在叶片表面上涂覆薄膜物理气相沉积(PVD)硬涂层来获得的，其在涡轮发动机压气机部段内的侵蚀摩擦事件中接触到可磨耗间隙控制涂层，例如(CoNiCrAlY-hBN、NiCrAl膨润土、NiCrAl-hBN、NiCrFeAl-hBN)。
换言之，根据本发明，被涂覆至叶片且尤其是叶片叶顶的PVD硬涂层确实有针对源自叶片叶顶与可磨耗基材的相互作用的磨损的保护用途。
出乎意料地，从切削刀具应用中知晓的PVD涂层可以有利地被用在本环境中并显示出色的保护性能，尤其如果被涂覆在钛合金、不锈钢和/或镍合金叶片上，这些叶片被用在航空发动机的低压和高压压气机转子和整体叶盘上以及工业气体涡轮机压气机转子上。
在以下全文中，术语“覆尖”用于指：至少在顶端上且优选也在叶片顶端外围上提供涂层。为了定义词语“外围”，假定在叶片表面上的一点，如果该点与所安装叶片的最外侧部分(从旋转轴看)的距离不超过涂层厚度的100倍，根据本发明其应该被认为是叶片叶顶外围的一部分。
迄今为止，在现有技术中还未知在叶片叶顶上涂覆PVD涂层以达到覆尖的目的。常用的叶片不带有任何形式的覆尖，作为(就制造而言)最经济的解决方式。
但在采用覆尖的情况下，已知的技术总体受限于较厚的硬涂层，例如那些通过热喷涂技术例如大气等离子体喷涂(APS)和高速氧燃料(HVOF)热喷涂所沉积的涂层。通过这些技术涂覆的涂层通常是100-200微米厚且有如下缺点，例如：
-与叶片叶顶材料粘附不足；APS和HVOF涂层被机械结合至待涂覆表面。
-涂层尺寸(厚度)和重量太大，尤其对于被用在高压航空压气机中的薄叶片叶顶。
-待涂覆材料准备需要表面粗糙化，例如通过喷砂，其可能损伤叶片部件的机械完整性。
相比之下，通过PVD技术被沉积在叶顶上的涂层大多被冶金地结合到基体材料上并具有极高的粘附强度，不需要可能不利地损伤叶片材料的表面预准备技术，极其坚硬且抗氧化。根据本发明，通过PVD技术所沉积的叶顶涂层能以极薄层的形式被涂覆到叶片叶顶，例如1-40微米、优选5-25微米厚，优点是可控的固有涂层应力和适度的表面粗糙度，而与此同时该PVD涂层显示出高密度和耐磨性。
根据本发明用PVD涂层对叶片覆尖意味着：例如对叶片叶顶和/或叶顶外围涂覆薄(例如1-40微米厚)而硬的(如1000-3500HV固有涂层硬度)PVD涂层，例如氮化钛(TiN)、氮化钛铝(TiAlN)、硅氮化钛(TiSiN)、碳氮化钛(TiCN)、氮化铬(CrN)或氮化铝铬(AlCrN)或者其组合物。它们是通常应用于切削刀具环境中的硬涂层。
相当让人吃惊的是，发明人发现了，利用这些PVD涂层且尤其是利用通常用于切削刀具领域中的硬薄膜PVD涂层，叶片磨损可以在大范围的叶片对覆材侵蚀条件下被减轻和/或消除。还让人吃惊的是，所述氮化物基涂层并未遭到提前氧化，尽管已知这些氮化物基涂层相比于例如氧化物或立方氮化硼具有明显更低的高温抗氧化性，如以上所解释的那样。
这是如何起效的尚未完全清楚，但一种可能的解释可能是，在叶片叶顶和可磨耗表面相互作用中存在的状况大约近似于在高速刀具切削金属合金工件时的状况。
现在，将借助例子来详述本发明。
本发明的研究基于广泛的可磨耗材料。尽管这些可磨耗材料也是被涂覆上的(例如在外壳上)，但这些材料总体将被称为涂覆覆材以使其清楚地区别于PVD涂层。
试验基于如下的覆材涂覆材料：
1.Ni 4Cr 4Al 21膨润土
产品名称：Durabrade 2313、Metco 314NS、Metco 312NS、Durabrade 2311
这些是由完全封装稳定化膨润土芯的镍铬铝合金构成的金属陶瓷粉末。封装利用化学覆层工艺来获得。这提供了坚固的、高质量的无粘合剂的复合材料粉末。这种粉末被设计用于制造具有变化的耐蚀性和可磨耗性的基材以适应最终应用。基材被设计用于与镍基合金或钢制件摩擦。
2.CoNiCrAlY-hBN聚酯
在这些材料的基材中的CoNiCrAlY(钴镍铬铝钇)母材相比于其它镍铬基可磨耗材料提供了改善的抗氧化性和耐蚀性。氮化硼成分提供固体润滑，由此在摩擦侵蚀中改善可磨耗能力并减轻叶片磨损。基材多孔性可以在35-60体积％之间变化，它通过涂层中夹带的聚酯量来控制。正是这种可控的网状金属结构允许相对于钛合金、钢或超级合金成分的出色的易碎性。
这些基材可以在高达750℃(1380°F)的工作温度使用，但在650℃(1200°F)以上可预期易氧化性增强。为了在极端环境条件下使用或者当需要坚硬耐蚀涂层时，推荐使用坚硬的覆尖匹配叶片或刀刃。Metco 2042和Metco 2043的涂层在高达650℃(1200°F)的工作温度下易于被裸露未覆尖的镍合金和不锈钢部件切削。为了相对于裸露未处理的钛部件来使用，建议在高达550℃(1020°F)的工作温度下使用Metco 2042。
3.NiCrFeAl-hBN
产品名称：Metco 301C-NS和Metco 301NS，即Ni13Cr8Fe6.5BN3.5Al2。
镍铬合金/氮化硼热喷涂粉末是由镍铬合金、六方氮化硼和铝组成的金属陶瓷复合材料，并且利用机械覆层技术来制造。这种粉末被设计为用于生产具有变化的耐蚀性和可磨耗性的基材以适应最终应用。粉末最好利用燃烧粉末喷涂工艺进行涂覆，采用氢气或乙炔为燃料气体。
4.铝青铜聚酯
产品名称：Metco 604NS，Metco 605NS，Metco 610NS
Metco 604NS、Metco 605NS和Metco 610NS是设计为生产用于航空和在海洋环境(忧虑盐腐蚀)中运行的工业涡轮机间隙控制应用的可磨耗基材的粉末材料。这些粉末的金属母材是预合金化铝青铜材料。具体配比的聚酯材料与铝青铜母材材料组合以形成低密度基材结构。在Metco 604NS和605NS情况下，聚酯与金属组分混合。Metco 610NS是利用固态有机粘合剂将聚酯成分覆层到金属组分上的复合材料。
关于NiCrAl-hBN-聚酯，可参考美国专利申请WO2011/094222A1(多夫曼、威尔森等人)所述的基材。
为了表明本发明的技术效果，进行评估程序，在评估程序框架内，测试在欧瑞康巴尔查斯(Oerlikon Balzers)利用物理气相沉积(PVD)工艺在叶片叶顶上沉积的TiAlN涂层的性能。于是，对TiAl6V4和英科耐尔(Inconel)718叶片进行TiAlN-覆尖并进行相对于特定的Oerlikon Metco可磨耗基材的侵蚀测试。
TiAlN-覆尖的TiAl6V4合金叶片在450℃相对于以下材料进行摩擦试验：
1)M2042可磨耗基材：分别是标准硬度水平HR15Y 39和高硬度水平HR15Y 69，以及
2)M314NS可磨耗基材：标准硬度水平HR15Y 50
此外，TiAlN覆尖的IN718合金叶片在750℃相对于以下材料进行摩擦试验：
1)M2043可磨耗硬度HR15Y 67
2)M314可磨耗硬度HR15Y 50
所有可磨耗基材在瑞士的Oerlikon Metco所在地(OM-CH)进行热喷涂。
在Oerlikon Metco(OM)侵蚀试验设备上进行一组十六次侵蚀试验。
这些试验在250m/s和410m/s速度下进行，此时测定的侵蚀率为5μm/s或500μm/s。要达到的侵蚀深度是1.0mm。
在所给出的试验条件下，裸露的钛合金叶片相对于Metco 2042和Metco 2043可磨耗材料通常经受显著磨损(大多在低叶片叶顶速度和高侵蚀速度下)。相比之下，TiAlN覆尖被发现产生了改善的摩擦性能，其结果是没有观察到叶片磨损，即0％叶片磨损，这是以叶片叶顶侵入可磨耗涂覆覆材中的总侵入深度的百分比来测量的，名义上是1.0mm。获得了某些略为负的叶片磨损值例如-1.0％，其表明覆材略微转移至叶片叶顶，没有观察到对叶片叶顶或叶顶涂层的损伤。
Metco 314NS在用无覆尖的裸露TiAl6V4叶片来摩擦时也显示出叶片磨损。但是，在用TiAlN覆尖这些叶片之后，侵蚀试验显示出改善的摩擦性能，没有叶片磨损。
所述程序清楚示出，涂覆薄硬PVD涂层至叶片叶顶例如钛合金和镍合金叶片叶顶，可以观察到叶片叶顶磨损的显著减小，表明所喷涂的特定的可磨耗(间隙控制)基材材料的切削性能改善到高达至少70HR15Y硬度值(聚合物烧尽后热处理状态)。
本发明的第二实施例涉及用于高压压气机间隙控制应用例如空气涡轮、工业气体涡轮和涡轮增压器的可磨耗涂层。
所关注的叶片材料是例如钛合金、不锈钢合金和镍基超级合金。
用于这些应用的现有技术的可磨耗材料通常是具有低的热稳定性的金属合金基的，因为它们显示出低的抗氧化性和/或抗烧结性。它们特意在更软更多孔的条件下被制造以便减轻对叶片的损伤，此时叶片在大多数情况下没有保护性覆尖。这导致具有低宏观硬度的可磨耗材料。可磨耗涂层的多孔性质使其因为较大的金属合金外露表面积而尤其易于高温氧化。另外，所需要的较高的多孔性削弱了涂层抗拉强度并减小了其耐蚀性。
尤其如果关注的是高温应用，则那些材料总体并不耐热是缺点。
根据现有技术，有热稳定的锆基聚酯陶瓷热喷涂粉末，其常被用作用于在航空和工业气体涡轮发动机涡轮段中的间隙控制应用的高温可磨耗涂层，此时叶片合金通常由镍基超级合金制造。另外，多孔耐热镍钴合金基涂层也被用在航空和工业气体涡轮发动机的高压压气机区域中，在此叶片合金由钛合金、不锈钢或镍基超级合金制造。但是，对于大多数较高温度的密封应用，叶片叶顶必须分别用立方氮化硼磨蚀性颗粒覆盖，其利用已确立的电镀和高温硬焊技术来涂覆，因为裸露的钛合金、不锈钢合金或镍合金相比于这些坚硬陶瓷可磨耗材料显示出太高的磨损。另外且尤其如果采用钛合金，则如果被高硬度可磨耗涂层磨损有可能出现钛火。
以上的第一实施例披露了硬薄膜涂层，其被涂覆至叶片叶顶以防止由可磨耗材料引起的磨损。出乎意料地，发明人还发现，当裸露的叶片叶顶被涂覆硬耐磨薄膜涂层时，则甚至耐高温覆材如热喷涂的多孔氧化锆或其它多孔的低密度陶瓷材料例如铝化镁(镁尖晶石)都可以被用作覆材，而不会损伤叶片叶顶。因此，这点现在可容许专门在航空涡轮机、工业气体涡轮机和涡轮增压器的低压和高压压气机区域中使用热稳定(高熔点、高抗氧化性)的陶瓷基或金属间化合物基间隙控制材料。
用于高压压气机间隙控制(可磨耗)应用的当前现有技术是可磨耗的涂层，其
·比陶瓷可磨耗材料的宏观硬度更低(更软)，
·比陶瓷可磨耗材料更多孔，
·通常是具有比陶瓷材料低的热稳定性(抗氧化和抗烧结)的金属合金基。
它们需要在更柔软且更多孔的条件下制造以便缓解叶片损伤，此时叶片在大多数情况下不具有保护性覆尖。
另一方面，已知涂覆叶片叶顶以消除叶片损伤(磨损)。沉积在叶片叶顶上的PVD薄膜涂层例如TiAlN和AlCrN的使用被应用在涡轮机器中。
其中，叶片材料例如：
·钛合金如TiAl6V4、Ti6242、γTiAl型(Ti-45Al-8Nb)，
·不锈钢合金，例如17-4PH钢，
·镍基超级合金，如英科耐尔718。
现在，发明人发现了薄膜硬涂层的防磨保护作用如此高，以致可以有利地采用具有更高热稳定性(高熔点，抗烧结性，高抗氧化性)的更硬的可磨耗覆材材料，如热喷涂多孔氧化锆涂层如Metco 2460(M2460)。
TiAlN涂层利用物理气相沉积(PVD)工艺被沉积在叶片叶顶(英科耐尔718)上。进行相对于两套不同的Metco2460NS可磨耗涂层(热喷涂)的侵蚀试验。
在侵蚀试验设备上进行两次侵蚀试验。第一次试验是通过将TiAlN叶片叶顶涂层与硬质版的等离子体喷涂M2460NS涂层摩擦进行，而第二次试验是通过采用另一套利用标准喷涂参数等离子体喷涂的M2460NS涂层进行。
两次试验都在如下条件下进行：
·410m/s叶片叶顶速度，
·50μm/s侵蚀率，
·1100℃覆材温度，
·0.2mm或0.5mm的侵蚀深度。
M2460NS是锆基聚酯陶瓷热喷涂粉末，其如上所述是常被用作用于在航空和工业气体涡轮发动机的涡轮段中的间隙控制应用的高温可磨耗涂层，其中，根据现有技术采用立方氮化硼作为叶片材料。
所述涂层的以下两个变型通过热喷涂来制造且被热处理以烧尽聚酯多孔原体。
高硬度M2460NS：宏观硬度测量为平均59HR15N(聚合物烧尽条件下)。该M2460NS可磨耗涂层样品在聚合物烧尽(550℃/6h)后被试验。通过采用410m/s的叶片叶顶速度和50μm/s的侵蚀率进行的试验显示出无叶片磨损的良好摩擦性能。
标准硬度M2460NS涂层：宏观硬度测量为平均36HR15N(聚合物烧尽条件下)。该M2460NS可磨耗涂层样品在聚合物烧尽(550℃/6h)后被试验。通过采用410m/s的叶片叶顶速度和50μm/s的侵蚀率进行的试验显示出无叶片磨损的良好摩擦性能和表面叶片高度增大(相对于侵蚀深度的百分比的2.1％的叶片高度增大)。
在进行相对于M2460覆材的侵蚀试验时，未覆尖(未涂覆)的英科耐尔718叶片可见的典型的叶片磨损范围是相对于总侵蚀深度的百分比的70-100％磨损。通常，在相对于M2460覆材进行侵蚀试验时，现有技术的立方氮化硼覆尖英科耐尔718叶片可见零叶片磨损。
出乎意料地，针对TiAlN涂覆叶片叶顶所见范围类似于从现有技术的立方氮化硼覆尖叶片中所见，即，相对于总侵蚀深度的百分比的零叶片磨损。
基于这些结果，可以假定如果叶片叶顶涂覆有AlCrN，则所述范围即使不是更好也至少是相当的。尤其在高温范围内，AlCrN可能是优选的。这可能追溯到该PVD涂层的更高的耐热性。
对侵蚀试验(切削)后的覆材表面进行表面粗糙度测量并将其与利用商业可得的标准叶片叶顶(磨蚀性立方氮化硼)所切削的那些进行比较。所述结果(如以下在表1和表2中所列)表明，PVD覆尖叶片产生了更光滑的低粗糙度的表面光洁度。这样的改善对于在航空涡轮机器的所有部段(压气机和涡轮)中的航空间隙控制应用至关紧要。
表1示出相对于本发明的PVD覆尖叶片侵蚀后的M2460NS覆材粗糙度。
表2示出相对于根据现有技术的cBN覆尖叶片侵蚀后的M2460NS覆材粗糙度。
表1
表2
通过使用在叶片上的TiAlN和/或AlCrN PVD涂层而观察到的改进：
·相比于未覆尖的叶片(叶片磨损一般高达总侵蚀深度的70-100％)，叶片磨损减轻至零。
·与当前现有技术的立方氮化硼覆尖叶片所观察到的等同的叶片磨损(零)。
·相比于当前现有技术的立方氮化硼覆尖叶片所观察到的改善的覆材表面粗糙度减小。
·相比于当前现有技术的立方氮化硼覆尖叶片所观察到的，PVD覆尖叶片的更低的成本、更小的尺寸(涂层厚度)和更高的制造鲁棒性。尤其是，可通过PVD技术涂覆具有复杂的叶顶几何结构的更薄的叶片叶顶的简易性提供了相比于现有技术的明显优势。
·因为可利用硬薄膜PVD涂层成形并涂覆超级镍合金和不锈钢叶片材料的简易性，故它们现在容许将多孔陶瓷基可磨耗材料用在涡轮机器的高压压气机段中，相比于现有技术的高压压气机可磨耗材料(金属合金基)的显著性能优势在于：
i)抗氧化性，
ii)抗烧结性，
iii)耐蚀性。
·因为可利用硬薄膜PVD涂层涂覆其它叶片材料如钛合金的简易性，故现在它们开创了将多孔陶瓷基可磨耗材料用在涡轮机器的低压压气机段的机会，相比于现有技术的低压压气机可磨耗材料(通常基于铝合金)的显著优势在于：
i)耐蚀，
ii)改善的热胀失配和残余应力相容性。
硬薄膜涂覆叶片叶顶和作为可磨耗材料的热稳定多孔陶瓷覆材的组合根据披露相比于现有技术更有优势。优选地，硬薄膜涂层包括复合材料例如Me1Me2X，其中，Me1优选是由Ti、Cr或Zr或者其组合构成的组中的元素，Me2优选是Al和/或Si并且X优选是由N、O或B或其组合构成的组中的元素。本领域技术人员已知用于在叶片叶顶上有效涂覆这样的涂层的许多方法，其中，优选物理气相沉积例如阴极电弧沉积或者溅射。
根据本发明的另一方面，披露了一种使用硬薄膜涂层涂覆叶片的方法。此方面不仅涉及叶片叶顶和这些叶片叶顶的防可磨耗覆材的保护，也涉及所述叶片的防腐蚀颗粒例如以许多入射角度高速撞击叶片表面的灰尘的保护。如上所述，物理气相沉积是用于将这样的薄膜涂层涂覆到叶片表面的众多优选方法之一。例子是阴极电弧蒸发以及溅射。通常，阴极电弧蒸发提供极其致密而坚硬的层，其在本发明所关注的应用中是有利的。待沉积粒子带有大量正电荷时可以实现这种密度。向基材施加负偏电压将这些离子向待涂覆表面加速。但是，所形成的涂层通常具有相当大的表面粗糙度，这是因为所谓的液滴，其一般在电弧蒸发中产生且被沉积到表面且被并入薄膜中。如以上所讨论的，在涂覆叶顶的环境中，这样的粗糙度可能是不利的。除此之外，叶片表面上的表面粗糙度产生腐蚀粒子可攻击的中心并且产生天然地削弱防蚀保护的腐蚀中心。此外，表面粗糙度以偶然且难以控制的方式不利地影响到涡轮中的流动。存在在阴极电弧蒸发中主要地避免这种液滴沉积在薄膜表面上和并入薄膜中的技术。例如人们可以利用过滤电弧，在此磁场和/或电场被用来影响待沉积的带电粒子的飞行。因为液滴不带电或者它们主要是宏观的，以致不能被显著加速，故涂层颗粒在其到达待涂覆基材的途中与液滴分离。
溅射是基于物理气相沉积的用于涂覆薄膜至基材的另一优选方法。就溅射而言，所谓的工作气体的电离化粒子被加速到溅射靶的表面。当这些离子撞击靶表面时，靶材粒子被弹射而出。电离化工作气体粒子的加速基于施加至靶的负电压。因为这些粒子轰击靶使其变热，故可以运行靶的能量密度通常有限。溅射薄膜相比于通过阴极电弧蒸发沉积的薄膜显示出更低的表面粗糙度，因为在沉积过程中未形成液滴。但是，溅射颗粒通常不带电，或者电离化程度至少极低。因此，一旦颗粒离开材料提供靶的表面，这些颗粒可能无法向待涂覆表面加速。现在，本发明的发明人找到了途径并设想到采用特殊的PVD涂覆方法来涂覆叶片，这样的方法可获得高密度薄膜且不会在薄膜中并入任何液滴。
相应的方法基于溅射，但用以运行溅射过程的能量密度相比于传统溅射被显著提高。这样的提高可获得自靶表面射出的带电粒子，因此可以向待涂覆基材施加负偏电压以便使带电涂覆颗粒向基材加速。可以通过周期性地高频率地关断各自的靶上电压来避免靶变热。所谓的HIPIMS，如所述是一种溅射方法，但缺点是需要以高频率提供匀称且可再现的高功率脉冲的复杂的电力发电机。就由申请人研发的另一种溅射方法而言，功率未被关断，而是被切换至不同的靶和/或功率转储。申请人以商标“S3p”提供该方法。可以在专利申请WO2013/060415A1中找到实施相应溅射方法的一个例子的详细说明。
根据本发明的一个方面，可以加速涂层颗粒至这样的速度，即它们在撞击表面时所具有的速度与所预期的在叶片使用时灰尘颗粒撞击其表面的平均速度处于相同的量级内。
硬薄膜涂层优选通过HIPIMS、尤其优选通过S3p产生，且包括复合材料例如Me1Me2X，其中，Me1优选是由Ti、Cr或Zr或其组合构成的组中的元素，Me2优选是Al和/或Si并且X优选是由N、O或B或者其组合构成的组中的元素。
在以上描述中提到的所有PVD涂层可以是单层或多层的涂层。它们可以通过与涡轮叶片基材间的粘附层来涂覆，但优选直接涂覆到基材材料本身上。假设是多层，中间层例如金属中间层可以被预见到。也可以具有含有材料构成梯度(作为涂层厚度的函数)的一个或多个层，但优选是单层，尤其优选是AlCrN单层。
也可以用相对于叶片叶顶的其它涂层涂覆叶片主体表面。例如人们可以用将用于叶片叶顶的涂层来涂覆叶片的所有外露表面部分，该涂层优选可以是AlCrN单层。在此之后，可以遮掩所述叶顶并再用某种更软的薄膜材料涂覆其它表面部分以针对冲击这些表面的灰尘颗粒。
披露了一种具有涡轮段的涡轮发动机，其包括壳体和至少一个可转动地安装在所述壳体内的涡轮叶片，其中，壳体内表面的至少一部分覆盖有作为可磨耗材料的覆材以在所述至少一个叶片的叶顶和所述内表面间提供间隙控制，其中，所述叶片叶顶涂覆有硬PVD涂层，其特征是，该覆材至少包含且优选是多孔陶瓷基材料。
PVD涂层可以是包含复合材料例如Me1Me2X的涂层，其中，Me1优选是由Ti、Cr或Zr或其组合构成的组中的元素，Me2优选是Al和/或Si并且且X优选是由N、O或B或其组合构成的组中的元素。覆材至少可以包含且优选是锆基聚酯陶瓷材料。
披露了一种用于制造如以上所述涡轮发动机的涡轮发动机的方法，该方法包括以下步骤：
-将所述覆材热喷涂至壳体内表面，
-PVD涂覆有待用在壳体之内的叶片的至少叶顶。
PVD涂覆步骤可以通过高功率脉冲磁控管溅射来进行，其功率密度脉冲等于或大于5W/cm2且优选等于或小于50W/cm2、更优选等于或小于40W/cm2且最优选等于或小于30W/cm2。
可以由直流电力发电机提供所述功率并且所述脉冲通过将功率从一个材料输送溅射靶切换至另一个材料输送溅射靶和/或假靶来实现。
出乎意料地，通过高功率脉冲磁控管溅射所产生的PVD涂层95进一步显示出均匀的涂层厚度分布，与平均涂层厚度t的最大偏差约为10％，这是在叶片叶顶9上测定的。涂层厚度和性能的高度均匀性也适用于叶片叶顶9与涡轮叶片的周面91之间的被涂覆的角部沿线以及涡轮叶片周围，如图2所示。事实表明，基本上无液滴的涂层显示出极其致密的结构，其减小了运行时涂层失效的可能性。这种特征被认为是所述PVD涂层针对金属或陶瓷覆材的高耐用性的原因，几乎与它们的孔体积无关。
本发明的PVD涂层的几个变型例如Ti50Al50N、Ti40Al60N、Ti33Al67N以及Al50Cr50N、Al60Cr40N和Al70Cr30N已经被沉积并获得相似的良好的涂层厚度分布。如果PVD涂层95显示出40-70原子％的Me2含量(当从Me1Me2X中的Me2/(Me1+Me2)计算时，由此只考虑涂层的金属组成)，则已获得最佳的性能结果。
已经发现，本发明的PVD涂层能以薄层形式来沉积，例如1-40微米、优选5-25微米厚。

Claims (9)

1.一种至少具有高压涡轮段和低压涡轮段的涡轮发动机，包括壳体和至少一个可转动地安装在所述壳体中的涡轮叶片，
其中，所述壳体的内表面的至少一部分覆有作为可磨耗材料的覆材，以在所述内表面和所述至少一个叶片的叶顶之间提供间隙控制，并且其中，所述叶片叶顶涂覆有硬PVD涂层，
其特征是，
至少该高压段和/或该低压段的所述覆材包括多孔陶瓷基材料，并且在所述叶片叶顶上的所述硬PVD涂层主要由无液滴的氮化物涂层构成。
2.根据权利要求1的涡轮发动机，其特征是，所述基本上无液滴的PVD涂层是包含复合材料的涂层，所述复合材料例如是Me1Me2X，其中，Me1优选是由Ti、Cr或Zr或其组合构成的组中的元素，Me2优选是Al和/或Si并且X优选是由N、O或B或者其组合构成的组中的元素。
3.根据权利要求1的涡轮发动机，其特征是，所述基本上无液滴的PVD涂层由复合材料Me1Me2X构成，其中，Me2优选是Al和/或Si并且当计算Me2/(Me1+Me2)时，Me2在40-70原子％范围内。
4.根据权利要求1至3之一的涡轮发动机，其特征是，所述基本上无液滴的涂层具有1-40μm、优选5-25μm的涂层厚度。
5.根据权利要求1至4之一的涡轮发动机，其特征是，所述高压段和/或低压段的所述覆材至少包括且优选是锆基聚酯陶瓷材料。
6.一种制造根据权利要求1至5之一的涡轮发动机的方法，包括以下步骤：
-将所述覆材热喷涂至壳体的内表面，
-PVD涂覆所述壳体内的待用的叶片的至少叶顶。
7.根据权利要求6的方法，包括以下附加步骤：
-遮掩所述叶片叶顶并且
-用不同于所述叶片叶顶涂层的涂层，PVD涂覆所述叶片的主体。
8.根据权利要求6或7的方法，其特征是，PVD涂覆步骤通过高功率脉冲磁控管溅射进行，其功率密度脉冲等于或大于5W/cm2且优选等于或小于50W/cm2、更优选等于或小于40W/cm2且最优选等于或小于30W/cm2。
9.根据权利要求8的方法，其特征是，由直流电力发电机提供功率，且所述脉冲是通过将功率从一个材料输送溅射靶切换至另一个材料输送溅射靶和/或假靶来实现的。
CN201680077542.6A 2015-11-10 2016-11-09 涡轮间隙控制涂层和方法 Active CN108431290B (zh)

Applications Claiming Priority (5)

Application Number Priority Date Filing Date Title
US201562253194P 2015-11-10 2015-11-10
US62/253,194 2015-11-10
EP16000977.5 2016-05-01
EP16000977 2016-05-01
PCT/EP2016/001854 WO2017080645A1 (en) 2015-11-10 2016-11-09 Turbine clearance control coatings and method

Publications (2)

Publication Number Publication Date
CN108431290A true CN108431290A (zh) 2018-08-21
CN108431290B CN108431290B (zh) 2021-03-23

Family

ID=55862504

Family Applications (1)

Application Number Title Priority Date Filing Date
CN201680077542.6A Active CN108431290B (zh) 2015-11-10 2016-11-09 涡轮间隙控制涂层和方法

Country Status (8)

Country Link
US (1) US11859499B2 (zh)
EP (1) EP3374539B1 (zh)
KR (1) KR102630007B1 (zh)
CN (1) CN108431290B (zh)
CA (1) CA3004481C (zh)
ES (1) ES2928580T3 (zh)
PL (1) PL3374539T3 (zh)
WO (1) WO2017080645A1 (zh)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN110905607A (zh) * 2019-11-29 2020-03-24 中国航发沈阳黎明航空发动机有限责任公司 一种钛合金压气机叶尖间隙的控制方法
WO2021114068A1 (zh) * 2019-12-10 2021-06-17 中国航发贵州黎阳航空动力有限公司 一种航空发动机钛合金零件TiN涂层制备方法

Families Citing this family (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2949875B1 (en) 2014-05-27 2017-05-17 United Technologies Corporation Air seal with abradable layer comprising maxmet composite powders and method of manufacturing thereof
CA2965607C (en) * 2014-12-25 2019-07-23 Ihi Corporation Exfoliative coating for compressor vane or blade
CA2970492A1 (en) * 2016-08-31 2018-02-28 Skf Magnetic Mechatronics Landing bearing assembly and rotary machine equipped with such an assembly and a magnetic bearing
EP3326746A1 (en) * 2016-11-25 2018-05-30 Helmholtz-Zentrum Geesthacht Zentrum für Material- und Küstenforschung GmbH Method for joining and/or repairing substrates of titanium aluminide alloys
EP3631040B1 (en) 2017-05-23 2023-10-25 Oerlikon Surface Solutions AG, Pfäffikon Thick tialtan/alcrn multilayer coating films on turbine components
US11795295B2 (en) 2017-11-06 2023-10-24 Rtx Corporation Wear resistant coating, method of manufacture thereof and articles comprising the same
US10927685B2 (en) 2018-07-19 2021-02-23 Raytheon Technologies Corporation Coating to improve oxidation and corrosion resistance of abrasive tip system
US11073028B2 (en) 2018-07-19 2021-07-27 Raytheon Technologies Corporation Turbine abrasive blade tips with improved resistance to oxidation
US11028721B2 (en) * 2018-07-19 2021-06-08 Ratheon Technologies Corporation Coating to improve oxidation and corrosion resistance of abrasive tip system
FR3090426B1 (fr) * 2018-12-21 2022-02-11 Safran Procede de fabrication d’un noyau metallique, et procede de fabrication d’un bouclier de bord d’attaque d’une aube a partir d’un tel noyau metallique
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
US11536151B2 (en) 2020-04-24 2022-12-27 Raytheon Technologies Corporation Process and material configuration for making hot corrosion resistant HPC abrasive blade tips
US11066936B1 (en) * 2020-05-07 2021-07-20 Rolls-Royce Corporation Turbine bladed disc brazed sealing plate with flow metering and axial retention features
CN114807843A (zh) * 2022-04-19 2022-07-29 中国航发动力股份有限公司 一种涡轮工作叶片涂层工艺重量控制防护卡具及使用方法

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20050158171A1 (en) * 2004-01-15 2005-07-21 General Electric Company Hybrid ceramic matrix composite turbine blades for improved processibility and performance

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB9405744D0 (en) 1994-03-23 1994-05-11 Rolls Royce Plc A multilayer erosion resistant coating and a method for its production
DE4432998C1 (de) 1994-09-16 1996-04-04 Mtu Muenchen Gmbh Anstreifbelag für metallische Triebwerkskomponente und Herstellungsverfahren
GB2450933A (en) * 2007-07-13 2009-01-14 Hauzer Techno Coating Bv Method of providing a hard coating
WO2014126732A1 (en) 2013-02-12 2014-08-21 United Technologies Corporation Metallic coating fixed stator tip treatment
DE102013218687A1 (de) 2013-09-18 2015-04-02 MTU Aero Engines AG Galvanisch hergestellte Verschleißschutzbeschichtung und Verfahren hierfür
US20150078900A1 (en) 2013-09-19 2015-03-19 David B. Allen Turbine blade with airfoil tip having cutting tips

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20050158171A1 (en) * 2004-01-15 2005-07-21 General Electric Company Hybrid ceramic matrix composite turbine blades for improved processibility and performance

Non-Patent Citations (2)

* Cited by examiner, † Cited by third party
Title
R.RAJENDRAN: "Gas turbine coatings-An overview", 《ENGINEERING FAILURE ANALYSIS》 *
RONGHUA WEI ET AL: "Erosion Resistance of Thick Nitride and Carbonitride Coatings Deposited using Plasma Enhanced Magnetron Sputtering", 《PLASMA PROCESSES AND POLYMERS》 *

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN110905607A (zh) * 2019-11-29 2020-03-24 中国航发沈阳黎明航空发动机有限责任公司 一种钛合金压气机叶尖间隙的控制方法
WO2021114068A1 (zh) * 2019-12-10 2021-06-17 中国航发贵州黎阳航空动力有限公司 一种航空发动机钛合金零件TiN涂层制备方法

Also Published As

Publication number Publication date
PL3374539T3 (pl) 2022-12-05
CN108431290B (zh) 2021-03-23
KR20180075611A (ko) 2018-07-04
WO2017080645A8 (en) 2017-12-21
EP3374539A1 (en) 2018-09-19
KR102630007B1 (ko) 2024-01-26
EP3374539B1 (en) 2022-08-03
CA3004481A1 (en) 2017-05-18
CA3004481C (en) 2024-02-06
US11859499B2 (en) 2024-01-02
US20180347390A1 (en) 2018-12-06
ES2928580T3 (es) 2022-11-21
WO2017080645A1 (en) 2017-05-18

Similar Documents

Publication Publication Date Title
CN108431290A (zh) 涡轮间隙控制涂层和方法
JP4004577B2 (ja) 区画された摩耗しやすいシーリングシステム、区画された摩耗しやすいセラミックコーティング方法、ガスタービンエンジン構成要素流路ダクトセグメントコーティング、および区画された摩耗しやすいセラミックコーティング
EP2053141B1 (en) Alumina-based protective coating for thermal barrier coatings and process for depositing thereof
US8790789B2 (en) Erosion and corrosion resistant coatings, methods and articles
EP1254967B1 (en) Improved plasma sprayed thermal bond coat system
EP2088225B1 (en) Erosion and corrosion-resistant coating system and process therefor
EP1791989B1 (en) Chromium and active elements modified platinum aluminide coatings
US6620525B1 (en) Thermal barrier coating with improved erosion and impact resistance and process therefor
US9511436B2 (en) Composite composition for turbine blade tips, related articles, and methods
JP2008163449A (ja) 耐浸食性コーティング及び製法
EP2172577A2 (en) Surface treatments for turbine components to reduce particle accumulation during use thereof
RU2594092C2 (ru) Турбомашинный компонент с эрозионно- и коррозионно-устойчивой системой покрытия, а также способ изготовления такого компонента
US20100304084A1 (en) Protective coatings which provide erosion resistance, and related articles and methods
JP2010209913A (ja) 耐エロージョン性・耐食性タービン圧縮機翼形部及びその製造方法
EP3604742B1 (en) Outer airseal abradable rub strip
US20100304181A1 (en) Protective coatings which provide erosion resistance, and related articles and methods
EP3927863B1 (en) Dense abradable coating with brittle and abradable components
EP1391533B1 (en) Method for protecting articles, and related compositions
US8196600B1 (en) High-temperature jointed assemblies and wear-resistant coating systems therefor
CN104651835B (zh) 一种燃气轮机叶片复合涂层
JP2018535322A (ja) タービンのクリアランス制御コーティング及び方法
Arulvel et al. Wear/Erosion Resistant High-Temperature Coatings

Legal Events

Date Code Title Description
PB01 Publication
PB01 Publication
SE01 Entry into force of request for substantive examination
SE01 Entry into force of request for substantive examination
GR01 Patent grant
GR01 Patent grant