EP4263896A1 - Beschichtung für thermisch und abrasiv beladene turbinenschaufeln - Google Patents

Beschichtung für thermisch und abrasiv beladene turbinenschaufeln

Info

Publication number
EP4263896A1
EP4263896A1 EP21801831.5A EP21801831A EP4263896A1 EP 4263896 A1 EP4263896 A1 EP 4263896A1 EP 21801831 A EP21801831 A EP 21801831A EP 4263896 A1 EP4263896 A1 EP 4263896A1
Authority
EP
European Patent Office
Prior art keywords
layer
coating
mcraly
layers
blade tip
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.)
Pending
Application number
EP21801831.5A
Other languages
German (de)
English (en)
French (fr)
Inventor
Bernhard KOHLHAUSER
Jürgen RAMM
Oliver HUNOLD
Edgar BALTER
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 Pfaeffikon
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 Pfaeffikon filed Critical Oerlikon Surface Solutions AG Pfaeffikon
Publication of EP4263896A1 publication Critical patent/EP4263896A1/de
Pending legal-status Critical Current

Links

Classifications

    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C14/00—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material
    • C23C14/06—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material characterised by the coating material
    • C23C14/14—Metallic material, boron or silicon
    • C23C14/16—Metallic material, boron or silicon on metallic substrates or on substrates of boron or silicon
    • C23C14/165—Metallic material, boron or silicon on metallic substrates or on substrates of boron or silicon by cathodic 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
    • C23C14/00—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material
    • C23C14/0021—Reactive sputtering or evaporation
    • C23C14/0036—Reactive sputtering
    • C23C14/0057—Reactive sputtering using reactive gases other than O2, H2O, N2, NH3 or CH4
    • 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
    • C23C14/0635—Carbides
    • 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
    • C23C14/067—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
    • 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
    • C23C14/24—Vacuum evaporation
    • C23C14/32—Vacuum evaporation by explosion; by evaporation and subsequent ionisation of the vapours, e.g. ion-plating
    • C23C14/325—Electric arc evaporation
    • 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
    • C23C14/3407—Cathode assembly for sputtering apparatus, e.g. Target
    • C23C14/3414—Metallurgical or chemical aspects of target preparation, e.g. casting, powder metallurgy
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C28/00—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D
    • C23C28/30—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer
    • C23C28/32—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer
    • C23C28/321—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer with at least one metal alloy layer
    • C23C28/3215—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer with at least one metal alloy layer at least one MCrAlX layer
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C28/00—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D
    • C23C28/30—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer
    • C23C28/34—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one inorganic non-metallic material layer, e.g. metal carbide, nitride, boride, silicide layer and their mixtures, enamels, phosphates and sulphates
    • 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
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/10—Metals, alloys or intermetallic compounds
    • F05D2300/17—Alloys
    • F05D2300/175—Superalloys
    • 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
    • F05D2300/226—Carbides
    • 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
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/611—Coating

Definitions

  • Gas turbines have the task of moving a gas in one direction.
  • the gas turbine comprises at least one rotor which rotates about an axis and which has a carrier on the periphery of which a multiplicity of radially outwardly projecting turbine blades are arranged.
  • a turbine liner is provided to ensure a gap with a minimal gap distance between the turbine blade and the turbine liner.
  • inlet layers on the turbine lining side. These inlet layers serve to keep the gap distance between a turbine blade and the surrounding turbine liner as small as possible in order to prevent pressure losses.
  • the running-in layers are generally porous and only weakly bonded. The consequence of this is that the turbine blade tip, which at the beginning still frequently touches the running-in layer, wears it away until essentially contact-free concentricity is achieved with a minimal gap distance.
  • the turbine blades for example during their thermal expansion or vibration-induced deflection of the turbine from the center, can erode the porous and only weakly bonded running-in layer in an undesired manner and thus increase the gap spacing and reduce efficiency.
  • Blade tip coatings are used to protect the blade tip from wear. These blade tip coatings typically consist of abrasive particles (such as cubic boron nitride) embedded in a matrix (such as MCrAlY). “M” stands for a metal, which is usually cobalt, nickel or a cobalt-nickel alloy. “Cr” stands for chromium, “AI” for aluminum and “Y” stands for yttrium.
  • a disadvantage of the coatings produced in this way according to the prior art is the poor adhesion of the layers.
  • the energy input is relatively low and there are hardly any diffusion processes at the interface to the substrate surface, which normally ensure acceptable layer adhesion.
  • failure and delamination of the entire layer or the abrasive particles can already occur due to the forces occurring during rotation.
  • both the abrasive particles used in the prior art and the matrix are not resistant to oxidation at high temperatures and fail due to oxidation.
  • the abrasive particles typically used have a particle size in the order of magnitude of the layer thickness and can therefore reach from the surface to the interface between the coating and the substrate. If the particle is now oxidized, the blade material or the corresponding interface is directly attacked, which can lead to direct attack of the blade material or the interface between the blade material and the coating if the particle is oxidized.
  • the adhesion of blade tip coatings can be significantly improved through the use of reactive spark evaporation, since a higher energy input of the gas ions contributes to improved layer adhesion. Also the Manufacturing parameters can be chosen more freely, which means that deposition at higher temperatures is possible.
  • a bonding layer and/or matrix as well as abrasive phases such as oxides, borides, carbides or nitrides can be deposited in a single process. These phases can either be introduced as layers in a multilayer structure or as macroparticles in a matrix.
  • abrasive phases such as oxides, borides, carbides or nitrides
  • These phases can either be introduced as layers in a multilayer structure or as macroparticles in a matrix.
  • very small particles or thin layers can be completely embedded in a matrix (e.g.
  • a protective effect of the blade tip against the running-in layer on the lining can be achieved, even in the event of contact or abrasion situations after a longer period of operation than with conventional blade tip coatings.
  • the layer can consist of several layers, whereby an adhesive layer can be adapted to the substrate material in order to enable optimal adhesion.
  • the abrasive phase of the blade tip coating can be matched to the break-in coating on the turbine liner. These abrasive phases can be built into the layer either as layers or as particles.
  • Layer thicknesses can be varied in order to adapt the coating to the thermal and abrasive stress profile and thus increase service life.
  • a thermally less stressable layer can be deposited over the blade tip coating, for example to increase the wear resistance of the entire blade tip coating in the initial break-in process.
  • FIG. 1 schematically shows a layer system according to the invention made up of an MCrAlY layer and an overlying oxide layer.
  • FIG. 2 schematically shows a multilayer coating system according to the invention.
  • FIG. 3 shows the schematic representation of a turbine
  • FIG. 4 shows an SEM of the cross-section of a multilayer coating system according to the invention after it had been exposed to a temperature of 1200° C. for 10 hours
  • FIG. 5 shows the X-ray diffractogram of an abrasive phase of an aluminum oxide-chromium oxide.
  • the turbine shown in Figure 3 has at least one turbine blade 5 on a rotating disk 3 with a blade base 7 and a blade tip 9.
  • Figure 3 also shows a running-in layer 11 on a turbine liner 1 opposite the blade tip 9 and separated from it by a gap G.
  • a superalloy blade tip (may for example be single crystal) is deposited a coating of composition MCrAlY - aluminum chromium oxide, or a multilayer coating of alternating layers of MCrAlY - aluminum chromium oxide.
  • the MCrAlY layer can have thicknesses of 0.1 - 100 microns according to the required
  • the oxide layer is now deposited on the MCrAlY adhesion and oxidation protection layer.
  • the aluminum chromium oxide layers are made of metallic AlCr Targets deposited by reactive cathodic spark evaporation in an oxygen atmosphere.
  • the oxide layer can be 0.5 to 50 microns thick.
  • the oxide layer can also be deposited as a multi-layer coating in which the MCrAlY layer alternates with an aluminum-chromium oxide layer at regular or other intervals of 0.1-20 microns.
  • the oxide coating provides a diffusion barrier, which also serves as an abrasive phase that is not sensitive to oxidation.
  • the MCrAlY layer adhering directly to the substrate also provides excellent adhesion to the blade tip and the sum of all MCrAlY layers in the entire blade tip coating prevent inwardly oriented diffusion processes and efficiently protect the substrate from oxidation.
  • the hardness of the overall layer system according to the invention can be adjusted by the ratio of abrasive phase to MCrAlY in order to enable optimal removal of the running-in layer.
  • abrasive phase for example, layers with oxide phases in the range of 7 to 25 GPa can be adjusted.
  • harder abrasive phases such as nitrides, borides or carbides are used, the hardness can be increased up to 45 GPa.
  • the layer in Figure 4 has a hardness of about 13 GPa.
  • aluminum oxide-chromium oxide is used as the abrasive phase, it forms a mixed crystal in the corundum structure with a strong preferred orientation in the cathodic spark evaporation, as can be seen in FIG.
  • the mixed oxide is in its thermally stable high-temperature modification and can therefore reach the high application temperatures without phase transformation. The volume changes associated with the phase transformation, which can lead to the failure of the layer, can thus be prevented.

Landscapes

  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Materials Engineering (AREA)
  • Organic Chemistry (AREA)
  • Metallurgy (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Inorganic Chemistry (AREA)
  • General Engineering & Computer Science (AREA)
  • Physical Vapour Deposition (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Other Surface Treatments For Metallic Materials (AREA)
  • Application Of Or Painting With Fluid Materials (AREA)
EP21801831.5A 2020-12-15 2021-10-27 Beschichtung für thermisch und abrasiv beladene turbinenschaufeln Pending EP4263896A1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102020007662 2020-12-15
PCT/EP2021/000134 WO2022128144A1 (de) 2020-12-15 2021-10-27 Beschichtung für thermisch und abrasiv beladene turbinenschaufeln

Publications (1)

Publication Number Publication Date
EP4263896A1 true EP4263896A1 (de) 2023-10-25

Family

ID=78500592

Family Applications (1)

Application Number Title Priority Date Filing Date
EP21801831.5A Pending EP4263896A1 (de) 2020-12-15 2021-10-27 Beschichtung für thermisch und abrasiv beladene turbinenschaufeln

Country Status (7)

Country Link
US (1) US12392249B2 (https=)
EP (1) EP4263896A1 (https=)
JP (1) JP2023554044A (https=)
KR (1) KR20230122015A (https=)
CN (1) CN117083411A (https=)
CA (1) CA3206459A1 (https=)
WO (1) WO2022128144A1 (https=)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102023129550A1 (de) 2023-10-26 2025-04-30 Oerlikon Surface Solutions Ag, Pfäffikon Schicht mit eingebauten abrasiven Partikeln

Family Cites Families (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4328285A (en) * 1980-07-21 1982-05-04 General Electric Company Method of coating a superalloy substrate, coating compositions, and composites obtained therefrom
US6835465B2 (en) * 1996-12-10 2004-12-28 Siemens Westinghouse Power Corporation Thermal barrier layer and process for producing the same
US5935407A (en) * 1997-11-06 1999-08-10 Chromalloy Gas Turbine Corporation Method for producing abrasive tips for gas turbine blades
WO2000025005A1 (de) * 1998-10-22 2000-05-04 Siemens Aktiengesellschaft Erzeugnis mit wärmedämmschicht sowie verfahren zur herstellung einer wärmedämmschicht
US6394755B1 (en) * 2000-01-24 2002-05-28 General Electric Company Enhanced coating system for turbine airfoil applications
JP4502475B2 (ja) * 2000-08-04 2010-07-14 株式会社神戸製鋼所 硬質皮膜および耐摩耗部材並びにその製造方法
JP2011125943A (ja) * 2009-12-16 2011-06-30 Sumitomo Electric Ind Ltd 被膜、切削工具および被膜の製造方法
US9511572B2 (en) * 2011-05-25 2016-12-06 Southwest Research Institute Nanocrystalline interlayer coating for increasing service life of thermal barrier coating on high temperature components
DE102015212588A1 (de) * 2015-07-06 2017-01-12 Oerlikon Surface Solutions Ag, Trübbach Konturtreue Schutzschicht für Verdichterbauteile von Gasturbinen
KR102630007B1 (ko) * 2015-11-10 2024-01-26 오를리콘 서피스 솔루션스 아크티엔게젤샤프트, 페피콘 터빈 틈새 제어 코팅 및 방법
EP3612655A1 (en) * 2017-04-21 2020-02-26 Oerlikon Surface Solutions AG, Pfäffikon Superalloy sputtering target
US12196093B2 (en) * 2017-05-25 2025-01-14 Rtx Corporation Aluminum-chromium oxide coating and method therefor
EP3728695B1 (de) * 2017-12-22 2022-08-03 Oerlikon Surface Solutions AG, Pfäffikon Korrosions- und erosionsbeständige beschichtung für turbinenschaufeln von gasturbinen
US11661657B2 (en) * 2018-04-24 2023-05-30 Oerlikon Surface Solutions Ag, Pfäffikon Coating comprising MCrAl-X coating layer
KR102806680B1 (ko) * 2018-10-17 2025-05-13 외를리콘 서피스 솔루션즈 아게, 페피콘 초합금 기재용 pvd 배리어 코팅

Also Published As

Publication number Publication date
KR20230122015A (ko) 2023-08-22
US12392249B2 (en) 2025-08-19
CN117083411A (zh) 2023-11-17
CA3206459A1 (en) 2022-06-23
JP2023554044A (ja) 2023-12-26
US20240026793A1 (en) 2024-01-25
WO2022128144A1 (de) 2022-06-23

Similar Documents

Publication Publication Date Title
KR102630007B1 (ko) 터빈 틈새 제어 코팅 및 방법
DE69831779T2 (de) Keramische Ueberzuege mit mehrschichtiger Porositaet
DE69509293T2 (de) Mehrfachlagiger erosionsresistenter Überzug und Verfahren zu seiner Herstellung
EP2398936B1 (de) Erosionsschutz-beschichtungssystem fur gasturbinenbauteile
DE2829369C3 (de) Verfahren zum Ausbilden von harten, verschleißfestenMetallkarbide enthaltenden Überzügen
DE60038355T2 (de) Verfahren zur Herstellung von Beschichtungen aus Keramik
US10041361B2 (en) Turbine blade coating composition
EP2084307B1 (en) Multilayer nitride-containing coatings
US5952085A (en) Multiple layer erosion resistant coating and a method for its production
CH704833A1 (de) Komponente für eine Turbomaschine und ein Verfahren zum Herstellen einer derartigen Komponente.
DE102015114981A1 (de) Eine Einlaufdichtung und Verfahren zur Herstellung einer Einlaufdichtung
Houdková et al. The high-temperature wear and oxidation behavior of CrC-based HVOF coatings
EP1637622A1 (de) Verfahren zum Aufbringen einer Schutzschicht
DE102016002630A1 (de) Haftvermittlerschicht zur Anbindung einer Hochtemperaturschutzschicht auf einem Substrat, sowie Verfahren zur Herstellung derselben
EP3320127B1 (de) Konturtreue schutzschicht für verdichterbauteile von gasturbinen
EP1260602B1 (de) Verfahren zum Erzeugen eines wärmedämmenden Schichtsystems auf einem metallischen Substrat
DE112009002430T5 (de) Verfahren zur Abscheidung einer Beschichtung auf eine Blisk
EP4263896A1 (de) Beschichtung für thermisch und abrasiv beladene turbinenschaufeln
WO2019122229A1 (de) Korrosions- und erosionsbeständige beschichtung für turbinenschaufeln von gasturbinen
WO2020177999A1 (de) Zweilagige abrasive schicht für laufschaufelspitze, verfahren, bauteil und turbinenanordnung
WO2018209374A1 (de) VERFAHREN ZUR VERBESSERUNG DER VERSCHLEIßBESTÄNDIGKEIT EINES BAUTEILS
WO2012038217A1 (de) Turbinenschaufel mit keramischer erosionsschutzschicht für eine niederdruckstufe einer dampfturbine
US20230160316A1 (en) Abrasive material, a method for manufacturing an abrasive material and a substrate coated with an abrasive material
EP3947776A1 (de) Schweissverfahren mit ummantelten abrasiven teilchen, ummanteltes abrasives teilchen, schichtsystem und dichtungssystem
DE69835208T2 (de) Haftbeschichtung für wärmedämmendes Beschichtungssystem

Legal Events

Date Code Title Description
STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: UNKNOWN

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

Free format text: STATUS: THE INTERNATIONAL PUBLICATION HAS BEEN MADE

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

Free format text: ORIGINAL CODE: 0009012

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

Free format text: STATUS: REQUEST FOR EXAMINATION WAS MADE

17P Request for examination filed

Effective date: 20230615

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

DAV Request for validation of the european patent (deleted)
DAX Request for extension of the european patent (deleted)