EP2714957A1 - Procédé d'application d'une couche de protection, élément revêtu d'une couche de protection et turbine à gaz dotée d'un tel élément - Google Patents

Procédé d'application d'une couche de protection, élément revêtu d'une couche de protection et turbine à gaz dotée d'un tel élément

Info

Publication number
EP2714957A1
EP2714957A1 EP12725000.9A EP12725000A EP2714957A1 EP 2714957 A1 EP2714957 A1 EP 2714957A1 EP 12725000 A EP12725000 A EP 12725000A EP 2714957 A1 EP2714957 A1 EP 2714957A1
Authority
EP
European Patent Office
Prior art keywords
layer
diffusion layer
component
diffusion
protective layer
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.)
Withdrawn
Application number
EP12725000.9A
Other languages
German (de)
English (en)
Inventor
Norbert Czech
Sharad Chandra
Roland Herzog
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.)
MAN Energy Solutions SE
Original Assignee
MAN Diesel and Turbo SE
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 MAN Diesel and Turbo SE filed Critical MAN Diesel and Turbo SE
Publication of EP2714957A1 publication Critical patent/EP2714957A1/fr
Withdrawn legal-status Critical Current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
    • C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
    • C23C4/04—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge characterised by the coating material
    • C23C4/10—Oxides, borides, carbides, nitrides or silicides; Mixtures thereof
    • C23C4/11—Oxides
    • 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
    • C23C10/00—Solid state diffusion of only metal elements or silicon into metallic material surfaces
    • C23C10/02—Pretreatment of the material to be coated
    • 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
    • C23C10/00—Solid state diffusion of only metal elements or silicon into metallic material surfaces
    • C23C10/28—Solid state diffusion of only metal elements or silicon into metallic material surfaces using solids, e.g. powders, pastes
    • C23C10/34—Embedding in a powder mixture, i.e. pack cementation
    • C23C10/36—Embedding in a powder mixture, i.e. pack cementation only one element being diffused
    • C23C10/48—Aluminising
    • 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
    • C23C10/00—Solid state diffusion of only metal elements or silicon into metallic material surfaces
    • C23C10/60—After-treatment
    • 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
    • C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
    • C23C4/02—Pretreatment of the material to be coated, e.g. for coating on selected surface areas
    • 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
    • C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
    • C23C4/04—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge characterised by the coating material
    • C23C4/06—Metallic material
    • C23C4/073—Metallic material containing MCrAl or MCrAlY alloys, where M is nickel, cobalt or iron, with or without non-metal elements
    • 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
    • C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
    • C23C4/04—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge characterised by the coating material
    • C23C4/10—Oxides, borides, carbides, nitrides or silicides; Mixtures thereof
    • 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
    • C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
    • C23C4/12—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge characterised by the method of spraying
    • C23C4/134—Plasma spraying
    • 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
    • C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
    • C23C4/18—After-treatment
    • 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

Definitions

  • the invention relates to a method for applying a protective layer on a base metal detail with the features of the preamble of claim 1 and a coated with such a protective layer component for use in a
  • a method of the type mentioned in the introduction is e.g. from EP 1 637 622 A1.
  • Thermal barrier coatings serve to lower the material temperature of cooled components. As a result, their life can be extended, cooling air saved or the gas turbine can be operated with higher inlet temperatures.
  • Thermal barrier coating systems always consist of a metallic adhesive layer connected by diffusion to the base metal ⁇ base metal) and an overlying ceramic layer with poor thermal conductivity, which represents the actual barrier against heat flow and protects the base metal detail against high temperature corrosion and high temperature erosion.
  • Ceramic material for the thermal barrier coating has zirconia
  • thermal insulation layers are classified according to the respective application method into two main classes.
  • a first class are thermal barrier coatings by physical
  • thermal barrier coating is chemically bonded by formation of an Al, Zr mixed oxide on a pure alumina (TGO) film formed by the bond coat during application and then in service.
  • TGO pure alumina
  • thermal barrier coatings which are sprayed thermally (usually with atmospheric plasma, APS).
  • Thermal barrier coatings depending on the desired layer thickness and stress distribution, a porosity between about 10 and 25 vol .-% set. Since the bonding of the ceramic layer to the adhesive layer should take place here by mechanical clamping, the adhesive layer is sprayed in a targeted rough manner in order to maximize the interface and thus the adhesion forces. A certain amount of chemical bonding due to TGO formation only occurs during long-term operation. This application process is relatively simple, resulting in relatively cheap coating costs.
  • the invention has the object of developing a method according to the preamble of claim 1 so that it achieves a good thermal fatigue resistance of the protective layer, but nevertheless can be carried out in a simple manner. This is achieved with the features in the characterizing part of claim 1 reached
  • the invention is also based on the object, one with a against
  • Protective layer on the component can be produced in a simple manner and has a good thermal fatigue resistance. This is achieved with a component according to claim 7 or with a gas turbine according to claim 8.
  • M Ni, Co
  • MCrAlY layers contain the intermetallic ß phase NiCoAl as an aluminum supply, but this also has a
  • the MCrAlY layers are overly aluminized with an Al diffusion layer. Because of the risk of embrittlement, this is largely due to aluminum arms (AI ⁇ 8%)
  • the structure of an aluminized MCrAlY layer consists of an inner, largely unchanged y, ß mixed phase, ie a diffusion zone in which the Al content increases to about 20%, and an outer ß-NiAl phase with a proportion of about 30% AI.
  • This outer ß-NiAi phase represents a certain weak point of the layer system in terms of brittleness and crack sensitivity. It therefore becomes subjected the overaligned layer to an abrasive treatment so that the outer ⁇ -NiAl phase is removed down to the diffusion zone.
  • the aluminum activity is favorably influenced, so that the ability to TGO formation is favored.
  • a good bonding of the ceramic layer can be achieved without the need for a rough adhesion layer, which makes it possible, inter alia, for the MC rAI Y layer by means of low-pressure plasma spraying (LPPS) or by thermal spraying, for example high-speed flame spraying (HVOF ) or vacuum plasma spraying.
  • LPPS low-pressure plasma spraying
  • HVOF high-speed flame spraying
  • vacuum plasma spraying for example high-speed flame spraying (HVOF ) or vacuum plasma spraying.
  • High-speed fluid injection is less expensive and tends to produce smoother surfaces.
  • a method of applying a high temperature corrosion and high temperature erosion resistant protective layer to a base metal wherein an MCrAlY based adhesive layer is applied to the base metal, the adhesive layer
  • Overalumination is coated with an Al diffusion layer, the Al diffusion layer is subjected to an abrasive treatment, so that an outer build-up layer of the Al diffusion layer is removed, and on the remaining Al diffusion layer, a ceramic thermal barrier layer of yttria partially stabilized zirconia is applied.
  • the method is characterized in that the ceramic thermal barrier coating is applied to the remaining AL diffusion layer by atmospheric plasma spraying.
  • the applied adhesive layer is subjected to a smoothing treatment prior to its over-alkalization.
  • a smoothing treatment Preferably, in the smoothing treatment, a surface roughness of Ra ⁇ 2 ⁇ m is generated on the adhesive layer.
  • the adhesive layer is applied to the base metal by means of thermal spraying, for example high-speed flame spraying (HVOF) or vacuum plasma spraying of high-velocity flame spraying or vapor phase deposition.
  • HVOF high-speed flame spraying
  • vapor phase deposition for example high-speed flame spraying (HVOF) or vacuum plasma spraying of high-velocity flame spraying or vapor phase deposition.
  • the AL diffusion layer is subjected to a smoothing treatment, such that a smoothing treatment takes place on the remaining AL diffusion layer
  • the outer build-up layer of the AL diffusion layer is removed so far that the content of Al in a surface of the remaining Al diffusion layer exceeds 18 wt%. and less than 30% by weight.
  • a component for use in a hot gas region of a gas turbine having a surface which is at least partially applied in any conceivable combination by a method according to one, several or all of the previously described embodiments of the invention
  • High temperature corrosion and high temperature erosion resistant protective coating is provided.
  • a gas turbine having a hot gas area and a component arranged therein according to the second aspect of the invention.
  • the protective layer has a good thermal endurance, but can nevertheless be produced in a simple manner.
  • the invention provides a thermal barrier coating concept that combines the low cost of the APS process with the advantages of chemical bonding between the adhesive and ceramic layers.
  • the TCF behavior compared to the classic APS layers can be improved.
  • thermal barrier coatings with improved thermal endurance can be produced more easily and thus at lower cost than with EB-PVD processes.
  • FIG. 1 shows in a sectional view a region provided with a protective layer of a component of a component arranged in a hot gas region Gas turbine according to an embodiment of the invention.
  • FIG. 1 shows a sectional view of a region of a component 10, which is provided in a hot gas region, provided with a protective layer 12-14
  • Gas turbine 1 according to an embodiment of the invention.
  • the component 10 ' which for example can be designed as a turbine blade or as another hot gas to come into contact component of the gas turbine 1 "has a base metal 11 (base material) having a surface on" the protection against high-temperature corrosion and high-temperature erosion completely or partially with a
  • resistant ceramic thermal barrier coating 13 is provided.
  • the ceramic thermal barrier coating 13 consists of
  • Zirconia partially stabilized with about 7% by weight of yttria International Abbreviation: "YPSZ" by Ytfria Partially Stabiiised Zirconia.
  • the adhesive layer 12 is made of a MCrAlY based special alloy (e.g., LCO 22).
  • LPPS Low-pressure plasma spraying
  • High speed flame spraying HVOF
  • the applied adhesive layer 12 is subjected to a smoothing treatment (e.g., fine flattening), to which an adhesive layer 12 is applied
  • the overbalancing can be realized by a treatment in which a reactive Al-containing gas, which may be an Al halide (AIX2), at higher temperature
  • the outer make coat 14.2 is subjected to abrasive treatment such as abrasion treatment.
  • abrasive treatment such as abrasion treatment.
  • Hard particle blasting e.g., corundum, silicon carbide, reduced metal wires, etc.
  • machining with other known grinding or grinding techniques
  • polishing down to the inner diffusion zone 14.1 of the Al diffusion layer 14 removed.
  • the abrasive treatment is driven so far that the surface of the remaining Al diffusion layer 14 (diffusion zone 14.1) has an Al content of more than about 18% by weight and less than about 30% by weight.
  • the AL diffusion layer 14 is subjected to a smoothing treatment (e.g., fine flattening), so that a surface roughness of .mu.m is applied to the remaining AL diffusion layer 14 (diffusion zone 14.1)
  • a smoothing treatment e.g., fine flattening
  • the ceramic thermal barrier coating (YPSZ ceramic layer) 13 is then applied to the thus prepared surface of the remaining aluminum diffusion layer 14 by atmospheric plasma spraying (APS), wherein the same parameters can be used for the APS process as in the conventional one Adhesive layers.
  • APS atmospheric plasma spraying

Landscapes

  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Materials Engineering (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Plasma & Fusion (AREA)
  • Physics & Mathematics (AREA)
  • General Engineering & Computer Science (AREA)
  • Coating By Spraying Or Casting (AREA)
  • Other Surface Treatments For Metallic Materials (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

L'invention concerne un procédé d'application d'une couche de protection, un élément revêtu d'une couche de protection et une turbine à gaz dotée d'un tel élément. Selon ce procédé, une couche adhésive (12) à base de MCrAI Y est appliquée sur un métal de base (11), la couche adhésive (12) est revêtue d'une couche de diffusion d'Al (14) par calorisation, la couche de diffusion d'Al (14) est soumise à un traitement abrasif, de sorte qu'une couche de formation extérieure (14.2) de la couche de diffusion d'Al (14) soit retirée. Une couche d'isolation thermique céramique (13) composée d'oxyde de zirconium en partie stabilisé par de l'oxyde d'yttrium est appliquée sur la couche de diffusion d'Al (14) subsistante, de sorte qu'une couche de protection résistante à la corrosion due à une température élevée et à l'érosion due à une température élevée soit produite. Le procédé selon l'invention permet d'obtenir une bonne résistance à la fatigue thermique de la couche de protection et peut être mis en oeuvre facilement. A cet effet, la couche d'isolation thermique céramique (13) est appliquée par projection au plasma atmosphérique sur la couche de diffusion d'Al (14) subsistante.
EP12725000.9A 2011-05-31 2012-05-31 Procédé d'application d'une couche de protection, élément revêtu d'une couche de protection et turbine à gaz dotée d'un tel élément Withdrawn EP2714957A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102011103731A DE102011103731A1 (de) 2011-05-31 2011-05-31 Verfahren zum Aufbringen einer Schutzschicht, mit einer Schutzschicht beschichtetes Bauteil und Gasturbine mit einem solchen Bauteil
PCT/EP2012/060195 WO2012163991A1 (fr) 2011-05-31 2012-05-31 Procédé d'application d'une couche de protection, élément revêtu d'une couche de protection et turbine à gaz dotée d'un tel élément

Publications (1)

Publication Number Publication Date
EP2714957A1 true EP2714957A1 (fr) 2014-04-09

Family

ID=46201638

Family Applications (1)

Application Number Title Priority Date Filing Date
EP12725000.9A Withdrawn EP2714957A1 (fr) 2011-05-31 2012-05-31 Procédé d'application d'une couche de protection, élément revêtu d'une couche de protection et turbine à gaz dotée d'un tel élément

Country Status (6)

Country Link
US (1) US20140141276A1 (fr)
EP (1) EP2714957A1 (fr)
JP (1) JP5878629B2 (fr)
CA (1) CA2837415C (fr)
DE (1) DE102011103731A1 (fr)
WO (1) WO2012163991A1 (fr)

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FR3002239B1 (fr) * 2013-02-15 2015-04-10 Messier Bugatti Dowty Procede de fabrication d'une piece d'aeronef comportant un substrat et une couche de revetement du substrat
US9518325B2 (en) * 2013-03-19 2016-12-13 General Electric Company Treated coated article and process of treating a coated article
CN104404436B (zh) * 2014-11-25 2017-02-22 西安交通大学 基于液相过滤的低压等离子喷涂制备柱状陶瓷涂层的方法
DE102016103664A1 (de) 2016-03-01 2017-09-07 Lufthansa Technik Ag Strömungselement und Verfahren zum Beschichten eines Strömungselements
GB201903484D0 (en) * 2019-03-14 2019-05-01 Rolls Royce Plc A method of removing a ceramic coating from a ceramic coated metallic article

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Also Published As

Publication number Publication date
CA2837415A1 (fr) 2012-12-06
JP5878629B2 (ja) 2016-03-08
CA2837415C (fr) 2016-11-08
US20140141276A1 (en) 2014-05-22
JP2014520205A (ja) 2014-08-21
WO2012163991A1 (fr) 2012-12-06
DE102011103731A1 (de) 2012-12-06

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