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EP1931811A1 - Composition seche, son utilisation et procede de revetement - Google Patents

Composition seche, son utilisation et procede de revetement

Info

Publication number
EP1931811A1
EP1931811A1 EP06806827A EP06806827A EP1931811A1 EP 1931811 A1 EP1931811 A1 EP 1931811A1 EP 06806827 A EP06806827 A EP 06806827A EP 06806827 A EP06806827 A EP 06806827A EP 1931811 A1 EP1931811 A1 EP 1931811A1
Authority
EP
European Patent Office
Prior art keywords
dry composition
carbon
protective layer
layer
substrate
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Withdrawn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
EP06806827A
Other languages
German (de)
English (en)
Inventor
Roman Karmazin
Steffen Walter
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.)
Siemens AG
Original Assignee
Siemens AG
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 Siemens AG filed Critical Siemens AG
Priority to EP06806827A priority Critical patent/EP1931811A1/fr
Publication of EP1931811A1 publication Critical patent/EP1931811A1/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Withdrawn legal-status Critical Current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
    • C23C10/00—Solid state diffusion of only metal elements or silicon into metallic material surfaces
    • C23C10/04—Diffusion into selected surface areas, e.g. using masks
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
    • B22F1/00—Metallic powder; Treatment of metallic powder, e.g. to facilitate working or to improve properties
    • B22F1/10—Metallic powder containing lubricating or binding agents; Metallic powder containing organic material
    • B22F1/107—Metallic powder containing lubricating or binding agents; Metallic powder containing organic material containing organic material comprising solvents, e.g. for slip casting
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C1/00—Making non-ferrous alloys
    • C22C1/04—Making non-ferrous alloys by powder metallurgy
    • C22C1/0433—Nickel- or cobalt-based alloys
    • 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
    • C23C14/042—Coating on selected surface areas, e.g. using masks 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
    • C23C16/00—Chemical coating by decomposition of gaseous compounds, without leaving reaction products of surface material in the coating, i.e. chemical vapour deposition [CVD] processes
    • C23C16/04—Coating on selected surface areas, e.g. using masks
    • C23C16/042—Coating on selected surface areas, e.g. using masks 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
    • C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
    • C23C4/01—Selective coating, e.g. pattern coating, without pre-treatment of the material to be coated
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
    • B22F2998/00—Supplementary information concerning processes or compositions relating to powder metallurgy
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
    • B22F2998/00—Supplementary information concerning processes or compositions relating to powder metallurgy
    • B22F2998/10—Processes characterised by the sequence of their steps
    • 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
    • Y10T428/31504—Composite [nonstructural laminate]
    • Y10T428/31678—Of metal

Definitions

  • the invention relates to a dry composition, a use thereof, a layer system and a method for coating.
  • the object is achieved by a dry composition according to claim 1 and by a use of those according to claim 5.
  • the object is achieved by a layer system according to ⁇ demanding. 6
  • the object is achieved by a method according to claim 11.
  • FIG. 3 4 schematically a component with local masking and a method for coating
  • FIG. 5, 6 further exemplary embodiments of the invention
  • FIG. 7 a perspective view of a gas turbine
  • FIG. 8 a perspective view of a combustion chamber
  • Figure 9 is a perspective view of a turbine blade.
  • Figure 1 shows a component 1, be a substrate 4 ⁇ is, is applied to the protective layer. 7
  • the component 1 can be a turbine blade 120, 130 (FIG. 9), a housing 138 (FIG. 7) or a combustion chamber element 155 (FIG. 8) of a steam or gas turbine 100 (FIG be any component which is coated by a known coating method.
  • the substrate 4 has an outer surface 10 and an inner surface 13, wherein the outer surface 10 is not to be coated in a coating process, so that the outer surface 10 is the non-coating area 11. Therefore, the protective layer 7 is applied on the entire surface 11.
  • the protective layer 7 comprises a dry composition according to the invention consisting of carbon (C) and nickel (Ni) powder.
  • the carbon may be in chemically bonded form with other chemical elements, especially as an organic binder, which converts to carbon upon heat treatment (curing).
  • the carbon of the dry composition may be present at least partially, in particular completely in chemically bound form.
  • the carbon of the dry composition may be at least partially or completely of a det ⁇ carbon powder, such as graphite powder or carbon black gebil-.
  • the carbon of the dry composition ⁇ reduction of carbon in powder form and a binder which is converted to a heat treatment process in carbon.
  • the dry composition can be applied to the surface 11 of a component 1, 120, 130, 138, 155 in the form of a paste or a slurry.
  • the protective layer 7 can be applied to each surface 10 or 13 of the component 1, 120, 130 and is preferably applied as a slurry over a large area, but also locally limited to the component 1, 120, 130, 138, 155.
  • the binder is either so soft (viscous) that it can be applied as a paste or a solvent (for example water, alcohol) is added to the dry composition which lowers the viscosity sufficiently.
  • a solvent for example water, alcohol
  • the binder is mixed with novolac.
  • Base resin Novolak is a polymer product of phenol and / or cresol and formaldehyde, which is formed by polycondensation reaction.
  • the number of chain segments n is about 1000 to 2000.
  • Novolac is a very brittle material, its softening point is about 100 0 C.
  • Another non-carbonaceous binder or other carbonaceous binder can be added to the dry composition, paste, or slurry.
  • the binder and / or the carrier can be expelled and preferably the nickel carbon ⁇ powder be sintered.
  • the protective layer 7 is preferably suitable for gas-phase coating processes such as.
  • a gas-phase coating process such as.
  • a masking is formed by the protective layer 7, which acts as a diffusion barrier by the nickel reacts with the gaseous coating material.
  • the nickel reacts to nickel aluminum (eg Al 3 Ni), whereby the protective effect of the protective layer 7 continues to increase.
  • the coating material can not layer by this protection ⁇ penetrate 7th
  • the resulting protective layer 7 is often very brittle and can by a simple decoating method such. B. dry ice blasting are removed.
  • Such a protective layer 7 can be used in a chromation.
  • the Ni / C composition is used in nickel-based materials, as here a diffusion of nickel of the substrate 4 in the masking or a reaction of
  • Nickel of the substrate 4 with the nickel-containing protective layer 7 is reduced or even prevented, since a concentration ⁇ gradient is present, which counteracts.
  • the particular higher nickel content in the protective layer 7 during the coating process forms a nickel concentration gradient. This prevents the Dif ⁇ fusion of nickel from the base material in the devis perennialna ⁇ hen layers.
  • the higher nickel concentration in the protective layer 7 on the surface 11 of the substrate 4 counteracts the nickel diffusion in the substrate 4 and prevents its segregation.
  • FIG. 2 shows a further protective layer 7 'according to the invention.
  • the protective layer 7 ' is constructed in two layers, wherein the protective layer 7 has ben as in Figure 1 beschrie ⁇ the composition. However, below the protective layer 7 there is a further layer 8, which in particular rests directly on the substrate 4.
  • the protective layer 8 is a carbons ⁇ -containing layer, which either only of carbon or Kohlenstoffprecursormaterialien such. B. organic materials.
  • the layer 8 consists of carbon powder and a binder, which in turn advantageously novolak is used.
  • This carbon-containing layer allows the lighter Ent ⁇ fernung the protective layer 7, after the component 1, 120, 130, 155 was coated, as the carbon layer 8 does not react with the substrate 4 and not material comes with the coating in contact.
  • this two-ply layer system 7 ' is used in an alitization.
  • Figure 3 schematically shows a process sequence of OF INVENTION ⁇ to the invention coating process.
  • the substrate 4 is not to be coated in a region 11, so that locally a paste or a slip on the
  • FIG. 3 shows a comparable and schematic process sequence as in FIG. 3, with the difference that no layer 16 is formed on the surface 10 here, but rather that the coating material, here likewise, for example, aluminum, locally penetrates into the substrate 4, so that local regions are formed 19 with an increased aluminum content ausbil ⁇ the.
  • Figure 5 shows a further embodiment of the method according OF INVENTION ⁇ dung and a further use of the protective layer. 7
  • the component 1, 120, 130, 155 has a cavity 22 which is to be coated entirely or locally alone. This is the game as if the outer surface of the sub ⁇ strats 4 already an MCrAlX layer and optionally bearing a ceramic layer at ⁇ the case, but the cavity 22 is also aluminized onstik disrupt to corrosion or is to be chromed.
  • a paste or slurry for forming a protective layer 7 is applied to the outer surface 10 of the substrate 4 or an outer coating on the substrate 4 so that no coating material can reach the outer surface 11 and only one coating takes place in the cavity 22 ,
  • FIG. 7 shows by way of example a gas turbine 100 in a longitudinal partial section.
  • the gas turbine 100 has an axis by a rotational ⁇ 102 rotatably mounted rotor 103 having a shaft 101, which is also referred to as the turbine rotor.
  • an intake housing 104 a compressor 105, for example, a toroidal combustion chamber 110, in particular annular combustion chamber, with a plurality of coaxially arranged burners 107, a turbine 108 and the exhaust housing 109th
  • a compressor 105 for example, a toroidal combustion chamber 110, in particular annular combustion chamber, with a plurality of coaxially arranged burners 107, a turbine 108 and the exhaust housing 109th
  • the annular combustion chamber 110 communicates with an annular annular hot gas channel 111, for example.
  • An annular annular hot gas channel 111 for example.
  • turbine stages 112 connected in series form the turbine 108.
  • Each turbine stage 112 is formed, for example, from two blade rings .
  • a series 125 formed of rotor blades 120 follows.
  • the guide vanes 130 are fastened to an inner housing 138 of a stator 143, whereas the moving blades 120 of a row 125 are attached to the rotor 103 by means of a turbine disk 133, for example. Coupled to the rotor 103 is a generator or work machine (not shown).
  • air 135 is sucked by the compressor 105 through the intake housing and ver ⁇ seals.
  • the loading 105 compressed air provided at the turbine end of the compressor to the burners leads 107 ge ⁇ where it is mixed with a fuel.
  • the mixture is then burned to form the working fluid 113 in the combustion chamber 110.
  • the working medium 113 flows along the hot gas channel 111 past the guide vanes 130 and the rotor blades 120.
  • the working medium 113 expands in a pulse-transmitting manner, so that the rotor blades 120 drive the rotor 103 and drive the machine coupled to it.
  • the components exposed to the hot working medium 113 are subject to thermal loads during operation of the gas turbine 100.
  • the guide vanes 130 and rotor blades 120 of the first turbine stage 112, viewed in the flow direction of the working medium 113, are subjected to the greatest thermal stress in addition to the heat shield elements lining the annular combustion chamber 110. To withstand the prevailing temperatures, they can be cooled by means of a coolant.
  • substrates of the components may have a directional structure, i. they are monocrystalline (SX structure) or have only longitudinal grains (DS structure).
  • Iron, nickel or cobalt-based superalloys are used as material for the components, in particular for the turbine blades 120, 130 and components of the combustion chamber 110.
  • Such superalloys are known, for example, from EP 1 204 776 B1, EP 1 306 454, EP 1 319 729 A1, WO 99/67435 or WO 00/44949; These documents are part of the disclosure regarding the chemical composition of the alloys.
  • the blades 120, 130 may be anti-corrosion coatings (MCrAlX; M is at least one element of the group iron (Fe), cobalt (Co), nickel (Ni), X is an active element and is yttrium (Y) and / or silicon and / or at least one element of the rare earths or hafnium).
  • M is at least one element of the group iron (Fe), cobalt (Co), nickel (Ni)
  • X is an active element and is yttrium (Y) and / or silicon and / or at least one element of the rare earths or hafnium).
  • Such alloys are known from EP 0 486 489 B1, EP 0 786 017 B1, EP 0 412 397 B1 or EP 1 306 454 A1, which are to be part of this disclosure with regard to the chemical composition.
  • MCrAlX may still be present a thermal barrier coating, and consists for example of ZrO 2 , Y 2 O 3 -ZrO 2 , ie it is not, partially or completely stabilized by yttrium oxide and / or calcium oxide and / or magnesium oxide.
  • Suitable coating processes such as electron beam evaporation (EB-PVD), produce stalk-shaped grains in the thermal barrier coating.
  • the guide vane 130 has an inner housing 138 of the turbine 108 facing guide vane root (not provide Darge ⁇ here) and a side opposite the guide-blade root vane root.
  • the vane head faces the rotor 103 and fixed to a mounting ring 140 of the stator 143.
  • the combustion chamber 110 is designed for example as so-called an annular combustion chamber, in the circumferential direction in which a plurality of an axis of rotation 102 of burners 107 arranged in a common combustion chamber space 154, the flames 156 generate.
  • the combustion chamber 110 is configured in its entirety as an annular structure, which is positioned around the axis of rotation 102 around.
  • the combustion chamber 110 is designed for a comparatively high temperature of the working medium M of about 1000 ° C. to 1600 ° C.
  • the combustion chamber wall 153 is provided on its side facing the medium M, Anlagenme- facing side with a formed from heat shield elements 155. liner.
  • Each heat shield element 155 made of an alloy is equipped on the working fluid side with a particularly heat-resistant protective layer (MCrAlX layer and / or ceramic coating) or is made of high-temperature-resistant material (solid ceramic blocks).
  • M is at least one element of the group iron (Fe), cobalt (Co), nickel (Ni), X is an active element and stands for yttrium (Y) and / or
  • Such alloys are known from EP 0 486 489 B1, EP 0 786 017 Bl, EP 0 412 397 B1 or EP 1 306 454 Al, which should be part of this disclosure with respect to the chemical composition of the alloy.
  • a ceramic thermal insulation layer may be present and consists for example of ZrO 2 , Y 2 O 4 -ZrO 2 , ie it is not, partially or fully ⁇ dig stabilized by yttrium and / or calcium oxide and / or magnesium oxide.
  • Electron beam evaporation produces stalk-shaped grains in the thermal barrier coating.
  • Reprocessing means that heat shield elements must be freed 155 after use, where appropriate, protective layers (for example by sandblasting). This is followed by removal of the corrosion and / or oxidation layers or products. If necessary, cracks in the heat shield element 155 are also repaired. This is followed by a recoating of the heat shield elements 155 and a renewed use of the heat shield elements 155.
  • the heat shield elements 155 are then, for example, hollow and possibly still have film cooling holes (not shown) which open into the combustion chamber space 154.
  • FIG. 9 shows a perspective view of a moving blade 120 or guide blade 130 of a turbomachine that extends along a longitudinal axis 121.
  • the turbomachine may be a gas turbine of an aircraft or a power plant for power generation, a steam turbine or a compressor.
  • the blade 120, 130 has along the longitudinal axis 121 to each other, a securing region 400, an adjoining blade or vane platform 403 and an airfoil 406.
  • the vane 130 may have tip at its vane 415 a further platform (not Darge ⁇ asserted).
  • a blade root 183 is formed, which serves for attachment of the blades 120, 130 to a shaft or a disc (not shown).
  • the blade root 183 is, for example, as a hammerhead staltet out ⁇ . Other designs as Christmas tree or Schwalbenschwanzfuß are possible.
  • the blade 120, 130 has a medium which flows past felblatt 406 at the spectacle ⁇ a leading edge 409 and a trailing edge on the 412th
  • Such superalloys are known, for example, from EP 1 204 776 B1, EP 1 306 454, EP 1 319 729 A1, WO 99/67435 or WO 00/44949; These documents are part of the disclosure regarding the chemical composition of the alloy.
  • the blade 120, 130 can hereby be manufactured by a casting process, also by directional solidification, by a forging process, by a milling process or combinations thereof.
  • Workpieces with a monocrystalline structure or structures are used as components for machines which are exposed to high mechanical, thermal and / or chemical stresses during operation.
  • Such monocrystalline workpieces for example, by directed solidification from the melt. These are casting processes in which the liquid metallic alloy to monocrystalline structure, ie the single-crystal workpiece, or directionally solidified.
  • dendritic crystals are aligned along the heat flow and form either a columnar grain structure (columnar, ie grains that run the entire length of the workpiece and here, in common parlance, referred to as directionally solidified) or a monocrystalline structure, ie the whole workpiece be ⁇ is made of a single crystal.
  • Structures are also known as directionally rigidified structures
  • Refurbishment means that components 120, 130 may need to be deprotected after use (e.g., by sandblasting). This is followed by removal of the corrosion and / or oxidation layers or products. Optionally, even cracks in the component 120, 130 are repaired. This is followed by a re-coating of the component 120, 130 and a renewed use of the component 120, 130.
  • the blade 120, 130 may be hollow or solid. If the blade 120 is to be cooled 130, it is hollow and, if necessary, has film cooling holes 418 (indicated by dashed lines) on.

Landscapes

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

Abstract

En général, des procédés de revêtement sont utilisés souvent localement. De ce fait, des procédés de revêtements locaux ne peuvent pas toujours être utilisés, de sorte qu'un masque doit souvent être utilisé. L'invention concerne une couche de protection (7) contenant un liant et de l'oxyde de titane, laquelle peut être utilisée en tant que barrière de diffusion, de sorte qu'un matériau de revêtement n'est appliqué que localement, lors d'un procédé de revêtement. Le liant est transformé avant le processus de revêtement en carbone.
EP06806827A 2005-10-07 2006-09-26 Composition seche, son utilisation et procede de revetement Withdrawn EP1931811A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP06806827A EP1931811A1 (fr) 2005-10-07 2006-09-26 Composition seche, son utilisation et procede de revetement

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
EP20050021897 EP1772529A1 (fr) 2005-10-07 2005-10-07 Composition chimique sèche, utilisation de celle-ci composition pour fabriquer un revêtement multicouche et méthode pour fabriquer ce revêtement
EP06806827A EP1931811A1 (fr) 2005-10-07 2006-09-26 Composition seche, son utilisation et procede de revetement
PCT/EP2006/066744 WO2007042392A1 (fr) 2005-10-07 2006-09-26 Composition seche, son utilisation et procede de revetement

Publications (1)

Publication Number Publication Date
EP1931811A1 true EP1931811A1 (fr) 2008-06-18

Family

ID=35677546

Family Applications (2)

Application Number Title Priority Date Filing Date
EP20050021897 Withdrawn EP1772529A1 (fr) 2005-10-07 2005-10-07 Composition chimique sèche, utilisation de celle-ci composition pour fabriquer un revêtement multicouche et méthode pour fabriquer ce revêtement
EP06806827A Withdrawn EP1931811A1 (fr) 2005-10-07 2006-09-26 Composition seche, son utilisation et procede de revetement

Family Applications Before (1)

Application Number Title Priority Date Filing Date
EP20050021897 Withdrawn EP1772529A1 (fr) 2005-10-07 2005-10-07 Composition chimique sèche, utilisation de celle-ci composition pour fabriquer un revêtement multicouche et méthode pour fabriquer ce revêtement

Country Status (3)

Country Link
US (1) US7998600B2 (fr)
EP (2) EP1772529A1 (fr)
WO (1) WO2007042392A1 (fr)

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CN102223956B (zh) * 2008-11-20 2015-05-06 欧瑞康贸易股份公司(特吕巴赫) 用于涂覆设备的清洁方法
WO2010138096A1 (fr) * 2009-05-26 2010-12-02 Siemens Aktiengesellschaft Système de revêtement stratifié présentant une couche de mcralx et une couche riche en chrome, ainsi que procédé pour sa production
DE102010005762A1 (de) * 2010-01-25 2011-07-28 Oerlikon Trading Ag, Trübbach Reinigungsverfahren für Beschichtungsanlagen
US20190284941A1 (en) * 2018-03-16 2019-09-19 United Technologies Corporation Location-specific slurry based coatings for internally-cooled component and process therefor

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US20090263579A1 (en) 2009-10-22
US7998600B2 (en) 2011-08-16
WO2007042392A1 (fr) 2007-04-19
EP1772529A1 (fr) 2007-04-11

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