EP1859076A1 - Système de couches avec une couche pour l'inhibition de la diffusion - Google Patents

Système de couches avec une couche pour l'inhibition de la diffusion

Info

Publication number
EP1859076A1
EP1859076A1 EP06704271A EP06704271A EP1859076A1 EP 1859076 A1 EP1859076 A1 EP 1859076A1 EP 06704271 A EP06704271 A EP 06704271A EP 06704271 A EP06704271 A EP 06704271A EP 1859076 A1 EP1859076 A1 EP 1859076A1
Authority
EP
European Patent Office
Prior art keywords
layer
substrate
diffusion inhibiting
elements
aluminum
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Withdrawn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
EP06704271A
Other languages
German (de)
English (en)
Inventor
Ursus KRÜGER
Jan Steinbach
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
Siemens Corp
Original Assignee
Siemens AG
Siemens Corp
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, Siemens Corp filed Critical Siemens AG
Priority to EP06704271A priority Critical patent/EP1859076A1/fr
Publication of EP1859076A1 publication Critical patent/EP1859076A1/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Withdrawn legal-status Critical Current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
    • 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
    • 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
    • C23C28/32—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer
    • C23C28/325—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer with layers graded in composition or in physical properties
    • 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
    • C23C28/345—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 with at least one oxide 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
    • C23C28/345—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 with at least one oxide layer
    • C23C28/3455—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 with at least one oxide layer with a refractory ceramic layer, e.g. refractory metal oxide, ZrO2, rare earth oxides or a thermal barrier system comprising at least one refractory oxide layer
    • 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

Definitions

  • the invention concerns a layer system consisting of a substrate, a diffusion inhibiting layer, a bonding- or corrosion protective layer.
  • the lifespan of a layer system with a bonding or corrosion protective layer (MCrAlX) and a thermal barrier coating (TBC) in the hot gas part of gas turbines is limited basically by interdiffusion occurrences.
  • MrAlX bonding or corrosion protective layer
  • TBC thermal barrier coating
  • a time-steered and temperature-steered concentration balance across phase interfaces occurs in particular for aluminum from the layer as well as for Ta, Ti, W, Mo, Nb and partial Re and Hf (in SX- or DS-alloys) from the base metal away.
  • the inhibition of diffusion occurrences in the MCrAlX layer or between MCrAlX and basic material is also realized by the development and the application of very diffusion-sluggish MCrAlX compositions of base metal or combinations. On this occasion, additions of high-melting elements are also used. Inhibiting layers in the interface to the base metal or to the TBC should limit the diffusion activity. However they are a cost factor for the layer system, because they cause an additional procedure step with relatively expensive materials. To reach a sufficient continuity of these layers, they are mostly made relatively thick.
  • the task of the invention is to indicate a layer system with a diffusion inhibiting layer which works properly, does not cause problems during stripping in a refurbishment process and can be produced at justifiable cost and technological effort.
  • the task is solved by a layer system with a diffusion inhibiting layer according to claim 1.
  • Figure 1 shows schematically a layer construction of a layer system
  • Figure 2 shows a listing of chemical compositions of superalloys of a substrate of a layer system
  • Figure 3 shows a turbine blade or vane
  • Figure 4 shows a combustion chamber
  • Figure 5 shows a gas turbine.
  • Figure 1 shows schematically the layer construction of a layer system 1 according to the invention.
  • the layer system 1 has a substrate 4 which is in particular made of a superalloy based on iron, nickel and/or cobalt. Examples of such compositions are listed in the table of figure 2.
  • the layer system 1 can be an a new made or a refurbished component of a turbine, e.g. of a steam or gas turbine 100 (Fig. 5), and is in particular a turbine blade or vane 120, 130, a heat shield element 155 (Fig. 4) or a casing 138 (Fig. 5) .
  • the substrate 4 has a certain first aluminum content AIi.
  • a bonding or corrosion protective layer 7, in particular of the type MCrAlX is applied to the substrate 4.
  • This bonding or corrosion protective layer 7 has a second aluminum content Al 2 which differs from the first aluminum content AIi of the substrate 4 and is higher in particular.
  • an outer thermal barrier coating 10 is applied to the bonding or corrosion protective layer 7.
  • a diffusion inhibiting layer 13 is applied which has a similar composition like the substrate 4, but the aluminum content Al d of the diffusion inhibiting layer 13 was such changed that the aluminum content Al d lies between the first aluminum content AIi of the substrate 4 and the second aluminum content Al 2 of the bonding layer 7. Similar means that most of the elements of the substrate 4 or in particular all elements of the substrate 4 are also present in the diffusion inhibiting layer 13.
  • the elements with small amounts in particular ⁇ lwt%, e.g. C, B, Zr, Hf must not be present in the diffusion inhibiting layer 13.
  • the diffusion inhibiting layer 13 can also contains all elements of the substrate 4.
  • the second aluminum content Al 2 of the bonding or protective layer 7 and the exemplary lower first aluminum content AIi of the substrate 4 result in a difference
  • the aluminum content Al d of the diffusion inhibiting layer 13 is raised by 10% to 90%, 20% to 80%, 30% to 70% or 40% to 60% of this difference ⁇ compared to the first aluminum content AIi of the substrate 4 or amount preferably to 60%, 50% or more preferably 40% or 30% of this difference ⁇ .
  • Al d Rl 1 + a* ⁇ ; (0.1 ⁇ a ⁇ 0.9).
  • the substrate 4 contains at least the elements
  • the amount of Al d is fixed according to the formula given above .
  • the amount Mei of the alloy elements of the diffusion inhibiting layer 13 i.e. the amounts of Ni, Cr and Co are calculated according to the formula
  • the new alloy of the diffusion inhibiting layer 13 can have even more elements Mei than Ni, Cr, Co and Al.
  • Al d A higher amount of Al d can be compensated by a reduction of the amount of all elements Mei of the alloy (Al 2 , AIi in wt%)
  • Mei Ni, Cr, Co, ..., not Al .
  • the substrate 4 can contain at least one of the elements W, Ta, Ti, Nb, Mo, C, B, Zr, Hf and/or C.
  • Ti, C, B, Zr, Hf and/or C can be kept at the same level as in the substrate 4 for the diffusion inhibiting layer 13.
  • Another possibility to compensate the higher aluminium content Al d is to reduce only the concentration of Ti, Ta,
  • composition of the diffusion inhibiting layer 13 is therefore:
  • the content of Al is exemplary again raised e.g. to 20%, that means e.g.
  • composition of the diffusion inhibiting layer 13 is therefore .
  • alloy IN 939, IN 6203 DS, IN 738 LC, Rene 80, IN792 CC, IN 792 DS, MAR M 002, MAR M 247 LC DS, PWA 1483 SX, ECY 768, MAR M 509, CM 247 can be used and which are emphasized in Figure 2.
  • the diffusion inhibiting layer 13 can also contain platinum, or a thin (1 - lO ⁇ m) platinum layer can be situated between diffusion inhibiting layer 13 and layer 7.
  • this Pt-layer would be transferred into a PTAl-layer or zone (10...100 ⁇ m) which is much more diffusion intransparent than the diffusion inhibiting layer 13 itself. That zone and the diffusion inhibiting layer due to Al-diffusion from the MCrAlY-coating into base metal direction. This results in a higher (electro- ) chemical solubility in acidic etching processes and therefore the coating will be underwent by the etching medium and layerwise released from the substrate.
  • Figure 3 shows in a perspective view a blade 120 or vane 130 of a turbine which has a long axis 121.
  • the turbine can be a gas turbine of an airplane or of a power station for the production of electricity, a steam turbine or a compressor.
  • the blade 120 or vane, 130 shows along the axis 121 a connection area 400, a blade platform 403 adjoining in it as well as a blade sheet 406.
  • the vane can show at her other end 415 another platform (not shown) .
  • connection area 400 a blade foot 183 is formed which serves as connection of the blade 120, 130 in a disc (not shown) .
  • the blade foot 183 is formed, for instance, as a hammer head.
  • the blade 120, 130 shows for a medium, that flows around the blade sheet 406, a leading edge 409 and an leaving edge 412.
  • customary vanes 120, 130 for instance massive metallic materials, in particular superalloys are used in all areas 400, 403, 406 of the vane.
  • superalloys are, for instance, known from the EP 1 204 776 Bl, EP 1 306 454, EP 1 319 729 Al, WO 99/67435 or WO 00/44949.
  • the vane 120, 130 can be manufactured by a casting procedure or by means of directed solidification. Work pieces with single crystalline structure are used as components for machines which are exposed to high mechanical, thermal and/or chemical loads.
  • vanes 120, 130 can have coatings against corrosion or oxidation (MCrAlX; M is at least an element of the group Iron (Fe) , cobalt (Co) , nickel (Ni) , X is an active element and stands for yttrium (Y) and/or silicon and/or at least an element of the rare earth and/or hafnium (Hf) ) .
  • M is at least an element of the group Iron (Fe) , cobalt (Co) , nickel (Ni)
  • X is an active element and stands for yttrium (Y) and/or silicon and/or at least an element of the rare earth and/or hafnium (Hf) ) .
  • Such alloys are known from the EP 0 486 489 Bl, EP 0 786 017 Bl, EP 0 412 397 Bl or EP 1 306 454 Al which shall be a part of this disclosure related to of the chemical composition of the alloy.
  • thermal barrier coating can be applied and consists, for instance of ZrO 2 , Y 2 O 4 -ZrO 2 , i.e. is not, partially or entirely stabilized by yttrium oxide and/or calcium oxide and/or magnesium oxide.
  • suitable coating procedures as for example electron beam evaporation (EB-PVD) columnar grains are generated in the thermal barrier coating.
  • EB-PVD electron beam evaporation
  • Reworking means that components 120, 130 must be stripped after her application if necessary from protective coatings (e.g. by sand blacting) . Then the removal of the corrosion and/or oxidation layers or products is performed. If necessary cracks are repaired in the components 120, 130. Then the components 120, 130 are recoated and a renewed application of the component 120, 130 is possible.
  • the vane 120, 130 can be made as an hollow or massive component .
  • vane 120, 130 should be cooled, it is hollow and shows if necessary also film cooling holes 418.
  • FIG 4 shows a combustion chamber 110 of a gas turbine 100.
  • the combustion chamber 110 is configured, for example, as what is known as an annular combustion chamber, in which a multiplicity of burners 102, arranged around the turbine shaft 103 in the circumferential direction, open out into a common combustion chamber space.
  • the combustion chamber 110 as a whole is configured as an annular structure positioned around the turbine shaft 103.
  • the combustion chamber 110 is designed for a relatively high temperature of the working medium M of approximately 1000°C to 1600°C.
  • the combustion chamber wall 153 is provided, on its side facing the working medium M, with an inner lining formed from heat shield elements 155.
  • each heat shield element 155 is equipped with a particularly heat-resistant protective layer and/or the diffusion inhibiting layer 13 or is made from material which is able to withstand high temperatures.
  • a cooling system is provided for the heat shield elements 155 and/or for the holding elements thereof.
  • Figure 5 shows a longitudinal part-section through a gas turbine 100.
  • the gas turbine 100 has a rotor 103 which is mounted rotatably about an axis of rotation 102 and is also referred to as the turbine rotor.
  • the annular combustion chamber 106 is in communication with an, for example, annular hot-gas duct 111, where, by way of example, four turbine stages 112, connected in series, form the turbine 108.
  • Each turbine stage 112 is formed from two bladed rings.
  • a row 125 formed from rotor blades 120 follows a row 115 of guide vanes 130 in the hot- gas duct 111.
  • the guide vanes 130 are secured to the stator 143, whereas the rotor blades 120 belonging to a row 125 are arranged on the rotor 103 by means of a turbine wheel 133.
  • a generator or a machine (not shown) is coupled to the rotor 103.
  • the compressed air provided at the turbine- side end of the compressor 105 is passed to the burners 107, where it is mixed with a fuel.
  • the mixture is then burnt in the combustion chamber 110, so as to form the working medium 113.
  • the working medium 113 flows along the hot- gas duct 111, past the guide vanes 130 and the rotor blades 120.
  • the working medium 113 expands at the rotor blades 120, transferring its momentum, so that the rotor blades 120 drive the rotor 103 and the latter drives the machine coupled to it.
  • the components which are exposed to the hot working medium 113 are subject to thermal loads while the gas turbine 100 is operating.
  • the guide vane 130 has a guide vane root (not shown here) facing the inner housing 138 of the turbine 108 and a guide vane head on the opposite side from the guide vane root.
  • the guide vane head faces the rotor 103 and is fixed to a securing ring 140 of the stator 143.

Landscapes

  • Chemical & Material Sciences (AREA)
  • Inorganic Chemistry (AREA)
  • Engineering & Computer Science (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Ceramic Engineering (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Other Surface Treatments For Metallic Materials (AREA)

Abstract

L’invention permet de déterminer la durée de vie d’un système de couches à hautes températures par diffusion de simples éléments entre le substrat et les couches sur le substrat. Une couche inhibitrice de diffusion (13) selon l’invention avec une teneur adaptée en aluminium (Ald), située entre la teneur en aluminium (Al2) du substrat (4) et la teneur en aluminium (Al1) de la couche de liaison ou de protection contre la corrosion (7) empêche la diffusion d’aluminium et augmente par conséquent la durée de vie du système de couches.
EP06704271A 2005-03-08 2006-01-11 Système de couches avec une couche pour l'inhibition de la diffusion Withdrawn EP1859076A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP06704271A EP1859076A1 (fr) 2005-03-08 2006-01-11 Système de couches avec une couche pour l'inhibition de la diffusion

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
EP05005047A EP1700932A1 (fr) 2005-03-08 2005-03-08 Système de couches avec une couche pour l'inhibition de la diffusion
EP06704271A EP1859076A1 (fr) 2005-03-08 2006-01-11 Système de couches avec une couche pour l'inhibition de la diffusion
PCT/EP2006/050160 WO2006094845A1 (fr) 2005-03-08 2006-01-11 Système de couches avec couche inhibitrice de diffusion

Publications (1)

Publication Number Publication Date
EP1859076A1 true EP1859076A1 (fr) 2007-11-28

Family

ID=34934128

Family Applications (2)

Application Number Title Priority Date Filing Date
EP05005047A Withdrawn EP1700932A1 (fr) 2005-03-08 2005-03-08 Système de couches avec une couche pour l'inhibition de la diffusion
EP06704271A Withdrawn EP1859076A1 (fr) 2005-03-08 2006-01-11 Système de couches avec une couche pour l'inhibition de la diffusion

Family Applications Before (1)

Application Number Title Priority Date Filing Date
EP05005047A Withdrawn EP1700932A1 (fr) 2005-03-08 2005-03-08 Système de couches avec une couche pour l'inhibition de la diffusion

Country Status (3)

Country Link
US (1) US20080274368A1 (fr)
EP (2) EP1700932A1 (fr)
WO (1) WO2006094845A1 (fr)

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EP1780294A1 (fr) * 2005-10-25 2007-05-02 Siemens Aktiengesellschaft Alliage, couche protectrice pour proteger un élément structurel contre la corrosion et l'oxydation aux temperatures hautes et élément structurel
US7858205B2 (en) * 2007-09-19 2010-12-28 Siemens Energy, Inc. Bimetallic bond layer for thermal barrier coating on superalloy
EP3372707B1 (fr) * 2013-03-15 2022-06-29 Raytheon Technologies Corporation Revêtement de barrière thermique résistant à l'éclatement

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Also Published As

Publication number Publication date
WO2006094845A1 (fr) 2006-09-14
EP1700932A1 (fr) 2006-09-13
US20080274368A1 (en) 2008-11-06

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