US20090155120A1 - Alloy, Protective Layer for Protecting a Component Against Corrosion and/or Oxidation at High Temperatures, and Component - Google Patents

Alloy, Protective Layer for Protecting a Component Against Corrosion and/or Oxidation at High Temperatures, and Component Download PDF

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Publication number
US20090155120A1
US20090155120A1 US12/085,701 US8570106A US2009155120A1 US 20090155120 A1 US20090155120 A1 US 20090155120A1 US 8570106 A US8570106 A US 8570106A US 2009155120 A1 US2009155120 A1 US 2009155120A1
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alloy
component
protective layer
nickel
oxidation
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US12/085,701
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English (en)
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Werner Stamm
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Siemens AG
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Siemens AG
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Publication of US20090155120A1 publication Critical patent/US20090155120A1/en
Abandoned legal-status Critical Current

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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B15/00—Layered products comprising a layer of metal
    • B32B15/01—Layered products comprising a layer of metal all layers being exclusively metallic
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C19/00—Alloys based on nickel or cobalt
    • C22C19/03—Alloys based on nickel or cobalt based on nickel
    • C22C19/05—Alloys based on nickel or cobalt based on nickel with chromium
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C19/00—Alloys based on nickel or cobalt
    • C22C19/03—Alloys based on nickel or cobalt based on nickel
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C19/00—Alloys based on nickel or cobalt
    • C22C19/07—Alloys based on nickel or cobalt based on cobalt
    • 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
    • C23C28/34—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

Definitions

  • the invention relates to an alloy as described in the claims, a protective layer for protecting a component against corrosion and/or oxidation at high temperatures and a component as described in the claims.
  • the invention relates in particular to a protective layer for a component that consists of a nickel-base or cobalt-base superalloy.
  • MCrAlX MCrAlX
  • U.S. Pat. No. 6,280,857 B1 discloses a protective layer which contains the elements cobalt, chromium and aluminum, based on nickel, with the optional addition of rhenium and obligatory admixtures of yttrium and silicon.
  • EP 1 439 245 A1 discloses a cobalt-based rhenium-containing layer.
  • a protective layer has to be employed to achieve sufficient resistance to oxidation and corrosion.
  • a protective layer also has to have sufficiently good mechanical properties, not least with a view to the mechanical interaction between the protective layer and the base material.
  • the protective layer must be sufficiently ductile to enable any deformation of the base material to be followed and not to crack, since points of attack for oxidation and corrosion would be created in this way.
  • the invention is based on the object of providing an alloy and a protective layer which has a good high-temperature stability with regard to corrosion and oxidation, good long-term stability and, moreover, is particularly well matched to mechanical stresses which are expected at a high temperature in particular in a gas turbine.
  • a further object of the invention is to provide a component which offers increased protection against corrosion and oxidation.
  • the invention is based on the discovery, inter alia, that the desired protective layer has brittle precipitates in the layer and also in the transition region between the protective layer and the base material.
  • These brittle phases the formation of which increases over time and with use temperature, in operation lead to highly pronounced longitudinal cracks in the layer and in the layer/base material interface, with subsequent layer detachment.
  • the interaction with carbon which can diffuse out of the base material into the layer or diffuses into the layer through the surface during a heat treatment in the furnace, additionally increases the brittleness of the precipitates.
  • the susceptibility to cracking is boosted still further by oxidation of the brittle precipitates.
  • nickel which determines thermal and mechanical properties
  • FIG. 1 shows a layer system having a protective layer
  • FIG. 2 shows compositions of superalloys
  • FIG. 3 shows a gas turbine
  • FIG. 5 shows a perspective view of a turbine blade or vane
  • FIG. 4 shows a perspective view of a combustion chamber.
  • the reduction in the mechanical stresses resulting from the selected nickel content improves the mechanical properties.
  • the protective layer with a good resistance to corrosion, has a particularly good resistance to oxidation and is furthermore distinguished by especially good ductility properties, making it particularly well qualified for use in a gas turbine with a further increase in the inlet temperature. Scarcely any embrittlement occurs during operation.
  • the trace elements in the powder to be sprayed which form precipitates and therefore constitute sources of embrittlement, also play an important role.
  • the powders are applied, for example, by plasma spraying (APS, LPPS, VPS, . . . ).
  • Other processes are also conceivable (PVP, CVD, cold spraying).
  • the protective layer 7 described also acts as a bonding layer to a superalloy.
  • the protective layer 7 is advantageously applied to a substrate 4 made from a nickel-base or cobalt-base superalloy.
  • a suitable substrate has in particular the following composition (details in wt %):
  • compositions of this type are known as casting alloys under the names GTD222, IN939, IN6203 and Udimet 500.
  • FIG. 2 Further alternatives for the substrate of the component are listed in FIG. 2 .
  • the thickness of the protective layer 7 on the component 1 is preferably between approximately 100 ⁇ m and 300 ⁇ m.
  • the protective layer 7 is particularly suitable for protecting a component against corrosion and oxidation when the component is exposed to a flue gas at a material temperature of around 950° C., and in the case of aircraft turbines even around 1100° C.
  • the protective layer 7 according to the invention is therefore particularly well qualified for protecting a component of a gas turbine 100 , in particular a guide vane 120 , rotor blade 130 or other component, which is exposed to hot gas upstream of or in the turbine of the gas turbine.
  • the protective layer 7 can be used as an overlay (the protective layer is the outer layer) or as a bond coat (the protective layer is an interlayer).
  • FIG. 1 shows a layer system 1 as a component.
  • the layer system 1 comprises a substrate 4 .
  • the substrate 4 may be metallic and/or ceramic.
  • the substrate 4 consists of a nickel-base, cobalt-base or iron-base superalloy.
  • the protective layer 7 according to the invention is present on the substrate 4 .
  • this protective layer 7 is applied by LPPS (low pressure plasma spraying).
  • a ceramic thermal barrier coating 10 is present on the protective layer 7 .
  • the protective layer 7 can be applied to newly produced components and refurbished components.
  • Refurbishment means that after they have been used, layers (thermal barrier coating) may have to be detached from components 1 and corrosion and oxidation products removed, for example by an acid treatment (acid stripping). If appropriate, cracks also have to be repaired. This can be followed by recoating of a component of this type, since the substrate 4 is very expensive.
  • FIG. 3 shows by way of example a partial longitudinal section through a gas turbine 100 .
  • the gas turbine 100 has a rotor 103 which is mounted such that it can rotate about an axis of rotation 102 , has a shaft 102 , and is also referred to as the turbine rotor.
  • the annular combustion chamber 110 is in communication with a for example annular hot gas duct 111 .
  • a for example annular hot gas duct 111 There, by way of example, four successive turbine stages 112 form the turbine 108 .
  • Each turbine stage 112 is formed for example from two blade rings. As seen in the direction of flow of a working medium 113 , a guide vane row 115 is followed in the hot gas duct 111 by a row 125 formed from rotor blades 120 .
  • the guide vanes 130 are secured to an inner casing 138 of a stator 143 , whereas the rotor blades 120 belonging to a row 125 are arranged on the rotor 103 , for example by means of a turbine disk 133 .
  • a generator (not shown) is coupled to the rotor 103 .
  • air 135 is drawn in through the intake casing 104 and compressed by the compressor 105 .
  • the compressed air provided at the turbine 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 , forming 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 is expanded at the rotor blades 120 , transferring its momentum, so that the rotor blades 120 drive the rotor 103 and the latter in turn drives the generator coupled to it.
  • Substrates of the components may likewise have a directional structure, i.e. they are in single-crystal form (SX structure) or have only longitudinally oriented grains (DS structure).
  • SX structure single-crystal form
  • DS structure longitudinally oriented grains
  • iron-base, nickel-base or cobalt-base superalloys are used as material for the components, in particular for the turbine blade or vane 120 , 130 and components of the combustion chamber 110 .
  • the guide vane 130 has a guide vane root (not shown here) facing the inner casing 138 of the turbine 108 and a guide vane head at the opposite end 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 .
  • FIG. 5 shows a perspective view of a rotor blade 120 or guide vane 130 of a turbomachine, which extends along a longitudinal axis 121 .
  • the turbomachine may be a gas turbine of an aircraft or of a power plant for generating electricity, a steam turbine or a compressor.
  • the blade or vane 120 , 130 has, in succession along the longitudinal axis 121 , a securing region 400 , an adjoining blade or vane platform 403 , a main blade or vane part 406 and a blade or vane tip 415 .
  • the vane 130 may have a further platform (not shown) at its vane tip 415 .
  • a blade or vane root 183 which is used to secure the rotor blades 120 , 130 to a shaft or a disk (not shown), is formed in the securing region 400 .
  • the blade or vane root 183 is designed, for example, in hammerhead form. Other configurations, such as a fir-tree or dovetail root, are possible.
  • the blade or vane 120 , 130 has a leading edge 409 and a trailing edge 412 for a medium which flows past the main blade or vane part 406 .
  • the blade or vane 120 , 130 may in this case be produced by a casting process, also by means of directional solidification, by a forging process, by a milling process or combinations thereof.
  • Workpieces with a single-crystal structure or structures are used as components for machines which, in operation, are exposed to high mechanical, thermal and/or chemical stresses.
  • Single-crystal workpieces of this type are produced, for example, by directional solidification from the melt. This involves casting processes in which the liquid metallic alloy solidifies to form the single-crystal structure, i.e. the single-crystal workpiece, or solidifies directionally.
  • dendritic crystals are oriented along the direction of heat flow and form either a columnar crystalline grain structure (i.e. grains which run over the entire length of the workpiece and are referred to here, in accordance with the language customarily used, as directionally solidified) or a single-crystal structure, i.e. the entire workpiece consists of one single crystal.
  • a transition to globular (polycrystalline) solidification needs to be avoided, since non-directional growth inevitably forms transverse and longitudinal grain boundaries, which negate the favorable properties of the directionally solidified or single-crystal component.
  • directionally solidified microstructures refers in general terms to directionally solidified microstructures, this is to be understood as meaning both single crystals, which do not have any grain boundaries or at most have small-angle grain boundaries, and columnar crystal structures, which do have grain boundaries running in the longitudinal direction but do not have any transverse grain boundaries.
  • This second form of crystalline structures is also described as directionally solidified microstructures. (directionally solidified structures).
  • the blades or vanes 120 , 130 may likewise have protective layers 7 according to the invention protecting against corrosion or oxidation.
  • the density is preferably 95% of the theoretical density.
  • thermal barrier coating which is preferably the outermost layer and consists for example of ZrO 2 , Y 2 O 3 —ZrO 2 , i.e. unstabilized, partially stabilized or fully stabilized by yttrium oxide and/or calcium oxide and/or magnesium oxide, to be present on the MCrAlX.
  • the thermal barrier coating covers the entire MCrAlX layer.
  • Columnar grains are produced in the thermal barrier coating by means of suitable coating processes, such as for example electron beam physical vapor deposition (EB-PVD).
  • suitable coating processes such as for example electron beam physical vapor deposition (EB-PVD).
  • the thermal barrier coating may have grains that are porous and/or include micro-cracks or macro-cracks in order to improve the resistance to thermal shocks. Therefore, the thermal barrier coating is preferably more porous than the MCrAlX layer.
  • the blade or vane 120 , 130 may be hollow or solid in form. If the blade or vane 120 , 130 is to be cooled, it is hollow and may also have film-cooling holes 418 (indicated by dashed lines).
  • FIG. 4 shows a combustion chamber 110 of the 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 107 , which generate flames 156 and are arranged circumferentially around an axis of rotation 102 , open out into a common combustion chamber space 154 .
  • the combustion chamber 110 overall is of annular configuration positioned around the axis of rotation 102 .
  • 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 which faces the working medium M, with an inner lining formed from heat shield elements 155 .
  • a cooling system may also be provided for the heat shield elements 155 and/or their holding elements, on account of the high temperatures in the interior of the combustion chamber 110 .
  • the heat shield elements 155 are then for example hollow and may also have cooling holes (not shown) which open out into the combustion chamber space 154 .
  • each heat shield element 155 made from an alloy is equipped with a particularly heat-resistant protective layer (MCrAlX layer and/or ceramic coating) or is made from material that is able to withstand high temperatures (solid ceramic bricks).
  • M is at least one element selected from the group consisting of iron (Fe), cobalt (Co), nickel (Ni), X is an active element and stands for yttrium (Y) and/or silicon and/or at least one of the rare earth elements, or hafnium (Hf). Alloys of this type are known from EP 0 486 489 B1, EP 0 786 017 B1, EP 0 412 397 B1 or EP 1 306 454 A1.
  • a for example ceramic thermal barrier coating consisting for example of ZrO 2 , Y 2 O 3 —ZrO 2 , i.e. unstabilized, partially stabilized or fully stabilized by yttrium oxide and/or calcium oxide and/or magnesium oxide, may also be present on the MCrAlX.
  • Columnar grains are produced in the thermal barrier coating by suitable coating processes, such as for example electron beam physical vapor deposition (EB-PVD).
  • EB-PVD electron beam physical vapor deposition
  • the thermal barrier coating may have grains that are porous and/or include micro-cracks or macro-cracks in order to improve the resistance to thermal shocks.
  • Refurbishment means that after they have been used, protective layers may have to be removed from turbine blades or vanes 120 , 130 , heat shield elements 155 (e.g. by sand-blasting). Then, the corrosion and/or oxidation layers and products are removed.
  • cracks in the turbine blade or vane 120 , 130 or the heat shield element 155 are also repaired. This is followed by recoating of the turbine blades or vanes 120 , 130 , heat shield elements 155 , after which the turbine blades or vanes 120 , 130 or the heat shield elements 155 can be reused.

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  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Inorganic Chemistry (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Ceramic Engineering (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Coating By Spraying Or Casting (AREA)
  • Other Surface Treatments For Metallic Materials (AREA)
US12/085,701 2005-12-02 2006-11-30 Alloy, Protective Layer for Protecting a Component Against Corrosion and/or Oxidation at High Temperatures, and Component Abandoned US20090155120A1 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
EP05026378A EP1793008A1 (fr) 2005-12-02 2005-12-02 Alliage, couche protectrice pour proteger un élément structurel contre la corrosion et l'oxydation aux temperatures hautes et élément structurel
EP05026378.9 2005-12-02
PCT/EP2006/069104 WO2007063091A1 (fr) 2005-12-02 2006-11-30 Alliage, couche de protection destinee a proteger un composant contre la corrosion et l'oxydation a haute temperature, et composant

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Publication Number Publication Date
US20090155120A1 true US20090155120A1 (en) 2009-06-18

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US12/085,701 Abandoned US20090155120A1 (en) 2005-12-02 2006-11-30 Alloy, Protective Layer for Protecting a Component Against Corrosion and/or Oxidation at High Temperatures, and Component

Country Status (5)

Country Link
US (1) US20090155120A1 (fr)
EP (2) EP1793008A1 (fr)
KR (1) KR20070099675A (fr)
CN (1) CN101133173A (fr)
WO (1) WO2007063091A1 (fr)

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US20160031186A1 (en) * 2013-03-13 2016-02-04 General Electric Company Coatings for metallic substrates

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CN102115836B (zh) * 2009-12-30 2013-04-17 沈阳天贺新材料开发有限公司 一种MCrAlY合金体系的高温防护涂层及制备方法
CN102011463B (zh) * 2010-11-01 2012-06-20 山东大学 一种不锈钢复合耐腐蚀钢筋及其制备方法
CN102094163B (zh) * 2011-02-25 2012-09-05 中国科学院金属研究所 一种CoNiCrAlY抗腐蚀热喷涂合金粉末及制备方法
CN105920665B (zh) * 2016-06-21 2018-12-14 太仓碧奇新材料研发有限公司 铕锡钴合金/聚四氟乙烯支架材料的制备方法
CN106075569B (zh) * 2016-06-21 2018-12-14 太仓碧奇新材料研发有限公司 铽锰镍合金/聚醚醚酮支架材料的制备方法
CN106039399B (zh) * 2016-06-21 2018-12-14 太仓碧奇新材料研发有限公司 镝钼镍合金/聚甲基丙烯酸甲酯支架材料的制备方法
CN105999402B (zh) * 2016-06-21 2018-12-14 太仓碧奇新材料研发有限公司 钆钼钴合金/聚酰胺支架材料的制备方法
CN105963775B (zh) * 2016-06-21 2018-12-14 太仓碧奇新材料研发有限公司 钐锰钴合金/聚氨酯支架材料的制备方法

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US5401307A (en) * 1990-08-10 1995-03-28 Siemens Aktiengesellschaft High temperature-resistant corrosion protection coating on a component, in particular a gas turbine component
US6024792A (en) * 1997-02-24 2000-02-15 Sulzer Innotec Ag Method for producing monocrystalline structures
US6280857B1 (en) * 1997-10-30 2001-08-28 Alstom High temperature protective coating
US7338719B2 (en) * 2002-05-24 2008-03-04 Siemens Aktiengesellschaft MCrAl layer

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CN101133173A (zh) 2008-02-27
KR20070099675A (ko) 2007-10-09
WO2007063091A1 (fr) 2007-06-07
EP1834004A1 (fr) 2007-09-19

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