EP1834004A1 - Alliage, couche de protection destinee a proteger un composant contre la corrosion et l'oxydation a haute temperature, et composant - Google Patents

Alliage, couche de protection destinee a proteger un composant contre la corrosion et l'oxydation a haute temperature, et composant

Info

Publication number
EP1834004A1
EP1834004A1 EP06830208A EP06830208A EP1834004A1 EP 1834004 A1 EP1834004 A1 EP 1834004A1 EP 06830208 A EP06830208 A EP 06830208A EP 06830208 A EP06830208 A EP 06830208A EP 1834004 A1 EP1834004 A1 EP 1834004A1
Authority
EP
European Patent Office
Prior art keywords
component
alloy
protective layer
nickel
oxidation
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Withdrawn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
EP06830208A
Other languages
German (de)
English (en)
Inventor
Werner Stamm
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 EP06830208A priority Critical patent/EP1834004A1/fr
Publication of EP1834004A1 publication Critical patent/EP1834004A1/fr
Withdrawn legal-status Critical Current

Links

Classifications

    • 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 according to claim 1, a protective layer for protecting a component against corrosion and / or oxidation at high temperatures according to claim 14 and a component according to claim 15.
  • the invention relates in particular to a protective layer for ⁇ a component made of a superalloy based on nickel or cobalt base.
  • MCrAlX MCrAlX
  • US Pat. No. 6,280,857 B1 discloses a protective layer which discloses the elements cobalt, chromium and aluminum based on nickel, the optional addition of rhenium as well as compelling admixtures of yttrium and silicon.
  • EP 1 439 245 A1 discloses a rhenium-containing cobalt-based layer.
  • the effort to increase the inlet temperatures both in stationary gas turbines and in aircraft engines has in the field of gas turbines of great importance, since the inlet temperatures are important determinants of the achievable with gas turbines thermodynamic efficiencies.
  • inlet temperatures are possible significantly higher than 1000 0 C.
  • the prior art allows inlet temperatures of 95O 0 C and more in stationary gas turbines and HOO 0 C and more in gas turbines of aircraft engines.
  • a protective layer In addition to the sufficient chemical resistance of a protective layer under the attacks that are expected of flue gases at temperatures in the order of 1000 0 C, a protective layer must also have sufficient mechanical properties, not least in view of the mechanical interaction between the protective layer and the base material , to have. In particular, the protective layer must be sufficiently ductile in order to be able to follow any deformations of the base material and not to break, since in this way points of attack for oxidation and corrosion would be created.
  • the typical problem is that an increase in the An ⁇ parts of elements such as aluminum and chromium, the resistance of a protective layer against oxidation and corrosion can lead to a deterioration of the ductility of the protective layer, so that mechanical deformation , in particular the formation of cracks, is to be expected in the case of a mechanical load normally occurring in a gas turbine.
  • an object of the present invention to provide an alloy and a protective layer which has good high-temperature resistance in corrosion and oxidation, has good long-term stability and, in addition, a mechanical stress to be expected particularly in a gas turbine at a high temperature well adjusted.
  • the object is achieved by an alloy according to claim 1 and a protective layer according to claim 14.
  • Another object of the invention is to provide a component which has increased protection against corrosion and oxidation.
  • a component according to claim 15 in particular a component of a gas turbine or steam turbine, which has a protective layer of the type described above for protection against corrosion and oxidation at high temperatures.
  • the invention is u. a. the realization that the
  • Protective layer in the layer and in the transition region between protective layer and base material brittle precipitates shows. These are used with time and temperature in use. Strengthens forming brittle phases lead in operation to pronounced longitudinal cracks in the layer as well as in the interface layer-base material with subsequent detachment of the layer. In addition, the brittleness of the precipitates increases as a result of the interaction with carbon which can diffuse from the base material into the layer or diffuses through the surface into the layer during a heat treatment in the furnace. By oxidation of the brittle precipitations, the driving force for cracking is further enhanced.
  • FIG. 1 shows a layer system with a protective layer
  • FIG. 2 shows compositions of superalloys
  • FIG. 3 shows a gas turbine
  • Figure 5 is a perspective view of a turbine blade and Figure 4 is a perspective view of a combustion chamber.
  • the protective layer with good corrosion resistance, has a particularly good resistance to oxidation and is also distinguished by particularly good ductility properties, so that it is particularly qualified for use in a gas turbine with a further increase in the inlet temperature. During operation, embrittlement hardly occurs.
  • the powders are applied for example by plasma spraying (APS, LPPS, VPS, ).
  • Other methods are also conceivable (PVD, CVD, cold gas spraying).
  • the protective layer 7 described also acts as Haftvermitt ⁇ Lersch layer to a superalloy.
  • this protective layer 7 may further layers insbeson ⁇ particular ceramic thermal barrier layers are deposited 10th
  • the protective layer 7 is advantageous ⁇ as applied to a substrate 4 made of a superalloy tion on nickel or cobalt base.
  • substrate 4 made of a superalloy tion on nickel or cobalt base.
  • the following composition is suitable as substrate (data in wt%):
  • compositions of this type are known as casting alloys under the names GTD222, IN939, IN6203 and Udimet known 500 be ⁇ .
  • the thickness of the protective layer 7 on the component 1 is preferably dimensioned to a value of between about 100 ⁇ m and 300 ⁇ m.
  • the protective layer 7 is particularly suitable for protecting a component against corrosion and oxidation, while the component is acted upon by a flue gas at a material temperature of about 95O 0 C, in airplanes also by about HOO 0 C.
  • the protective layer 7 according to the invention is therefore particularly qualified for protecting a component of a gas turbine 100, in particular a guide blade 120, blade 130 or another component that is exposed to hot gas before or in the turbine of the gas turbine.
  • the protective layer 7 can be used as an overlay (protective layer is the outer layer or as a bondcoat (protective layer is an intermediate layer).
  • FIG. 1 shows a layer system 1 as a component.
  • the layer system 1 consists of a substrate 4.
  • the substrate 4 may be metallic and / or ceramic.
  • turbine components such as e.g. Turbine barrel 120 (FIG. 5) or vanes 130 (FIGS. 3, 5), combustor liners 155 (FIG. 4), as well as other housing parts of a steam or gas turbine 100 (FIG. 3)
  • the substrate 4 is made of nickel alloy. , cobalt or iron based superalloy.
  • cobalt-based or nickel-based superalloys are used.
  • the protective layer 7 according to the invention is present.
  • this protective layer is applied by LPPS (low pres sure ⁇ plasma spraying). 7
  • This can be used as outer layer (not shown) or intermediate layer (FIG. 1). In the latter case, a ceramic thermal barrier coating 10 is present on the protective layer 7.
  • the protective layer 7 can be applied to newly manufactured components and remanufactured components are introduced from the refurbishment be ⁇ .
  • Reprocessing means that components 1 are separated after their use, if appropriate, of layers (heat insulating layer) and corrosion and oxidation products are removed, for example by a sheurebehand ⁇ averaging (acid stripping). If necessary, cracks must still be repaired. Thereafter, such a component can be coated again because the substrate 4 is very expensive.
  • FIG. 3 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 102, 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 be at the turbine end of the compressor 105 ⁇ compressed air provided is supplied to the burners 107, 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 on the rotor blades 120 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.
  • substrates of the components can have a directional structure, ie they are monocrystalline (SX structure) or have only longitudinal grains (DS structure).
  • SX structure monocrystalline
  • DS structure longitudinal grains
  • iron-, nickel- or cobalt-based superalloys are used as a material for the components.
  • 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 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.
  • FIG. 5 shows a perspective view of a rotor blade 120 or guide vane show ⁇ 130 of a turbomachine, which extends along a longitudinal axis of the 121st
  • 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 a blade 406 and a blade tip 415.
  • 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
  • the blades 120, 130 may have protection layers 7 according to the invention against corrosion or oxidation.
  • the density is preferably 95% of the theoretical density.
  • TGO thermal grown oxide layer
  • thermal barrier coating which is preferably the outermost layer, and consists for example of ZrO 2 , Y 2 O 3 -ZrO 2 , ie it is not, partially ⁇ or fully stabilized by yttria and / or calcium oxide and / or magnesium oxide.
  • the thermal barrier coating covers the entire MCrAlX layer. Suitable coating processes, such as electron beam evaporation (EB-PVD), produce stalk-shaped grains in the thermal barrier coating. Other coating methods are conceivable, for example atmospheric plasma spraying (APS), LPPS, VPS or CVD.
  • the heat insulating layer can ⁇ porous, micro- or macro-cracked compatible grains have for better thermal shock resistance.
  • the thermal barrier coating is therefore preferably more porous than the MCrAlX layer.
  • the blade 120, 130 may be hollow or solid. If the blade 120, 130 is to be cooled, it is hollow and may still 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 designed, for example, as a so-called annular combustion chamber, in which a multiplicity of burners 107 arranged in the circumferential direction about a rotation axis 102 open into 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 working medium M facing side with a formed from heat shield elements 155. liner.
  • the heat shield elements 155 Due to the high temperatures inside the combustion chamber 110 may also be provided for the heat shield elements 155 and for their holding elements, a cooling system.
  • the heat- Shield elements 155 are then hollow, for example, and possibly still have cooling holes (not shown) which open into the combustion chamber space 154.
  • 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 silicon and / or at least one element of the rare earths, or hafnium (Hf).
  • MCrAlX means: 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 silicon and / or at least one element of the rare earths, or hafnium (Hf).
  • 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 A1.
  • a ceramic thermal insulation layer may be present and consists for example of ZrO 2 , Y 2 O 3 -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.
  • the heat insulation layer ⁇ can porous, micro- or macro-cracked pERSonal for better thermal shock resistance.
  • Reprocessing means that turbines ⁇ blades 120, 130, heat shield elements 155 after they set ⁇ A may need to be stripped of protective layers (for example by sandblasting). This is followed by removal of the corrosion and / or oxidation layers or products. Optionally, cracks in the turbine blade 120, 130 or the heat shield element 155 are also repaired. After that a re-coating of the turbine blades 120, 130, heat shield elements 155 and a renewed use of the turbine blades 120, 130 or the heat shield elements 155

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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)

Abstract

Les couches de protection connues, à haute teneur en Cr et qui contiennent en outre du silicium forment des phases fragiles qui sont rendues encore plus fragiles en utilisation sous l'action du carbone. La couche de protection selon l'invention est composée de 27 % à 31 % de nickel, 23 % à 29 % de chrome, 7 % à 11 % d’aluminium, 0,5 % à 0,7 % d'yttrium et/ou d'au moins un métal équivalent de l'ensemble qui comprend le scandium et les éléments des terres rares, facultativement de 0,6 % à 0,8 % de silicium, facultativement de 0,5 % à 0,7 % de zirconium, le reste étant du cobalt.
EP06830208A 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 Withdrawn EP1834004A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP06830208A EP1834004A1 (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

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
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
EP06830208A EP1834004A1 (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

Publications (1)

Publication Number Publication Date
EP1834004A1 true EP1834004A1 (fr) 2007-09-19

Family

ID=36658725

Family Applications (2)

Application Number Title Priority Date Filing Date
EP05026378A Withdrawn 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
EP06830208A Withdrawn EP1834004A1 (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

Family Applications Before (1)

Application Number Title Priority Date Filing Date
EP05026378A Withdrawn 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

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)

Families Citing this family (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
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
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KR20070099675A (ko) 2007-10-09
EP1793008A1 (fr) 2007-06-06

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