EP2376677A1 - Couche de mcralx avec teneurs différentes en chrome et en aluminium - Google Patents

Couche de mcralx avec teneurs différentes en chrome et en aluminium

Info

Publication number
EP2376677A1
EP2376677A1 EP09795967A EP09795967A EP2376677A1 EP 2376677 A1 EP2376677 A1 EP 2376677A1 EP 09795967 A EP09795967 A EP 09795967A EP 09795967 A EP09795967 A EP 09795967A EP 2376677 A1 EP2376677 A1 EP 2376677A1
Authority
EP
European Patent Office
Prior art keywords
layer
mcralx
content
mcralx layer
layer system
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Withdrawn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
EP09795967A
Other languages
German (de)
English (en)
Inventor
Friedhelm Schmitz
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
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 EP09795967A priority Critical patent/EP2376677A1/fr
Priority to EP13005373.9A priority patent/EP2698450A1/fr
Publication of EP2376677A1 publication Critical patent/EP2376677A1/fr
Withdrawn legal-status Critical Current

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    • 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
    • C23C28/02—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 only coatings only including layers of metallic material
    • C23C28/021—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 only coatings only including layers of metallic material including 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
    • C23C28/02—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 only coatings only including layers of metallic material
    • C23C28/021—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 only coatings only including layers of metallic material including at least one metal alloy layer
    • C23C28/022—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 only coatings only including layers of metallic material including at least one metal alloy layer with 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
    • C23C28/02—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 only coatings only including layers of metallic material
    • C23C28/028—Including graded layers in composition or in physical properties, e.g. density, porosity, grain size
    • 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
    • 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
    • C23C28/36—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including layers graded in composition or physical properties
    • 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.]
    • Y10T428/12736—Al-base component
    • Y10T428/12764—Next to Al-base component

Definitions

  • the invention relates to a two-layer MCrAlX layer in which the chromium and aluminum contents differ.
  • Ni and Co base materials are used in the hot gas path of gas turbines. However, because of their optimization to the highest possible strength, these materials often lack sufficient oxidation and high temperature corrosion resistance in the hot gas. The materials must therefore be protected with suitable protective coatings against hot gas attack.
  • a ceramic layer of zirconium oxide is additionally applied to thermal insulation on thermally highly stressed components. The underlying metallic layer serves as an adhesive layer for the ceramic thermal insulation layer and as an oxidation protection layer for the base material.
  • protective coatings are applied to the hottest components by means of thermal spraying or EB-PVD methods. These usually consist of so-called MCrAlX coating layers which, in addition to Ni and / or Co, also contain chromium, aluminum, silicon, rhenium or rare earths such as yttrium.
  • MCrAlX coating layers which, in addition to Ni and / or Co, also contain chromium, aluminum, silicon, rhenium or rare earths such as yttrium.
  • MCrAlX coating layers which, in addition to Ni and / or Co, also contain chromium, aluminum, silicon, rhenium or rare earths such as yttrium.
  • the elements Ni, Co, Cr, Al are of importance here. Because these elements are due to Diffusion also xn interaction mxt the base material are, xst dxes also ber ⁇ ckssexchtigen. Due to the high level of raw material extrusion, especially the special alloying elements, a cost-optimized composition must be ensured.
  • the object of the invention is to solve the above-mentioned problem.
  • the object is achieved by a layer system according to claim 1 and 2.
  • FIG. 4 is a perspective view of a turbine blade
  • FIG. 5 is a perspective view of a combustion chamber
  • FIG. 6 is a list of superalloys.
  • FIG. 1 shows a first example.
  • the component 1, 120, 130, 155 has a substrate 4.
  • the substrate 4 has a superalloy, in particular according to FIG.
  • a metallic protective layer 13 is present.
  • the metallic protective layer 13 comprises two MCrAlX- different in their chemical composition. Schxraum 7, 10, wherein the outer layer 10 preferably has a higher chromium content.
  • the alumimum content of the outer layer 10 is higher than the Alumimumgehalt the underlying layer. 7
  • the difference in chromium content for the two layers 7, 10 is preferably (at least in absolute terms) preferably at least 1 wt% (
  • 10 is preferably (in absolute terms) preferably at least lwt% (
  • the protective layer 13 preferably consists only of two different MCrAlX layers 7, 10.
  • a metallic protective layer 13 which has a better oxidation resistance than the previously used MCrAlX layers compared to the layers used hitherto with simultaneously the same good thermomechanical properties
  • the chromium content of the inner layer 7 is higher than that of the outer layer 10, the aluminum content of the outer layer 10 being higher than the Alummium content of the inner layer 7.
  • the same is preferably true for a layer system 7, 10 containing yttrium (Y).
  • Y yttrium
  • Higher yttrium content means at least one absolute difference of 0.15wt%, (
  • the inner layer 7 close to the base material (substrate 4) preferably has the following basic composition (in wt-o): Ni about 38 t in the chemical composition of the powder or ingot used. to about 66.6% and Co from 8% to 22%.
  • This basic composition means that despite a high Cr content of 21% to 29 ⁇ little or no ⁇ -Cr phases occur and a good ductility of the layer is maintained.
  • the relatively high Cr and Y content acts as a getter for sulfur in the base material and is said to prevent a damaging effect on the TGO.
  • the relatively low Al content of 4% to 9% requires the ductility behavior of layer 7, but also leads to a low interdiffusion with the base material (substrate). On the other hand, it is still high enough to favorably influence the life of a thermal insulation layer 16, since there is sufficient Al for subsequent diffusion.
  • the phases occurring at this concentration of the main alloying constituents in the new and operationally stressed state are Y (gamma), Y 'and ⁇ (beta).
  • the yttrium content should preferably be greater than 0.4wt to 0.9wt and also a gettering effect for sulfur.
  • the yttrium should also be able to diffuse into the overlying outer layer 10.
  • the layer can also Re up to 1- ,. contained in order to further delay interdiffusion.
  • the outer MCrAlX layer 10 located above has a thickness that is preferably the same as the first layer 7 within the scope of the manufacturing tolerances.
  • This basic composition in conjunction with a lowered Cr content of preferably around 20 Wt 5 and an Al content of preferably 11.5 wt s, leads to an excellent AlyO cover layer formation, which is further enhanced by the low contents of Si of 0.2%. 0.4% and Y from 0.1% - 0.2% in terms of
  • Dre Marsh 10 essentially has a phase composition of gamma, beta, is thermally stable and avoids brittle phases, which in turn leads to good ductility properties of MCrAlX layer 10.
  • the MCrAlX layers 7, 10 are NiCoCrAlY layers.
  • the protective layer 13 has two superimposed layers, preferably with the composition of layer 7 (in wt s):
  • Y 0.4-0.0-s preferably> 0.4- ⁇ -0.6-_>, very preferably 0.5-0,
  • outer layer 10 preferably 0-o, preferably the list above (Ni, Co, Cr, Al, Y, Re) is final, and with the composition of outer layer 10:
  • Hf, Zr, P and other trace elements can provide up to 0.3% positive properties through mutual interaction.
  • FIG. 3 shows by way of example a gas turbine 100 in a longitudinal section.
  • the gas turbine 100 has inside a rotatably mounted about a rotation axis 102 rotor 103 with a shaft, which is also referred to as a turbine runner.
  • 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.
  • 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 of guide vanes 115 follows a series of vanes 120 in the hot gas duct 111 of a row of vanes 115.
  • the guide vanes 130 are fastened to an inner housing 138 of a stator 143, whereas the rotor 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 105 is sucked and compressed by the compressor 105 through the intake housing 104.
  • the compressed air provided at the turbine-side end of the compressor 105 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 which is coupled to it ,
  • the components exposed to the hot working medium 113 are subject to thermal loads during the operation of the gas turbine 100.
  • the guide vanes 130 and rotor blades 120 of the first turbine stage 112, viewed in the direction of flow 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 may have a directional structure, i. they are monocrystalline (SX structure) or have only slow-moving grains (DS structure).
  • iron-, nickel- or cobalt-based superalloys are used as the material for the components, in particular for the turbine blade 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.
  • the vane 130 has a Leitschaufelfuß facing the réellegehause 138 of the turbine 108 (not shown here) and a Leitschaufelfuß the opposite vane head on.
  • the vane head is the rotor 103 facing and fixed to a mounting ring 140 of the stator 143.
  • FIG. 4 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 power plant for power generation, a steam turbine or a compressor.
  • the blade 120, 130 has along the longitudinal axis 121 in succession a fastening region 400, an adjacent blade platform 403 and an airfoil 406 and a blade tip 415.
  • the blade 130 may have at its blade tip 415 another platform (not shown).
  • 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 designed, for example, as a hammer head. Other designs as Christmas tree or Schwalbenschwanzfuß are possible.
  • the blade 120, 130 has a leading edge 409 and a downstream edge 412 for a medium flowing past the airfoil 406.
  • blades 120, 130 for example, solid metallic materials, in particular superalloys, are used in all regions 400, 403, 406 of the blade 120, 130.
  • 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.
  • the blade 120, 130 can be made by a casting process, also by directional solidification, by a forging process, by a Fras vide or combinations thereof.
  • Single-crystalline structures or structures are used as components for machines that are subject to high mechanical, thermal and / or chemical stresses during operation.
  • the production of such eink ⁇ stallinen workpieces is done for example by directed solidification from the melt.
  • These are casting processes in which the liquid metallic alloy solidifies to a monocrystalline structure, ie to a single-crystalline workpiece, or directionally.
  • dendritic crystals are aligned along the warm flow and form either a prismatic crystalline grain structure (columnar, ie grains that run the entire length of the workpiece and here, in common usage, are referred to as directionally solidified) or a monocrystalline structure, ie the whole
  • the work consists of a single crystal.
  • 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 ones Earth, or hafnium (Hf)).
  • 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 should be part of this disclosure with regard to the chemical composition of the alloy.
  • the density is preferably 95? the theoretical density.
  • the layer composition comprises Co-30Ni-28Cr-8A1-0, 6Y-0, 7Si or Co-28Ni-24Cr-10Al-0, 6Y.
  • nickel-based protective layers such as Ni-10Cr-12Al-0.6Y-3Re or Ni-12Co-21Cr-IIAl-O, 4Y-2Re or Ni-25Co-17Cr-10Al-0.4Y-1 are also preferably used , 5RE.
  • a thermal insulation layer which is preferably the outermost layer, and consists for example of ZrO 2 , Y 2 OsZrO 2 , ie it is not, partially or completely stabilized by yttria and / or calcium oxide and / or magnesium oxide ,
  • the thermal insulation layer covers the entire MCrAlX layer.
  • Suitable coating processes such as electron beam evaporation (EB-PVD), are used to produce protuberant grains in the thermal insulation layer.
  • the thermal insulation layer can have porous, microporous or macroporous corns for better thermal shock resistance.
  • the thermal insulation layer is therefore preferably more porous than the MCrAlX layer.
  • the blade 120, 130 may be hollow or solid. When the blade 120, 130 is to be cooled, it is hollow and possibly still has film cooling holes 418 (indicated by dashed lines).
  • FIG. 5 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 around an axis of rotation 102 in circumferential direction pass into a common combustion chamber space 154, which produce flames 156 ,
  • 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 with an inner lining formed of heat shield elements 155.
  • the 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, for example, hollow and possibly still have m cooler holes (not shown) which are still in contact with the combustion chamber space 154.
  • Each heat shield element 155 made of an alloy is equipped on the working medium 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 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 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 barrier layer may be present and consists for example of ZrCv, Y / O-ZrCv, ie it is not, partially or completely stabilized by yttrium oxide and / or calcium oxide and / or magnesium oxide.
  • Electron Beam Evaporation produces proton grains in the thermal insulation layer.
  • the thermal insulation layer may have porous, microporous or macroporous grains for better thermal shock resistance.
  • Refurbishment means that turbine blades 120, 130, heat shield elements 155 may need to be deprotected (e.g., by sandblasting) after use. 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. Thereafter, a re-coating of the Turbmenschaufein 120, 130, heat shield elements 155 and a renewed use of
  • Turbomachine 120, 130 or the heat shield elements 155 are examples of Turbomachine 120, 130 or the heat shield elements 155.

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

Abstract

L'invention concerne un revêtement MCrAlX à deux couches destiné à améliorer à la fois la résistance à l'oxydation et la résistance thermomécanique, dans lequel les teneurs en nickel et en cobalt, mais aussi en Cr, en Al et en Y, diffèrent nettement.
EP09795967A 2009-01-08 2009-12-14 Couche de mcralx avec teneurs différentes en chrome et en aluminium Withdrawn EP2376677A1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP09795967A EP2376677A1 (fr) 2009-01-08 2009-12-14 Couche de mcralx avec teneurs différentes en chrome et en aluminium
EP13005373.9A EP2698450A1 (fr) 2009-01-08 2009-12-14 Couche de MCrAIX ayant des teneurs différentes en chrome et aluminium

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
EP09000160A EP2206805A1 (fr) 2009-01-08 2009-01-08 Couche de MCrAIX ayant des teneurs différentes en chrome et aluminium
PCT/EP2009/067097 WO2010079049A1 (fr) 2009-01-08 2009-12-14 Couche de mcralx avec teneurs différentes en chrome et en aluminium
EP09795967A EP2376677A1 (fr) 2009-01-08 2009-12-14 Couche de mcralx avec teneurs différentes en chrome et en aluminium

Related Child Applications (1)

Application Number Title Priority Date Filing Date
EP13005373.9A Division EP2698450A1 (fr) 2009-01-08 2009-12-14 Couche de MCrAIX ayant des teneurs différentes en chrome et aluminium

Publications (1)

Publication Number Publication Date
EP2376677A1 true EP2376677A1 (fr) 2011-10-19

Family

ID=40489392

Family Applications (3)

Application Number Title Priority Date Filing Date
EP09000160A Withdrawn EP2206805A1 (fr) 2009-01-08 2009-01-08 Couche de MCrAIX ayant des teneurs différentes en chrome et aluminium
EP13005373.9A Withdrawn EP2698450A1 (fr) 2009-01-08 2009-12-14 Couche de MCrAIX ayant des teneurs différentes en chrome et aluminium
EP09795967A Withdrawn EP2376677A1 (fr) 2009-01-08 2009-12-14 Couche de mcralx avec teneurs différentes en chrome et en aluminium

Family Applications Before (2)

Application Number Title Priority Date Filing Date
EP09000160A Withdrawn EP2206805A1 (fr) 2009-01-08 2009-01-08 Couche de MCrAIX ayant des teneurs différentes en chrome et aluminium
EP13005373.9A Withdrawn EP2698450A1 (fr) 2009-01-08 2009-12-14 Couche de MCrAIX ayant des teneurs différentes en chrome et aluminium

Country Status (6)

Country Link
US (1) US20110268987A1 (fr)
EP (3) EP2206805A1 (fr)
JP (1) JP2012514692A (fr)
CN (1) CN102272354B (fr)
RU (1) RU2011133090A (fr)
WO (1) WO2010079049A1 (fr)

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Also Published As

Publication number Publication date
CN102272354B (zh) 2013-10-23
RU2011133090A (ru) 2013-02-20
JP2012514692A (ja) 2012-06-28
EP2698450A1 (fr) 2014-02-19
WO2010079049A1 (fr) 2010-07-15
US20110268987A1 (en) 2011-11-03
CN102272354A (zh) 2011-12-07
EP2206805A1 (fr) 2010-07-14

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