EP2761057A1 - Système stratifié à surface de substrat structurée et procédé de fabrication - Google Patents

Système stratifié à surface de substrat structurée et procédé de fabrication

Info

Publication number
EP2761057A1
EP2761057A1 EP12761600.1A EP12761600A EP2761057A1 EP 2761057 A1 EP2761057 A1 EP 2761057A1 EP 12761600 A EP12761600 A EP 12761600A EP 2761057 A1 EP2761057 A1 EP 2761057A1
Authority
EP
European Patent Office
Prior art keywords
layer
substrate
boundary surface
layer system
roughness
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.)
Granted
Application number
EP12761600.1A
Other languages
German (de)
English (en)
Other versions
EP2761057B1 (fr
Inventor
Alessandro Casu
Oliver Lüsebrink
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 Energy Global GmbH and Co KG
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 EP12761600.1A priority Critical patent/EP2761057B1/fr
Publication of EP2761057A1 publication Critical patent/EP2761057A1/fr
Application granted granted Critical
Publication of EP2761057B1 publication Critical patent/EP2761057B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/005—Selecting particular materials
    • 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
    • C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • F01D5/282—Selecting composite materials, e.g. blades with reinforcing filaments
    • 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
    • Y10T428/24—Structurally defined web or sheet [e.g., overall dimension, etc.]
    • Y10T428/24355—Continuous and nonuniform or irregular surface on layer or component [e.g., roofing, etc.]

Definitions

  • the invention relates to a layer system and a method for the production in which the substrate surface has a greater roughness than an interface between the layers.
  • Heat input to be protected is preferably done by layers, in which an outer ceramic layer is applied to a metallic adhesion promoter layer which has been applied to a metallic substrate.
  • the roughness of the metallic adhesion promoter layer plays a decisive role for the service life of the ceramic thermal barrier coating
  • Claim 1 and a method for producing a
  • Figure 1 is a layer system according to the prior
  • FIGS. 2, 7, 8 show a layer system according to the invention
  • FIG. 3 shows a gas turbine
  • FIG. 4 shows a turbine blade
  • FIG. 5 shows a combustion chamber
  • thermal coating methods in particular by plasma spraying (APS, VPS, LPPS) or by HVOF.
  • FIG. 1 is a simplified illustration because the application is curved the substrate 4 as with an airfoil 406 (FIG. 4) of a turbine blade 120, 130 (FIG. 4).
  • the maximum difference between the highest elevation 24 'and the deepest depression 21' of the rough surface 10 'of the layer 7' according to the prior art is r s .
  • Highest increase 24 'and deepest pit 21' of these max / min values for r s need not be adjacent.
  • the maximum distance measured from tip to tip between two directly adjacent elevations 24 'of the rough surface 10' of the layer 7 ' is d s .
  • the texture (roughness) of the surface 10 ' is irregular and therefore has no periodicity. Same definition applies to the rough surface 16 'of the
  • Substrate 4 'with r' s (maximum difference between the highest elevation 24 and the deepest depression 21 of the rough surface 16 'of the substrate 4', analogous to r s ) and d ' s (maximum Distance between two peaks of two directly adjacent
  • Elevations 24 of the substrate 4 ' analogous to d s ).
  • the values r ' s and d' s result from the casting or processing,
  • An average line of elevations 24 'and depressions 21' of the rough surface 10 ' would be between the highest elevation 24' and the deepest depression 21 'of the rough surface 10'.
  • Substrate 4 ' i. a line that is the mean of the
  • Ridges 24 'and depressions 21' of the rough surface 16 ' represent a layer thickness center line 33' of the layer 7 ', i. a line running in the middle of the layer 7 'and a layer surface centerline 36', i. a line representing the average of the ridges 24 and the recesses 21 of the rough surface 10 'of the substrate are straight.
  • the layer system 1 according to the invention according to FIG. 2 has a substrate 4 in which the structure of FIG
  • Boundary surface 16 of the substrate 4 was selectively and controlled changed and thus also the boundary surface 10 of the layer 7, on which a ceramic coating 13 takes place.
  • the boundary surface 16 of the substrate 4 has a different structure, ie a higher roughness than the surface 16 '(between substrate 4' and layer 7 ') according to the prior art (FIG. 1).
  • a valley 23 and a mountain 20 or valleys and mountains make the boundary surface 16 of the substrate 4 rougher, the quasi through Undulation of a substrate 4 'is formed and increase the boundary surface 16 with respect to the surface 16' of the substrate 4 '(Fig. 1).
  • the preferably wave-shaped boundary surface 16 also has the superposed roughness R s , which, however, is smaller than the specifically set roughness Ri 4 of the substrate 4.
  • D 'i (maximum distance mountain 20' and valley 23 'of layer 7) is comparable to Di.
  • d 'i, ie the maximum distance between two peaks of adjacent ridges 224 of the wavy rough surface 16 ', here then boundary surface 16, is comparable to d' s .
  • R 7 i is comparable to the value R 4 i, since the metallic layer 7 is not the mountains 20 and valleys 23 of the surface 16 of the substrate 4
  • Boundary surface 16 comparable to r ' s .
  • the value R s ie the maximum difference between the highest elevation 224 'and the deepest depression 221' of the layer 7, for the interface 10 is comparable to the value r s of the prior art (FIG. 1) for the same coating technique and powder.
  • the square or average roughness (Rq or Ra) can also be used.
  • the roughness of the surface 16 of the substrate 4 is at least 20%, in particular 30% rougher than the interface 10 'between the layers 7', 13 'according to the prior art (FIG. 1), ie the value R 7 i or R 4 i is at least 20%, in particular 30% greater than value r s or r ' s .
  • the roughness with the valley 23 and the top 20 of the substrate 4 is preferably uniform at least in places, that is, for example, sinusoidal or has at least one constant wavelength (waviness) or constant
  • the unprocessed surface 16 has no particular
  • the waviness of the boundary surface 16 of the substrate 4 is greater than that of the surface 10 'according to the prior art, ie at least 20%, ie, the distances between two "mountains" 20 are greater
  • the smallest distance Di (FIG. neighboring mountains 20 is at least 20%, in particular 30% larger than the largest distance d ⁇ (or d s ) of adjacent elevations for the boundary surface 10th
  • the waviness of the boundary surface 16 of the substrate 4 is also continued through the coating 7 on the boundary surface 10 with the mountain 20 'of the layer 7 and valley 23 of the layer 7.
  • Adhesive layer 7 the adhesion
  • Overlying layer 13 continues to improve.
  • the substrate 4 may be structured over the entire boundary surface 16 or only locally.
  • the substrate 4 preferably has a cobalt or
  • the substrate 4 can already have the desired structure on the boundary surface 16 after casting by means of a correspondingly shaped casting mold or it can be cast after casting
  • FIG. 3 shows by way of example a gas turbine 100 in a longitudinal partial section.
  • the gas turbine 100 has a rotatably mounted about a rotational axis 102 ⁇ rotor 103 having a shaft 101, which is also referred to as the turbine rotor.
  • a compressor 105 for example, a torus-like
  • 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 . As seen in the direction of flow of a working medium 113, in the hot gas channel 111 of a row of guide vanes 115, 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 105 ⁇ be compressed air provided at the turbine end of the compressor is ge ⁇ leads 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 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 may have a directional structure, i. they are monocrystalline (SX structure) or have only longitudinal grains (DS structure).
  • the components in particular for the turbine blade or vane 120, 130 and components of the combustion chamber 110.
  • iron-, nickel- or cobalt-based superalloys are used.
  • 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 blades 120, 130 may be anti-corrosion coatings (MCrAlX; M is at least one element of the group iron (Fe), cobalt (Co), nickel (Ni), X is an active element and is yttrium (Y) and / or silicon , Scandium (Sc) and / or at least one element of the rare earth or hafnium).
  • M is at least one element of the group iron (Fe), cobalt (Co), nickel (Ni)
  • X is an active element and is yttrium (Y) and / or silicon , Scandium (Sc) and / or at least one element of the rare earth or hafnium.
  • Such alloys are known from EP 0 486 489 B1, EP 0 786 017 B1, EP 0 412 397 B1 or EP 1 306 454 A1.
  • MCrAlX may still be present a thermal barrier coating, and consists for example of Zr02, Y203-Zr02, ie it is not, partially or completely stabilized by Ytt ⁇ riumoxid and / or calcium oxide and / or magnesium oxide.
  • Electron beam evaporation produces stalk-shaped grains in the thermal barrier coating.
  • the guide blade 130 has a guide blade foot facing the inner housing 138 of the turbine 108 (not shown here). ) and a vane head opposite the vane root.
  • the vane head faces the rotor 103 and fixed to a mounting ring 140 of the stator 143.
  • FIG. 4 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 be pointed on its shovel 415 have 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 out staltet ⁇ .
  • Other designs as Christmas tree or Schwalbenschwanzfuß are possible.
  • the blade 120, 130 has a medium felblatt to the Schau- 406 flows past, a leading edge 409 and a trailing edge 412th
  • the blade 120, 130 can be made 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 takes place e.g. by directed solidification from the melt.
  • These are casting processes in which the liquid metallic alloy is transformed into a monocrystalline structure, i. to 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.
  • 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
  • a monocrystalline structure ie the whole workpiece be ⁇ is made of a single crystal.
  • Structures are also called directionally solidified structures. Such methods are known from US Pat. No. 6,024,792 and EP 0 892 090 A1.
  • the blades 120, 130 may have coatings against corrosion or oxidation, e.g. B. (MCrAlX, M is at least one element of the group iron (Fe), cobalt (Co),
  • Nickel (Ni) 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 B1, EP 0 412 397 B1 or EP 1 306 454 A1.
  • the density is preferably 95% of the theoretical
  • 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-10A1-0, 4Y-1 are also preferably used , 5Re.
  • a thermal barrier coating which is preferably the outermost layer, and consists for example of Zr0 2 , Y2Ü3-Zr02, ie it is not, partially ⁇ or fully stabilized by yttria
  • the thermal barrier coating covers the entire MCrAlX layer.
  • Electron beam evaporation produces stalk-shaped grains in the thermal barrier coating.
  • the heat insulation layer may have ⁇ porous, micro- or macro-cracked compatible grains for better thermal shock resistance.
  • the Thermal insulation layer is therefore preferably more porous than the
  • Refurbishment means that components 120, 130 may need to be deprotected after use (e.g., by sandblasting). This is followed by removal of the corrosion and / or oxidation layers or products. Optionally, even cracks in the component 120, 130 are repaired. This is followed by a re-coating of the component 120, 130 and a renewed use of the component 120, 130.
  • the blade 120, 130 may be hollow or solid. If the blade 120, 130 is to be cooled, it is hollow and also has, if necessary, film cooling holes 418 (indicated by dashed lines) on.
  • FIG. 5 shows a combustion chamber 110 of a gas turbine.
  • the combustion chamber 110 is configured, for example, as so-called an annular combustion chamber, in which a plurality of in the circumferential direction about an axis of rotation 102 arranged burners 107 open into a common combustion chamber space 154 and generate flames 156th
  • 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.
  • Each heat shield element 155 made of an alloy is on the working medium side with a particularly heat-resistant protective layer (MCrAlX layer and / or ceramic coating). equipped or is made of high temperature resistant material (solid ceramic stones).
  • 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 B1, EP 0 412 397 B1 or EP 1 306 454 A1.
  • a ceramic Wär ⁇ medämm Anlagen be present and consists for example of ZrÜ2, Y203 ⁇ Zr02, ie it is not, partially or completely 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 may have ⁇ porous, micro- or macro-cracked compatible grains for better thermal shock resistance.
  • Reprocessing means that heat shield elements may need to be removed 155 after use of protective layers (for example by sandblasting). This is followed by removal of the corrosion and / or oxidation layers or products. If necessary, cracks in the heat shield element 155 are also repaired.
  • 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 hollow and have, for example possibly still in the combustion chamber 154 opening cooling holes (not shown).

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  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Inorganic Chemistry (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • General Engineering & Computer Science (AREA)
  • Ceramic Engineering (AREA)
  • Physics & Mathematics (AREA)
  • Plasma & Fusion (AREA)
  • Composite Materials (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Coating By Spraying Or Casting (AREA)

Abstract

Grâce à une surface structurée du substrat, cette rugosité se trouve positionnée au niveau d'une interface avec les couches situées dessus, ce qui permet d'améliorer l'adhérence entre les couches.
EP12761600.1A 2011-11-14 2012-09-14 Système de couche doté d'une surface de substrat structurée et son procédé de fabrication Active EP2761057B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP12761600.1A EP2761057B1 (fr) 2011-11-14 2012-09-14 Système de couche doté d'une surface de substrat structurée et son procédé de fabrication

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
EP11188983.8A EP2592174A1 (fr) 2011-11-14 2011-11-14 Système de couche doté d'une surface de substrat structurée et son procédé de fabrication
PCT/EP2012/068055 WO2013072092A1 (fr) 2011-11-14 2012-09-14 Système stratifié à surface de substrat structurée et procédé de fabrication
EP12761600.1A EP2761057B1 (fr) 2011-11-14 2012-09-14 Système de couche doté d'une surface de substrat structurée et son procédé de fabrication

Publications (2)

Publication Number Publication Date
EP2761057A1 true EP2761057A1 (fr) 2014-08-06
EP2761057B1 EP2761057B1 (fr) 2020-03-25

Family

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EP11188983.8A Withdrawn EP2592174A1 (fr) 2011-11-14 2011-11-14 Système de couche doté d'une surface de substrat structurée et son procédé de fabrication
EP12761600.1A Active EP2761057B1 (fr) 2011-11-14 2012-09-14 Système de couche doté d'une surface de substrat structurée et son procédé de fabrication

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EP11188983.8A Withdrawn EP2592174A1 (fr) 2011-11-14 2011-11-14 Système de couche doté d'une surface de substrat structurée et son procédé de fabrication

Country Status (3)

Country Link
US (1) US10371004B2 (fr)
EP (2) EP2592174A1 (fr)
WO (1) WO2013072092A1 (fr)

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US20200064670A1 (en) * 2018-08-22 2020-02-27 Innolux Corporation Electronic device and method for manufacturing the same

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Publication number Priority date Publication date Assignee Title
DE3926479A1 (de) 1989-08-10 1991-02-14 Siemens Ag Rheniumhaltige schutzbeschichtung, mit grosser korrosions- und/oder oxidationsbestaendigkeit
DE58908611D1 (de) 1989-08-10 1994-12-08 Siemens Ag Hochtemperaturfeste korrosionsschutzbeschichtung, insbesondere für gasturbinenbauteile.
KR100354411B1 (ko) 1994-10-14 2002-11-18 지멘스 악티엔게젤샤프트 부식,산화및과도한열응력으로부터부품을보호하기위한보호층및그제조방법
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US10371004B2 (en) 2019-08-06
EP2761057B1 (fr) 2020-03-25
EP2592174A1 (fr) 2013-05-15
WO2013072092A1 (fr) 2013-05-23
US20140302282A1 (en) 2014-10-09

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