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
• • 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
• • 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
• • 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
  • B32B33/00—Layered products characterised by particular properties or particular surface features, e.g. particular surface coatings; Layered products designed for particular purposes not covered by another single class
• • 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
• • 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
  • C22C19/03—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
  • C22C19/05—Alloys based on nickel or cobalt based on nickel with chromium
  • C22C19/058—Alloys based on nickel or cobalt based on nickel with chromium without Mo and W
• • C—CHEMISTRY; METALLURGY
  • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
  • C22C—ALLOYS
  • C22C21/00—Alloys based on aluminium
• • C—CHEMISTRY; METALLURGY
  • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
  • C22C—ALLOYS
  • C22C30/00—Alloys containing less than 50% by weight of each constituent
• • 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
• • 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
• • 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
  • F01D25/007—Preventing corrosion
• • 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
  • F01D5/288—Protective coatings for blades
• • 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
  • B32B2250/00—Layers arrangement
  • B32B2250/03—3 layers
• • 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
  • B32B2255/00—Coating on the layer surface
  • B32B2255/06—Coating on the layer surface on metal layer
• • 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
  • B32B2255/00—Coating on the layer surface
  • B32B2255/20—Inorganic coating
• • 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
  • B32B2311/00—Metals, their alloys or their compounds
  • B32B2311/22—Nickel or cobalt
• • 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
  • B32B2603/00—Vanes, blades, propellers, rotors with blades
• • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
  • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
  • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
  • Y02T50/00—Aeronautics or air transport
  • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
• • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
  • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
  • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
  • Y10T428/00—Stock material or miscellaneous articles
  • Y10T428/12—All metal or with adjacent metals
  • Y10T428/12493—Composite; i.e., plural, adjacent, spatially distinct metal components [e.g., layers, joint, etc.]
  • Y10T428/12535—Composite; i.e., plural, adjacent, spatially distinct metal components [e.g., layers, joint, etc.] with additional, spatially distinct nonmetal component
  • Y10T428/12611—Oxide-containing component
  • Y10T428/12618—Plural oxides
• • 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.]
  • Y10T428/12771—Transition metal-base component
  • Y10T428/12861—Group VIII or IB metal-base component
  • Y10T428/12931—Co-, Fe-, or Ni-base components, alternative to each other
• • 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.]
  • Y10T428/12771—Transition metal-base component
  • Y10T428/12861—Group VIII or IB metal-base component
  • Y10T428/12937—Co- or Ni-base component next to Fe-base component
• • 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.]
  • Y10T428/12771—Transition metal-base component
  • Y10T428/12861—Group VIII or IB metal-base component
  • Y10T428/12944—Ni-base component

Definitions

• the invention relates to a protective layer for protecting a component against corrosion and / or oxidation, in particular at high temperatures, according to claim 1.
• M stands for at least one of the elements from the group consisting of iron, cobalt and nickel and wei ⁇ tere essential components are chromium, aluminum and yttrium.
• 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 ° 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.
• 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 second layer comprises an MCrAlX alloy ent ⁇ neither with tantalum (Ta) and / or iron (Fe)
• X is optional and at least one of the elements from the group comprising scandium, rhenium and the elements of the rare earths,
• Y yttrium
• the lower layer alloy (7) contains 24% - 26% cobalt (Co);
• the lower layer (7) contains 15% - 16% chromium (Cr);
• the lower layer (7) contains 12% - 14% chromium (Cr);
• the lower layer (7) contains 0.3% - 0.5% yttrium (Y);
• the lower layer alloy consists of cobalt (Co), chromium (Cr), aluminum (AI), yttrium (Y) and nickel (Ni);
• the content of tantalum (Ta) in the alloy of the upper layer is between 0.1% by weight to 7.0% by weight, in particular> 1% by weight; the proportion of tantalum (Ta) in the alloy of the upper layer is at least 2.0% by weight,
• tantalum (Ta) in the alloy of the upper layer is between 3.0% by weight and 6.0% by weight; the proportion of tantalum (Ta) in the alloy of the upper layer is between 4% by weight and 8% by weight,
• the content of cobalt (Co) in the upper layer alloy is at least 1 wt%; the alloy of the upper layer has at least 1% by weight of chromium (Cr); the alloy of the upper layer (10) comprises 15% by weight to 16% by weight of chromium (Cr), in particular 15.5% by weight of Cr; the lower layer alloy has no rhenium (Re); the content of aluminum (Al) in the alloy of the upper layer is between 5% by weight and 15% by weight,
• the content of aluminum (Al) in the alloy of the upper layer (10) is between 10.5 wt .-% - 12 wt .-%, in particular 11.5 wt .-%; the alloy of the upper layer has no rhenium (Re); for alloys of metallic layers:
• gallium (Ga) not containing gallium (Ga) and / or
• the alloy of the lower layer and / or the upper layer contains no silicon (Si); the upper layer alloy is between 22% and 26% by weight
• the alloy of the upper layer (10) has at least 1% by weight of chromium (Cr); the alloy of the upper layer is nickel-based; the alloy of the lower layer is nickel-based; the upper layer has the ⁇ -phase, the ⁇ '-phase and optionally the ⁇ -phase,
• the alloy of the upper layer comprises at least 1% by weight of aluminum (AI); the alloy of the upper layer (10) has at least 0.1% by weight of yttrium (Y),
• the content of cobalt (Co) in the alloy of the upper layer is between 15% by weight and 30% by weight
• the content of chromium (Cr) in the alloy of the upper layer is between 12% by weight and 22% by weight
• the upper layer contains the ⁇ -phase
• the upper layer comprises an alloy of nickel (Ni), cobalt (Co), aluminum (Al), chromium (Cr), tantalum (Ta) and optionally yttrium (Y),
• the upper layer comprises an alloy of nickel (Ni), cobalt (Co), aluminum (Al), chromium (Cr), tantalum (Ta), iron (Fe) and optionally yttrium (Y),
• the upper layer comprises an alloy of nickel (Ni), cobalt (Co), aluminum (Al), chromium (Cr), tantalum (Ta) and yttrium (Y),
• the upper layer comprises an alloy of nickel (Ni), cobalt (Co), aluminum (Al), chromium (Cr), tantalum (Ta), iron (Fe) and yttrium (Y),
• Layer is between 12% by weight and 16% by weight
• the proportion of aluminum (AI) in the alloy of the upper layer is between 7% by weight and 8% by weight
• the proportion of rhenium (Re) in the alloy of the upper layer is 0.1% by weight - 2% by weight; the content of tantalum (Ta) in the upper-layer alloy is between 5% by weight and 6.8% by weight; the alloy of metallic layers contains no platinum (Pt); the content of cobalt (Co) in the upper layer alloy is between 11% by weight and 14.5% by weight; the content of chromium (Cr) in the upper layer alloy is between 14% by weight - 16% by weight; the content of aluminum (Al) in the alloy of the upper layer is between 9 wt .-% - 13 wt .-%; the content of yttrium (Y) in the upper layer alloy is between 0.1% by weight - 0.7% by weight; the alloy of the upper layer has (Ta) Zvi ⁇ rule 4 wt .-% and 7.5 wt .-% tantalum,
• the content of tantalum (Ta) in the alloy of the upper layer is between 3.5% by weight and 5.5% by weight, in particular 4.5% by weight; the content of cobalt (Co) in the alloy of the upper layer is between 21% by weight and 25% by weight,
• the content of chromium (Cr) in the upper layer alloy is between 18% by weight and 22% by weight;
• the upper layer does not contain yttrium (Y), the content of aluminum (Al) in the alloy of the upper layer is between 8% by weight and 12% by weight; the content of yttrium (Y) in the upper layer alloy is between 0.1% by weight - 0.7% by weight;
• the content of yttrium in the upper layer is 0.2% by weight - 0.6% by weight of yttrium (Y),
• FIG. 1 shows a layer system with a protective layer
• FIG. 2 shows compositions of superalloys
• FIG. 3 shows a gas turbine
• Figure 4 shows a turbine blade
• Figure 5 is a combustion chamber.
• the layer system 1, 120, 130, 155 (FIG. 1) for protecting a component with a substrate 4 against corrosion and oxidation at a high temperature has the following:
• Y yttrium
• the second layer 10 comprising an MCrAl alloy with either tantalum (Ta) and / or iron (Fe) or with the ⁇ and ⁇ 'phases and optionally the ⁇ phase.
• the protective layer 13 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 100 (FIG. 3) with a further increase in the inlet temperature ,
• the protective layer 13 comprises a lower MCrAlX layer 7 and an outer layer 10 comprising an MCrAlX alloy with tantalum (Ta) and / or iron (Fe).
• X is optional and preferably scandium, rare earth group, in particular yttrium and / or rhenium.
• the lower layer 7 is preferably a pure NiCoCrAl layer, ie without additions of tantalum and / or iron, wherein the outer layer 10 has additives such as tantalum and / or iron for setting phases, phase transition for good oxidation protection.
• the lower layer 7 is in its composition preferential ⁇ as relatively narrow set and alloys of nickel or cobalt super, in particular in accordance with Figure 2 adapted or the same expansion and good adhesion. Their ductility is significantly higher, at least 10%, in particular 20%, more pronounced than that of the outer metallic layer 10. Therefore, the outer layer 10 can be made extremely variable, much more independent of the composition of the substrate (4) and without compromise, depending on the application be: high temperature use (with fast oxide growth) or medium temperatures and long oxidation protection:
• the outer layer 10 has an excellent oxidation protection on the other hand, the lower layer has a very high Zähig ⁇ resistance and so protects the substrate 4, which may then be for a new use ⁇ error-free re-used.
• the powders are applied, for example, by plasma spraying (APS, LPPS, VPS, etc.). Other methods are also conceivable (PVD, CVD, cold gas spraying, ).
• the protective layer 13 also functions as described Haftvermitt ⁇ Lersch layer to a superalloy.
• the protective layer 7 more layers, in particular ⁇ ceramic thermal barrier coatings 16 can be applied.
• the protective layer 13 is before ⁇ geous legally applied to a substrate 4 made of a superalloy based on nickel or cobalt base, in particular according to FIG. 2
• compositions of this type are known as casting alloys under the designations GTD222, IN939, IN6203 and Udimet 500.
• the thickness of the protective layer 13 on the component 1 is preferably ⁇ sized to a value between about ⁇ and 300 ⁇ .
• the protective layer 13 is particularly suitable for protecting the component 1, 120, 130, 155 against corrosion and oxidation, while the component at a material temperature of about 950 ° C, in aircraft turbines also about 1100 ° C, with a
• the protective layer 13 according to the invention is thus particularly qualified for protecting a component of a gas turbine 100, in particular a guide blade 120, blade 130 or a heat shield element 155, which is acted upon with hot gas before or in the turbine of the gas turbine 100 or the steam turbine ⁇ .
• the protective layer 13 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 has a substrate 4.
• the substrate 4 may be metallic and / or ceramic. Particularly in turbine components, such as turbine runners 120 (FIG. 4) or guide vanes 130 (FIGS. 3, 4), heat shield elements 155 (FIG. 5) and other housing parts of a steam generator. or gas turbine 100 (FIG. 3), the substrate 4 comprises a nickel-, cobalt-based superalloy, in particular consisting thereof.
• nickel-based superalloys are used.
• the protective layer 13 according to the invention is present.
• this protective layer 13 is applied by plasma spraying (VPS, LPPS, APS1,).
• a ceramic j ⁇ specific heat-insulating layer 16 is provided on the protective layer. 13
• An aluminum oxide layer forms during operation on the metallic layer 13 and / or during the application of the ceramic layer 16.
• the protective layer 13 can be introduced ⁇ newly-manufactured components and remanufactured components from the refurbishment.
• 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 still have to 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 a rotatably mounted about a rotational axis 102 ⁇ rotor 103 having a shaft 101, 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 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 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.
• the working medium 113 expands in a pulse-transmitting manner, so that the blades 120 drive the rotor 103 and this drives 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. To withstand the prevailing temperatures, they can be cooled by means of a coolant.
• 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 ⁇ 120, 130 and components of the combustion chamber 110, for example, 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 guide vane 130 has an inner housing 138 of the turbine 108 facing guide vane root (not Darge here provides ⁇ ) 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. 4 shows a perspective view of a moving show ⁇ blade 120 or guide vane 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 designed, for example, as a hammer head. Other designs as Christmas tree or Schwalbenschwanzfuß are possible.
• the blade 120, 130 has for a medium which flows past the scene ⁇ felblatt 406 on a leading edge 409 and a trailing edge 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.
• the blade 120, 130 can hereby be produced 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.
• directionally solidified microstructures which means both single crystals that have no grain boundaries or at most small angle grain boundaries, and stem crystal structures that have probably longitudinal grain boundaries but no transverse grain boundaries. These second-mentioned crystalline structures are also known as directionally solidified 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
• thermal barrier coating which is preferably the outermost layer, and consists for example of ZrC> 2, Y203-ZrC> 2, ie it is not, partially ⁇ or fully stabilized by yttrium oxide
• 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
• 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.
• 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, 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 are then, for example, hollow 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 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).
• These protective layers 7 may be similar to the turbine blades.
• a ceramic Wär ⁇ medämm harsh be present and consists for example of ZrC> 2, Y203-ZrC> 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 insulating layer can comprise porous, micro- or macro-cracked compatible grains for better thermal shock resistance.
• Reprocessing means that turbines ⁇ blades 120, 130, heat shield elements 155, after entry set may need to have protective layers (for example by sandblasting). This is followed by removal of the corrosion and / or oxidation layers or products.
• cracks in the turbine blade 120, 130 or the heat shield element 155 are also repaired. This is followed by 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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• Organic Chemistry (AREA)
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• Inorganic Chemistry (AREA)
• Chemical Kinetics & Catalysis (AREA)
• Turbine Rotor Nozzle Sealing (AREA)
• Other Surface Treatments For Metallic Materials (AREA)
• Laminated Bodies (AREA)
• Physical Vapour Deposition (AREA)

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• 2011
  • 2011-09-12 RU RU2014114495/02A patent/RU2597459C2/ru not_active IP Right Cessation
  • 2011-09-12 US US14/344,208 patent/US9556748B2/en not_active Expired - Fee Related
  • 2011-09-12 CN CN201180073412.2A patent/CN103796828B/zh not_active Expired - Fee Related
  • 2011-09-12 EP EP11764501.0A patent/EP2729302A1/de not_active Withdrawn
  • 2011-09-12 KR KR1020147006214A patent/KR20140050714A/ko active Search and Examination
  • 2011-09-12 WO PCT/EP2011/065736 patent/WO2013037391A1/de active Application Filing

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