Classifications

• • 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
• • 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

Definitions

• the invention relates to a component for a turbomachine, in particular steam turbine, with a component surface.
• a component for a turbomachine in particular steam turbine
• Protective coatings for high operating temperatures are commonly used today in turbomachinery.
• the main field of application of such high-temperature protective layers is found in the field of thermal turbomachines, especially in highly stressed steam turbine components.
• Such protective layers serve to extend the service life of the high-temperature materials to be protected.
• Zones of a steam turbine can be used to fulfill two characteristics. These are on the one hand the oxidation resistance and on the other hand the creep rupture strength. Basically, materials are known that can meet such requirements, such as nickel-based alloys, which are increasingly used. However, such materials are relatively expensive. Therefore, the materials mentioned above are replaced by much cheaper materials, such as ferritic 10% chromium steel or similar replaced. The disadvantage of such ferritic 10% chromium steels or other similar materials is that they do not have sufficient oxidation resistance and are therefore unsuitable for some applications in the steam turbine.
• the thermally stressed components have been exposed in areas exposed to approximately 600 ° C hot steam, such as e.g. High-pressure or medium-pressure turbine blades, partially made of nickel-based alloys.
• the established chromium steels are generally no longer used at steam temperatures in the range of well above 600 ° C., since the oxidation resistance of such chromium steels in this range is no longer sufficient.
• a component for a turbomachine in particular a steam turbine, with a component surface, wherein a ceramic hard material layer is applied directly to the component surface, wherein a metallic layer is applied directly to the ceramic hard material layer.
• a duplex protective layer consisting of two layers is applied to the component.
• the component has a component surface, wherein a ceramic hard material layer is arranged directly on this component surface. It is essential here that the ceramic hard material layer is applied directly to the component surface, ie, that no intermediate layer is arranged between the component surface and the ceramic hard material layer.
• a metallic layer is applied directly to this ceramic hard material layer. It is also important here again that no further intermediate layer is arranged between the ceramic hard material layer and the metallic layer.
• the invention is based on the idea that the duplex layer according to the invention offers improved oxidation protection and improved erosion resistance. This means that the base material of the component does not necessarily have to be a nickel-based alloy. Instead, cheaper materials can be used instead of the nickel-based alloy.
• the component has the following materials:
• High temperature suitable Cr alloyed steels for use in turbomachines such as e.g. X20Cr13 (1.4021),
• the metallic layer comprises the following materials:
• the duplex layer is further developed into a triplex layer by applying a second ceramic hard material layer directly to the metallic layer.
• a second ceramic hard material layer directly to the metallic layer.
• the ceramic hard material layer is arranged directly on the metallic layer, ie that no further intermediate layer is applied between the ceramic hard material layer and the metallic layer.
• the second ceramic hard material layer comprises the following materials:
• the thicknesses of the ceramic hard material layer, the metallic protective layer and the second ceramic hard material layer have thicknesses in the range of 5 ⁇ to 25 ⁇ .
• FIG. 1 shows a duplex protective layer according to the invention
• FIG. 2 shows a triplex protective layer according to the invention.
• FIG. 1 shows a component 1.
• This component is designed for use in a turbomachine.
• turbomachine is understood, for example, a steam turbine, a compressor or a gas turbine or other thermal machines.
• the component has a component surface 2.
• a ceramic hard material layer 3 is arranged directly.
• the ceramic hard material layer 3 is arranged directly on the component surface, ie no further layer is arranged between the ceramic hard material layer 3 and the component surface 2.
• a metallic layer 4 is arranged directly.
• the metallic one Layer 4 is arranged directly on the ceramic hard material layer 3, ie no further intermediate layer is arranged between the metallic layer 4 and the ceramic hard material layer 3.
• the component contains the following materials:
• High temperature suitable Cr alloyed steels for use in turbomachines such as e.g. X20Cr13 (1.4021), X22CrMoV12-1 (1.4923), X12CrMoWVNbN10-1- (1.4906), 10CrMo9-10 (1.7380).
• the chemical compositions are as follows (in% by weight):
• MO 1.00 - 1.20 N: 0, 040 - 0.060
• Nb 0, 040-0.060
• the ceramic hard material layer comprises the following materials:
• the metallic layer comprises the following materials:
• the embodiment according to FIG. 1 can be referred to as a duplex layer, since the protective layer protects against erosion and
• Oxidation on the component surface 2 comprises two layers.
• FIG. 2 shows a further development of the component from FIG. 1.
• the further development consists in the fact that a second ceramic hard material layer 5 is now applied to the metallic layer 4.
• the second ceramic hard material layer 3 comprises the following materials: - CrN
• the ceramic hard material layer 3 is formed such that the thickness of the ceramic hard material layer 3 is in the range of 5 ⁇ to 25 ⁇ .
• the metallic layer 4 is formed such that the metallic layer 4 has a thickness which is in the range between 5 ⁇ and 25 ⁇ .
• the second ceramic hard material layer 5 is formed in such a way that the second ceramic hard material layer 5 has a thickness which lies in the range between 5 ⁇ m to 25 ⁇ m.
• the component is designed, for example, as a turbine blade for a steam turbine.
• the turbine blade may be a rotor blade or a vane.
• the combination of the two layers comprising the ceramic hard material layer 3 and the metallic layer 4 form a very good protection of the component 1 against oxidation and at the same time also offer good erosion resistance.
• the ceramic hard material layer 3 acts primarily as a diffusion barrier, which ensures that interdiffusion between the base material of the component 1 and the metallic protective layer 4 does not occur. In addition, this layer already offers good oxidation protection.
• the metallic layer 4 offers a very good protection against oxidation and erosion, in particular against particles which strike the surface perpendicular to the surface.
• the triplex layer is carried out at sites particularly subject to erosion.
• the second ceramic hard material layer 5 in the triplex layer offers particularly good protection as erosion protection and additionally as oxidation protection.
• the duplex and / or triplex layers are preferably applied by means of a PVD method, in which case in particular sputtering methods are to be used.

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• Chemical & Material Sciences (AREA)
• Inorganic Chemistry (AREA)
• Chemical Kinetics & Catalysis (AREA)
• Engineering & Computer Science (AREA)
• Materials Engineering (AREA)
• Mechanical Engineering (AREA)
• Metallurgy (AREA)
• Organic Chemistry (AREA)
• Turbine Rotor Nozzle Sealing (AREA)
• Other Surface Treatments For Metallic Materials (AREA)

Priority Applications (1)

Applications Claiming Priority (2)

Publications (1)

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Citations (5)

• 2012
  • 2012-07-11 EP EP12175910.4A patent/EP2684982A1/fr not_active Withdrawn
• 2013
  • 2013-06-12 WO PCT/EP2013/062155 patent/WO2014009089A1/fr not_active Ceased
  • 2013-06-12 CN CN201390000611.5U patent/CN204803410U/zh not_active Expired - Fee Related

Patent Citations (5)

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