EP3333279A1 - Method and device to produce a segmented porous ceramic coating, and a component thereof - Google Patents

Method and device to produce a segmented porous ceramic coating, and a component thereof Download PDF

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Publication number
EP3333279A1
EP3333279A1 EP16202821.1A EP16202821A EP3333279A1 EP 3333279 A1 EP3333279 A1 EP 3333279A1 EP 16202821 A EP16202821 A EP 16202821A EP 3333279 A1 EP3333279 A1 EP 3333279A1
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EP
European Patent Office
Prior art keywords
ceramic coating
component
coating
heat treatment
grains
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Withdrawn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
EP16202821.1A
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German (de)
French (fr)
Inventor
Uwe Rettig
Andreas Wolff
Dimitrios Zois
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Siemens AG
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Siemens AG
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Publication date
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Priority to EP16202821.1A priority Critical patent/EP3333279A1/en
Publication of EP3333279A1 publication Critical patent/EP3333279A1/en
Withdrawn legal-status Critical Current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
    • C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
    • C23C4/04—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge characterised by the coating material
    • C23C4/10—Oxides, borides, carbides, nitrides or silicides; Mixtures thereof
    • C23C4/11—Oxides
    • 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
    • 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
    • C23C4/12—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge characterised by the method of spraying
    • 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
    • C23C4/18—After-treatment
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/30—Manufacture with deposition of material
    • F05D2230/31—Layer deposition
    • F05D2230/312—Layer deposition by plasma spraying
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/40—Heat treatment
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/90—Coating; Surface treatment
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/20—Oxide or non-oxide ceramics
    • F05D2300/21—Oxide ceramics
    • F05D2300/2118—Zirconium oxides
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/50—Intrinsic material properties or characteristics
    • F05D2300/514—Porosity

Definitions

  • the invention relates to a heat treatment of a porous ceramic coating to yield a segmentation and a device.
  • TBC thermal barrier coatings
  • the stationary temperature gradient can be higher than 1000 K/mm. Under transient conditions (heating up, shut down) with temperature rates >> 100 K/s the local temperature gradient can be much higher resulting in strains, which exceed the coating strain tolerance and lead to crack formation.
  • the focus for the development of TBC's with enhanced life is to increase and maintain the strain tolerance under high temperature exposure by keeping the thermal conductivity as low as possible.
  • the second pathway to reduce thermal stresses in the coatings is to try to adopt the columnar structure of the EB-PVD coatings, which has shown evidently its long life due to its unique architecture.
  • This, in thermal spraying, is succeeded with producing a Dense Vertical Cracked (or Segmented) microstructure.
  • the vertical cracks produced in the coating allow it to "balance" different strain rates along its thickness.
  • the disadvantage of this pathway is the higher effective thermal conductivity in thickness direction which has to be compensated by thicker coating.
  • the problem is solved by a method according to claim 1 and a device according to claim 4 and a component according to claim 6.
  • the idea of the present invention is to introduce vertical cracks in a porous coating after spraying.
  • the process is preferably based on a 8YSZ coating typically thermally sprayed on samples or components.
  • the coated component is subjected to a steady sintering stage under a controlled thermal gradient wherein the heat flow is directed from the surface of the coating to the substrate.
  • the heat sources can be lasers, high power lamps, hot gas burners, plasma guns or special designed ovens.
  • the surface temperature has to be monitored and used to control the heating power.
  • the surface temperature has to be high enough to initiate the sinter process of the coating within reasonable times (>1523K). To avoid phase transitions and melting an upper temperature limit has to be established as well.
  • the spacing of the vertical crack pattern is mainly determined by the coating stiffness, which depends on the exposure time and temperature level as well as on the cooling rate. By adjusting the time at temperature-gradient-exposure and cooling rate a well-defined vertical crack pattern or segmentation network with tuned spacing can be formed.
  • the figure 1 shows an inventive device 1.
  • the device 1 comprises at least an oven 10 in which several hollow components 7', 7", ..., 100 can be mounted on adapters 11', 11", ... which provide a cooling medium.
  • the cooling medium is especially provided by one or several tubes 4 which is especially air or any gas especially from outside the oven 10.
  • This cooling medium must not be at ambient temperature but can be heated too.
  • the heating on an outer side of the ceramic coating 70 can especially performed by laser beams.
  • a control unit 13 is used for regulating the cooling, the heating of the coating 70 and the temperature of the oven.
  • Figure 2 shows a component 100 which is an example for component 7', 7".
  • the component 100 has especially a metallic substrate 40 which is especially a nickel or cobalt based super alloy.
  • these substrate 40 several coatings like metallic bond coats (not shown, e. g. NiCoCrAlY) are present and at least an outer ceramic coating 70.
  • metallic bond coats e. g. NiCoCrAlY
  • the ceramic coating 70 is especially made of zirconia, especially 8YSZ, 48YSZ or a pyrochlore structure.
  • the ceramic coating 70 has a porosity of at least 3%, especially of at least 5% and maximum 15%, especially maximum 10%, very especially maximum 8%.
  • the ceramic coating 70 Before the heat treatment the ceramic coating 70 has no long, vertical cracks, wherein “vertical” means almost perpendicular to the outermost surface towards substrate 40 and “long” means at least 10% to 90% especially 20% to 80% of the thickness of the ceramic coating 70.
  • FIG 3 an enlarged view of the microstructure of the coating 70 is shown.
  • the ceramic coating 70 comprises some pores 75, wherein due to the thermal treatment in the oven 10 vertical cracks 77 were firstly developed, which start from the outermost surface of the coating 70.
  • the coating 70 was produced by a spraying method (APS, VPS, LPPS, HVOF, cold spray, ...) using powder grains. By the heat treatment the powder grains sinter together.

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

Abstract

By a subsequent heat treatment of a porous ceramic coating a segmented porous coating can be yield.

Description

  • The invention relates to a heat treatment of a porous ceramic coating to yield a segmentation and a device.
  • The most severe failure mode for thermal barrier coatings (TBC) is delamination followed by spallation. The driving forces are thermal strains caused by steep temperature gradients in thickness direction and mismatch of thermal expansion between coating and underlying bond coat/substrate.
  • On newly developed engines the stationary temperature gradient can be higher than 1000 K/mm. Under transient conditions (heating up, shut down) with temperature rates >> 100 K/s the local temperature gradient can be much higher resulting in strains, which exceed the coating strain tolerance and lead to crack formation. The focus for the development of TBC's with enhanced life is to increase and maintain the strain tolerance under high temperature exposure by keeping the thermal conductivity as low as possible.
  • The possible solutions to address the temperature induced stresses in thermally sprayed coatings follow two different pathways:
    • The first has pushed thermal spray coatings porosity upwards in order to decrease the elastic modulus which directly decreases the thermally induced stresses. Additionally, higher porosity reduces the thermal conductivity, rendering the coating a better thermal insulator.
    However, that has caused the shrinkage of the sprayability window that allows coatings to combine high porosity and good cohesion. As a result of the dwindling coating cohesion, erosion has started manifesting itself as a major issue for coatings in specificparts and engines. The problem is relatively new and no solution has been implemented till now. Additionally as the firing temperature of turbines increases, sintering of the coatings occurs rather fast which leads to an increase in coating stiffness and elastic modulus. Thus the same thermal strains cause higher stresses under progressive sintering which reduce the TBC life.
  • The second pathway to reduce thermal stresses in the coatings is to try to adopt the columnar structure of the EB-PVD coatings, which has shown evidently its long life due to its unique architecture. This, in thermal spraying, is succeeded with producing a Dense Vertical Cracked (or Segmented) microstructure. The vertical cracks produced in the coating allow it to "balance" different strain rates along its thickness. The disadvantage of this pathway is the higher effective thermal conductivity in thickness direction which has to be compensated by thicker coating.
  • It is therefore aim of the invention to overcome the problem listed above.
  • The problem is solved by a method according to claim 1 and a device according to claim 4 and a component according to claim 6.
  • In the subclaims further advantageous features are listed which can be arbitrarily combined with each other to yield further advantages.
  • The idea of the present invention is to introduce vertical cracks in a porous coating after spraying.
  • The process is preferably based on a 8YSZ coating typically thermally sprayed on samples or components.
    The coated component is subjected to a steady sintering stage under a controlled thermal gradient wherein the heat flow is directed from the surface of the coating to the substrate. The heat sources can be lasers, high power lamps, hot gas burners, plasma guns or special designed ovens.
  • The surface temperature has to be monitored and used to control the heating power. The surface temperature has to be high enough to initiate the sinter process of the coating within reasonable times (>1523K). To avoid phase transitions and melting an upper temperature limit has to be established as well.
  • To ensure a steep thermal gradient and to protect the metallic part from oxidation, the metallic substructures have to be cooled actively and in a controlled manner. Complex hot gas path components have internal cooling structures already included which need to be used. Under this uneven steady temperature gradient two processes take place:
    1. i) sintering which increases the stiffness of the coating and leads to shrinkage
    2. ii) creep, which leads to a complete relaxation of the mostly compressive stress within the hot coating surface region. The sintering driven shrinkage of the coating material can already form a network of vertical cracks. But the major driving force for segmentation are the high tensile stresses applied during cooling down and boosted due to stress reversion of the relaxed compressive stresses.
  • The spacing of the vertical crack pattern is mainly determined by the coating stiffness, which depends on the exposure time and temperature level as well as on the cooling rate. By adjusting the time at temperature-gradient-exposure and cooling rate a well-defined vertical crack pattern or segmentation network with tuned spacing can be formed.
  • This method presents the following advantages, regarding design and manufacturability:
    1. 1) The initial coating can be a typical ceramic coating, which means that the overall porosity is lower than the currently used dense vertical cracked (DVC) TBCs. Thus, the resulting coatings of this type can be thinner by offering the same thermal insulation.
    2. 2) The manufacturability of this process is easier of the ones followed to manufacture a segmented TBC on a gas turbine part. Typically the segmented TBCs need a tight control of the substrate temperature and can be expensive depending on the hardware consumed during spraying.
  • The most significant benefit though is related to performance:
    • During testing of the same coating before and after a sintering treatment a significant difference in the performance of the coating has been detected. Specifically, during thermal cycling on a High Heat Flux Test rig where the difference between coating surface and substrate temperature was more than 973K, the sintered coating has shown more than 100 times life increase. While the porous 8YSZ coating lasted only 6 cycles, the thermally pre-segmented coating lasted more than 800 cycles.
      Figure 1
      shows an inventive device,
      figure 2
      a component and
      figure 3
      a enlarged view of a ceramic coating.
  • The figure 1 shows an inventive device 1.
  • The device 1 comprises at least an oven 10 in which several hollow components 7', 7", ..., 100 can be mounted on adapters 11', 11", ... which provide a cooling medium.
  • The cooling medium is especially provided by one or several tubes 4 which is especially air or any gas especially from outside the oven 10.
  • This cooling medium must not be at ambient temperature but can be heated too.
  • The heating on an outer side of the ceramic coating 70 (fig. 2) can especially performed by laser beams.
  • A control unit 13 is used for regulating the cooling, the heating of the coating 70 and the temperature of the oven.
  • Figure 2 shows a component 100 which is an example for component 7', 7".
  • The component 100 has especially a metallic substrate 40 which is especially a nickel or cobalt based super alloy.
  • On this substrate 40 several coatings like metallic bond coats (not shown, e. g. NiCoCrAlY) are present and at least an outer ceramic coating 70.
  • The ceramic coating 70 is especially made of zirconia, especially 8YSZ, 48YSZ or a pyrochlore structure.
  • The ceramic coating 70 has a porosity of at least 3%, especially of at least 5% and maximum 15%, especially maximum 10%, very especially maximum 8%.
  • Before the heat treatment the ceramic coating 70 has no long, vertical cracks, wherein "vertical" means almost perpendicular to the outermost surface towards substrate 40 and "long" means at least 10% to 90% especially 20% to 80% of the thickness of the ceramic coating 70.
  • In figure 3 an enlarged view of the microstructure of the coating 70 is shown. The ceramic coating 70 comprises some pores 75, wherein due to the thermal treatment in the oven 10 vertical cracks 77 were firstly developed, which start from the outermost surface of the coating 70.
  • The coating 70 was produced by a spraying method (APS, VPS, LPPS, HVOF, cold spray, ...) using powder grains. By the heat treatment the powder grains sinter together.

Claims (8)

  1. Method
    to produce a segmented porous ceramic coating (70), wherein firstly a grained ceramic coating on a hollow component (100, 7', 7", ...) is provided or
    a grained ceramic coating is applied on a hollow substrate (40) of a component (100, 7', 7", ...),
    wherein almost no long, vertical cracks are present in the ceramic coating (70),
    applying a heat treatment to the component (7', 7", ...) with the coating,
    to sinter the grains of the ceramic coating (70), wherein the hollow component (100, 7', 7", ...) is simultaneously cooled inside during the heat treatment to yield a thermal gradient between the cooled area and the ceramic coating (70) to yield the long vertical cracks.
  2. Method according to claim 1,
    wherein the ceramic coating (70) comprises zirconia, especially 8YSZ,
    or a pyrochlore structure.
  3. Method according to claim 1 or 2,
    wherein the temperature of the heat treatment is at least 1523K.
  4. Method according to claim 1, 2 or 3,
    wherein the duration of the heat treatment enables sintering of the grains of the ceramic coating (70).
  5. Device,
    especially to perform a method according to claim 1, 2, 3 or 4,
    which at least comprises:
    an oven (10),
    at least one adapter (11', 11", ...) for components (7', 7", ...) at least one in the oven,
    wherein the adapter (11', 11", ...) supplies a cooling medium into the component (7', 7", ...),
    heating elements and
    a control unit (13).
  6. Device according to claim 5,
    where the heating elements are laser beams.
  7. Component (100, 7', 7", ...),
    which comprises
    an hollow substrate (40),
    which can be cooled inside and
    at least an outer ceramic coating (70),
    wherein the ceramic coating (70) comprises zirconia, which has a porosity of at least 3%,
    especially of at least 5%, and
    vertical cracks (77),
    wherein the ceramic coating (70) was produced by spraying grains of powder and
    wherein the sprayed grains are sintered together after spraying.
  8. Component according to claim 7,
    wherein the ceramic coating 70 has a porosity of at least 3%, especially of at least 5% and
    maximum 15%, especially maximum 10%, very especially maximum 8%.
EP16202821.1A 2016-12-08 2016-12-08 Method and device to produce a segmented porous ceramic coating, and a component thereof Withdrawn EP3333279A1 (en)

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Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN109161889A (en) * 2018-07-19 2019-01-08 西安交通大学 The anti-sintering bimodulus composite construction thermal barrier coating of one kind and its preparation process
WO2023078633A1 (en) * 2021-11-08 2023-05-11 Siemens Energy Global GmbH & Co. KG A method to produce porous segmented thermal barrier coating and a porous segmented thermal barrier coating
US20230184132A1 (en) * 2020-05-19 2023-06-15 Forschungszentrum Jülich GmbH Operation of a gas turbine at a high temperature and gas turbine assembly

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20040156724A1 (en) * 2001-06-15 2004-08-12 Taiji Torigoe Thermal barrier coating material method of production thereof, gas turbine member using the thermal barrier coating material, and gas turbine
US20100136258A1 (en) * 2007-04-25 2010-06-03 Strock Christopher W Method for improved ceramic coating

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20040156724A1 (en) * 2001-06-15 2004-08-12 Taiji Torigoe Thermal barrier coating material method of production thereof, gas turbine member using the thermal barrier coating material, and gas turbine
US20100136258A1 (en) * 2007-04-25 2010-06-03 Strock Christopher W Method for improved ceramic coating

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
KARGER M ET AL: "Atmospheric plasma sprayed thermal barrier coatings with high segmentation crack densities: Spraying process, microstructure and thermal cycling behavior", SURFACE AND COATINGS TECHNOLOGY, ELSEVIER BV, AMSTERDAM, NL, vol. 206, no. 1, 18 June 2011 (2011-06-18), pages 16 - 23, XP028261462, ISSN: 0257-8972, [retrieved on 20110625], DOI: 10.1016/J.SURFCOAT.2011.06.032 *

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN109161889A (en) * 2018-07-19 2019-01-08 西安交通大学 The anti-sintering bimodulus composite construction thermal barrier coating of one kind and its preparation process
CN109161889B (en) * 2018-07-19 2020-05-22 西安交通大学 Anti-sintering dual-mode composite structure thermal barrier coating and preparation process thereof
US20230184132A1 (en) * 2020-05-19 2023-06-15 Forschungszentrum Jülich GmbH Operation of a gas turbine at a high temperature and gas turbine assembly
WO2023078633A1 (en) * 2021-11-08 2023-05-11 Siemens Energy Global GmbH & Co. KG A method to produce porous segmented thermal barrier coating and a porous segmented thermal barrier coating

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