EP2971240B1 - Hybrid thermal barrier coating and process of making the same - Google Patents
Hybrid thermal barrier coating and process of making the same Download PDFInfo
- Publication number
- EP2971240B1 EP2971240B1 EP13878078.8A EP13878078A EP2971240B1 EP 2971240 B1 EP2971240 B1 EP 2971240B1 EP 13878078 A EP13878078 A EP 13878078A EP 2971240 B1 EP2971240 B1 EP 2971240B1
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- EP
- European Patent Office
- Prior art keywords
- layer
- barrier coating
- thermal barrier
- forming
- porosity
- Prior art date
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- 239000012720 thermal barrier coating Substances 0.000 title claims description 32
- 238000000034 method Methods 0.000 title claims description 19
- 230000008569 process Effects 0.000 title claims description 14
- 238000000576 coating method Methods 0.000 claims description 11
- 239000007921 spray Substances 0.000 claims description 11
- 239000000758 substrate Substances 0.000 claims description 10
- 229910001233 yttria-stabilized zirconia Inorganic materials 0.000 claims description 10
- 239000011248 coating agent Substances 0.000 claims description 9
- 239000000463 material Substances 0.000 claims description 6
- 239000002245 particle Substances 0.000 claims description 6
- 230000005855 radiation Effects 0.000 claims description 6
- 239000000725 suspension Substances 0.000 claims description 6
- 239000000843 powder Substances 0.000 claims description 4
- 239000006194 liquid suspension Substances 0.000 claims description 3
- 238000005328 electron beam physical vapour deposition Methods 0.000 description 7
- CMIHHWBVHJVIGI-UHFFFAOYSA-N gadolinium(iii) oxide Chemical compound [O-2].[O-2].[O-2].[Gd+3].[Gd+3] CMIHHWBVHJVIGI-UHFFFAOYSA-N 0.000 description 4
- 239000000203 mixture Substances 0.000 description 4
- OKKJLVBELUTLKV-UHFFFAOYSA-N Methanol Chemical compound OC OKKJLVBELUTLKV-UHFFFAOYSA-N 0.000 description 3
- 238000000151 deposition Methods 0.000 description 3
- 230000003628 erosive effect Effects 0.000 description 3
- LFQSCWFLJHTTHZ-UHFFFAOYSA-N Ethanol Chemical compound CCO LFQSCWFLJHTTHZ-UHFFFAOYSA-N 0.000 description 2
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 description 2
- 239000000956 alloy Substances 0.000 description 2
- 229910045601 alloy Inorganic materials 0.000 description 2
- 230000008901 benefit Effects 0.000 description 2
- 239000000919 ceramic Substances 0.000 description 2
- 230000008859 change Effects 0.000 description 2
- 230000008021 deposition Effects 0.000 description 2
- 230000009467 reduction Effects 0.000 description 2
- 229910002076 stabilized zirconia Inorganic materials 0.000 description 2
- 229910000531 Co alloy Inorganic materials 0.000 description 1
- 229910052688 Gadolinium Inorganic materials 0.000 description 1
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 description 1
- 150000001298 alcohols Chemical class 0.000 description 1
- 230000004888 barrier function Effects 0.000 description 1
- 238000005524 ceramic coating Methods 0.000 description 1
- 229910010293 ceramic material Inorganic materials 0.000 description 1
- 239000002131 composite material Substances 0.000 description 1
- 125000004122 cyclic group Chemical group 0.000 description 1
- UIWYJDYFSGRHKR-UHFFFAOYSA-N gadolinium atom Chemical compound [Gd] UIWYJDYFSGRHKR-UHFFFAOYSA-N 0.000 description 1
- 239000011159 matrix material Substances 0.000 description 1
- 229910052759 nickel Inorganic materials 0.000 description 1
- 239000010936 titanium Substances 0.000 description 1
- 229910052719 titanium Inorganic materials 0.000 description 1
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 1
Images
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
- 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
- C23C4/134—Plasma 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
- 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
- C23C28/04—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D only coatings of inorganic non-metallic material
- C23C28/042—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D only coatings of inorganic non-metallic material including a refractory ceramic layer, e.g. refractory metal oxides, ZrO2, rare earth 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
- 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
Definitions
- the present disclosure relates to a thermal barrier coating for use on a turbine engine component and to a process of making the thermal barrier coating.
- a thermal barrier coating (TBC) is created to meet one or more performance requirements including, but not liited to, spallation life, calcia-magnesia-alumina-silicate (CMAS) resistance, foreign object damage (FOD) resistance, erosion, and low conductivity.
- CMAS calcia-magnesia-alumina-silicate
- FOD foreign object damage
- a turbine barrier coating is applied to a turbine engine component, such as a turbine blade/vane, to help the component withstand the relatively high temperatures of its operational environment.
- TBCs are often formed using a singular coating process such as an electron beam physical vapor deposition (EB-PVD) process.
- EB-PVD electron beam physical vapor deposition
- a TBC may be formed from two separate EB-PVD layers formed from two different materials, such as 7 wt% yttria stabilized zirconia and gadolinia stabilized zirconia in order to improve the thermal conductivity properties of the coating.
- the strain-tolerant columnar structure of an EB-PVD coating helps to increase the TBC spallation life.
- a more porous TBC however may minimize the TBC thermal conductivity and possibly the thermal radiation through the coating.
- TBC there is a porous outer layer over a more dense inner layer made by an EB-PVD process.
- the two layers have different porosity levels.
- Such a structure can be formed by changing the coating temperature. More power equals more density but also more temperature. It is also known to form a dense vertically cracked microstructure for the TBC where the deposition is conducted at a two inch stand-off for the dense layer and a six inch stand-off for the porous layer.
- EP 2 341 166 discloses a TBC on a substrate, the TBC comprising a bond coat, a ceramic coating, and a ceramic layer.
- US 2011/244216 A1 discloses a combination of SPS and APS methods for deposition of multilayer thermal barrier coatings on turbine components.
- the applied materials comprise partially or fully YSZ as well as pyrochlores.
- EP 2 336 381 A1 discloses a thermal barrier coating deposited by APS, consisting of a first 7YSZ layer and a second gadolinia stabilized zirconia layer with a porosity of 5-20 vol.%.
- EP 2 450 465 A1 discloses a multilayer ceramic TBC deposited by APS, comprising an inner YSZ layer of low porosity, an intermediate YSZ layer with higher porosity than the inner layer and an outer porous layer of gadolinium zirconate.
- the second layer has a porosity in the range of from 10 to 40%.
- the first layer forming step comprises suspending a powder feedstock in a liquid suspension and injecting the powder feedstock and the suspension into a plasma jet under conditions where the first layer is formed with the strain-tolerant columnar microstructure.
- the second layer forming step comprises changing spray parameters so as to form the porous and radiation thermally resistant second layer.
- the second layer forming step comprises forming the second layer so as to have a porosity of from 10 to 40%.
- the first and second layer forming steps comprise using a powdered feedstock having a particle size in the range of from 10nm to 10 micrometers
- the first and second layer forming steps comprises using a powdered feedstock having a particle size in the range of from 10nm to 2.0 micrometers.
- the turbine engine component may be any component which requires a thermal barrier coating such as a blade/vane.
- the turbine engine component 10 may have a substrate 12 formed from any suitable material known in the art including, but not limited to, a nickel based alloy, a cobalt based alloy, a titanium based alloy, a ceramic material, and an organo-matrix composite material.
- a thermal barrier coating 14 is deposited on the substrate 12.
- the thermal barrier coating 14 has a first layer 16 which interfaces with the surface 18 of the substrate 12 and an outer second layer 20.
- the first layer 16 is formed so as to have a strain-tolerant columnar microstructure at the interface with the surface 18 of the substrate.
- the second layer 20 is formed to have a porous thermal conduction and radiant heat transfer resistant microstructure at an outer surface 22 of the thermal barrier coating.
- the first layer 16 and the second layer 20 is formed from a material having the same composition.
- Each of the layers 16 and 20 is formed from a 7 wt% yttria stabilized zirconia (7YSZ).
- each of the layers 16 and 20 is formed using suspension plasma spray (SPS) technique such as that shown in FIG. 2 .
- SPS suspension plasma spray
- a powdered feedstock is suspended in a liquid suspension 30.
- the powdered feedstock may be 7YSZ which may be suspended in ethanol, water, or other alcohols such as methanol.
- the powdered feedstock may have a particle size in the range of from 10 nm to 10 micrometers mean size diameter. In another non-limiting embodiment, the particles size may be in the range of from 10 nm to 2.0 micrometers.
- the powdered feedstock in the suspension is injected into a plasma jet 32 created by a plasma torch 34 and thus deposited onto the substrate 12.
- the spray conditions are such that the first layer 16 is formed to have the desired strain tolerant columnar microstructure.
- the deposition technique may have a short stand off (similar to that used in dense vertically cracked coatings) and high power/enthalpy plasma conditions.
- the spray conditions may be changed so as to form the second layer 20 with the porous thermal conduction and radiant heat transfer resistant microstructure.
- porosity (1) the angle of the spray nozzle could be changed from normal relative to the surface on which the layer 20 is being deposited; (2) the stand off may be increased; and/or (3) the plasma power/enthalpy may be reduced. More porosity in the second layer 20 than in the first layer 16 creates a reduction in thermal conductivity.
- the second layer 20 may have a reduction of at least 10% in thermal conductivity. This may come purely from a porosity increase or a change in the structure from columnar to more splat like. An increase in porosity increases the erosion rate. A useful limit may be 10 to 40% porosity in the second layer 20.
- the columnar structure SPS gives a thermal cyclic spallation resistance similar to EB-PVD (much higher than APS and higher than dense vertically cracked). Erosion is a function of porosity content and can be greater or less than EB-PVD (generally higher than APS and more like dense vertically cracked). Thermal conductivity, as discussed above, follows the porosity content.
- the spray conditions are discreetly or incrementally changed throughout the spray run.
- the spray conditions are changed so that a continuously graded microstructure is formed where there is the strain-tolerant columnar microstructure at the interface with the substrate 12 for thermal barrier coating spallation resistance and a porous thermal conduction and radiation thermally resistant layer at the outer surface 22.
- thermal barrier coating can be formed using a single piece of equipment and in a single coating.
- Another advantage is that one can easily change the composition of the second layer 20 so that it is different than the composition of the first layer 16. This can easily be done by changing the composition of the feedstock being injected into the plasma jet.
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- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Plasma & Fusion (AREA)
- Chemical Kinetics & Catalysis (AREA)
- Materials Engineering (AREA)
- Mechanical Engineering (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- Ceramic Engineering (AREA)
- Inorganic Chemistry (AREA)
- Coating By Spraying Or Casting (AREA)
Description
- The present disclosure relates to a thermal barrier coating for use on a turbine engine component and to a process of making the thermal barrier coating.
- A thermal barrier coating (TBC) is created to meet one or more performance requirements including, but not liited to, spallation life, calcia-magnesia-alumina-silicate (CMAS) resistance, foreign object damage (FOD) resistance, erosion, and low conductivity. A turbine barrier coating is applied to a turbine engine component, such as a turbine blade/vane, to help the component withstand the relatively high temperatures of its operational environment.
- TBCs are often formed using a singular coating process such as an electron beam physical vapor deposition (EB-PVD) process. For example, a TBC may be formed from two separate EB-PVD layers formed from two different materials, such as 7 wt% yttria stabilized zirconia and gadolinia stabilized zirconia in order to improve the thermal conductivity properties of the coating. The strain-tolerant columnar structure of an EB-PVD coating helps to increase the TBC spallation life. A more porous TBC however may minimize the TBC thermal conductivity and possibly the thermal radiation through the coating.
- In one TBC, there is a porous outer layer over a more dense inner layer made by an EB-PVD process. In some TBCs, the two layers have different porosity levels. Such a structure can be formed by changing the coating temperature. More power equals more density but also more temperature. It is also known to form a dense vertically cracked microstructure for the TBC where the deposition is conducted at a two inch stand-off for the dense layer and a six inch stand-off for the porous layer.
EP 2 341 166 discloses a TBC on a substrate, the TBC comprising a bond coat, a ceramic coating, and a ceramic layer. -
US 2011/244216 A1 discloses a combination of SPS and APS methods for deposition of multilayer thermal barrier coatings on turbine components. The applied materials comprise partially or fully YSZ as well as pyrochlores. -
EP 2 336 381 A1 discloses a thermal barrier coating deposited by APS, consisting of a first 7YSZ layer and a second gadolinia stabilized zirconia layer with a porosity of 5-20 vol.%. -
EP 2 450 465 A1 discloses a multilayer ceramic TBC deposited by APS, comprising an inner YSZ layer of low porosity, an intermediate YSZ layer with higher porosity than the inner layer and an outer porous layer of gadolinium zirconate. - In accordance with the present disclosure, there is provided a coating according to claim 1 and a process according to claim 3.
- In another and alternative embodiment, the second layer has a porosity in the range of from 10 to 40%.
- In another and alternative embodiment, the first layer forming step comprises suspending a powder feedstock in a liquid suspension and injecting the powder feedstock and the suspension into a plasma jet under conditions where the first layer is formed with the strain-tolerant columnar microstructure.
- In another and alternative embodiment, the second layer forming step comprises changing spray parameters so as to form the porous and radiation thermally resistant second layer.
- In another and alternative embodiment, the second layer forming step comprises forming the second layer so as to have a porosity of from 10 to 40%.
- In another and alternative embodiment, the first and second layer forming steps comprise using a powdered feedstock having a particle size in the range of from 10nm to 10 micrometers
- In another and alternative embodiment, the first and second layer forming steps comprises using a powdered feedstock having a particle size in the range of from 10nm to 2.0 micrometers.
- Other details of the hybrid thermal barrier coating and the process of making same are set forth in the following detailed description and the accompanying drawings wherein like reference numerals depict like elements.
-
-
FIG. 1 illustrates a turbine engine component having a thermal barrier coating in accordance with the present disclosure deposited thereon; and -
FIG. 2 illustrates a system for forming the coating on the turbine engine component. - Referring now to
FIG. 1 , there is shown aturbine engine component 10. The turbine engine component may be any component which requires a thermal barrier coating such as a blade/vane. Theturbine engine component 10 may have asubstrate 12 formed from any suitable material known in the art including, but not limited to, a nickel based alloy, a cobalt based alloy, a titanium based alloy, a ceramic material, and an organo-matrix composite material. - A
thermal barrier coating 14 is deposited on thesubstrate 12. Thethermal barrier coating 14 has afirst layer 16 which interfaces with thesurface 18 of thesubstrate 12 and an outersecond layer 20. Thefirst layer 16 is formed so as to have a strain-tolerant columnar microstructure at the interface with thesurface 18 of the substrate. Thesecond layer 20 is formed to have a porous thermal conduction and radiant heat transfer resistant microstructure at an outer surface 22 of the thermal barrier coating. - The
first layer 16 and thesecond layer 20 is formed from a material having the same composition. Each of thelayers - Each of the
layers FIG. 2 . In this technique, a powdered feedstock is suspended in aliquid suspension 30. For example, the powdered feedstock may be 7YSZ which may be suspended in ethanol, water, or other alcohols such as methanol. The powdered feedstock may have a particle size in the range of from 10 nm to 10 micrometers mean size diameter. In another non-limiting embodiment, the particles size may be in the range of from 10 nm to 2.0 micrometers. The powdered feedstock in the suspension is injected into aplasma jet 32 created by aplasma torch 34 and thus deposited onto thesubstrate 12. The spray conditions are such that thefirst layer 16 is formed to have the desired strain tolerant columnar microstructure. The deposition technique may have a short stand off (similar to that used in dense vertically cracked coatings) and high power/enthalpy plasma conditions. After thefirst layer 16 has been formed, the spray conditions may be changed so as to form thesecond layer 20 with the porous thermal conduction and radiant heat transfer resistant microstructure. To add porosity, (1) the angle of the spray nozzle could be changed from normal relative to the surface on which thelayer 20 is being deposited; (2) the stand off may be increased; and/or (3) the plasma power/enthalpy may be reduced. More porosity in thesecond layer 20 than in thefirst layer 16 creates a reduction in thermal conductivity. Thesecond layer 20 may have a reduction of at least 10% in thermal conductivity. This may come purely from a porosity increase or a change in the structure from columnar to more splat like. An increase in porosity increases the erosion rate. A useful limit may be 10 to 40% porosity in thesecond layer 20. - The columnar structure SPS gives a thermal cyclic spallation resistance similar to EB-PVD (much higher than APS and higher than dense vertically cracked). Erosion is a function of porosity content and can be greater or less than EB-PVD (generally higher than APS and more like dense vertically cracked). Thermal conductivity, as discussed above, follows the porosity content.
- The spray conditions are discreetly or incrementally changed throughout the spray run. The spray conditions are changed so that a continuously graded microstructure is formed where there is the strain-tolerant columnar microstructure at the interface with the
substrate 12 for thermal barrier coating spallation resistance and a porous thermal conduction and radiation thermally resistant layer at the outer surface 22. - One of the advantages of the process described herein is that the thermal barrier coating can be formed using a single piece of equipment and in a single coating.
- Another advantage is that one can easily change the composition of the
second layer 20 so that it is different than the composition of thefirst layer 16. This can easily be done by changing the composition of the feedstock being injected into the plasma jet. - There has been described herein a hybrid thermal barrier coating and a process for making same.
Claims (8)
- A thermal barrier coating (14) applied to a turbine engine component (10) having a substrate (2), said coating comprising:a first layer (16) which has a strain tolerant, columnar microstructure at an interface with the substrate for spallation resistance; anda second layer (20) which is porous, conduction and radiation thermally resistant at an outer surface of the thermal barrier coating;wherein there is a continuously graded microstructure from the interface to the outer surface;wherein said first and second layers are formed from the same material;wherein each of said first and second layers is formed from 7wt% yttria stabilized zirconia; andwherein said first layer has a first thermal conductivity and said second layer has a second thermal conductivity which is at least 10% lower than the first thermal conductivity.
- The thermal barrier coating of claim 1, wherein said second layer has a porosity in the range of from 10 to 40%.
- A process for applying a thermal barrier coating (14) to a turbine engine component (10) comprising:forming a first layer (16) which has a strain tolerant columnar microstructure at an interface of the first layer and a substrate using a suspension plasma spray technique;forming a second layer (20) which is porous and radiation thermally resistant at an outer surface of the thermal barrier coating using said suspension plasma spray technique;forming a continuously graded microstructure from said interface to said outer surfacewherein said first and second layer forming steps comprises forming said layers from the same material;wherein each of said first and second layers is formed from 7wt% yttria stabilized zirconia; andwherein said second layer forming step comprises forming said second layer with more porosity than the first layer so as to have a thermal conductivity which is at least 10% lower than a thermal conductivity of said first layer.
- The process of claim 3, wherein said first layer forming step comprises suspending a powder feedstock in a liquid suspension and injecting said powder feedstock and said suspension into a plasma jet under conditions where said first layer is formed with said strain-tolerant columnar microstructure.
- The process of claim 4, wherein said second layer forming step comprises changing spray parameters so as to form said porous and radiation thermally resistant second layer.
- The process of claim 3, wherein said second layer forming step comprises forming said second layer so as to have a porosity of from 10 to 40%.
- The process of claim 3, wherein said first and second layer forming steps comprise using a powdered feedstock having a particle size in the range of from 10nm to 10 micrometers.
- The process of claim 7, wherein said first and second layer forming steps comprise using a powdered feedstock having a particle size in the range of from 10nm to 2 micrometers.
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US201361781656P | 2013-03-14 | 2013-03-14 | |
PCT/US2013/078186 WO2014143363A1 (en) | 2013-03-14 | 2013-12-30 | Hybrid thermal barrier coating and process of making same |
Publications (3)
Publication Number | Publication Date |
---|---|
EP2971240A1 EP2971240A1 (en) | 2016-01-20 |
EP2971240A4 EP2971240A4 (en) | 2016-12-21 |
EP2971240B1 true EP2971240B1 (en) | 2018-11-21 |
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ID=51537485
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
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EP13878078.8A Active EP2971240B1 (en) | 2013-03-14 | 2013-12-30 | Hybrid thermal barrier coating and process of making the same |
Country Status (3)
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US (2) | US20160017475A1 (en) |
EP (1) | EP2971240B1 (en) |
WO (1) | WO2014143363A1 (en) |
Families Citing this family (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR3043411B1 (en) * | 2015-11-09 | 2017-12-22 | Commissariat Energie Atomique | HIGH-TEMPERATURE THERMAL PROTECTION MULTI-LAYER CERAMIC COATING, IN PARTICULAR FOR AERONAUTICAL APPLICATION, AND PROCESS FOR PRODUCING THE SAME |
US10436042B2 (en) | 2015-12-01 | 2019-10-08 | United Technologies Corporation | Thermal barrier coatings and methods |
JP6908973B2 (en) * | 2016-06-08 | 2021-07-28 | 三菱重工業株式会社 | Manufacturing methods for thermal barrier coatings, turbine components, gas turbines, and thermal barrier coatings |
Family Cites Families (10)
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JP3872632B2 (en) * | 2000-06-09 | 2007-01-24 | 三菱重工業株式会社 | Thermal barrier coating material, gas turbine member and gas turbine using the same |
US20090110953A1 (en) * | 2007-10-29 | 2009-04-30 | General Electric Company | Method of treating a thermal barrier coating and related articles |
DE102008007870A1 (en) * | 2008-02-06 | 2009-08-13 | Forschungszentrum Jülich GmbH | Thermal barrier coating system and process for its preparation |
US20110143043A1 (en) * | 2009-12-15 | 2011-06-16 | United Technologies Corporation | Plasma application of thermal barrier coatings with reduced thermal conductivity on combustor hardware |
US20110151132A1 (en) * | 2009-12-21 | 2011-06-23 | Bangalore Nagaraj | Methods for Coating Articles Exposed to Hot and Harsh Environments |
EP2341166A1 (en) * | 2009-12-29 | 2011-07-06 | Siemens Aktiengesellschaft | Nano and micro structured ceramic thermal barrier coating |
JP2010255121A (en) * | 2010-07-20 | 2010-11-11 | Mitsubishi Heavy Ind Ltd | Film material |
EP2450465A1 (en) * | 2010-11-09 | 2012-05-09 | Siemens Aktiengesellschaft | Porous coating system with porous internal coating |
US9017792B2 (en) * | 2011-04-30 | 2015-04-28 | Chromalloy Gas Turbine Llc | Tri-barrier ceramic coating |
US20130260132A1 (en) * | 2012-04-02 | 2013-10-03 | United Technologies Corporation | Hybrid thermal barrier coating |
-
2013
- 2013-12-30 EP EP13878078.8A patent/EP2971240B1/en active Active
- 2013-12-30 US US14/775,031 patent/US20160017475A1/en not_active Abandoned
- 2013-12-30 WO PCT/US2013/078186 patent/WO2014143363A1/en active Application Filing
-
2018
- 2018-06-04 US US15/996,929 patent/US20180282853A1/en not_active Abandoned
Non-Patent Citations (1)
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None * |
Also Published As
Publication number | Publication date |
---|---|
EP2971240A1 (en) | 2016-01-20 |
US20160017475A1 (en) | 2016-01-21 |
US20180282853A1 (en) | 2018-10-04 |
EP2971240A4 (en) | 2016-12-21 |
WO2014143363A1 (en) | 2014-09-18 |
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