EP3957827A1 - Système de revêtement d'un composant d'un moteur à turbine à gaz - Google Patents

Système de revêtement d'un composant d'un moteur à turbine à gaz Download PDF

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Publication number
EP3957827A1
EP3957827A1 EP20425031.0A EP20425031A EP3957827A1 EP 3957827 A1 EP3957827 A1 EP 3957827A1 EP 20425031 A EP20425031 A EP 20425031A EP 3957827 A1 EP3957827 A1 EP 3957827A1
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EP
European Patent Office
Prior art keywords
layer
range
tbc
coating system
micrometers
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.)
Pending
Application number
EP20425031.0A
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German (de)
English (en)
Inventor
Hans-Peter-Peter Bossmann
Anish Paul
Alessandra Bonadei
Giuseppe Carlo Gualco
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Ansaldo Energia Switzerland AG
Ansaldo Energia SpA
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Ansaldo Energia Switzerland AG
Ansaldo Energia SpA
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Application filed by Ansaldo Energia Switzerland AG, Ansaldo Energia SpA filed Critical Ansaldo Energia Switzerland AG
Priority to EP20425031.0A priority Critical patent/EP3957827A1/fr
Priority to CN202110948384.XA priority patent/CN114075644A/zh
Publication of EP3957827A1 publication Critical patent/EP3957827A1/fr
Pending 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
    • C23C4/12—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
    • 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
    • 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
    • C23C4/02—Pretreatment of the material to be coated, e.g. for coating on selected surface areas
    • 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
    • C23C4/06—Metallic material
    • C23C4/073—Metallic material containing MCrAl or MCrAlY alloys, where M is nickel, cobalt or iron, with or without non-metal elements
    • 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
    • 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
    • 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
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2270/00—Control
    • F05B2270/10—Purpose of the control system
    • F05B2270/109—Purpose of the control system to prolong engine life
    • F05B2270/1091—Purpose of the control system to prolong engine life by limiting temperatures
    • 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
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/15—Heat shield
    • 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
    • F05D2240/00—Components
    • F05D2240/35—Combustors or associated equipment
    • 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
    • F05D2250/00—Geometry
    • F05D2250/60—Structure; Surface texture
    • F05D2250/63—Structure; Surface texture coarse
    • 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
    • F05D2300/10—Metals, alloys or intermetallic compounds
    • F05D2300/17—Alloys
    • F05D2300/175—Superalloys
    • 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
    • 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
    • F05D2300/516—Surface roughness

Definitions

  • the present invention relates to a coating system for a component of a gas turbine engine.
  • Gas turbine engines comprise a compressor, one or more sequential combustion chambers, with or without a high-pressure turbine or a diluter in-between, and a turbine (low pressure turbine). Air is compressed at the compressor, a fuel is mixed with the compressed air and combusted at the combustors, generating a high-pressure hot gas that is expanded in the turbine.
  • the components of the gas turbine engine that come into contact with the hot gas are highly thermally stressed and often also highly mechanically stressed.
  • these components can include the combustion chambers and their components such as liner, burners, etc., the turbines and their components, such as vanes (non-rotating blades), blades (rotating blades), heat shields, etc.
  • a base material e.g. a metal alloy or a ceramic material
  • a coating system including a bond coat layer (BC layer) e.g. made of a MCrAlY alloy (in the case of a metallic BC layer) and a ceramic thermal barrier coating layer (TBC layer) e.g. made of Zirconia fully stabilized or partially stabilized with Yttria (YSZ).
  • BC layer bond coat layer
  • MCrAlY alloy in the case of a metallic BC layer
  • TBC layer ceramic thermal barrier coating layer
  • New gas turbine engines have increased flame temperatures, which result in higher material temperatures, and/or they require longer lifetime; consequently the coating has to provide higher temperature capability and/or longer minimum lifetime.
  • An aspect of the invention includes providing a coating system for a component of the hot gas part of a gas turbine engine with longer minimum lifetime.
  • the invention is based on the recognition that tight ranges (tighter than in existing solutions) for the BC layer roughness, BC layer thickness, TBC layer thickness and TBC layer porosity can be selected in order to achieve a minimum lifetime that shows a surprisingly high peak compared to the selection of other parameters or, for the selected parameters, compared to broader ranges.
  • a component of the hot gas part of a gas turbine engine comprises a base element 1 and a coating system with a BC layer 2 (bond coat layer) and a TBC layer 3 (thermal barrier coating layer); optionally, a second TBC layer 4 (second thermal barrier coating layer) can be provided on the TBC layer 3; in this case, the second TBC layer 4 is the outer layer of the coating and the TBC layer 3 is an intermediate layer between the BC layer 2 and the second TBC layer 4.
  • the base element 1 can be made of a Nickel superalloy, the BC layer 2 of a MCrAlY alloy, the TBC layer 3 of Yttria partially stabilized Zirconia (e.g.
  • 7YSZ where 7YSZ stands for Zirconia partially stabilized with 7wt% Yttria
  • the second TBC layer 4 if provided
  • Yttria fully stabilized Zirconia (e.g. 14YSZ, i.e. Zirconia fully stabilized with 14wt% Yttria).
  • the minimum lifetime of the coating system can be increased, and this can be achieved independently from the particular materials of the BC layer, TBC layer and, if provided, second TBC layer.
  • the BC layer has a thickness in the range 180-300 micrometers and a roughness Ra of its surface 6 facing the TBC layer in a range 12.8-19.0 micrometers.
  • the TBC layer has a thickness in the range 200-700 micrometers and a porosity in the range 15.0-23.0 vol%. In the above ranges, the ends of the ranges are to be considered included in the ranges.
  • ranges include a BC layer with a thickness in the range 185-280 micrometers and a roughness Ra of its surface facing the TBC layer in a range 13.0-18.0 micrometers, and the TBC layer with a thickness in the range 210-640 micrometers and a porosity in the range 15.5-20.2 vol%, wherein the ends of ranges are included in the same ranges.
  • Further preferred embodiments include the BC layer with a thickness in the range 201-217 micrometers and a roughness Ra of its surface facing the TBC layer in a range 13.0-16.5 micrometers, and the TBC layer with a thickness in the range 220-249 micrometers and a porosity in the range 15.6-20.2 vol%, with ends of ranges included in the ranges.
  • BC Thickness BC Roughness TBC Thickness TBC Porosity Range 1 (R1) 180 12.8 200 15.0 300 19.0 700 23.0 Range 2 (R2) 185 13.0 210 15.5 280 18.0 640 20.2 Range 3 (R3) 201 13.0 220 15.6 217 16.5 249 20.2
  • FCT-life i.e. the lifetime of each sample in hours for cyclic test carried out at 1100°C.
  • the samples were discs made of nickel superalloy provided with different coating systems.
  • the coating systems of the samples had none of the relevant parameters (i.e. BC layer thickness and roughness and TBC layer thickness and porosity) in the ranges R1, R2, R3 (these ranges are summarized in the above table) or only one or two or three or all four relevant parameters in the ranges R1, R2, R3.
  • the BC layer was made of different MCrAlY alloys.
  • the BC Thickness i.e. the thickness in micrometers of the BC layer
  • the BC Thickness was measured by cutting a cross section of each sample and obtaining an image by optical microscopy of the cross section and then applying computer based image analysis to obtain the required measurement.
  • the images of the cross section were captured using an optical microscope and on the basis of these images the thickness was measured by an appropriate software.
  • a commercially available software for this task is IMAGE PRO premier of Media Cybernetic.
  • the BC Roughness i.e. the roughness of the surface of the BC layer that faces the TBC layer, i.e. with reference to figures 1 and 2 this is the roughness of the surface 6, was measured by a roughness tester (perthometer) using a 2.5 mm cut-off wavelength; alternatively the roughness can be measured by computer based image analysis technique; in this case the images have to be captured with the required magnification.
  • the TBC layer was made of 7YSZ por, i.e. porous Zirconia partially stabilized with 7 wt% Yttria.
  • the TBC layer was applied by spray technique, in this case the required porosity is achieved by spraying zirconia powder having a size 20-90 micrometers with a plasma spray gun.
  • the TBC layer was applied by mixing polypropylene (or other polymeric powders) to the 7YSZ powders having a size of 20-120 micrometers and then applying the mixed powder by spraying with a plasma gun with parameters that don't produce complete burning of the polymer grains; after spraying a heat treatment in air was carried out to burn the polymer grains embedded in the TBC, producing the porosity.
  • the TBC Thickness i.e. the thickness in micrometers of the TBC layer, was measured in the same manner as the thickness of the BC layer.
  • the TBC Porosity i.e. the porosity of the TBC layer in %vol, was measured by computer-based image analysis technique on the cross section of the TBC layer; preferably the porosity of the TBC layer was measured at the same positions where the thickness of the TBC layer was measured.
  • the porosity was measured by measuring the cross section area with material and the cross section area without material (empty area), porosity was thus obtained by dividing the empty area by the total area (i.e. material area + empty area).
  • Some samples were also provided with a second TBC layer provided above the TBC layer, the material of this second TBC layer was porous Zirconia fully stabilized with 14 wt% Yttria applied by spray technique.
  • Figure 3 shows the minimum FCT-life for samples having respectively 1, 2, 3 and 4 parameters in the ranges R1; the same figure 3 also shows the minimum FCT-life for samples having 4 parameters in the ranges R2 and R3.
  • Figure 3 shows that when the values of all four parameters are in the range R1, the minimum FCT-life is 2004 h, whereas when less than four parameters lie in the range R1 the minimum lifetime drastically drops down to 1024 h for three parameters or 535 h for two parameters or 1187 h for only one parameter in the selected range.
  • samples with all four parameters in the range R1 have a minimum FCT-life at least about double the FCT-Life of samples with 3 or less parameters in the range R1.
  • Samples with parameters in the range R2 showed an increased minimum FCT-life of 2305 h and samples with parameters in the range R3 showed a further increased minimum FCT-life of 4100 h.
  • FCT-Life minimum lifetime
  • Figures 4-7 show the FCT-life achieved for the different samples during the tests; figures 4-7 are linked, because the four parameters of the coating system of each sample are shown with reference to the FCT-life achieved.
  • the proposed coating system achieves longer minimum lifetime (and/or higher temperature capabilities) compared to existing coating systems.

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  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Materials Engineering (AREA)
  • Plasma & Fusion (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Physics & Mathematics (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Inorganic Chemistry (AREA)
  • General Engineering & Computer Science (AREA)
  • Ceramic Engineering (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP20425031.0A 2020-08-18 2020-08-18 Système de revêtement d'un composant d'un moteur à turbine à gaz Pending EP3957827A1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP20425031.0A EP3957827A1 (fr) 2020-08-18 2020-08-18 Système de revêtement d'un composant d'un moteur à turbine à gaz
CN202110948384.XA CN114075644A (zh) 2020-08-18 2021-08-18 用于燃气涡轮发动机的组件的涂层系统

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EP20425031.0A EP3957827A1 (fr) 2020-08-18 2020-08-18 Système de revêtement d'un composant d'un moteur à turbine à gaz

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EP3957827A1 true EP3957827A1 (fr) 2022-02-23

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Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5817372A (en) * 1997-09-23 1998-10-06 General Electric Co. Process for depositing a bond coat for a thermal barrier coating system
EP2196559A1 (fr) * 2008-12-15 2010-06-16 ALSTOM Technology Ltd Système de revêtement de barrière thermique, composants revêtus avec celle-ci et procédé pour l'application d'un système de revêtement de barrière thermique à des composants
WO2011019486A1 (fr) * 2009-08-11 2011-02-17 Praxair S.T. Technology, Inc. Systèmes de revêtement de barrière thermique
WO2015073175A1 (fr) * 2013-11-14 2015-05-21 United Technologies Corporation Articles revêtus de céramique et procédés de fabrication
EP3162917A1 (fr) * 2015-10-28 2017-05-03 General Electric Company Procédés de réparation d'un revêtement barrière thermique d'un composant de turbine à gaz et composants ainsi obtenus
GB2559806A (en) * 2017-02-21 2018-08-22 Siemens Ag Coating and method of applying a coating for an aerofoil of a gas turbine engine

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