US20160215631A1 - Article comprising environmental barrier coating - Google Patents

Article comprising environmental barrier coating Download PDF

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US20160215631A1
US20160215631A1 US14/445,665 US201414445665A US2016215631A1 US 20160215631 A1 US20160215631 A1 US 20160215631A1 US 201414445665 A US201414445665 A US 201414445665A US 2016215631 A1 US2016215631 A1 US 2016215631A1
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Prior art keywords
substrate
article according
layer
article
porous transition
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Abandoned
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US14/445,665
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English (en)
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Julin Wan
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General Electric Co
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General Electric Co
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Application filed by General Electric Co filed Critical General Electric Co
Priority to US14/445,665 priority Critical patent/US20160215631A1/en
Assigned to GENERAL ELECTRIC COMPANY reassignment GENERAL ELECTRIC COMPANY ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: WAN, JULIN
Priority to PCT/US2015/039331 priority patent/WO2016018570A1/en
Priority to CN201580040649.9A priority patent/CN106715362B/zh
Priority to JP2017503606A priority patent/JP6505206B2/ja
Priority to CA2955692A priority patent/CA2955692C/en
Priority to EP15753221.9A priority patent/EP3174839B1/en
Publication of US20160215631A1 publication Critical patent/US20160215631A1/en
Abandoned legal-status Critical Current

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    • 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
    • C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
    • C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
    • C04B41/00—After-treatment of mortars, concrete, artificial stone or ceramics; Treatment of natural stone
    • C04B41/009—After-treatment of mortars, concrete, artificial stone or ceramics; Treatment of natural stone characterised by the material treated
    • C—CHEMISTRY; METALLURGY
    • C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
    • C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
    • C04B41/00—After-treatment of mortars, concrete, artificial stone or ceramics; Treatment of natural stone
    • C04B41/45—Coating or impregnating, e.g. injection in masonry, partial coating of green or fired ceramics, organic coating compositions for adhering together two concrete elements
    • C04B41/52—Multiple coating or impregnating multiple coating or impregnating with the same composition or with compositions only differing in the concentration of the constituents, is classified as single coating or impregnation
    • C—CHEMISTRY; METALLURGY
    • C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
    • C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
    • C04B41/00—After-treatment of mortars, concrete, artificial stone or ceramics; Treatment of natural stone
    • C04B41/80—After-treatment of mortars, concrete, artificial stone or ceramics; Treatment of natural stone of only ceramics
    • C04B41/81—Coating or impregnation
    • C04B41/89—Coating or impregnation for obtaining at least two superposed coatings having different compositions
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/002—Wall structures

Definitions

  • This invention relates to articles comprising an environmental barrier coating (EBC), for example, high-temperature machine components. More particularly, this invention relates to coating systems and articles comprising the same for protecting machine components from exposure to high-temperature environments. This invention also relates to methods for making and protecting articles.
  • EBC environmental barrier coating
  • High-temperature materials such as, for example, ceramics, alloys, and intermetallics
  • the environments characteristic of these applications often contain reactive species, such as water vapor, which at high temperatures may cause significant degradation of the material structure.
  • water vapor has been shown to cause significant surface recession and mass loss in silicon-bearing materials. The water vapor reacts with the structural material at high temperatures to form volatile silicon-containing species, often resulting in unacceptably high recession rates.
  • EBC's Environmental barrier coatings
  • silicon-bearing materials and other material susceptible to attack by reactive species, such as high temperature water vapor.
  • EBC's provide protection by prohibiting contact between the environment and the surface of the material.
  • EBC's applied to silicon-bearing materials for example, are designed to be relatively stable chemically in high-temperature, water vapor-containing environments.
  • One exemplary conventional EBC system as described in U.S. Pat. No.
  • 6,410,148 comprises a silicon or silica bond layer applied to a silicon-bearing substrate; an intermediate layer comprising mullite or a mullite-alkaline earth aluminosilicate mixture deposited over the bond layer; and a top layer comprising an alkaline earth aluminosilicate deposited over the intermediate layer.
  • the top layer is a yttrium silicate layer rather than an alumino silicate.
  • U.S. Pat. No. 6,299,988 and U.S. Publication No. 2011/0052925 also describe EBC's.
  • the above coating systems can provide suitable protection for articles in demanding environments, but opportunities for improvement in coating performance exist.
  • Implementation of different materials in EBC's offers an opportunity for use in an expanded array of applications and environments, yet use of different materials can also result in new technical problems that can detrimentally impact the integrity of an EBC and/or the article comprising the EBC.
  • the invention provides an article comprising a substrate, a substantially hermetic sealing layer disposed on the substrate, and a porous transition layer disposed on the substrate between the sealing layer and the substrate, wherein the article comprises one or more openings extending through the substrate to the porous transition layer.
  • the invention provides a method for making an article.
  • the method includes: disposing a bondcoat over a substrate, disposing a porous transition layer over the bondcoat, disposing a sealing layer over the porous transition layer, wherein the sealing layer comprises a rare earth silicate or an alkaline-earth aluminosilicate, and forming one or more openings, the openings extending through the substrate and bondcoat to the porous transition layer.
  • the method does not comprise disposing a bondcoat over the substrate.
  • the method further comprises: disposing an intermediate layer over the porous transition layer, the intermediate layer comprising a barrier material that is substantially inert with respect to silica; and optionally disposing a topcoat over the sealing layer.
  • FIG. 1 is a schematic cross-section illustration of one exemplary embodiment of the present invention.
  • FIG. 2 is a simplified schematic cross-section illustration of another exemplary embodiment of the present invention.
  • the substantially hermetic sealing layer which may be referred to herein as a “sealing layer,” refers to a layer/coating, or multiple layers/coatings, that can prevent gases in the environment from accessing the substrate from the coated side.
  • the term “substantially hermetic” as used herein means that the coating has a gas permeability that is below about 2 ⁇ 10 ⁇ 14 cm 2 (about 2 ⁇ 10 ⁇ 6 Darcy), the detection limit of commonly used measurement techniques.
  • the sealing layer comprises material (“sealing material”) capable of forming a flowable phase, such as a liquid or a glassy phase, at or above a known temperature (“sealing temperature”) that is below a melting temperature of the bulk of the coating.
  • This liquid or glassy phase has a viscosity at the sealing temperature suitable to allow the flowable phase to flow into and at least partially fill defects such as cracks and pores, thereby enhancing the ability of the coating to block the movement of detrimental species from the external environment into the substrate.
  • sealing material capable of forming a flowable phase, such as a liquid or a glassy phase, at or above a known temperature (“sealing temperature”) that is below a melting temperature of the bulk of the coating.
  • This liquid or glassy phase has a viscosity at the sealing temperature suitable to allow the flowable phase to flow into and at least partially fill defects such as cracks and pores, thereby enhancing the ability of the coating to block the movement of detrimental species from the external environment into the substrate.
  • FIG. 1 depicts an exemplary article 200 of the present invention.
  • sealing layer 210 is disposed over a substrate 202 .
  • Substrate 202 may be made from any suitable material, such as a ceramic, a metal alloy, or an intermetallic material.
  • the substrate comprises a ceramic, for example an oxide, nitride, or carbide.
  • Substrate 202 may include a silicon-containing material, such as silicon nitride, molybdenum disilicide, or silicon carbide.
  • This material in certain embodiments, is a ceramic-matrix composite material, such as a material made of a matrix phase and a reinforcement phase; in particular embodiments, the matrix phase and the reinforcement phase comprise silicon carbide (SiC).
  • article 200 is a component of a gas turbine assembly, such as, for example, a combustion liner, transition piece, shroud, vane, or blade.
  • a gas turbine assembly such as, for example, a combustion liner, transition piece, shroud, vane, or blade.
  • the ability of the sealing layer to protect substrate 202 from exposure to water vapor at high temperatures may be advantageous for its application to silicon-bearing turbine components. It will be understood that although the application of embodiments of the present invention may be described with reference to applications on silicon-bearing substrates for protection against attack by water vapor, such references are exemplary and that embodiments of the present invention include substrate materials other than silicon-bearing materials.
  • a bondcoat 204 is disposed over substrate 202 , between the sealing layer 210 and the substrate 202 .
  • Bondcoat 204 may be used, for example, to mitigate thermal stresses or to inhibit chemical reactions between, e.g., substrate 202 and sealing layer 210 .
  • bondcoat 204 is a nonoxide layer that serves as an oxygen getter that inhibits and/or prevents oxidation of the substrate.
  • the bondcoat 204 may comprise silicon.
  • bondcoat 204 in some embodiments, comprises elemental silicon or a silicide.
  • bondcoat 204 comprises silicon carbide and/or silicon nitride.
  • bond coat 204 comprises a carbide, nitride, and/or silicide.
  • articles e.g., articles comprising environmental barrier coatings (EBCs)
  • substrates e.g., silicon carbide-based ceramic matrix composites
  • the bondcoat i.e., a silicon bond coat
  • the bondcoat comprises a material that is more refractory than silicon.
  • Such embodiments offer utility in that they allow articles (e.g., turbines that use ceramic matrix composites (CMCs) on, e.g., hot-section parts), to benefit from a higher firing temperature.
  • CMCs ceramic matrix composites
  • a refractory bondcoat generates a gaseous reaction product upon oxidation.
  • carbides oxidize to release carbon monoxide or carbon dioxide
  • nitrides oxidize to release nitrogen gas
  • silicides oxidize to release metal oxides that may, in some cases, be in a gaseous state.
  • These gaseous reaction products cause spallation in traditional EBC's because they include a hermetic layer and therefore do not permit permeation of these gaseous products.
  • gas bubbles build up underneath the hermetic layer(s), which, overtime, lead to spallation of the EBC.
  • expanded, non-silicon bond coats offer advantages such as expanded temperature applications, they can also introduce new problems, such as potential article spallation due to gas bubbles caused by gaseous reactant products, thereby necessitating new EBC/CMC design.
  • the present invention addresses, inter alia, the problem of spallation due to bubbles caused by gaseous reactant products via the inclusion of porous transition layer 208 , which is disposed on substrate 202 between the sealing layer 210 and the substrate 202 , and by inclusion of one or more openings 212 extending through the substrate 202 to the porous transition layer 208 . As shown in the embodiment depicted in FIG. 1 , where bondcoat 204 is present, the one or more openings 212 also extend through the bondcoat.
  • the porosity of porous transition layer 208 allows for redistribution of gaseous reaction product.
  • the porous transition layer comprises an oxide or non-oxide ceramic or a combination thereof, which is thermally and chemically compatible with the substrate and the sealing layer.
  • the porous layer in some embodiment can be a rare earth silicate. In another embodiment it can be silicon carbide.
  • the desired porosity of the porous transition layer may change depending on the intended application of the inventive article, and the on the nature of the other materials used in the article (e.g., on the nature of the bond coat, where present). While the porous transition layer may have any porosity that effectuates the intended purpose of the layer, in some embodiments, the porous transition layer has a porosity of 10 to 90% (e.g., 10, 15, 20, 25, 30, 35, 40, 45, 50, 55, 60, 65, 70, 75, 80, 85, or 90%), including any and all ranges and subranges therein (e.g., 15-85%, 12-75%, etc.), preferably 20 ⁇ 50%.
  • the porous transition layer will have a specified, and optionally pre-determined average pore diameter, which again, may vary depending on application and nature of the inventive article.
  • the porous transition layer has an average pore diameter of 0.1 to 100 ⁇ m (e.g., 0.1, 0.2, 0.3, 0.4, 0.5, 0.6, 0.7, 0.8, 0.9, 1, 2, 3, 4, 5, 10, 15, 20, 25, 30, 35, 40, 45, 50, 55, 60, 65, 70, 75, 80, 85, 90, 95, or 100 ⁇ m), including any and all ranges and subranges therein (e.g., 0.1 to 20 ⁇ m, 0.1 to 15 ⁇ m, etc.).
  • the chemical composition and physical features of the porous layer described as above are subject to change during the service of the article, and thereby may drift out of the ranges specified above. For example, sintering and coarsening may occur which lead to reduced porosity and increased pore diameter.
  • silicon carbide is used to form the porous layer
  • oxidation will turn this layer into a silica based layer partially or entirely.
  • the material that is used to make the porous layer can be applied in its pure form, or in mixture with a second phase or as an alloy with a minor dopant, to enhance the property of the layer according to specific application requirements.
  • Article 200 includes openings 212 , which extend through the substrate 202 to the porous transition layer 208 .
  • the openings 212 serve as escape holes for gaseous species, which are first redistributed through porous transition layer 208 .
  • the openings 212 may be created in any desired or art/acceptable fashion. For example, in some embodiments, the openings 212 are created by drilling through the layer(s) preceding the porous transition layer 208 (e.g., drilling through substrate 202 and bond coat 204 ). In some embodiments, the openings 212 extend into the porous transition layer 208 .
  • the one or more openings 212 may have equivalent or differing diameters, and diameters may be selected depending on the nature and application of the article.
  • the one or more openings have an average diameter of 1 to 1000 ⁇ m (e.g., 1, 2, 3, 4, 5, 6, 7, 8, 9, 10, 20, 30, 40, 50, 60, 70, 80, 90, 100, 200, 300, 400, 500, 600, 700, 800, 900, or 1000 ⁇ m), including any and all ranges and subranges therein (e.g., 1-20 ⁇ m, 2 to 40 ⁇ m, etc.).
  • the cross section of the opening can be of any shape, including but not limited to circular, oval, square, rectangular, triangular, or any other regular or irregular geometry.
  • the spacing between the openings can be periodical or random, and can range from 10 ⁇ m to 100 mm, depending on the application requirements. Longitudinally the openings can be straight or tortuous through the substrate and the coating layers.
  • gaseous product is conducted through the porous transition layer 208 to the openings 212 , from which the gaseous product escapes.
  • FIG. 2 depicts another exemplary article 300 of the present invention.
  • the article comprises a substrate cavity 214 , and the openings 212 enter into the cavity 214 .
  • the cavity 214 is an open chamber that is optionally in pressure equilibrium with the external environment (e.g., combustion environment), and may optionally be protected by a flux of dry air.
  • the cavity 214 is a self-contained closed chamber that is isolated from the external (e.g., combustion) environment.
  • vent 216 is a controlled valve, or a thermal-expansion enabled seal that can close at high temperatures and open at low temperatures, such that, for example, pressure inside the cavity 214 may be released during a service cycle.
  • an intermediate layer may be disposed between sealing layer 210 and bond coat 204 (e.g., between the sealing layer 210 and the porous transition layer 208 , or between the porous transition layer 208 and the bondcoat 204 ).
  • the bond coat 204 comprises silicon or silicon oxide
  • the intermediate layer comprises a barrier material that is substantially inert with respect to silicon oxide to promote chemical stability in the coating system. “Substantially inert” means that there is at most only incidental interaction (solubility or reactivity) between silica and the barrier material.
  • Rare-earth disilicates such as disilicates of yttrium, ytterbium, lutetium, scandium, and other rare-earth elements, are non-limiting examples of suitable barrier materials.
  • topcoat 206 is disposed over sealing layer 210 .
  • Topcoat 206 may be used to provide thermal insulation (a thermal barrier coating), environmental protection (an environmental barrier coating), or a combination of these functions. The selection of a suitable topcoat material will depend on the type of environment the article is to be exposed to, the composition of the underlying coatings and substrate, the cost of processing, and other factors known in the art.
  • topcoat 206 is a ceramic material. Many classes of ceramic materials may serve as thermal and/or environmental barrier coatings; these materials include, but are not limited to, silicates, aluminosilicates, and yttria-stabilized zirconia.
  • topcoat 206 contains a rare earth monosilicate and/or rare earth disilicate; in particular embodiments, topcoat 206 is a dual-layer coating, with an outer layer of rare earth monosilicate and an inner layer of rare earth disilicate.
  • the rare earth elements associated with these monosilicate and disilicate materials may include one or more of yttrium, ytterbium, lutetium, and scandium.
  • the outer layer is yttrium monosilicate and the inner layer is a rare earth disilicate (such as yttrium disilicate, for instance).
  • any of the various coating layers described above is generally chosen to provide adequate protection for a given service time while keeping thermal stresses to a sustainable level.
  • coating thickness may also be determined by the ability of a selected coating method to produce a continuous layer over the deposition area.
  • approximate thickness ranges for the various coatings include the following: for the sealing layer, from about 25 micrometers to about 1000 micrometers; for the porous transition layer, from about 25 micrometers to about 1000 micrometers; for the bondcoat, from about 25 micrometers to about 200 micrometers; for the intermediate layer, from about 50 micrometers to about 100 micrometers; for the topcoat layer, from about 50 micrometers to about 500 micrometers.
  • the yttrium monosilcate outer layer can be from about 25 micrometers to about 50 micrometers in certain embodiments.
  • the coatings described above can be deposited using coating technology that may result in a substantial amount of cracking and internal open porosity.
  • Plasma spray technology and slurry-based coating processes are examples of coating methods that generate coatings with such features.
  • the presence of the sealing layer serves to considerably enhance the hermeticity, and thus the efficacy of protection, of the coating.
  • the sealing layer may be effective in sealing cracks or other damage to the coating that may occur after processing, including for instance damage created during installation of components, or service of components.
  • the sealing layer may be heated to the sealing temperature (described above) at which at least a portion of the sealing layer will flow; the flowable portion thus moves into cracks and pores and, upon solidification, seals off these defects that would otherwise serve as pathways for detrimental species, such as water vapor, from the environment to the substrate.
  • the heating step may be performed immediately after depositing the sealing layer, after all coatings have been deposited but prior to putting the finished article into service, or even during service itself if the service temperature is allowed to be sufficiently high.
  • the sealing temperature is maintained for an effective time to allow time for the flowable material to reach and at least partially fill or otherwise seal off the defects.
  • the length of time needed to achieve this is generally selected based on the number and nature of the defects to be sealed and the quantity of flowable material available in the sealing layer.
  • the sealing layer is heated to a sealing temperature in a range from about 950 degrees Celsius to about 1350 degrees Celsius for a time in the range from about 30 minutes to about 10 hours; in particular embodiments the time is in the range from about 30 minutes to about 4 hours.
  • the temperature is in the range from about 950 degrees Celsius to about 1050 degrees Celsius for a time in the range from about 30 minutes to about 4 hours, while in other embodiments the temperature is from about 1250 degrees Celsius to about 1350 degrees Celsius for a time in the range from about 30 minutes to about 4 hours.
  • the heating step to seal the coating may be performed in air, vacuum, an inert atmosphere, or other environment, depending at least in part on the requirements of the materials being heated (i.e., the substrate and other coating layers, if present).
  • the method that is applied to deposit the porous layer is selected to fulfill the geometric requirements as described above.
  • the layer is applied by thermal spray with parameters selected to target a specific porosity, such as controlling the spray gun energy, standoff distance, and particle size of the powder feed.
  • a sacrificial phase is added to the powder feed to enhance the porosity.
  • organic particles such as but not limited to polystyrene particles, are added to the powder feed during the coating process, which can be burned off during subsequent steps and leave behind pores in the coating.
  • a dissolvable salt is added and subsequently dissolved away to generate the pores.
  • glass particles are added to the powder feed, after applying the layer, the glass phase is leached away by soaking the part in a hydrofluoric acid solution to leave behind a porous structure.
  • a glass layer is deposited and then a subsequent heat-treatments is applied to lead to partial crystallization or phase separation of the glass, subsequently the coating is soaked in an acid solution to leach out one phase and leave behind a porous structure.
  • Similar technology can be applied in slurry coating, wherein either controlling parameters to facilitate partial sintering, or otherwise employment of a sacrificial phase can be used to achieve a structure that contain appropriate porosity.
  • Partial sintering can be realized by solid phase or liquid sintering of coarse particle compact at lower temperatures, or use a bonding agent to facilitate necking with minimal volume shrinkage, or sintering of a multimodal powder mixture.
  • Sacrificial phases as stated above, can be an organic or carbonaceous phase, or a dissolvable salt or a glass phase that can be etched away. In general, any technologies known by those skilled in the art of making porous ceramics can be applied in this invention.
  • each range is intended to be a shorthand format for presenting information, where the range is understood to encompass each discrete point within the range as if the same were fully set forth herein.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Ceramic Engineering (AREA)
  • Materials Engineering (AREA)
  • Structural Engineering (AREA)
  • Organic Chemistry (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Combustion & Propulsion (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Other Surface Treatments For Metallic Materials (AREA)
  • Laminated Bodies (AREA)
US14/445,665 2014-07-29 2014-07-29 Article comprising environmental barrier coating Abandoned US20160215631A1 (en)

Priority Applications (6)

Application Number Priority Date Filing Date Title
US14/445,665 US20160215631A1 (en) 2014-07-29 2014-07-29 Article comprising environmental barrier coating
PCT/US2015/039331 WO2016018570A1 (en) 2014-07-29 2015-07-07 Article comprising environmental barrier coating
CN201580040649.9A CN106715362B (zh) 2014-07-29 2015-07-07 包括环境阻隔涂层的物品
JP2017503606A JP6505206B2 (ja) 2014-07-29 2015-07-07 耐環境コーティングを備える物品
CA2955692A CA2955692C (en) 2014-07-29 2015-07-07 Article comprising environmental barrier coating
EP15753221.9A EP3174839B1 (en) 2014-07-29 2015-07-07 Article comprising environmental barrier coating

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US14/445,665 US20160215631A1 (en) 2014-07-29 2014-07-29 Article comprising environmental barrier coating

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EP (1) EP3174839B1 (ja)
JP (1) JP6505206B2 (ja)
CN (1) CN106715362B (ja)
CA (1) CA2955692C (ja)
WO (1) WO2016018570A1 (ja)

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US11624289B2 (en) * 2021-04-21 2023-04-11 Rolls-Royce Corporation Barrier layer and surface preparation thereof
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CN106715362A (zh) 2017-05-24
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