Patent Description:
Mechanical structures interacting with high-temperature gases, such as jet engine exhaust systems, the exterior surfaces of hypersonic aircraft, and furnace liners, may be composed of a metal component providing strength, and coated with, e.g., a ceramic coating to provide thermal protection, preventing the metal component from being weakened by heating. In such an application, a coating with low thermal conductivity may be desirable, to reduce heat flow into the metal component. Exemplary embodiments of coatings and methods of providing such coatings of the prior art are disclosed in <CIT>, <CIT>, and <CIT>.

Certain related art ceramic coatings, such as <NUM> wt% yttria-stabilized zirconia thermal barrier coatings (TBCs) have a thermal conductivity in the range of <NUM> - <NUM> W/mK (Watts per meter - Kelvin) at room temperature. Such a coating may be applied utilizing either a plasma spray process or an electron-beam physical vapor deposition process, which may result in a porosity of <NUM>-<NUM>%. A lower thermal conductivity would be beneficial. Related art TBCs focus on protecting metal components, but are not well compatible with ceramic components due to their different coefficient of thermal expansion.

Thus, there is a need for a system and method of providing improved thermal and environmental protection for ceramic components exposed to high-temperature gases.

Aspects of embodiments of the present disclosure are directed toward a thermal and environmental barrier coating composed of ceramic hollow microspheres sintered together. In one embodiment the microspheres are sintered together with a powder of another material that acts as a binder, or with a powder of a material that may be the same as the material of the hollow microspheres, forming a matrix in which the hollow microspheres are embedded. The thermal and environmental barrier coating may have low conductivity as a result of including the hollow microspheres, and may be composed of a material with a high temperature capability, and with a low coefficient of thermal expansion similar to the ceramic substrate.

According to an embodiment of the present invention there is provided a article, including: a ceramic substrate, and a thermal barrier coating covering a surface of the ceramic substrate, the thermal barrier coating having: a void volume fraction of at least <NUM>% and a major part of the void volume being closed porosity, the thermal barrier coating including, as a major component, a plurality of hollow particles, each of the plurality of hollow particles including, as a major component, a first material, each of the plurality of hollow particles having: a maximum interior dimension less than about <NUM> millimeter (mm) and greater than about <NUM> micrometers, and a maximum wall thickness less than about <NUM>/<NUM> of the maximum interior dimension.

In one embodiment, each of a major portion of the plurality of hollow particles has a shape selected from the group consisting of ellipsoids, rods, cubes, spheres and combinations thereof.

Each of a major portion of the plurality of hollow particles has a substantially circular cross section with a diameter less than about <NUM> millimeter (mm) and greater than about <NUM> micrometers.

In one embodiment, the article includes, as a major component, a second material different from the first material.

The plurality of hollow particles are sintered together.

In one embodiment, the article includes a bond coat between the ceramic substrate, and the thermal barrier coating.

In one embodiment, the bond coat includes, as a major component, a material selected from the group consisting of SiO<NUM>, Al<NUM>O<NUM>, B<NUM>O<NUM>, and combinations thereof.

The article includes a capping layer covering a portion of a surface of the thermal barrier coating, the capping layer having a porosity less than <NUM>% and a thickness less than about <NUM>/<NUM> of the thickness of the thermal barrier coating.

In one embodiment, the article includes as a major component, a substance selected from the group consisting of silica, alumina, silicon oxycarbide, and combinations thereof, ceramic matrix composites including fibers, the fibers including, as a major component, a substance selected from the group consisting of SiC, Si<NUM>N<NUM>, C, Al<NUM>O<NUM>, Al<NUM>Si<NUM>O<NUM>, and combinations thereof, and combinations thereof.

In one embodiment, the article includes silica as a major component.

In one embodiment, the article includes, as a major component, a second material, the second material being the same as the first material.

The first material is selected from rare earth silicates.

In one embodiment, the first material is selected from the group consisting of: yttrium disilicates.

In one embodiment, the second material is selected from the group consisting of: rare earth silicates, rare earth aluminates, rare earth gallates, zirconate perovskites, hafnium titanates, zirconium titanates, monoclinic hafnias, scandium tantalates, aluminosilicates, mullites, silicon oxycarbides, zircons, magnesium aluminate spinels, aluminum phosphates, and combinations thereof.

It is also disclosed a thermal and environmental barrier material including, as a major component, a plurality of hollow particles, each of the plurality of hollow particles including, as a major component, a first material, each of the plurality of hollow particles having: a maximum interior dimension less than about <NUM> millimeter (mm) and greater than about <NUM> micrometers, and a maximum wall thickness less than about <NUM>/<NUM> of the maximum interior dimension, the first material being selected from the group consisting of: rare earth silicates, rare earth aluminates, rare earth gallates, zirconate perovskites, hafnium titanates, zirconium titanates, monoclinic hafnias, scandium tantalates, aluminosilicate glasses, silicon oxycarbides, zircons, magnesium aluminate spinels, aluminum phosphates, and combinations thereof.

In one embodiment, each of a major portion the plurality of hollow particles has a shape selected from the group consisting of ellipsoids, rods, cubes, spheres and combinations thereof.

In one embodiment, the material includes, as a major component, a second material different from the first material.

In one embodiment, the particles of the plurality of hollow particles are sintered together.

According to an embodiment of the present invention there is provided a method of forming an article as defined in the claims, the method including: receiving a ceramic substrate; forming a thermal barrier coating on the ceramic substrate, the thermal barrier coating to include, as a major component, a plurality of hollow particles, each of the plurality of hollow particles including, as a major component, a first material, the first material being selected from rare earth silicates.

In one embodiment, the method includes, as a major component, a second material different from the first material.

In one embodiment, the forming of the thermal barrier coating on the ceramic substrate includes: applying the plurality of hollow particles to the substrate by a process selected from the group consisting of painting, spraying, dipping, tape casting, doctor blading, and combinations thereof, and sintering together the hollow particles of the plurality of hollow particles.

In one embodiment, the forming of the thermal barrier coating includes adjusting a coefficient of thermal expansion of the thermal barrier coating by selecting a first material with a suitable coefficient of thermal expansion.

These and other features and advantages of the present invention will be appreciated and understood with reference to the specification, claims and appended drawings wherein:.

The detailed description set forth below in connection with the appended drawings is intended as a description of exemplary embodiments of a thermal and environmental barrier coating for ceramic substrates provided in accordance with the present invention and is not intended to represent the only forms in which the present invention may be constructed or utilized. The description sets forth the features of the present invention in connection with the illustrated embodiments. As denoted elsewhere herein, like element numbers are intended to indicate like elements or features.

Thus, a first element, component, region, layer or section discussed below could be termed a second element, component, region, layer or section, without departing from the scope of the inventive concept.

Spatially relative terms, such as "beneath", "below", "lower", "under", "above", "upper" and the like, may be used herein for ease of description to describe one element or feature's relationship to another element(s) or feature(s) as illustrated in the figures. It will be understood that the spatially relative terms are intended to encompass different orientations of the device in use or in operation, in addition to the orientation depicted in the figures. For example, if the device in the figures is turned over, elements described as "below" or "beneath" or "under" other elements or features would then be oriented "above" the other elements or features. Thus, the example terms "below" and "under" can encompass both an orientation of above and below. The device may be otherwise oriented (e.g., rotated <NUM> degrees or at other orientations) and the spatially relative descriptors used herein should be interpreted accordingly. In addition, it will also be understood that when a layer is referred to as being "between" two layers, it can be the only layer between the two layers, or one or more intervening layers may also be present.

Further, the use of "may" when describing embodiments of the inventive concept refers to "one or more embodiments of present invention. " Also, the term "exemplary" is intended to refer to an example or illustration.

In contrast, when an element or layer is referred to as being "directly on," "directly connected to", "directly coupled to", or "immediately adjacent to" another element or layer, there are no intervening elements or layers present.

As used herein, the term "substantially," "about," and similar terms are used as terms of approximation and not as terms of degree, and are intended to account for the inherent deviations in measured or calculated values that would be recognized by those of ordinary skill in the art. As used herein, the term "major component" means a component constituting at least half, by weight, of a composition, and the term "major portion", when applied to a plurality of items means at least half of the items. A "nanopowder" means a powder in which a majority of the particles are less than <NUM> micrometer (micron) in size.

Any numerical range recited herein is intended to include all sub-ranges of the same numerical precision subsumed within the recited range. For example, a range of "<NUM> to <NUM>" is intended to include all subranges between (and including) the recited minimum value of <NUM> and the recited maximum value of <NUM>, that is, having a minimum value equal to or greater than <NUM> and a maximum value equal to or less than <NUM>, such as, for example, <NUM> to <NUM>. Any maximum numerical limitation recited herein is intended to include all lower numerical limitations subsumed therein and any minimum numerical limitation recited in this specification is intended to include all higher numerical limitations subsumed therein.

Referring to <FIG>, in one embodiment a ceramic substrate <NUM> forms a protective layer over a metallic substructure <NUM> and an additional thermal barrier coating <NUM> covers the ceramic substrate <NUM>, providing protection for the ceramic substrate <NUM>. The ceramic substrate <NUM> may, for example, be a layer of ceramic foam providing thermal protection for the metal substructure <NUM>. The assembly may be exposed to high-temperature gas, e.g., hot exhaust gas in a jet engine. In this embodiment, the thermal barrier coating <NUM> is composed of a material that can withstand higher temperatures than the ceramic substrate <NUM>, and that can withstand contact with the high-temperature gas. The thermal barrier coating <NUM> also has sufficiently low thermal conductivity to protect the ceramic substrate <NUM> from the hot gas. In other embodiments the thermal barrier coating <NUM> simply protects a ceramic substrate <NUM>, without an underlying metal substructure (<FIG>), as in the case of a high temperature tile that may be installed on the exterior of a hypersonic vehicle, or the thermal barrier coating <NUM> may protect a ceramic substrate <NUM> that is a ceramic matrix composite (<FIG>). The ceramic matrix composite may be based on fibers that are mostly carbon, SiC- or Si<NUM>N<NUM>. Al<NUM>O<NUM>- or mullite-fiber based composites may also be protected utilizing a thermal barrier coating <NUM>, although the coefficient of thermal expansion of these ceramic matrix composite materials is higher (being of order <NUM>*<NUM>-<NUM>/K), which may require adjusting the coefficient of thermal expansion of the thermal barrier coating <NUM>. A bond layer may be utilized between the ceramic element and the thermal barrier coating <NUM>, and a capping layer may be utilized on the exterior of the thermal barrier coating <NUM>.

Referring to <FIG>, in one embodiment, the thermal barrier coating <NUM> is composed of hollow microspheres <NUM>, and low thermal conductivity is achieved by introducing, by the inclusion of the hollow microspheres <NUM>, a suitable cellular architecture into the thermal barrier coating <NUM>. The high fraction of closed cell porosity on the micron scale, resulting from the inclusion of the hollow microspheres <NUM>, can lower the effective conductivity of the thermal barrier coating by a factor of up to <NUM>. The thermal barrier coating <NUM> may consist simply of the hollow microspheres sintered together, or of the hollow microspheres with a coating of binder to better bind them together, or of the hollow microspheres embedded in a matrix. In one embodiment, since the porosity is closed and may average only about <NUM> microns in diameter and constitute a volume fraction of <NUM> - <NUM>%, the use of hollow microspheres <NUM> is very efficient in decreasing the thermal conductivity. In one embodiment, the hollow spheres have an outer diameter of <NUM> - <NUM> microns, and a wall thickness of <NUM> - <NUM> microns.

The hollow microspheres may be composed of various materials, selected for their ability to withstand high temperatures, and for a low coefficient of thermal expansion (CTE). The CTE of the thermal barrier coating <NUM> may be adjusted by selecting a material, for the hollow microspheres, with a suitable CTE. A low coefficient of thermal expansion (CTE), and a high volume fraction of porosity resulting in a low elastic modulus of the coating, alone or in combination, reduce the likelihood that during thermal cycling, sufficient stress will be produced in the thermal barrier coating <NUM> or in the ceramic substrate to cause spallation or the formation of microcracks in the thermal barrier coating <NUM> or in the ceramic substrate. The desire for a low steam recession rate may also be a factor in selecting materials.

The hollow microspheres may be composed, for example, of one or more rare earth silicates, including yttrium monosilicate (Y<NUM>SiO<NUM>), yttrium disilicate (Y<NUM>Si<NUM>O<NUM>), ytterbium monosilicate (Yb<NUM>SiO<NUM>), ytterbium disilicate (Yb<NUM>Si<NUM>O<NUM>) and/or Sc<NUM>Si<NUM>O<NUM>. As used herein, the term "rare earth" refers to an element selected from the following list: scandium, yttrium, lanthanum, cerium, praseodymium, neodymium, samarium, europium, gadolinium, terbium, dysprosium, holmium, erbium, thulium, ytterbium, and lutetium.

Zirconate perovskites, hafnium titanate, zirconium titanate, monoclinic yttrium aluminate (Y<NUM>Al<NUM>O<NUM>), scandium tantalate and monoclinic hafnia all have relatively low coefficients of thermal expansion, with the following approximate values, in parts per million per °C: rare-earth disilicates: <NUM>, rare-earth monosilicates: <NUM>, scandium disilicate: <NUM>, mullite: <NUM>, aluminosilicate glass: <NUM>, amorphous silicon oxycarbide: <NUM>, zircon: <NUM>, hafnium titanate: <NUM>, zirconium titanate: <NUM>, monoclinic yttrium aluminate: <NUM>, scandium tantalate: <NUM>, monoclinic hafnia: <NUM>, magnesium aluminate spinel: <NUM>, and barium zirconate: <NUM>. Hafnium titanate and zirconium titanate are thought to have high temperature capability. Monoclinic yttrium aluminate, scandium tantalate and monoclinic hafnia are thought to have a low steam recession rate. Monoclinic hafnia, however, undergoes multiple phase transformations which may cause microcracking on thermal cycling. Silicon oxycarbide has a low coefficient of thermal expansion and good high temperature stability in oxidizing environments. Aluminosilicate glass has a low CTE. Mullite has a CTE of approximately <NUM> parts per million per °C and an intermediate steam recession rate and could be a suitable TBC material for silica and alumina based substrates. Zircon has a CTE of approximately <NUM> parts per million per °C and therefore is also more suitable for alumina-based substrates.

Various fabrication methods may be utilized to form hollow microspheres <NUM> of the desired materials. In one embodiment, the hollow microspheres <NUM> are fabricated by coating spherical templates, which are then either pyrolyzed during a carefully tailored heat treatment or which remain in place after being coated. The spherical templates may be hollow or solid polymer spheres that can be pyrolyzed, or ceramic hollow spheres that are compatible with various coating compositions. In one embodiment, cenospheres, e.g., Fillite™ cenospheres, composed of <NUM>% Al<NUM>O<NUM> and <NUM>% SiO<NUM>, with a melting temperature above <NUM> and a bulk density of <NUM>/cc, are utilized. In other embodiments, hollow templates with even higher temperature capability, such as hollow alumina spheres with a melting temperature of <NUM>, or hollow aluminum phosphate (AlPO<NUM>) spheres with a melting temperature of <NUM> are utilized.

The thermal barrier coating <NUM> may be formed from hollow microspheres <NUM> (in various suitable sizes) utilizing various suitable methods. In one embodiment illustrated in <FIG>, a layer of hollow microspheres <NUM> is applied to the ceramic substrate and sintered. The layer of hollow microspheres <NUM> may be applied by any of various suitable methods, e.g., involving first forming a slurry of the hollow microspheres <NUM>, and then applying the slurry to the ceramic substrate <NUM> utilizing brushing or painting, spraying, dipping the ceramic substrate <NUM> in the slurry, or slip-casting, and allowing the slurry to dry. A binder may be added to the slurry to insure the integrity of the coating after drying, i.e., to prevent the layer of hollow microspheres <NUM> from crumbling or flaking off of the ceramic substrate <NUM> as the slurry dries. In a slip-casting process the ceramic substrate <NUM> absorbs a significant portion of the liquid of the slurry as the slurry dries. In other processes, a thicker slurry may be utilized, making the absorption of liquid into the ceramic substrate <NUM> less important. Once the slurry has dried, it may be sintered by heating, e.g., for two to five hours at a temperature in the range of <NUM> to <NUM>.

In another embodiment illustrated in <FIG>, a slurry is formed of the hollow microspheres <NUM> (in various suitable sizes), together with a nanopowder of a material that acts as a binder <NUM> during sintering. Materials that may be suitable for use as a binder <NUM> include SiO<NUM>, SiO<NUM> based glass with a softening point tailored to promote adhesion of the spheres at the selected consolidation temperature, e.g. <NUM>, and transient liquid phase materials that melt at a lower temperature and then react with the hollow microsphere material to form a higher-melting phase that acts as a binder <NUM> and is stable at the operating temperature. For example, for hollow microspheres <NUM> composed of a rare-earth silicate (e.g. Y<NUM>Si<NUM>O<NUM>), such a binder <NUM> may be Na<NUM>Si<NUM>O<NUM> or a related sodium silicate composition. Sodium silicate Na<NUM>Si<NUM>O<NUM> melts at <NUM> and will then react with Y<NUM>Si<NUM>O<NUM> to form higher melting phases such as NaYSi<NUM>O<NUM> or NaY<NUM>Si<NUM>O<NUM>. Small amounts of Na and Si can also be dissolved into Y<NUM>Si<NUM>O<NUM> as a solid solution. A small amount of sodium silicate (e.g., <NUM> - <NUM> weight %) may be added to hollow rare earth silicate spheres as powder or as a coating on the spheres. After applying the slurry containing the hollow microspheres <NUM> to the ceramic substrate <NUM>, the slurry containing the hollow microspheres <NUM> may be dried and then heat treated, and the sodium silicate may melt at <NUM> and start reacting with the rare earth silicate. The liquid phase sodium silicate may aid in densification of the coating and the reaction products may then act as a binder <NUM> between the spheres.

In another embodiment illustrated in <FIG>, a slurry is formed of the hollow microspheres <NUM> (in various suitable sizes), together with a nanopowder of a material that acts as a matrix <NUM> in which the hollow microspheres <NUM> are embedded. The material utilized for the nanopowder may be selected according to criteria similar to those for selecting the material for the hollow microspheres <NUM>, i.e., a material may be selected that has a low coefficient of thermal expansion, a low elastic modulus, high temperature capability, and a low steam recession rate. In addition a material may be selected that will not react with the material of the hollow microspheres <NUM>, and that has a similar coefficient of thermal expansion, to avoid having thermal cycling cause microcracking.

Selecting the same material for the hollow microspheres <NUM> and for the nanopowder to form the matrix <NUM> will insure that the coefficient of thermal expansion of the hollow microspheres <NUM> and of the matrix <NUM> are matched, and that the hollow microspheres <NUM> will not react with the matrix <NUM>. When the material of the hollow microspheres <NUM> is the same as that of the matrix <NUM>, the hollow centers of the hollow microspheres <NUM> appear as bubbles in the surrounding material, which may be uniform except for the presence of the bubbles. In one embodiment such a structure may be formed by forming a slurry of polymer spheres and a nanopowder of a suitable matrix material, and, after applying the slurry to the ceramic substrate <NUM> and allowing it to dry, pyrolyzing the polymer spheres and sintering the nanopowder, to form a matrix <NUM> with bubbles. A thermal barrier coating formed according to embodiments of the present invention may have a high void volume fraction, exceeding <NUM>% (i.e., the fraction of the total volume of the material that is contributed by voids inside the material may exceed <NUM>%), e.g., a void fraction between <NUM>% and <NUM>%. Other embodiments may have void volume fractions exceeding <NUM>%, <NUM>%, or <NUM>%. A major part of the void volume, i.e., more than <NUM>% by volume (or, e.g., between <NUM>% and <NUM>% by volume), may be composed of closed porosity voids (i.e., voids each of which is a volume without openings), such as the interiors of closed hollow microspheres. In other embodiments more than <NUM>%, <NUM>% or <NUM>% of the void volume may be composed of closed porosity voids. A higher volume fraction of ceramic may increase the strength of the resulting coating. The compressive "crush" strength can be utilized as a measure of structural integrity and it can be estimated with the following equation:
<MAT>
where σpl is the plateau or crush strength of the hollow sphere material, σy,s is the yield strength of the solid constituent material, ρ is the density of the hollow sphere material and ρs is the density of the solid constituent material.

The formation of a thermal barrier coating <NUM> according to the embodiments of <FIG> has been demonstrated with materials based on hollow glass microspheres; scanning electron micrographs of the resulting composite materials (i.e., sintered hollow microspheres <NUM>, hollow microspheres <NUM> sintered with a binder <NUM>, and hollow microspheres <NUM> sintered in a matrix <NUM>) are shown in <FIG>, respectively. The three types of cellular architectures result in different volume fractions of porosity. The thermal conductivity of these materials is very low, as validated by laser flash thermal conductivity measurements.

<FIG> shows the thermal conductivity of Y<NUM>Si<NUM>O<NUM> and of SiO<NUM> in their dense state and in the material of thermal barrier coatings <NUM> of various relative densities according to embodiments of the present invention. All of the data points in the graph represent calculated values, except for the one point designated as "measured. " The calculated values of thermal conductivity shown were calculated utilizing the following equation:
<MAT>
where Vext is the volume fraction of the external phase (air or binder), λext is the conductivity of the external phase (air or binder), and λsph is the conductivity of the spheres (shell + internal air). This equation takes into account only heat transfer by conduction. Convective and radiative heat transfer can be neglected due to the small size of the hollow microspheres <NUM>.

The thermal barrier coating <NUM> may be utilized to shield silica-based foams from temperatures in excess of <NUM> °F and exhibit high durability and minimal water vapor hot gas corrosion and erosion. The thermal barrier coating <NUM> may achieve a very low thermal conductivity by virtue of its cellular architecture (high porosity and closed celled structure), which makes it possible to select oxides not suitable for use in related art thermal barrier structures, oxides which may have superior durability and erosion resistance and a well-matched coefficient of thermal expansion. In one embodiment the thermal barrier coating <NUM> is composed of hollow yttrium disilicate microspheres with a diameter of <NUM> microns and a wall thickness of <NUM> micron, that are sintered together onto a silica-based ceramic foam utilized in exhaust systems of jet engines. Such a thermal barrier coating <NUM> may exhibit a calculated thermal conductivity of <NUM> W/mK, which is a factor of <NUM> lower than related art zirconia-based thermal barriers, while providing much better cyclic durability due to a lower mismatch in the coefficient of thermal expansion and due to a lower elastic modulus. All three benefits may be provided by the advantageous cellular architecture.

Thermal barrier coatings <NUM> according to embodiments of the present invention lack several disadvantages that related art coatings may have. Such related art coatings may be composed of <NUM> wt% yttria stabilized zirconia (7YSZ), which may be applied by electron beam physical vapor deposition or thermal spray deposition on nickel-based superalloy components (e.g., combustors, blades, shrouds, or nozzles). The coefficient of thermal expansion of 7YSZ (<NUM>* <NUM>-<NUM> K-<NUM>) is large for use with a ceramic foam substrate, which may cause spallation of the coating upon thermal cycling due to coefficient of thermal expansion mismatch stresses. Moreover, the phase stability of 7YSZ is poor above <NUM>, which may lead to phase separation and transformation of the yttria-poor phase to monoclinic zirconia accompanied by a volume expansion that may shatter the coating.

Referring to <FIG>, a bond coat <NUM> may be formed between the thermal barrier coating <NUM> and the ceramic substrate <NUM>, to promote adhesion, or a barrier layer may be applied to mitigate any chemical incompatibility between the thermal barrier coating <NUM> and the ceramic substrate <NUM>. Such a bond coat <NUM> may be formed on the ceramic substrate <NUM> before forming the thermal barrier coating <NUM>. The bond coat <NUM> may be applied by dip coating in a slurry or solution, or by painting or spraying on a slurry or solution, allowing the slurry to dry, and subjecting the assembly to a sintering or heat treatment process. Alternatively the bond coat <NUM> may be applied utilizing a thermal spray, e.g. an air plasma spray. The bond coat <NUM> may be composed, for example, of SiO<NUM>, or of Al<NUM>O<NUM>, or of a mixture of these two materials which may also contain B<NUM>O<NUM>.

Referring to <FIG>, in one embodiment a dense capping layer <NUM> is applied to the top of the thermal barrier coating <NUM> to provide a dense, smooth surface and minimize the area available for hot gas erosion. The capping layer <NUM> includes or consists of the same material as the hollow spheres or the matrix <NUM>. The capping layer <NUM> may be formed by dipping or painting with slurry of solid (i.e., non-hollow) microparticles, that are small enough to form a dense layer after sintering, e.g., the microparticles may have a size of <NUM> microns or less, to reduce or minimize the porosity of the capping layer <NUM>. The capping layer <NUM> may be applied after sintering of the layer containing the hollow microspheres <NUM>, and sintered in a separate sintering process, or it may be applied after the slurry for forming the layer containing the hollow microspheres <NUM> has dried, and then both layers may be sintered simultaneously, in one sintering process.

A thermal barrier coating <NUM> formed according to an embodiment of the present invention may have a number of advantages over related art systems for thermal and environmental protection. The thermal barrier coating <NUM> formed according to an embodiment of the present invention may have a lower thermal conductivity (e.g., less than <NUM> W/mK), a lower coefficient of thermal expansion, which may be matched to silica-based substrates, a lower in-plane modulus (than related art systems which may have non-isotropic elastic moduli) resulting in lower thermal stresses on thermal cycling, higher resistance to water vapor hot gas corrosion, and a higher temperature capability.

Embodiments of the present invention may be utilized to provide protection, from heat and erosive high velocity exhaust flow, to the underlying ceramic structure in a jet engine exhaust system. Applications for embodiments of the present invention include scramjet combustors, high speed vehicle acreage thermal protection, thermal barrier coatings for jet engine exhaust structures, thermal barrier coatings for protection of high speed vehicles including reusable hypersonic strike and surveillance aircraft, hypersonic weapons and reusable rocket-based boosters, thermal and environmental barrier coatings for exhaust nozzles of commercial aircraft, and commercial furnace liners. Embodiments of the present invention may further find use in commercial and military jet engine applications as thermal barrier material on combustors, hot section blades, shrouds and nozzles, and exhaust structures (e.g. flaps and liners) if the components are fabricated from materials with a low coefficient of thermal expansion, such as SiC/SiC ceramic matrix composite (with a coefficient of thermal expansion of <NUM>-<NUM> parts per million per °C). Embodiments of the present invention may have similar applications in scramjet engines.

In one embodiment a coating is composed of hollow microspheres of amorphous aluminosilicate, e. g Fillite™ cenospheres with <NUM>%-<NUM>% Al<NUM>O<NUM>, <NUM>%-<NUM>% SiO<NUM> and <NUM>% Fe<NUM>O<NUM>, or amorphous silicon oxycarbide. Hollow spheres with a range of diameters, typically between <NUM>% and <NUM>% of the coating thickness, and a wall thickness between <NUM>%-<NUM>% of the diameter, are used. The hollow spheres are sintered together with a suitable ceramic binder resulting in a coating with at least <NUM>% void volume fraction, whereby the majority of these voids are closed porosity. This coating is applied to a ceramic foam or ceramic matrix composite substrate. The selected amorphous aluminosilicate or silicon oxycarbide coating material ensures a low CTE of <NUM> or <NUM> parts per million per °C respectively, which matches the CTE of the substrate well and mitigates thermal strains. Furthermore the amorphous nature of both materials circumvents CTE anisotropy which is common in other oxides with low CTE and may cause micro-cracking. The high volume fraction of closed porosity results in a very low thermal conductivity on the order of <NUM> W/mK or lower and a high in-plane compliance that can accommodate thermal strains.

Claim 1:
An article, comprising:
a ceramic substrate, and
a thermal barrier coating covering a surface of the ceramic substrate,
the thermal barrier coating having:
a void volume fraction of at least <NUM>% and
a major part of the void volume being closed porosity,
the thermal barrier coating comprising, as a major component, a plurality of hollow particles (<NUM>) sintered together, each of the plurality of hollow particles (<NUM>) comprising, as a major component, a first material, wherein the first material is selected from rare earth silicates, each of the plurality of hollow particles (<NUM>) having:
a maximum interior dimension less than <NUM> millimeter (mm) and greater than <NUM> micrometers, and
a maximum wall thickness less than <NUM>/<NUM> of the maximum interior dimension;
characterized in that
the article further comprises a capping layer (<NUM>) covering a portion of a surface of the thermal barrier coating, the capping layer (<NUM>) having a porosity less than <NUM>% and a thickness less than <NUM>/<NUM> of the thickness of the thermal barrier coating, wherein the capping layer (<NUM>) includes or consists of the same material as the hollow particles (<NUM>).