Patent Application
20230415193
A gas turbine engine typically includes a fan section, a compressor section, a combustor section and a turbine section. Air entering the compressor section is compressed and delivered into the combustion section where it is mixed with fuel and ignited to generate a high-energy exhaust gas flow. The high-energy exhaust gas flow expands through the turbine section to drive the compressor and the fan section. The compressor section typically includes low and high pressure compressors, and the turbine section includes low and high pressure turbines.
This disclosure relates to composite articles, such as those used in gas turbine engines, and methods of coating such articles. Components, such as gas turbine engine components, may be subjected to high temperatures, corrosive and oxidative conditions, and elevated stress levels. In order to improve the thermal and/or oxidative stability, the component may include a protective barrier coating.
An article according to an exemplary embodiment of this disclosure, among other possible things includes a substrate and a barrier layer on the substrate. The barrier layer includes a bond coat comprising a matrix, diffusive particles disposed in the matrix, and gettering particles disposed in the matrix; and a topcoat including a constituent that is reactive with calcium-magnesium-alumino-silicate (CMAS).
In a further example of the foregoing, the bond coat comprises a first bond coat layer adjacent the substrate and a second bond coat layer adjacent the top coat.
In a further example of any of the foregoing, each of the first and second layers include between about 5 and about 40 percent by volume matrix.
In a further example of any of the foregoing, the second layer includes between about 55 and 94 percent by volume gettering particles.
In a further example of any of the foregoing, the first layer includes between about 60 and about 95 percent by volume gettering particles.
In a further example of any of the foregoing, the second layer includes gettering particles having an average maximum dimension between about 1 and about 75 microns.
In a further example of any of the foregoing, the gettering particles in the second layer have a larger average diameter than the gettering particles in the first layer.
In a further example of any of the foregoing, the gettering particles are silicon carbide or silicon oxycarbide.
In a further example of any of the foregoing, the topcoat includes an interlayer adjacent the bondcoat that is free from the constituent that is reactive with calcium-magnesium-alumino-silicate (CMAS).
In a further example of any of the foregoing, the constituent that is reactive with calcium-magnesium-alumino-silicate (CMAS) includes titanium or cerium.
In a further example of any of the foregoing, the bond coat includes a sintering aid.
In a further example of any of the foregoing, the topcoat includes between about 2 and about 30 by weight constituent that is reactive with calcium-magnesium-alumino-silicate (CMAS).
An article according to an exemplary embodiment of this disclosure, among other possible things includes a ceramic matrix composite substrate and a barrier layer on the substrate. The barrier layer includes a bond coat comprising a silicone dioxide matrix, diffusive particles disposed in the matrix, and silicon carbide or silicon oxycarbide gettering particles disposed in the matrix; and a topcoat including a constituent that is reactive with calcium-magnesium-alumino-silicate (CMAS).
In a further example of the foregoing, the bond coat comprises a first bond coat layer adjacent the substrate and a second bond coat layer adjacent the top coat.
In a further example of any of the foregoing, the second layer includes gettering particles having an average maximum dimension between about 1 and about 75 microns. The gettering particles in the second layer have a larger average diameter than the gettering particles in the first layer.
In a further example of any of the foregoing, the constituent that is reactive with calcium-magnesium-alumino-silicate (CMAS) includes titanium or cerium.
In a further example of any of the foregoing, the bond coat includes a sintering aid.
In a further example of any of the foregoing, the topcoat includes between about 2 and about 30 by weight constituent that is reactive with calcium-magnesium-alumino-silicate (CMAS).
A method applying a calcium-magnesium-alumino-silicate (CMAS)-resistant topcoat according to an exemplary embodiment of this disclosure, among other possible things includes depositing a topcoat onto a bondcoat by thermal spray. A feedstock powder for the thermal spray includes between about 70 and 98% by weight topcoat material powder and the balance of CMAS-reactive constituent or precursor to CMAS-reactive constituent.
In a further example of the foregoing, the precursor to CMAS-reactive constituent is HfTiO4 or HfO2—CeO2.
The exemplary engine 20 generally includes a low speed spool 30 and a high speed spool 32 mounted for rotation about an engine central longitudinal axis A relative to an engine static structure 36 via several bearing systems 38. It should be understood that various bearing systems 38 at various locations may alternatively or additionally be provided, and the location of bearing systems 38 may be varied as appropriate to the application.
The low speed spool 30 generally includes an inner shaft 40 that interconnects, a first (or low) pressure compressor 44 and a first (or low) pressure turbine 46. The inner shaft 40 is connected to the fan 42 through a speed change mechanism, which in exemplary gas turbine engine 20 is illustrated as a geared architecture 48 to drive a fan 42 at a lower speed than the low speed spool 30. The high speed spool 32 includes an outer shaft 50 that interconnects a second (or high) pressure compressor 52 and a second (or high) pressure turbine 54. A combustor 56 is arranged in the exemplary gas turbine 20 between the high pressure compressor 52 and the high pressure turbine 54. A mid-turbine frame 57 of the engine static structure 36 may be arranged generally between the high pressure turbine 54 and the low pressure turbine 46. The mid-turbine frame 57 further supports bearing systems 38 in the turbine section 28. The inner shaft 40 and the outer shaft 50 are concentric and rotate via bearing systems 38 about the engine central longitudinal axis A which is collinear with their longitudinal axes.
The core airflow is compressed by the low pressure compressor 44 then the high pressure compressor 52, mixed and burned with fuel in the combustor 56, then expanded through the high pressure turbine 54 and low pressure turbine 46. The mid-turbine frame 57 includes airfoils 59 which are in the core airflow path C. The turbines 46, 54 rotationally drive the respective low speed spool 30 and high speed spool 32 in response to the expansion. It will be appreciated that each of the positions of the fan section 22, compressor section 24, combustor section 26, turbine section 28, and fan drive gear system 48 may be varied. For example, gear system 48 may be located aft of the low pressure compressor, or aft of the combustor section 26 or even aft of turbine section 28, and fan 42 may be positioned forward or aft of the location of gear system 48.
The engine 20 in one example is a high-bypass geared aircraft engine. In a further example, the engine 20 bypass ratio is greater than about six (6), with an example embodiment being greater than about ten (10), and can be less than or equal to about 18.0, or more narrowly can be less than or equal to 16.0. The geared architecture 48 is an epicyclic gear train, such as a planetary gear system or other gear system, with a gear reduction ratio of greater than about 2.3. The gear reduction ratio may be less than or equal to 4.0. The low pressure turbine 46 has a pressure ratio that is greater than about five. The low pressure turbine pressure ratio can be less than or equal to 13.0, or more narrowly less than or equal to 12.0. In one disclosed embodiment, the engine 20 bypass ratio is greater than about ten (10:1), the fan diameter is significantly larger than that of the low pressure compressor 44, and the low pressure turbine 46 has a pressure ratio that is greater than about five 5:1. Low pressure turbine 46 pressure ratio is pressure measured prior to an inlet of low pressure turbine 46 as related to the pressure at the outlet of the low pressure turbine 46 prior to an exhaust nozzle. The geared architecture 48 may be an epicycle gear train, such as a planetary gear system or other gear system, with a gear reduction ratio of greater than about 2.3:1 and less than about 5:1. It should be understood, however, that the above parameters are only exemplary of one embodiment of a geared architecture engine and that the present invention is applicable to other gas turbine engines including direct drive turbofans.
A significant amount of thrust is provided by the bypass flow B due to the high bypass ratio. The fan section 22 of the engine 20 is designed for a particular flight condition—typically cruise at about 0.8 Mach and about 35,000 feet (10,668 meters). The flight condition of 0.8 Mach and 35,000 ft (10,668 meters), with the engine at its best fuel consumption—also known as “bucket cruise Thrust Specific Fuel Consumption (‘TSFC’)”—is the industry standard parameter of lbm of fuel being burned divided by lbf of thrust the engine produces at that minimum point. The engine parameters described above and those in this paragraph are measured at this condition unless otherwise specified. “Low fan pressure ratio” is the pressure ratio across the fan blade alone, without a Fan Exit Guide Vane (“FEGV”) system. The low fan pressure ratio as disclosed herein according to one non-limiting embodiment is less than about 1.45, or more narrowly greater than or equal to 1.25. “Low corrected fan tip speed” is the actual fan tip speed in ft/sec divided by an industry standard temperature correction of [(Tram ° R)/(518.7° R)]0.5. The “Low corrected fan tip speed” as disclosed herein according to one non-limiting embodiment is less than about 1150.0 ft/second (350.5 meters/second), and can be greater than or equal to 1000.0 ft/second (304.8 meters/second).
The bond coat 102 includes a matrix 106, a dispersion of “gettering” particles 108, and a dispersion of diffusive particles 110. The matrix 106 may be silicon dioxide (SiO2), in one example. In one example, the gettering particles 108 are silicon oxycarbide particles (SiOC) or silicide particles such as molybdenum disilicide (MoSi2) particles 108, though other examples are contemplated. The gettering particles 108 could be, for instance, molybdenum disilicide particles, tungsten disilicide particles, vanadium disilicide particles, niobium disilicide particles, silicon oxycarbide particles, silicon carbide (SiC) particles, silicon nitride (Si3N4) particles, silicon oxycarbonitride (SiOCN) particles, silicon aluminum oxynitride (SiAlON) particles, silicon boron oxycarbonitride (SiBOCN) particles, or combinations thereof. The diffusive particles 110 could be, for instance, barium magnesium alumino-silicate (BMAS) particles, barium strontium aluminum silicate particles, magnesium silicate particles, calcium aluminosilicate particles (CAS), alkaline earth aluminum silicate particles, yttrium aluminum silicate particles, ytterbium aluminum silicate particles, other rare earth metal aluminum silicate particles, or combinations thereof.
The bond coat 102 protects the underlying substrate 104 from oxygen and moisture. For example, the substrate 104 can be a ceramic-based substrate, such as a silicon-containing ceramic material. One example is silicon carbide. Another non-limiting example is silicon nitride. Ceramic matrix composite (CMC) substrates 104 such as silicon carbide fibers in a silicon carbide matrix are also contemplated. These CMC substrates can be formed by melt infiltration, chemical vapor infiltration (CVI), polymer infiltration and pyrolysis (PIP), particulate infiltration, or any other known method.
The gettering particles 108 and the diffusive particles 110 function as an oxygen and moisture diffusion barrier to limit the exposure of the underlying substrate 104 to oxygen and/or moisture from the surrounding environment. Without being bound by any particular theory, the diffusive particles 110, such as BMAS particles 110, enhance oxidation and moisture protection by diffusing to the outer surface of the barrier layer opposite of the substrate 104 and forming a sealing layer that seals the underlying substrate 104 from oxygen/moisture exposure. Additionally, cationic metal species of the diffusive particles 110 (for instance, for BMAS particles, barium, magnesium, and aluminum) can diffuse into the gettering particles 108 to enhance oxidation stability of the gettering material. Further, the diffusion behavior of the diffusive particles 110 may operate to seal any microcracks that could form in the barrier layer. Sealing the micro-cracks could prevent oxygen from infiltrating the barrier layer, which further enhances the oxidation resistance of the barrier layer. The gettering particles 108 can react with oxidant species, such as oxygen or water that could diffuse into the bond coat 102. In this way, the gettering particles 108 could reduce the likelihood of those oxidant species reaching and oxidizing the substrate 104.
The bond coat 102 can be applied by any known method, such as a slurry coating method.
The bond coat 102 may include sintering aid such as silica, alkaline earth aluminosilicates, rare earth aluminosilicates, borosilicates, or combinations thereof.
A ceramic-based top coat 114 is interfaced directly with the bond coat 102. As an example, the ceramic-based top coat 114 can include one or more layers of an oxide-based material. The oxide-based material can be, for instance, hafnium-based oxides, zirconium-based oxides, or yttrium-based oxides (such as hafnia, hafnium silicate, yttrium silicates, yttria stabilized zirconia or gadolinia stabilized zirconia), calcium aluminosilicates, mullite, barium strontium aluminosilicate, or combinations thereof, but is not limited to such oxides. The topcoat 114 can be applied by any known method such as thermal spray (like air plasma spray) methods or slurry application methods. The topcoat 114 can be between about 2 and about 8 mils (50.8 and 203.2 microns) thick, in some examples.
The top coat 114 and bond coat 102 together form a barrier coating 116 for the substrate 104. The top coat 114 is the outermost layer of the barrier coating 116, and is exposed to the elements when the article 100 is in use.
Components in engine 20 such as the article 100 can be susceptible to attack by silicate-based deposits such as calcium-magnesium-alumino-silicate (CMAS) that can deposit on the surface of the article 100. During operation of the engine 20, silicate-based debris (e.g., sand, ash, dirt, etc.) can melt to component surfaces and subsequently form CMAS. The CMAS deposits can be molten at times, and can react with and/or wick into the article 100 or coatings on the component, which can cause damage the article/coating. As will be discussed below, the durability of these engine 20 components can be increased by including coatings which have CMAS-resistant components that can reduce the activity of CMAS. For example, the CMAS-resistant components can include one or more constituents that are reactive with respect to CMAS to form a compound that seals the surface of the article/coating in a process known an “reactive crystallization.”
Accordingly, the topcoat 114 is provided with constituents that are reactive with CMAS to induce reactive crystallization, thereby providing a CMAS-resistant topcoat 114. Oxides containing cerium (Ce) (such as ceria (CeO2)) and titanium (Ti) (such as titania (TiO2)) are two example constituents that are reactive with CMAS. Any of the example topcoat 114 materials discussed above can be co-deposited with constituents that are reactive with CMAS or precursors to constituents that are reactive with CMAS. Co-deposition can be achieved by any known method. For instance, where the topcoat 114 is applied by a thermal spray method such as air plasma spray, the desired constituents of the topcoat 114 can be co-sprayed. Where the topcoat 114 is applied by a slurry method, the desired constituents can be added to the slurry and deposited by any known method.
In a particular example, titania (TiO2) and/or ceria (CeO2) are co-deposited with topcoat 114 material. During or after the deposition, the titania and/or ceria react with the topcoat 114 material to form titanate-silicates and/or cerate-silicates. For instance, where the topcoat 114 materials is hafnium silicate (HfSiO4), the hafnium silicate is co-deposited with TiO2 and/or CeO2 which react to provide HfTixSiyO4/HfCexSiyO4, respectively, in the topcoat 114 during or after the deposition, where x=0 to 4 and y=0 to 4 and the sum of y and x is 4.
In another example, hafnium titanate (HfTiO4) and/or hafnium cerate (HfCeO4) are co-deposited with topcoat 114 material. During or after the deposition, the titania and/or ceria react with the topcoat 114 material to form titanate-silicates and/or cerate-silicates. For instance, where the topcoat 114 material is hafnium silicate (HfSiO4), the hafnium silicate is co-deposited with HfTiO4 and/or HfCeO4 which react to provide HfTixSiyO4/HfCexSiyO4, respectively, in the topcoat 114 during or after the deposition, where x=0 to 4 and y=0 to 4 and the sum of y and x is 4.
In another example, hafnium titanate-silicate (HfTixSiyO4) and/or hafnium cerate-silicate (HfCexSiyO4), where x=0 to 4 and y=0 to 4 and the sum of y and x is 4, are co-deposited with topcoat 114 material. During or after the deposition, the titania and/or ceria react with the topcoat 114 material to form different titanate-silicates and/or cerate-silicates. For instance, where the topcoat 114 materials is hafnium silicate (HfSiO4), the hafnium silicate is co-deposited with HfTiO4 and/or HfCeO4 which react to provide HfTiwSizO4/HfCewSizO4, respectively, in the topcoat 114 during or after the deposition, where w=0 to 4 and z=0 to 4 and the sum of w and z is 4.
In one particular example barrier layer 116 shown in
In a particular example, the gettering particles 108 in the second layer 102b have an average diameter higher than the average diameter of the gettering particles 108 in the first layer 102a. In general, smaller particles conform better to the adjoining surface, increasing adhesion of the particles to the surface. Smaller particles also exhibit improved packing and therefore provide a coating layer with lower porosity. Additionally, smaller particles have higher surface area-to-volume ratio, meaning there is a higher likelihood that oxidant particles in the barrier coating 116 will react with the gettering particle 108 than the substrate 104, providing an additional layer of protection near the substrate 104. On the other hand, larger gettering particles 108 have a longer lifetime in the barrier coating 116 because they have more matter that is available to react with oxidants and provide environmental protection as discussed above. Therefore, providing smaller gettering particles 108 in the first layer 102a improves adhesion of the first layer 102a to the substrate 104 and provides a relatively low porosity layer 102a, while providing larger gettering particles 108 in the second layer 102b improves the environmental protection and lifetime of the layer 102b, which is exterior to the first layer 102a and therefore more likely to encounter oxidant particles.
The topcoat 114 includes between about 2 and about 30% by weight CMAS-reactive constituent such as titania, ceria, hafnium titanates, hafnium cerates, hafnium titanate-silicates, and/or hafnium cerate-silicates.
In some examples, shown in
In a particular example, the topcoat 114 is applied by thermal spray such as air plasma spray with a feedstock powder that includes between about 70 and about 98% by weight topcoat 114 material powder such as hafnium silicate powder. The feedstock also includes the balance of CMAS-reactive constituent or precursor to CMAS-reactive constituent such as HfTiO4 and/or HfO2-CeO2.
As used herein, the term “about” has the typical meaning in the art, however in a particular example “about” can mean deviations of up to 10% of the values described herein.
Although the different examples are illustrated as having specific components, the examples of this disclosure are not limited to those particular combinations. It is possible to use some of the components or features from any of the embodiments in combination with features or components from any of the other embodiments.
The foregoing description shall be interpreted as illustrative and not in any limiting sense. A worker of ordinary skill in the art would understand that certain modifications could come within the scope of this disclosure. For these reasons, the following claims should be studied to determine the true scope and content of this disclosure.
