| Patent application number | Description | Published |
|---|
| 20090184280 | Low Thermal Conductivity, CMAS-Resistant Thermal Barrier Coatings - A thermal barrier coating composition including a base oxide; a primary dopant including ytterbia; a first co-dopant including samaria; and a second co-dopant including at least one of lutetia, scandia, ceria, gadolinia, neodymia, or europia. | 07-23-2009 |
| 20090186237 | CMAS-Resistant Thermal Barrier Coatings - A coating including a CMAS-resistant layer with a rare earth oxide. The CMAS-resistant layer is essentially free of zirconia and hafnia, and may further include at least one of alumina, silica, and combinations thereof. | 07-23-2009 |
| 20100080984 | COATING INCLUDING A RARE EARTH SILICATE-BASED LAYER INCLUDING A SECOND PHASE - A coating including a bond layer deposited on a substrate. The bond layer includes a rare earth silicate and a second phase, the second phase including at least one of silicon, silicides, alkali metal oxides, alkali earth metal oxides, glass ceramics, Al | 04-01-2010 |
| 20100129636 | ABRADABLE LAYER INCLUDING A RARE EARTH SILICATE - An abradable coating may include a rare earth silicate. The abradable coating may be deposited over a substrate, an environmental barrier coating, or a thermal barrier coating. The abradable coating may be deposited on a gas turbine blade track or a gas turbine blade shroud to form a seal between the gas turbine blade track or gas turbine blade shroud and a gas turbine blade. The abradable coating may also include a plurality of layers, such as alternating first and second layers including, respectively, a rare earth silicate and stabilized zirconia or stabilized hafnia. | 05-27-2010 |
| 20100129673 | REINFORCED OXIDE COATINGS - A reinforced coating may include an oxide matrix and a reinforcement. In some embodiments, the reinforcement may include at least one of SiC and Si | 05-27-2010 |
| 20100136349 | MULTILAYER THERMAL BARRIER COATINGS - A multilayer thermal barrier coating (TBC) may include a plurality of layers selected to provide properties to the multilayer TBC. For example, a multilayer TBC may include a first layer deposited over a substrate, a second layer deposited over the first layer and a third layer deposited over the second layer. The first layer may be selected to provide thermal cycling resistance, the second layer may be selected to provide low thermal conductivity and the third layer may be selected to provide at least one of erosion resistance and CMAS degradation resistance. The multilayer TBC may also include two layers, or more than three layers. | 06-03-2010 |
| 20100159136 | STATIC CHEMICAL VAPOR DEPOSITION OF y-Ni + y'-Ni3AI COATINGS - A static chemical vapor deposition (CVD) process may be used to deposit a coating including a γ-Ni+γ′-Ni | 06-24-2010 |
| 20100255260 | SLURRY-BASED COATING TECHNIQUES FOR SMOOTHING SURFACE IMPERFECTIONS - An article may include a substrate defining a surface imperfection and a coating deposited over the substrate. The coating does not substantially reproduce the surface imperfection, and the coating comprises mullite and at least one rare earth silicate, rare earth oxide, alumina, boron oxide, alkali metal oxide, alkali earth metal oxide, silicon, barium strontium aluminosilicate, barium aluminosilicate, strontium aluminosilicate, calcium aluminosilicate, magnesium aluminosilicate, or lithium aluminosilicate. In some examples, the coating may be a first coating deposited from a slurry over the substrate, and a second coating may be deposited over the first coating. In other examples, a first coating that substantially reproduces the surface imperfection may be deposited over the substrate, and the coating that does not substantially reproduce the surface imperfection may be deposited over the first coating. | 10-07-2010 |
| 20120128879 | ABRADABLE LAYER INCLUDING A RARE EARTH SILICATE - An abradable coating may include a rare earth silicate. The abradable coating may be deposited over a substrate, an environmental barrier coating, or a thermal barrier coating. The abradable coating may be deposited on a gas turbine blade track or a gas turbine blade shroud to form a seal between the gas turbine blade track or gas turbine blade shroud and a gas turbine blade. The abradable coating may also include a plurality of layers, such as alternating first and second layers including, respectively, a rare earth silicate and stabilized zirconia or stabilized hafnia. | 05-24-2012 |
| 20130122259 | FEATURES FOR MITIGATING THERMAL OR MECHANICAL STRESS ON AN ENVIRONMENTAL BARRIER COATING - An article may include a substrate comprising a matrix material and a reinforcement material, a layer formed on the substrate, an array of features formed on the layer, and a coating formed on the layer and the array of features. The article may have improved thermal and/or mechanical stress tolerance compared to an article not including the array of features formed on the layer. | 05-16-2013 |
| 20130189531 | MULTILAYER CMAS-RESISTANT BARRIER COATINGS - An article comprising a substrate, a calcia-magnesia-alumina-silicate-resistant (CMAS-resistant) layer or a plurality thereof, including a rare earth oxide and alumina formed over the substrate, and a barrier coating layer formed on the CMAS-resistant layer. The barrier coating layer or a plurality thereof, comprising a thermal barrier coating composition or an environmental barrier coating composition. | 07-25-2013 |
| 20130224457 | THERMAL BARRIER COATINGS INCLUDING CMAS-RESISTANT THERMAL BARRIER COATING LAYERS - An article may include a superalloy substrate and a calcia-magnesia-alumina-silicate (CMAS)-resistant thermal barrier coating (TBC) layer overlying the superalloy substrate. In some embodiments, the CMAS-resistant TBC layer includes between about 50 wt. % and about 90 wt. % of a TBC composition and between about 10 wt. % and about 50 wt. % of a CMAS-resistant composition. In some examples, the TBC composition includes at least one of yttria-stabilized zirconia, yttria-stabilized hafnia, zirconia stabilized with at least three rare earth oxides, or hafnia stabilized with at least three rare earth oxides. In some examples, the CMAS-resistant composition includes alumina, silica, and an oxide of at least one of Sc, Y, La, Ce, Pr, Nd, Pm, Sm, Eu, Gd, Yb, Dy, Ho, Er, Tm, Tb, or Lu. | 08-29-2013 |
| 20140065438 | CMAS- RESISTANT THERMAL BARRIER COATINGS - A coating including a CMAS-resistant layer with a rare earth oxide. The CMAS-resistant layer is essentially free of zirconia and hafnia, and may further include at least one of alumina, silica, and combinations thereof. | 03-06-2014 |
| 20140072816 | BOND LAYERS FOR CERAMIC OR CERAMIC MATRIX COMPOSITE SUBSTRATES - A bond layer may include a composition that may be stable at temperatures above about 1410° C. An article may include a substrate, a bond layer formed on the substrate, and an overlayer formed over the bond layer. In some examples, the bond layer may include a substantially homogeneous mixture of Si and at least one of SiO | 03-13-2014 |
| 20140199163 | ABRADABLE LAYER INCLUDING A LOW THERMAL CONDUCTIVITY COMPOSITION - A system may include a blade track or blade shroud and a gas turbine blade that includes a blade tip. The blade track or blade shroud may include a substrate and an abradable layer formed over the substrate. The abradable layer may include at least one of zirconia or hafnia; ytterbia; samaria; and at least one of lutetia, scandia, ceria, gadolinia, neodymia, or europia. The abradable layer may include a porosity between about 25 vol. % and about 50 vol. %. The blade track or blade shroud and the gas turbine blade may be configured so the blade tip contacts a portion of the abradable layer during rotation of the gas turbine blade, and the abradable layer may be configured to be abraded by the contact by the blade tip. | 07-17-2014 |
| 20140255680 | ENVIRONMENTAL BARRIER COATING-BASED THERMAL BARRIER COATINGS FOR CERAMIC MATRIX COMPOSITES - A thermal barrier coating composition for a ceramic matrix composite is provided. The thermal barrier coating comprises a porous layer and a doped rare earth disilicate layer. The porous layer is located over the doped rare earth disilicate layer. The porous layer includes a fugitive material. | 09-11-2014 |
| 20140261080 | RARE EARTH SILICATE ENVIRONMENTAL BARRIER COATINGS - A vapor deposition method may include applying a first electron beam to vaporize a portion of a first target material comprising a rare earth oxide, where the first electron beam delivers a first amount of energy. The method also may include applying a second electron beam to vaporize a portion of a second target material comprising silica, where the second electron beam delivers a second amount of energy different from the first amount of energy. In some examples, the second target material is separate from the first target material. Additionally, the portion of the first target material and the portion of the second target material may be deposited substantially simultaneously over a substrate to form a layer over the substrate. A system for practicing vapor deposition methods and articles formed using vapor deposition methods are also described. | 09-18-2014 |
| 20140272168 | METHOD FOR FABRICATING MULTILAYER ENVIRONMENTAL BARRIER COATINGS - A method of making a multilayer environmental barrier coating for a ceramic matrix composite is provided, comprising the steps of: plasma spray coating an oxide-based bond coat over top of the ceramic matrix composite and depositing a columnar top coat over the oxide-based bond coat. | 09-18-2014 |
| 20140272169 | METHOD FOR FABRICATING MULTILAYER ENVIRONMENTAL BARRIER COATINGS - A method of making a multilayer environmental barrier coating for a ceramic matrix composite is provided, comprising the steps of: plasma spray coating an oxide-based bond coat over top of the ceramic matrix composite and depositing a columnar top coat over the oxide-based bond coat. | 09-18-2014 |
| 20140272197 | DIRECTED VAPOR DEPOSITION OF ENVIRONMENTAL BARRIER COATINGS - In some examples, a method may include directing an electron beam at a coating source to create a vapor plume, wherein the coating source comprises alumina and at least one rare earth oxide. The method also may include transporting the vapor plume using a gas stream provided adjacent to the coating source to within an internal cavity defined by a surface of a substrate of a gas turbine engine blade, vane, blade track, or combustor liner, and wherein the substrate comprises at least one of a silicon-containing ceramic or a ceramic matrix composite. Additionally, the method may include depositing the alumina and the at least one rare earth oxide from the vapor plume over the surface of the internal cavity to form a calcia-magnesia-alumina-silicate (CMAS)-resistant environmental barrier coating (EBC) comprising the alumina and the at least one rare earth oxide. | 09-18-2014 |
| 20140272249 | SLURRY-BASED COATING RESTORATION - In some examples, a method includes identifying a damaged area in a ceramic matrix composite coating of an in-service component; applying a restoration slurry to the damaged area of the ceramic matrix composite coating, wherein the restoration slurry comprises a liquid carrier and a restoration coating material; drying the restoration slurry to form a dried restoration slurry; and heat treating the dried restoration slurry to form a restored portion of the ceramic matrix composite coating. In some examples, an assembly may include a component including a substrate and a coating on the substrate, where the coating defines a damaged portion; masking around the damaged portion on undamaged portions of the coating; and a restoration slurry in the damaged portion, wherein the restoration slurry comprises a liquid carrier and a restoration coating material. | 09-18-2014 |
| 20140272310 | COATING INTERFACE - In one example, article comprising a substrate defining an outer surface; a plurality of joint conduits formed in the outer surface of the substrate, wherein each conduit of the plurality of joint conduits exhibits an undercut configuration; and a coating formed on the outer surface of the substrate, wherein the coating substantially fills the plurality of joint conduits formed in the surface of the substrate. | 09-18-2014 |
