Thermal barrier coatings and methods to make such coatings present improved resistance to CMAS infiltration. The method for forming a thermal barrier coating includes applying a layer of the thermal barrier coating to a component having a surface, forming a plurality of first channels in the thermal barrier coating, and forming a plurality of second channels in the thermal barrier coating. The first channels extend through a thickness of the thermal barrier coating from an interface with the surface of the component to a free surface opposite the interface. The second channels are disposed between the free surface and the interface and extending lengthwise generally parallel to the free surface of the thermal barrier coating, wherein the thermal barrier coating comprises a material comprising yttrium aluminum garnet (YAG) or yttria stabilized zirconia (YSZ).

A method of manufacturing a fiber reinforced coating. The method includes providing a substrate and plasma spraying a ceramic matrix having fibers encapsulated in a precursor material onto the substrate.

A system may include an energy delivery device and a computing device. The computing device may be configured to: control the energy delivery device to deliver energy to an abrasive coating, wherein the abrasive coating comprises a metal matrix and abrasive particles at least partially encapsulated by the metal matrix; and control the energy delivery device to scan the energy across a surface of the abrasive coating and form a series of softened or melted portions of the metal matrix.

A coated gas turbine engine part includes a substrate and a calcium-magnesium-alumino-silicate (CMAS) protection layer present on the substrate. The protection layer includes a first phase of a calcium-magnesium-alumino-silicate CMAS protection material capable of forming an apatite or anorthite phase in the presence of calcium-magnesium-alumino-silicates CMAS and a second phase including particles of at least one rare-earth REa silicate dispersed in the first phase.

Embodiments of the present disclosure generally relate to protective coatings on turbine blades, turbine disks, and other aerospace components and methods for depositing the protective coatings. In one or more embodiments, a turbine blade includes a blade portion and a root coupled to the blade portion, where the root contains a protective coating disposed thereon. The protective coating is or contains one or more deposited crystalline film containing at least one of a metal oxide, a metal nitride, or a metal oxynitride and has a thickness of about 100 nm to about 10 μm. In some examples, a turbine blade assembly includes a disk and a plurality of the turbine blades coupled to the disk. The protective coating is disposed on the root on the turbine blade and/or a receiving surface on the turbine disk.

The present invention relates to a panel for tip clearance control formed by: a first perforated sheet adapted for being seated on the turbine casing; a second sheet arranged on said first sheet and configured for being attached to the first sheet leaving a gap between both sheets; and a third sheet arranged between both first sheet and second sheet such that respective spaces in fluid connection by at least one hole are configured: a distribution chamber and an impingement chamber, both chambers extending from one end of the panel to the other. The panel further comprises a closure element together with a sealing element at one of its lateral ends for allowing the passage of fluid with another adjacent panel, whereas the sealing element is configured for allowing relative movement between both adjoining panels.

An erosion and CMAS resistant coating arranged on a TBC coated substrate and including at least one porous vertically cracked (PVC) coating layer providing lower thermal conductivity and being disposed over a layer of MCrAlY wherein M represents Ni, Co or their combinations. At least one dense vertically cracked (DVC) erosion and CMAS resistant coating layer is deposited over the at least one PVC coating layer.

A method for repairing a pocket of a case for a variable stator assembly may comprise: receiving, via a processor, a plurality of wear depths, each wear depth in the plurality of wear depths corresponding to a wear portion in a stator pocket in a plurality of stator pockets; determining, via the processor, a plurality of thicknesses of a coating to be deposited based on the plurality of wear depths, each thickness of the coating in the plurality of thicknesses corresponding to the wear portion for each stator pocket in the plurality of stator pockets; and commanding, via the processor, a coating spray torch to deposit the coating in the wear portion of each stator pocket in the plurality of stator pockets.

An airfoil assembly includes an airfoil body extending from a root to a tip defining a longitudinal axis therebetween. The airfoil body includes a leading edge between the root and the tip. A sheath is direct deposited on the airfoil body. The sheath includes at least one metallic material layer conforming to a surface of the airfoil body. In accordance with another aspect, a method for assembling an airfoil assembly includes directly depositing a plurality of material layers on an airfoil body to form a sheath. In accordance with some embodiments, the method includes partially curing the airfoil body.

A powder of fused particles. The powder includes, in percentage by weight based on the oxides, more than 98% of a stabilized oxide selected from stabilized zirconium oxides, stabilized hafnium oxides and mixtures thereof, the stabilized oxide being stabilized by a stabilizer selected from the oxides of Y, Ca, Ce, Sc, Mg, In, La, Gd, Nd, Sm, Dy, Er, Yb, Eu, Pr, and Ta, called stabilizing oxides, and the mixtures of these stabilizing oxides. The powder has: a median particle size D.sub.50 under 15 m, a 90th percentile of the particle sizes, D.sub.90, under 30 m, and a size dispersion index (D.sub.90D.sub.10)/D.sub.10 below 2, and a relative density above 90%. The percentiles D.sub.n of the powder are the particle sizes corresponding to the percentages, by number, of n %, on the cumulative distribution curve of the powder particle size and the particle sizes are classified by increasing order.