In accordance with the present disclosure, there is provided a process for limiting a critical stabilizer content in coatings comprising placing a source coating material in a crucible of a vapor deposition apparatus having a coating chamber, the source coating material having compositional range of LnO.sub.1.5 comprising a single cation mol % of 30-50% relative to zirconia (ZrO.sub.2), where Ln=La, Pr, Nd, Sm, Eu, Gd, and Tb and combinations thereof; energizing the source coating material with an electron beam that delivers a power density to the material in the crucible forming a vapor cloud from the source coating material; and depositing the source coating material as a coating system onto a surface of a work piece.

An abrasive coating system for a substrate of an airfoil in a turbine engine high pressure compressor, comprising a plurality of grit particles adapted to be placed on a top surface of the substrate; a matrix material bonded to the top surface; the matrix material partially surrounds the grit particles, the matrix material consisting of unalloyed chromium and unalloyed aluminum distributed throughout the matrix material, wherein the grit particles extend above the matrix material relative to the top surface; and a film of oxidant resistant coating applied over the plurality of grit particles and the matrix material.

An article includes a ceramic-based substrate and a barrier layer on the ceramic-based substrate. The barrier layer includes a matrix, diffusive particles, and gettering particles. The gettering particles include at least one of non-gas-evolving particles and porous particles. An article and a method are also disclosed.

A seal for a gas turbine engine including an interlayer between a substrate and an abradable layer, the interlayer containing abrasive particles of which at least some abrasive particles protrude out of an interface that abuts the abradable layer.

A process for manufacturing an abradable layer, includes compressing a powder composition including at least micrometric ceramic particles having a number-average form factor greater than or equal to 3, a mass content of said micrometric ceramic particles in the powder composition being greater than or equal to 85%, the form factor of a particle being defined as the ratio [largest dimension of the particle]/[largest cross-sectional dimension of the particle], and sintering the powder composition thus compressed to obtain the abradable layer, wherein a temperature imposed during sintering, the sintering time and the compression pressure applied are selected so as to obtain a volume porosity rate of the abradable layer greater than or equal to 20%.

An article has a body having: a first face; and a first bevel surface extending from the first face. A plurality of first channels along the first bevel surface extending from the first face. A ceramic coating is along the inner diameter surface and the first bevel surface.

A space filler for forming a fibrous preform may comprise an additively manufactured ceramic material. The additively manufactured ceramic material may define a plurality of pores. A shape of the additively manufactured ceramic material may complement a shape of a void formed by fibrous regions of the fibrous preform.

An engine shaft assembly for an engine is provided. The engine shaft assembly includes a shaft and a thermal distribution layer. The thermal distribution layer is provided on the shaft, and is configured to minimize the effect of distortion of the shaft caused by asymmetric cooling on shutdown of the engine.

An abrasive coating for a substrate of a component in a gas path exposed to a maximum temperature of 1750 degree Fahrenheit, comprising a plurality of grit particles adapted to be placed on a top surface of the substrate; a matrix material bonded to the top surface; the matrix material partially surrounds the grit particles, wherein the grit particles extend above the matrix material relative to the top surface; a film of oxidant resistant coating applied over the plurality of grit particles and the matrix material and a thermal barrier coating material applied over said film of oxidant resistant coating.

A thermal barrier coated component, such as a turbine blade formed from a superalloy substrate, includes a thermal barrier coating applied onto the substrate. A metallic bond coat layer is on the substrate and includes rare-earth luminescent dopants. A ceramic top coat layer is on the bond coat layer. A temperature sensing thermally grown oxide (TGO) layer is formed at the interface of the bond coat layer and ceramic top coat layer. The temperature sensing TGO layer includes grown rare-earth luminescent ions migrated from the metallic bond coat layer in an amount sufficient to enable luminescence sensing of the TGO layer for real-time phosphor thermometry temperature measurements at the TGO layer.