Known protective layers having a high Cr-content and a silicone in addition, form brittle phases that embrittle further under the influence of carbon during use. The protective layer according to the invention is composed of 22% to 26% cobalt (Co), 10.5% to 12% aluminum (Al), 0.2% to 0.4% Yttrium (Y) and/or at least one equivalent metal from the group comprising Scandium and the rare earth elements, 15% to 16% chrome (Cr), optionally 0.3% to 1.5% tantal, the remainder nickel (Ni).

An extension tool includes a plurality of sequentially arranged links moveable to a first position, the plurality of sequentially arranged links rigidly fixed to one another in the first position, the plurality of sequentially arranged links defining a first passage and a second passage, the second passage being separate from the first passage when the plurality of sequentially arranged links are rigidly fixed to one another.

A thermal barrier coating (TBC) material includes calcic-magnesia-alumina-silicates-resistant rare-earth (RE) oxide powder blended with yttria-stabilized zirconia (YSZ). The RE oxide powder may include any of gadolinium oxide, samarium oxide, ytterbium oxide and cerium oxide. The RE oxide powder may include gadolinium zirconate (GZO).

The present disclosure provides a wear liner for a stator vane that has a first hook and a second hook that are connected by a base, providing in a generally S-shaped channel. The wear liner includes an outer surface that is adapted to lie against a first component and an inner surface that is adapted to lie against a second component. The first hook of the wear liner includes a first engaging end that is adapted to engage a first component, while the second hook is adapted to engage the second component. The first component may comprise a vane foot and the second component may comprise a slot for receiving and securing the vane foot.

A repaired oxidation and corrosion resistant coating may comprise a repair material applied to a damaged portion of the oxidation and corrosion resistant coating. The repair material may be free of hexavalent chromium and may be compatible with a plurality of oxidation and corrosion resistant materials that comprise hexavalent chromium. The repair material may be burnished. The oxidation and corrosion resistant coating may comprise hexavalent chromium.

A turbine component includes a substrate made from monocrystalline nickel-based superalloy including rhenium, which has a γ-γ′ Ni phase, and an average weight faction of chromium of less than 0.08, a sublayer made from nickel-based metal superalloy covering the substrate, in which the sublayer made from metal superalloy includes at least aluminium, nickel, chromium, silicon, hafnium and has, predominantly by volume, a γ′-Ni 3 Al phase.

Thermal sprayed coating made from a thermal spray powder material containing aluminum containing particles mechanically alloyed to a transition metal. The coating includes aluminum alloy portions alloyed to the transition metal. The thermal spray powder is made of aluminum containing particles mechanically alloyed to a transition metal.

A method is provided for adding material to a turbine engine component. The method includes cold spraying a powder towards a region of the component to form a deposit on the region of the component, the component being formed of a parent material, the parent material being a superalloy or a titanium alloy and defining a parent material property value, and the deposit defining a deposit material property value equal to at least fifty percent of the parent material property.

A coating composition for coating of components of a flow machine, especially a turbomachine such as a gas turbine with compressor, or of a compressor, which are exposed to the fluid stream of the flow machine or of the compressor, wherein the coating composition includes anticorrosion pigments, wherein the coating composition includes hard material particles, and wherein the coating composition is an RT-curing, UV-curing and/or thermally curing coating composition. A component of a flow machine or of a compressor has the coating composition. A method of maintaining a flow machine or a compressor uses the coating composition.

Methods for depositing protective coatings on aerospace components are provided and include sequentially exposing the aerospace component to a chromium precursor and a reactant to form a chromium-containing layer on a surface the aerospace component by an atomic layer deposition process. The chromium-containing layer contains metallic chromium, chromium oxide, chromium nitride, chromium carbide, chromium silicide, or any combination thereof.