A method of providing a self-healing coating includes providing substrate, applying a layer of an aluminum-containing MAX phase material and another material to the substrate. The method includes exposing the layer to a temperature greater than 2000° F. to form alpha aluminum.

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.

An article such as a heat shield panel includes a substrate and a multi-layered coating supported on the substrate. The multi-layered coating can include alternating layers of different ceramic material compositions having individual thicknesses of less than 25 micrometers.

Various embodiments include honeycomb structures including an abradable material, and a method of applying such honeycomb structures to steel components of a gas turbine engine in order to reduce rub damage. Particular embodiments include a honeycomb structure having a plurality of cells, each cell of the plurality of cells including a cell wall surrounding a void, and an abradable material within the void of each cell of the plurality of cells, the abradable material including a metallic alloy and hollow particles.

A turbine part, such as a turbine blade or a distributor fin, for example, including a substrate made of superalloy based on monocrystalline nickel, including rhenium and/or ruthenium, and having a -NisAI phase that is predominant by volume and a -Ni phase, the part also including a sublayer made of metal superalloy based on nickel covering the substrate, wherein the sublayer has a -NisAI phase that is predominant by volume and wherein the sublayer has an average atomic fraction of aluminium of between 0.15 and 0.25, of chromium of between 0.03 and 0.08, of platinum of between 0.01 and 0.05, of hafnium of less than 0.01 and of silicon of less than 0.01. A process for manufacturing a turbine part including a step of vacuum deposition of a sublayer made of a superalloy based on nickel having predominantly by volume a -NisAI phase, on a substrate made of superalloy based on nickel including rhenium and/or ruthenium.

A method of manufacturing a coated turbine vane (34) comprises manufacturing a turbine vane (34) having a platform (44) and an aerofoil (42) extending from the platform (44), a curved transition (60) connects the platform (44) to the aerofoil (42) and a recess (64) is provided in the curved transition (60) from the platform (44) to the aerofoil (42). A bond coating (70) is deposited on the platform (44), the aerofoil (42), the curved transition (60) and the recess (64). A ceramic thermal barrier coating (72) is deposited on the platform (44), the recess (64) and the curved transition (60) by plasma spraying. The recess (64) reduces the size of the step due to the ceramic thermal barrier coating (72) and hence improves the aerodynamics of the turbine vane (34).

Disclosed is a process for coating a component of a TiAl alloy in order to improve the high-temperature resistance of the component. The process comprises depositing a Pt- and Cr-free protective layer alloy comprising Ti, Al, Nb, Mo and B and optionally one or more of W, Si, C, Zr, Y, Hf, Er and Gd on the component by physical vapor deposition at a temperature of less than or equal to 600 C. The protective layer alloy has a higher Al content than the TiAl alloy of the component. A coated component made by this process is also disclosed.

A method of providing a self-healing coating includes providing substrate, applying a layer of an aluminum-containing MAX phase material and another material to the substrate. The method includes exposing the layer to a temperature greater than 2000 F. to form alpha aluminum.

Novel slurry formulations and processes for forming improved protective coatings used in the hot section components of gas turbine engines are provided. The process includes a unique two-step deposition methodology whereby the required concentration of reactive element within an improved reactive element doped aluminide coating can be consistently produced in a reproducible manner.

Provided are a composite coating layer having improved erosion resistance and a turbine component including the same. The composite coating layer may include a TiN layer; and a TiAlN layer, wherein the composite coating layer is formed by alternately stacking the TiN layer and the TiAlN layer, and a total number of layers including the TiN layer and the TiAlN layer is 6 to 18, whereby the composite coating layer is capable of exhibiting high erosion resistance, high hardness, superior high-cycle fatigue characteristics and low surface roughness. Moreover, the turbine component including the composite coating layer is also capable of manifesting improved properties, such as high erosion resistance, high hardness, superior high-cycle fatigue characteristics and low roughness, thus remarkably increasing lifespan characteristics.