Methods for forming protective coatings on aerospace components are provided. In one or more embodiments, the method includes exposing an aerospace component to a first precursor and a first reactant to form a first deposited layer on a surface of the aerospace component by a first deposition process (e.g., CVD or ALD), and exposing the aerospace component to a second precursor and a second reactant to form a second deposited layer on the first deposited layer by a second deposition process. The first deposited layer and the second deposited layer have different compositions from each other. The method also includes repeating the first deposition process and the second deposition process to form a nanolaminate film stack having from 2 pairs to about 1,000 pairs of the first deposited layer and the second deposited layer consecutively deposited on each other.

The present disclosure relates to a novel iron-based austenitic alloy for a turbocharger housing and to methods of its preparation.

Protective coatings on an aerospace component are provided. An aerospace component includes a surface containing nickel, nickel superalloy, aluminum, chromium, iron, titanium, hafnium, alloys thereof, or any combination thereof, and a coating disposed on the surface, where the coating contains a nanolaminate film stack having two or more pairs of a first deposited layer and a second deposited layer. The first deposited layer contains chromium oxide, chromium nitride, aluminum oxide, aluminum nitride, or any combination thereof, the second deposited layer contains aluminum oxide, aluminum nitride, silicon oxide, silicon nitride, silicon carbide, yttrium oxide, yttrium nitride, yttrium silicon nitride, hafnium oxide, hafnium nitride, hafnium silicide, hafnium silicate, titanium oxide, titanium nitride, titanium silicide, titanium silicate, or any combination thereof, and the first deposited layer and the second deposited layer have different compositions from each other.

There is provided a cobalt-based alloy product comprising: Co, C, N, B, Cr, Fe, Ni, W, Mo, Al, Si, and/or Mn with predetermined contents, and 0.5-4 mass % of an M component. The M component is a transition metal other than W and Mo and having an atomic radius of more than 130 pm. The product is a polycrystalline body of matrix phase crystal grains in which segregation cells are formed. There are at least two kinds of regions of the segregation cells wherein: a first region has an average size of 0.13-1.3 μm; a second region has an average size of 0.25-2 μm; and the average size of the second region is 1.3 times or more larger than that of the first region.

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.

The present invention concerns a turbine part comprising a substrate made of nickel-based monocrystalline superalloy, comprising chromium and at least one element chosen among rhenium and ruthenium, the substrate having a γ-γ′ phase, an average mass fraction of rhenium and of ruthenium greater than or equal to 4% and an average mass fraction of chromium less than or equal to 5% and preferably less than or equal to 3%, a sub-layer covering at least a part of a surface of the substrate, characterised in that the sublayer has a γ-γ′ phase and an average atomic fraction of chromium greater than 5%, of aluminium between 10% and 20% and of platinum between 15% and 25%.

There is provided a cobalt-based alloy product comprising: in mass %, 0.08-0.25% C; 0.1% or less B; 10-30% Cr; 5% or less Fe and 30% or less Ni, the total amount of Fe and Ni being 30% or less; W and/or Mo, the total amount of W and Mo being 5-12%; Ti, Nb and Ta, the total amount of Ti, Nb and Ta being 0.5-2%; 0.5% or less Si; 0.5% or less Mn; 0.003-0.04% N; and the balance being Co and impurities. The impurities include 0.5% or less Al, less than 0.05% Zr, and 0.04% or less 0. The product is a polycrystalline body of matrix phase crystal grains. In the matrix phase crystal grains, segregation cells with an average size of 0.13-2 gm are formed, in which components constituting an MC type carbide phase comprising Ti, Nb and/or Ta are segregated in boundary regions of the segregation cells.

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.

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 of 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.

Using the systems and methods discussed herein, CMAS corrosion is inhibited via CMAS interception in an engine environment and/or is prevented or reduced by the formation of a metal oxide protective coating on a hot engine section component. The CMAS interception can occur while the engine is in operation in flight or in a testing or quality control environment. The metal oxide protective coating can be applied over other coatings, including Gd-zirconates (GZO) or yttria-stabilized zirconia (YSZ). The metal oxide protective coating is applied at original equipment manufacturers (OEM) and can also be applied in-situ using a gas injection system during engine use in-flight or during maintenance or quality testing. The metal oxide protective coating contains a rare earth element, aluminum, zirconium, chromium, or combinations thereof.