A gas turbine engine component includes a metal substrate and a coating system disposed on the metal substrate. The coating system includes at least one layer of aluminum-chromium oxide.

Disclosed herein is a method of coating, comprising providing an article having an internal passage therein to be coated; electrolytically applying a first layer that comprises chromium or a chromium alloy onto a surface of the internal passage; electrolytically applying a second layer comprising aluminum or an aluminum alloy onto the first layer; and heat treating the article to promote interdiffusion between the first layer and the second layer.

A blade has an attachment root and an airfoil, the airfoil having a proximal end and a distal end. The blade has a compositional variation along the airfoil.

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 method for depositing a metal layer on a component includes applying an electrically conductive coating composition comprising a resin and metal particles on a coating region of the component and partially curing the resin to a gel state to form an electrically conductive coating. The method also includes applying additional metal particles to the partially cured resin in the gel state and depositing, via an electrodeposition process, a metal layer on the electrically conductive coating.

In a journal part of a 9 to 12 wt % Cr steel turbine rotor, a groove face is formed, and on the groove face, a lower build-up layer is formed by using a first welding material containing C: 0.10 to 0.25 wt %, Si: 0.20 to 0.80 wt %, Mn: 1.0 to 2.5 wt %, Ni: 0.4 to 1.0 wt %, Cr: 1.0 to 3.0 wt %, Mo: 0.2 to 1.5 wt %, V: 0.03 to 0.10 wt %, and a remainder composed of Fe and inevitable impurities, and further on this lower build-up layer, an upper build-up layer is formed using a second welding material containing C: 0.10 to 0.25 wt %, Si: 0.20 to 0.80 wt %, Mn: 1.0 to 2.5 wt %, Ni: 0.4 to 1.0 wt %, Cr: 1.0 to 3.0 wt %, Mo: 0.2 to 1.5 wt %, and a remainder consisting of Fe and inevitable impurities.

A coating process for applying a bifurcated coating to an article is disclosed including applying an aluminizing slurry to a first portion of the article, applying a chromizing slurry to a second portion of the article, and simultaneously heat treating the article, the aluminizing slurry, and the chromizing slurry. Heat treating the aluminizing slurry forms an aluminide coating on the first portion of the article and an aluminide diffusion zone between the article and the aluminide coating. Heat treating the chromizing slurry forms a chromide coating on the second portion of the article and a chromide diffusion zone between the article and the chromide coating. The first portion and the second portion are both maintained in an unmasked state while applying the aluminizing slurry and the chromizing slurry and during the heat treating.

A method is provided for casting an article such as a blade having an attachment root and an airfoil, the airfoil having a proximal end and a distal end. The method comprises introducing a molten alloy into a mold; and varying a composition of the introduced alloy during the introduction so as to produce a compositional variation.

A hybrid rocket engine system has: an oxidizer tank containing a liquid oxidizer; a rocket engine having a combustion chamber operatively connected to the oxidizer tank; a solid propellant fuel within the combustion chamber; a nozzle fluidly connected to the combustion chamber, the nozzle having a convergent section and a divergent section downstream of the convergent section; and a thrust vector control device operatively connected to the divergent section of the nozzle and operable to inject a fluid through at least one aperture defined through the divergent section for controlling a direction of a thrust generated by the rocket engine.

A method for applying an abrasive comprises: applying, to a substrate, the integral combination of a self-braze material, an abrasive, a matrix in which the abrasive is at least partially embedded, and an intermediate layer between the self-braze material and the matrix; and heating to cause the self-braze material to braze to the substrate.