A method of applying a protective coating to an article comprises the steps of a) depositing aluminum in a surface region of an article, and b) depositing chromium is the surface region of the article subsequent to step a), whereby at least a portion of the chromium replaces at least a portion of the aluminum. Another method and an article are also disclosed.

The invention relates to a method of providing a metallic surface with a protective diffusion layer, wherein a chromium-containing slip is applied to the surface and is then subjected to a heat treatment in order to produce the protective diffusion layer. In addition to the chromium powder, the slip contains silicon powder in order to shorten the hold time required in the heat treatment.

A steam valve includes a housing defining a steam inlet and steam outlet in fluid communication with a valve cavity, and an annular valve seat disposed within the valve cavity. A control valve is configured to selectively engage the valve seat. The steam valve further includes a stop valve configured to selectively engage the valve seat. The steam valve includes a pressure seal head configured to receive the stop valve. The pressure seal head includes an elongated body having a bore extending longitudinally through the body; and a nose piece extending from an end of the elongated body. The nose piece has at least a tapered end portion and a bore extending longitudinally therethrough. The bore of the nose piece is longitudinally with the bore of the elongated body. The nose piece is formed of a first material which has greater erosion properties than a second material forming the elongated body.

A turbine blade of a gas turbine engine is described which includes an airfoil extending away from the hub platform to a blade tip. The airfoil defines a leading edge, a trailing edge, and a span-wise length extending between the platform and the blade tip. A hot-corrosion-resistant coating is located on the leading edge of the airfoil within a radially inner portion thereof, the radially inner portion extending away from the hub platform a desired distance along the span-wise length.

A blade for a rotor of a gas turbine has a cast substrate including: a root for connecting the blade to a rotor of a gas turbine, a platform having a lower surface from which the root extends and an upper surface opposite to the lower surface, an aerofoil extending from the upper surface of the platform, the lower surface and the root having an anti-corrosion layer of an high Cr blade alloy over the substrate. A method for manufacturing a blade where the lower surface and the root have the anti-corrosion layer.

A split ring seal has: a first circumferential end and a second circumferential end; an inner diameter surface and an outer diameter surface; a first axial end face and a second axial end face. The outer diameter surface has a sealing surface. The first axial end face has: a first section; a second section outboard of the first section; and an axial protrusion between the first section and the second section The second axial end face has: a first sealing surface; a second sealing surface radially outboard of the first sealing surface; a circumferential channel between the first surface and the second sealing surface; and a plurality of channels extending radially outward from the circumferential channel.

An article comprising a turbine component formed of a nickel-chromium (NiCr) alloy including from 2 to 50 wt % chromium balanced by nickel is disclosed. The NiCr alloy is thicker than at least 125 m to make a self-supporting turbine component, and the turbine component includes a rotor blade, a stator, or a vane. The NiCr alloy is electroformed on a mandrel by providing an external supply of current to an anode and a cathode in a plating bath containing a solvent, a surfactant, and an ionic liquid including choline chloride, nickel chloride, and chromium chloride.

Disclosed is an austenitic stainless steel alloy that includes or consists of, by weight, about 24% to about 26% chromium, about 11% to about 13% nickel, about 4.5% to about 5.5% manganese, about 1.3% to about 1.7% silicon, about 1.2% to about 1.6% niobium, about 0.40% to about 0.50% carbon, about 0.2% to about 0.4% nitrogen, and a balance of iron with inevitable/unavoidable impurities. The alloy is suitable for use in turbocharger turbine applications for temperatures up to about 1050 C.

A method for coating a substrate having a cavity structure, in particular a cooling structure, inside the substrate, wherein the cavity structure includes openings in the surface of the substrate. At least one bonding layer, in particular a diffusion layer, or at least one metallic layer is applied onto the substrate, in particular onto the surface of the substrate, and subsequently at least one thermal protection layer is applied onto the at least one diffusion layer by using a plasma spray physical vapour deposition (PS-PVD) method, a hollow cathode sputtering method or a suspension plasma spray (SPS) method.

A component includes a diffusion coating comprising an inter-diffusion zone between the diffusion coating and a substrate and a non-metallic inclusions zone adjacent to an outer surface of the diffusion coating. A method of coating a component includes applying an aluminizing slurry to a localized area of a component and applying a chromizing slurry to the localized area of the component subsequent to heat treating the aluminizing slurry.