A turbocharger impeller includes: a cylindrical boss portion disposed around a rotary axis; a hub portion connected to the boss portion and extends in a radial direction of the rotary axis; and a blade portion protruding from the boss portion and the hub portion toward a tip end side in the direction of the rotary axis and the radial direction. At least a part of an outer peripheral part of the hub portion in the radial direction or a part of the blade portion is provided with a resin second section and the second section is bonded to an aluminum first section. The turbocharger impeller includes the aluminum first section and the resin second section.

The present invention relates to a blade or vane for a turbomachine, particularly for an aircraft engine, with a blade element for interacting with the flow medium, wherein the blade has different diffusion protective coatings in various regions on its surface for protection against corrosion and/or oxidation, wherein the diffusion protective coatings are produced by chromizing and/or aluminizing, wherein the blade element is divided into two regions along the longitudinal axis of the blade element, wherein the first region extends over 80 to 95% of the length of the blade element, and the second region extends over the remainder of the length of the blade element, and wherein in both regions, an AlCr diffusion protective coating is applied, and wherein in one of the regions, the AlCr diffusion protective coating has a higher Cr content.

A thermal barrier coating includes: a metal bonding layer made of an alloy containing Al; a thermal barrier layer; and an intermediate layer provided between the metal bonding layer and the thermal barrier layer. The thermal barrier layer contains a compound represented by the following general formula (1), Ln.sub.xTa.sub.yHf.sub.zO.sub.(3x+5y+4z)/2 (1) (wherein Ln is an atom of one element selected from among rare earth elements, x is 0 to 1.0, y is 0.8 to 3.0, and z is 0 to 7.0). The intermediate layer contains at least one layer selected from among the following (A) to (C): (A) a layer containing hafnium oxide (HfO.sub.2) as a main component; (B) a layer containing, as a main component, a compound consisting of tantalum (Ta), hafnium (Hf), and oxygen (O); and (C) a layer containing, as a main component, a compound consisting of a rare earth element, tantalum (Ta), hafnium (Hf), and oxygen (O).

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.

An attachment mechanism for a gas turbine engine component includes an elongated body having at least first and second ends. A first attachment feature is formed at the first end. A second attachment feature is formed at the second end. The first and second attachment features define attachment points configured to attach a first gas turbine engine component to a second gas turbine engine component. A fan section for a gas turbine engine and a gas turbine engine are also disclosed.

A turbocharger, having a turbine and a compressor. The turbine comprises a turbine housing and a turbine rotor with turbine blades. Radially outer edges of the rotor blades and a portion of the turbine housing or a stator-side component connected to the turbine housing define a turbine-side gap. The compressor comprises a compressor housing and a compressor rotor with compressor blades. Radially outer edges of the compressor blades and a portion of the compressor housing facing the compressor blades or a stator-side component connected to the compressor housing define a compressor-side gap. The portion of the turbine housing facing the turbine rotor blades or the stator-side component connected to the turbine housing and/or the portion of the compressor housing facing the compressor rotor blades or the stator-side component connected to the compressor housing comprises a running-in structure comprising hollow spaces.

An arrangement comprising a component (203) adjacent to a ceramic matrix composite in a gas turbine engine is shown. The component comprises a nickel-base superalloy substrate (301) and a cobalt-modified beta-nickel-aluminide coating (302) on the substrate to prevent interdiffusion between the substrate and the ceramic matrix composite. The substrate is coated by depositing a cobalt layer on the substrate, depositing an aluminium layer on the cobalt layer and then forming a cobalt-modified beta nickel aluminide coating.

A method of making a sheath for an airfoil may include the steps of forming an upper sleeve and a lower sleeve, and forming a central portion bonded to the upper sleeve and the lower sleeve. The central portion may be formed by depositing a material on the upper sleeve and the lower sleeve. A portion of the material may be removed from at least one of the central portion, the upper sleeve, or the lower sleeve. The sheath may include a first flank, a central portion bonded to the first flank, and a second flank bonded to the central portion. The central portion may have a substantially uniform microstructure resulting from additive manufacturing.

An airfoil surface includes a first titanium portion, a second titanium portion, an aluminum alloy braze disposed there between, and a titanium coating covering the aluminum alloy braze, at least part of the first titanium portion and at least part of the second titanium portion.

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.