A nickel-base superalloy is disclosed. The superally includes aluminum, cobalt, chromium, molybdenum, tantalum, titanium and tungsten, in addition to nickel, as alloy constituents, wherein rhenium can additionally be contained and the rhenium content is less than or equal to 2 wt. % and wherein the titanium content is greater than or equal to 1.5 wt. %. Further disclosed is a component made of the nickel-base superalloy.

An abradable powder composition is includes a metal component, a lubricant component, and a polymer component. A portion of the metal component is wrapped in the lubricant component to achieve high lubricity and abradability. The abradable powder composition can be used to form an abradable seal coating provided for use in a turbo machinery having a housing and a wheel having multiple blades. The housing houses the wheel which rotates therein. The seal coating is formed on the inner walls of housing adjacent where the wheel blades pass during their rotation. When the wheel is rotated such that the blades contact the seal coating, it is abraded to form a close fit gap. The abradable seal coating preferably does not produce significant wear of the blade tips or transfer abradable material significantly to the blade tips upon being abraded.

An impeller for use in a fan system includes a hub extending along an axis of rotation and having a hub outer surface. There also are a plurality of blades extending radially outwardly of the hub outer surface. The blades have a unique cross-section at several different locations that result in relatively thin blades. A fan system and method are also disclosed.

A method of repairing an erosion coating coupled to a substrate, wherein the coating comprises an anodization layer on the substrate, a bond primer layer on the anodization layer, a corrosion-resistant primer on the bond primer, and an erosion coating on the corrosion-resistant primer. The method comprises abrading an erosion coating; abrading a corrosion-resistant primer; creating an abraded surface comprising a bond primer over an anodization layer coupled to the substrate, applying a sol-gel adhesion promoter layer to said abraded surface; applying a corrosion-resistant layer over the sol-gel adhesion promoter layer; and applying an erosion coating layer over the corrosion-resistant layer.

A method for improving the heat resistance of a resistive element embedded in an alumina deposit covering a surface of a substrate, in which the alumina deposit includes a surface portion and a deep portion which is sandwiched between the surface portion and the surface of the substrate and in which the resistive element is located, is provided. The method includes a densification of the surface portion of the alumina deposit.

The present invention relates to a turbine engine comprising a wheel, (2) mounted on a shaft (4), and a disk (18), adjacent to the wheel (2) and mounted on the same shaft while being rotated by the latter. The disk (18) is made of a material having a density greater than that of the material used to manufacture the wheel (2). The invention is of use in a compressor/turbine.

New aluminum alloys having iron, vanadium, silicon, and copper, and with a high volume of ceramic phase therein are disclosed. The new products may include from 3 to 12 wt. % Fe, from 0.1 to 3 wt. % V, from 0.1 to 3 wt. % Si, from 1.0 to 6 wt. % Cu, from 1 to 30 vol. % ceramic phase, the balance being aluminum and impurities. The ceramic phase may be homogenously distributed within the alloy matrix.

A fan having an outer circumferential support with a plurality of radial penetrations. An inner circumferential support having a plurality of radial penetrations. A plurality of blades, each coupled to the outer circumferential support and the inner circumferential support. A plurality of radial supports, each radial support extending through a penetration of the inner circumferential support and a penetration of the outer circumferential support.

There is provided a turbocharger which can reduce whirl vibration. The turbocharger includes a shaft connecting a turbine and a compressor, a bearing housing having a bearing portion turnably supporting the shaft, and a sliding bearing interposed between the shaft and the bearing portion. The bearing portion is formed of an aluminum-based material, the shaft is formed of a steel material, and the sliding bearing is formed of a copper-based material.

The present disclosure is directed to a method for coating a component of a gas turbine engine. The method includes isolating a first portion of the component of the gas turbine engine from a second portion of the component. The method also includes simultaneously depositing a first coating material on the first portion of the component and a second coating material on the second portion of the component, wherein the first and second coating materials are different.