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.

An assembly is provided for a gas turbine engine. This assembly includes a rotating structure, a stationary structure and a bushing. The rotating structure extends axially along and is rotatable about a centerline. The stationary structure extends circumferentially about the rotating structure. The stationary structure is configured from or otherwise includes stationary structure material with a coefficient of thermal expansion between 10 μin/in-° F. and 15 μin/in-° F. The bushing is radially between the rotating structure and the stationary structure. The bushing includes a mount and a bearing within the mount. The mount is configured from or otherwise includes mount material with a coefficient of thermal expansion between 9 μin/in-° F. and 10 μin/in-° F. The mount material contacts the stationary structure material. The bearing is configured from or otherwise includes bearing material, where the bearing material is engaged with and rotatably supports the rotating structure. The bearing material is or otherwise includes copper.

An assembly is provided for a gas turbine engine. This assembly includes a rotating structure, a stationary structure and a bushing. The rotating structure extends axially along and is rotatable about a centerline. The stationary structure extends circumferentially about the rotating structure. The stationary structure is configured from or otherwise includes stationary structure material with a coefficient of thermal expansion between 10 μin/in-° F. and 15 μin/in-° F. The bushing is radially between the rotating structure and the stationary structure. The bushing includes a mount and a bearing within the mount. The mount is configured from or otherwise includes mount material with a coefficient of thermal expansion between 9 μin/in-° F. and 10 μin/in-° F. The mount material contacts the stationary structure material. The bearing is configured from or otherwise includes bearing material, where the bearing material is engaged with and rotatably supports the rotating structure. The bearing material is or otherwise includes copper.

A method for stripping a coating off of a blade includes discharging liquid nitrogen through a nozzle onto the blade at a coating to cause lifting of the coating from a substrate of the blade and traversing the nozzle along the blade to cause peeling of the coating off of the substrate of the blade as the nozzle traverses the blade.

Sealing arrangements and rotor assemblies are provided. A sealing arrangement includes a stationary component, a rotating component spaced apart from the stationary component. A clearance is defined between the stationary component and the rotating component. The sealing arrangement further includes a plurality of magnets embedded within the rotating component. The sealing arrangement further includes a brush seal having a frame and a plurality of magnetically responsive filaments. The plurality of magnetically responsive filaments each extending from the frame to a free end. The plurality of magnetically responsive filaments are attracted to the rotating component by the plurality of magnets. The plurality of magnetically responsive filaments at least partially covering the clearance, such that a flow of fluid across the clearance is restricted.

A method of coating a component includes attaching the component to a support that is configured to hold a plurality of components and placing a base of the support in a holder that is attached to rotatable member of a fixture, wherein an axis of the holder is parallel to an axis of rotation of the rotatable member. The method also includes transporting the fixture into a coating chamber wherein a direction of an exit stream of a coater in oriented perpendicularly to the axis of rotation, exposing the fixture and the component to a reverse transfer arc cleaning/pre-heating procedure, and exposing the fixture and the component to a coating procedure during which a coating is directed at the component in a direction perpendicular to the axis of rotation while the rotatable member is rotating. The method further includes transporting the fixture and removing the component from the support fixture.

A method for stripping a coating off of a blade includes discharging liquid nitrogen through a nozzle onto the blade at a coating to cause lifting of the coating from a substrate of the blade and traversing the nozzle along the blade to cause peeling of the coating off of the substrate of the blade as the nozzle traverses the blade.

Flow restricting arrangements and rotor assemblies are provided. A flow restricting arrangement includes a stationary component and a rotating component. The rotating component is radially spaced apart from the stationary component such that a clearance is defined between the stationary component and the rotating component. A first magnet is embedded within the stationary component. A second magnet embedded within the rotating component. A plurality of magnetically responsive particles is contained within the clearance by a magnetic field produced by the first magnet and the second magnet. The plurality of magnetically responsive particles at least partially span the clearance.

A method of coating a component includes attaching the component to a support that is configured to hold a plurality of components and placing a base of the support in a holder that is attached to rotatable member of a fixture, wherein an axis of the holder is parallel to an axis of rotation of the rotatable member. The method also includes transporting the fixture into a coating chamber wherein a direction of an exit stream of a coater in oriented perpendicularly to the axis of rotation, exposing the fixture and the component to a reverse transfer arc cleaning/pre-heating procedure, and exposing the fixture and the component to a coating procedure during which a coating is directed at the component in a direction perpendicular to the axis of rotation while the rotatable member is rotating. The method further includes transporting the fixture and removing the component from the support fixture.

Embodiments of the present disclosure generally relate to protective coatings on turbocharger components, such as turbine wheels and compressor wheels, and other rotary equipment components and methods for depositing the protective coatings on such components. In one or more embodiments, a coated turbocharger component is provided and includes a metallic substrate containing a nickel-based alloy or superalloy, a cobalt-based alloy or superalloy, a stainless steel, or a titanium-aluminum alloy and a protective coating disposed on the metallic substrate. The protective coating contains an aluminum oxide having a purity of greater than 99 atomic percent (at %). In some examples, the metallic substrate is a turbine wheel, a compressor wheel, an impeller, a fan blade, a disk, a heat shield, a pulley, or a shaft.