A seal assembly for a rotary machine, such as a turbine engine, may include one or more seal segments that respectively include a seal housing defining a seal chamber and one or more fluid supply apertures that pass through the seal housing, and a seal body defining a seal face and one or more fluid conduits that pass through the seal body to the seal face. The seal chamber may receive at least a portion of the seal body, and the seal body may move within the seal chamber along a radial axis of a rotor of the rotary engine. The fluid supply apertures may fluidly communicate with the fluid conduits, and the fluid conduits may fluidly communicate with a fluid-bearing gap defined between the seal face and a rotor face of the rotor.

A compressor wheel includes a compressor wheel body, and a thermal insulating coating layer disposed so as to cover at least a part of a back surface of the compressor wheel body.

There is provided an exhaust casing for a turbocharger that can be reduced in weight and can be easily machined. The exhaust casing (1) for the turbocharger includes an exhaust casing body (2) for the turbocharger that has a hollow structure and is made of a casting of iron-based metal, a light metal layer (3) that serves as an outer shell, and a heat insulating layer (4) that is provided between the exhaust casing body (2) and the light metal layer (3).

There is provided an exhaust casing for a turbocharger that can be reduced in weight and can be easily machined. The exhaust casing (1) for the turbocharger includes an exhaust casing body (2) for the turbocharger that has a hollow structure and is made of a casting of iron-based metal, a light metal layer (3) that serves as an outer shell, and a heat insulating layer (4) that is provided between the exhaust casing body (2) and the light metal layer (3).

A compressor wheel includes a compressor wheel body, and a thermal insulating coating layer disposed so as to cover at least a part of a back surface of the compressor wheel body.

A composite article includes a substrate, at least one protective layer on the substrate, and an intermediate layer between the protective layer and the substrate. The intermediate layer includes a first material that occupies a first continuous region and a second material that occupies a second continuous region next to the first continuous region. The first continuous region and the second continuous region are each in contact with the substrate and the protective layer.

A seal assembly for a rotary machine, such as a turbine engine, may include one or more seal segments that respectively include a seal housing defining a seal chamber and one or more fluid supply apertures that pass through the seal housing, and a seal body defining a seal face and one or more fluid conduits that pass through the seal body to the seal face. The seal chamber may receive at least a portion of the seal body, and the seal body may move within the seal chamber along a radial axis of a rotor of the rotary engine. The fluid supply apertures may fluidly communicate with the fluid conduits, and the fluid conduits may fluidly communicate with a fluid-bearing gap defined between the seal face and a rotor face of the rotor.

A propeller of a pulsed airflow generator, in particular for a standalone portable blower, of the type made up of the assembly of two parts coaxially adjoining one another, i.e.: a first front part made as a single piece and comprising a plurality of twisted blades connected to a central ring, and a second rear part with a generally conical shape also made as a single piece, the central portion of said assembly having a conical shape and making up the rear portion of an air-inlet cone, said propeller being characterised in that said first and second rear parts are secured by a clamping device made up of a hub including two parts assembled coaxially and between which said two parts that make up the propeller are clamped, said hub being rotatably secured to the latter and maintaining said front and rear parts in the assembled position thereof.

A method for a turbine blade assembly for a rotor groove is disclosed. A dovetail of the turbine blade includes a mounting arm and an end surface facing radially inward relative to the rotor axis. An extension insert includes a first end configured to contact the end surface of the dovetail and a second end. A single positioning leg extends radially inward relative to the axis from the second end of the insert. The dovetail and the extension insert are configured to be positioned in the rotor groove to mount the turbine blade to the rotor. The mounting arm engages a radially inward facing rotor hook of the rotor groove and the positioning leg engages one of a radially outward facing surface of the rotor groove and a planar plate shim between the positioning leg and the radially outward facing surface of the rotor groove.