An exhaust-gas turbocharger (1) having a compressor housing (2); a turbine housing (3); and a bearing housing (4) which has a compressor-side flange (5) and which has a turbine-housing-side flange (6). The turbine-housing-side flange (6) is produced from a material which corresponds in terms of its mechanical and thermal properties to the material of the turbine housing (2).

A device configured to generate an air flow, the device including: a compressor; an air flow duct arranged to convey a flow of air generated by the compressor; a gas-filled cavity disposed beside the air flow duct; a wall separating the air flow duct and the cavity, the wall including at least one aperture; and an acoustic resistive screen covering and held in tension over the aperture of the wall. The screen is in fluid contact with air in the air flow duct and gas in the cavity and is configured to resist air flow between the duct and the cavity. The resistive screen and the cavity together define a noise-damping resonator.

The invention relates to a turbomachine part comprising a substrate consisting of a metal material, or a composite material, and also comprising a layer of a coating for protection against the infiltration of CMAS-type compounds, at least partially covering the surface of the substrate, the protective coating layer comprising a plurality of elementary layers including elementary layers of a first assembly of elementary layers inserted between elementary layers of a second assembly of elementary layers, each elementary layer of the first assembly and each elementary layer of the second assembly comprising an anti-CMAS compound, and each contact zone between an elementary layer of the first assembly and an elementary layer of the second assembly forming an interface conducive to the spreading of cracks along said interface.

A rotor blade includes a main body that extends radially outward from a first end to a second end, and includes a platform at the second end that extends circumferentially between opposing first and second sidewalls. The platform includes a first lateral wall that is situated between leading and trailing edges of the platform. The first lateral wall extends circumferentially between the first and second sidewalls and radially outward from the platform. The first lateral wall includes an extension that extends the first lateral wall circumferentially outward from the first sidewall. Respective portions of the first and second sidewalls adjacent to the first lateral wall reside in respective first and second planes, and the extension includes an outer face situated outside of the first and second planes. A majority of the first lateral wall includes a first material, and the outer face includes a second material having a different resistance to wear than the first material.

A turbine blade for a turbomachine, having a blade airfoil with a blade tip region and a sealing region which has an auxetic material and is arranged and designed such that, when transitioning from a rest state to an operating state of the turbine blade, the blade tip region of the turbine blade expands in a first direction perpendicular to a longitudinal axis of the blade airfoil. An auxetic material is used for a turbine blade for sealing a gas path during operation of a turbomachine.

An alloy is disclosed, encompassing reduced amounts of Hafnium and Carbon so as to achieve an excellent oxidation resistance, as well as gas turbine applications using the same.

A rotor blade includes a main body that extends radially outward from a first end to a second end, and includes a platform at the second end that extends circumferentially between opposing first and second sidewalls. The platform includes a first lateral wall that is situated between leading and trailing edges of the platform. The first lateral wall extends circumferentially between the first and second sidewalls and radially outward from the platform. The first lateral wall includes an extension that extends the first lateral wall circumferentially outward from the first sidewall. Respective portions of the first and second sidewalls adjacent to the first lateral wall reside in respective first and second planes, and the extension includes an outer face situated outside of the first and second planes. A majority of the first lateral wall includes a first material, and the outer face includes a second material having a different resistance to wear than the first material.

A turbomachine blade comprising a metallic leading edge having a region having varying fracture resistance in a spanwise direction so as to increase energy absorption by the leading edge in the event of the blade being released from a turbomachine and impacting a casing of the turbomachine.

A gas turbine engine has a fan drive turbine driving a gear reduction, the gear reduction, in turn, driving a fan rotor, the fan rotor delivering air into a bypass duct as bypass air and into a compressor section as core flow. A forward bearing is positioned between the gear reduction and the fan rotor and supports the gear reduction. A second bearing is positioned aft of the gear reduction and supports the gear reduction. The second bearing is a thrust bearing. A fan drive turbine drive shaft drives the gear reduction. The fan drive turbine drive shaft has a weakened link which is aft of the second bearing such that the fan drive turbine drive shaft will tend to fail at the weakened link, and at a location aft of the second bearing.

A hot gas path component of an industrial machine includes a cooling pathway with a lattice structure therein. The component and lattice structure are made by additive manufacturing. The component includes an outer surface exposed to a working fluid having a high temperature; a thermal barrier coating over the outer surface; an internal cooling circuit; and a cooling pathway in communication with the internal cooling circuit and extending towards the outer surface. A lattice structure is in the cooling pathway at the outer surface. The lattice structure is configured to support the thermal barrier coating over the cooling pathway and in response to a spall in the thermal barrier coating occurring over the cooling pathway, allow a cooling medium from the internal cooling circuit to pass therethrough.