Turbine assemblies and related turbocharger systems having direct turbine interfaces are provided. One exemplary turbine assembly includes a first turbine housing having an outlet portion defining a fluid outlet of a first turbine and a second turbine housing having an inlet portion defining a fluid inlet of a second turbine, wherein at least a portion of the outlet portion radially surrounds at least a portion of the inlet portion to provide a direct interface from the fluid outlet of the first turbine to the fluid inlet of the second turbine in an axial direction.

A liquid cooling head includes an upper casing, an impeller, a bottom casing and a skived fin cooling plate. The upper casing has an inlet and an outlet, the upper casing is fixed on the bottom casing, and the impeller is arranged between the upper casing and the skived fin cooling plate. In addition, the skived fin cooling plate is fixed on the bottom casing, and the impeller sucks the heat-dissipating liquid from the inlet and drives the heat-dissipating liquid passing through the skived fin cooling plate, upwardly passing through the impeller and then discharged from the outlet.

A propeller having a plurality of blades extending radially outward from a hub, the blades forming a loop. Each loop can have an intake portion, an exhaust portion and a tip portion extending radially outward from the hub and a gap between the intake root and the exhaust root.

Provided in embodiments of the present disclosure are a fan blade assembly and a fan apparatus. The fan blade assembly includes: a primary fan blade, where multiple first blades circumferentially provided are arranged on the primary fan blade; an auxiliary fan blade arranged coaxial and adjacent to the primary fan blade, where multiple second blades circumferentially provided are arranged on the auxiliary fan blade, an air inlet direction of the auxiliary fan blade is an axial direction, an air outlet direction of the auxiliary fan blade is a radial direction, and the first blades and the second blades have different torsion directions; and an motor arranged on one side of the auxiliary fan blade away from the primary fan blade, where the primary fan blade has a maximum outer diameter greater than an outer diameter of the auxiliary fan blade. According to the embodiment of the present disclosure.

An electronic device with a heat-dissipating function and a liquid-cooling radiator module are provided. The electronic device includes a first circuit board, a second circuit board and a liquid-cooling radiator module. The second circuit board is mounted on the first circuit board. The liquid-cooling radiator module is attached on the second circuit board and in thermal contact with an electronic component of the second circuit board. The liquid-cooling radiator module includes plural airflow channels and a fan. The plural airflow channels are in parallel with the second circuit board. The fan produces airflow toward the plural airflow channel. After the airflow passes through the plural airflow channels, the airflow is outputted in a direction parallel with the second circuit board. Since the airflow is not obstructed by the adjacent function circuit boards, the heat-dissipating efficiency is enhanced.

A fan unit in which a structure of a fan and a driving source thereof is improved to realize stable and high-efficient fan driving, thereby obtaining a high suction force in a stick type electric cleaner. The fan unit installed in a stick type electric cleaner includes a first fan and a second fan disposed in a line on the same rotation axis and a driving motor configured to drive the first fan and the second fan. The second fan is configured to be rotated in a direction opposite a direction in which the first fan is rotated.

The LNG plant comprises a compression train and a further compression. The compression train (100) comprises comprising an engine and a compressor driven by the engine; the compressor is an axial compressor and comprises a first set of axial compression stages and a second set of axial compression stages arranged downstream the first set of axial compression stages; at least the first set and the second set of axial compression stages are housed inside one case. The further compression train comprises a further engine and a further compressor driven by the further engine; the further compressor is a centrifugal compressor and comprises a first set of impellers and a second set of impellers arranged downstream or upstream the first set of impellers.

A propeller having a means for creating fluid flow in a non-axial direction and redirecting it in an axial direction.

A gas turbine engine including a compressor, a turbine, and a transmission is disclosed. The turbine is coupled to the compressor to drive rotation of multiple stages of the compressor. The transmission is configured to transmit rotational power from the turbine to at least one stage of the compressor to drive rotation of the at least one stage of the compressor.

An extraction impeller for an axial compressor includes first vanes having an elongated S-shape arranged on the surface of an impeller body. The first vanes extend radially from an outer flow inlet edge of the body to a flow outlet hub centered on the surface at the rotation axis. A radially inner end of each of the first vanes connects at the flow outlet hub in a direction perpendicular to a rotation axis. Second vane(s) are arranged between adjacent first vanes, and third vanes are arranged between second vanes and between first vanes and second vanes. Second vanes are radially longer than third vanes. The impeller extracts air from the axial compressor and forms an axial flow with reduced vortex whistle. When used in an axial compressor of a gas turbine system, the impeller reduces flow unsteadiness.