A compressor impeller includes an impeller body which includes a boss portion and a plurality of compressor blades disposed on an outer peripheral surface of the boss portion, and a connection portion which is disposed on a side of a back surface of the impeller body and is configured to be connectable to one end of a rotational shaft. A ratio D1/D2 satisfies 0.18 or less, where D1 is a diameter of the boss portion on leading edges of the compressor blades, and D2 is a maximum outer diameter of the compressor blades.

A turbomachine (105) configured to compress supercritical carbon dioxide is shown. The turbomachine comprises, in fluid flow series, an inlet (201), an inducerless radial impeller (202) having a plurality of blades, and a fully vaneless diffuser (203).

A bearing housing cover for a gas turbine engine having an impeller. The bearing housing comprises an annular collar having a flange mountable to an exterior surface of a bearing housing. The bearing housing further comprises an impeller baffle integrated with the annular collar, the impeller baffle having an annular body with a front baffle face positionable adjacent a rear face of the impeller, a rear baffle face having a plurality of stiffening elements extending between the rear baffle face and the annular collar, and a central baffle opening.

A centrifugal compressor includes: a rotational shaft; a main casing surrounding at least a part of the rotational shaft, the main casing having an inlet and an outlet separated from each other in an axial direction of the rotational shaft and an annular space surrounding a section of the rotational shaft at a side of the inlet and communicating with the inlet; at least one impeller disposed in a fixed state to the rotational shaft inside the main casing; a flow guide member disposed inside the annular space and extending along the axial direction of the rotational shaft; a plurality of injection holes disposed along the flow guide member and separated from one another along the axial direction of the rotational shaft; and a flow path which extends inside the annular space and through which a cleaning fluid to be supplied to the plurality of injection holes is capable of flowing.

A system for use in a gas turbine engine fuel supply has an internal fuel filter having an internal bore and an external surface. A chamber within the internal bore of the fuel filter for receives a fuel and allows fuel to pass radially outwardly across the fuel filter. An oxygen removal unit is outwardly of the external surface of the fuel filter, such that fuel passes through the fuel filter, encounters the oxygen removal unit such that oxygen can be removed from the fuel, an outlet port for removed oxygen, and a separate outlet port for fuel having passed over the fuel filter and the oxygen removal unit.

A fan includes a fan frame, an impeller, and at least a supporting member. The fan frame includes a bottom plate and a cover plate spaced from the bottom plate. The bottom plate and the cover plate together define a first accommodating space. The cover plate has an air inlet disposed in an axial direction. A side of the fan frame is provided with at least an air outlet. The impeller is disposed in the first accommodating space and includes a hub and a plurality of blades. A cross-sectional area of the hub increases gradually along a direction from the cover plate to the bottom plate. The blades are disposed around the periphery of the hub. The supporting member is disposed between the bottom plate and the cover plate for supporting the cover plate.

A vapor cycle compressor includes a controller section, a drive section in communication with the controller section, and a compression section operatively engaged with the drive section. The compression section includes a first compression stage and a return channel assembly downstream of the first compression stage. The return channel vane assembly includes return channel vanes that are configured to adjust their angle of orientation. The compression section also includes a second compression stage downstream of the return channel vane assembly, wherein inlet guide vanes are absent between the return channel vane assembly and the second compression stage.

An improved air scrubber has an improved, more efficient, more robust impeller and impeller housing for mixing incoming air with water, scrubbing the air with increased efficiency and lower mean time between failures. Also water flow through the system is improved to prevent loss of scrubbing performance and to reduce user workload. In addition to these improvements, the water intake system has been redesigned to use less water, prevent using too much water, and to prevent previously common errors that require users to drain water from the impeller housing.

A system for use in a gas turbine engine fuel supply has an internal fuel filter having an internal bore and an external surface. A chamber within the internal bore of the fuel filter for receives a fuel and allows fuel to pass radially outwardly across the fuel filter. An oxygen removal unit is outwardly of the external surface of the fuel filter, such that fuel passes through the fuel filter, encounters the oxygen removal unit such that oxygen can be removed from the fuel, an outlet port for removed oxygen, and a separate outlet port for fuel having passed over the fuel filter and the oxygen removal unit.

A diffuser for a turbine engine includes a first wall that extends circumferentially about a centerline axis of the turbine engine. The diffuser also includes a second wall that extends circumferentially about the centerline axis. At least a portion of the second wall is positioned radially outwardly from at least a portion of the first wall. A flow path is defined by the first wall and the second wall. The flow path extends from an inlet configured to receive an axial flow of a fluid, to a circumferentially extending outlet configured to emit the fluid in a substantially radial direction. The outlet extends asymmetrically about the centerline axis.