In some embodiments, a plenum of an apparatus for transferring energy between a rotating element and a fluid may include a through hole disposed through the plenum; a plurality of inlet guide vanes disposed proximate a peripheral edge of the through hole, the plurality of inlet guide vanes comprising a first group of inlet guide vanes having a symmetrical profile, a second group of inlet guide vanes, and a third group of inlet guide vanes, wherein each inlet guide vane of the second group and third group have a cambered profile, wherein each inlet guide vane of the second group has same cambered profile, and further wherein each inlet guide vane of the third group has a different cambered profile from each other inlet guide vane of the third group.

A shrouded impeller includes an impeller having a plurality of blades and configured to rotate about an axis, and a shroud disposed adjacent to the impeller and configured to corotate about the axis with the impeller and translate axially relative to the impeller. A method of varying a geometry of a flow area of the shrouded impeller includes rotating the shroud and the impeller about the axis and axially translating the shroud relative to the impeller to increase or decrease a rate of flow between the shroud and the impeller.

A centrifugal compressor includes a shaft defining an axis, an impeller mounted to the shaft for rotation about the axis, and a diffuser section including a first wall, a second wall, and an opening defined between the first wall and the second wall. The opening of the diffuser section is arranged in fluid communication with the impeller. The first wall is rotatable about the axis and rotation of the first wall about the axis is mechanically driven.

A shaftless motor-compressor is disclosed, comprising a casing and at least one compressor stage arranged in the casing. Each compressor stage comprises a respective impeller arranged for rotation in the casing around a rotation axis. Each impeller is combined with an embedded electric motor housed in the casing and comprised of a motor stator and a motor rotor. The motor stator of each compressor stage circumferentially surrounds the impeller and the motor rotor, integral with the impeller. The motor rotor of each stage is arranged inside the respective motor stator.

A dual stage blower assembly includes a first fan configured to rotate about the rotational axis and including a first plurality blades. The first plurality of blades include a plurality of backward curved blades. The dual stage blower assembly also includes a second fan circumscribing the first fan and configured to rotate about the rotational axis. The second fan includes a second plurality of blades, wherein the second plurality of blades include one of a plurality of forward curved blades, a plurality of a radial blades, or a plurality of backward curved blades. At least one motor is coupled to the first fan and the second fan and configured to rotate the first fan and the second fan about the rotational axis.

A scroll casing forms a scroll flow passage of a centrifugal compressor, and, provided that, in a cross section of the scroll flow passage, Eo is an outer end of the scroll flow passage in a radial direction of the centrifugal compressor, Ef is a front end of the scroll flow passage in an axial direction of the centrifugal compressor, and Mw is a middle point of a maximum flow-passage width Wmax of the scroll flow passage in the radial direction, a flow passage height H of the scroll flow passage in the axial direction gradually increases from a position of the outer end Eo to a position of the front end Ef with respect to the radial direction, and the scroll flow passage has a recirculation flow suppressing cross section in which the front end Ef is disposed on an inner side, in the radial direction, of the middle point Mw, in a section disposed at least partially in a region closer to a scroll start than a connection position of the scroll start and a scroll end.

A gas turbine engine, with a conical screw integrated compression system, that utilizes at least one conical screw as an intermediary fluid transport device to facilitate the multi-staging of non-axial compressors, such as centrifugal and diagonal compressors, as well as or alternatively to combine non-axial compressors to axial compressors and to the fan. The conical screw in the compression system applies axial flow translation and funnels, as necessary, the exit flow of the impeller, fan or compressor into the next impeller or compressor.

A fluidic actuator is configured to be mounted to an airfoil surface. The actuator includes a rotor supported within a housing. The rotor contains at least one generally radially extending nozzle that converges from an entry at an interior circumference of the rotor to an exit at an exterior circumference thereof, the converging shape of the nozzle assuring high velocity airflow at the nozzle exit. In one form, each nozzle also includes a curved path by which high-pressure air is enabled to induce spinning of the rotor. The fluidic actuator further includes a diffuser through which high-pressure air from the nozzles is cyclically ejected from those of the nozzles instantaneously exposed to the diffuser. In one form, the rotor spins at 300 revolutions per second and provides nozzle ejections effective to avoid boundary layer separation; i.e. to maintain an attached boundary layer flow over the airfoil.

Provided is a clip fan including: a housing which has an air inlet provided to allow outside air to be introduced into the housing, and an air outlet provided to allow the air introduced through the air inlet to be discharged to the outside; a fan unit which includes a motor and a fan, is embedded in the housing, draws outside air through the air inlet, and discharges the air to the outside through the air outlet; and a clip which is coupled to an outer surface of the housing, and configured to be opened or closed by elastic force.

Provided are an inlet guide vane and a centrifugal compressor such that air can be caused to efficiently flow in with use of a simple shape. The inlet guide vane is disposed upstream of an impeller in a flow path of a centrifugal compressor. The inlet guide vane has: a plate-shaped plate section that is disposed in the flow path; and a rotation part that causes the plate section to rotate along an axis of rotation aligned with the radial direction of a rotary shaft of the centrifugal compressor. In a cross-section orthogonal to the axis of rotation of the rotation part, the plate section has, at the leading edge thereof on the upstream side of the flow path, a bent part that is tilted with respect to the other portions.