A fan shroud and a blower device are provided. The fan shroud includes a shroud wall surface and a plurality of ventilation openings. The shroud wall surface extends around a fan along a radial direction orthogonal to a rotation axis. The plurality of ventilation openings are formed through the shroud wall surface in a thickness direction of the shroud wall surface to allow passing of wind generated by a fan motor. A width of a wall surface side opening on a downstream side of the wind in the ventilation opening is smaller than a width of a lateral wall side opening on an upstream side of the wind in the ventilation opening.

A variable guide vane assembly is provided for a turbine defining a core air flowpath. The variable guide vane assembly includes an airfoil band defining a flowpath surface and a cavity. The variable guide vane assembly further includes an airfoil including a first end extending at least partially into the cavity of the airfoil band and an opposite second end, the airfoil extending generally along an axis between the first end and the second end and being moveable generally about the axis relative to the airfoil band. The variable guide vane assembly further includes a sealing element operable to form a seal between the first end of the airfoil and the airfoil band.

An EMI attenuation device includes a housing stator, a fan rotor, and an electrical bridge therebetween. The housing stator has an aperture therethrough, and at least a portion of the housing stator is electrically conductive. The fan rotor is adjacent to the aperture and has a rotational axis relative to the housing stator and a proximate surface proximate the housing stator. The fan rotor is electrically conductive, and the proximate surface is continuous around a rotational direction of the fan rotor. The electrical bridge is between the proximate surface of the fan rotor and a contact surface of the housing stator.

A diagonal fan includes an electric motor, a housing, and a diagonal impeller received inside the housing and drivable via the motor. The diagonal flow during operation is deflected in an axial flow direction. The diagonal impeller includes impeller blades distributed in the circumferential direction and a slinger ring encloses said blades. The diagonal fan includes an inlet nozzle on the suction side accommodating a main flow for the diagonal fan. The inlet nozzle extends overlapping at least in sections relative to the radial section of the slinger ring forming a nozzle gap therewith. A bypass channel on the housing forms a flow connection from a pressure-side surrounding region (U) of the diagonal fan to an inflow side of the nozzle gap. During operation of the diagonal fan, a swirl-free secondary flow (NS) is guided at the inflow side of the nozzle gap via the bypass channel.

A ducted fan includes a fan and a cowl having a cylindrical shape and including an introduction port configured to introduce air from a first end portion side. The fan includes a compressor blade provided on an outer circumferential side and a thrust blade provided on an inner circumferential side of the compressor blade. The cowl includes a housing portion configured to accommodate the compressor blade in an interior thereof, an outlet configured to allow air flowing through the housing portion to be blown therethrough by the compressor blade, and an inlet configured to suck air blown out. The outlet is provided inwards in a radial direction of the cowl and near the introduction port of the cowl, and the inlet is provided inwards in the radial direction of the cowl and between the outlet and the compressor blade in an axial line direction.

A rotor assembly is provided for a piece of rotational equipment. This rotor assembly includes a rotor disk, a rotor blade and a seal element. The rotor disk is configured to rotate about a rotational axis. The rotor blade includes an airfoil, a platform and a mount attaching the rotor blade to the rotor disk. The seal element is seated in a groove of the rotor disk. The seal element is configured to sealingly engage the platform and the mount.

The invention relates to a rotor blade (10) for a turbomachine, in particular of an aircraft, comprising an airfoil (12) comprising a pressure face (15) and a suction face (17) extending from a leading edge (14) to a trailing edge (16), the airfoil (12) comprising an axis of elongation extending substantially along the leading (14) and trailing (16) edges, the airfoil (12) comprising a radially firmer end for connection to a rotor and a free radially outer end. According to the invention, the airfoil (10) further comprises at least one series of fins (24) situated on said free end, each of these fins (24) comprising a pressure face (26) situated on the suction face (17) side of the airfoil (12), and a suction face (28) situated on the pressure face (15) side of the airfoil (12).

A free-tipped axial fan assembly features a shroud barrel comprising an inlet, the radius of said inlet at its upstream end being greater than the radius of said inlet at its downstream end. An angle, in a plane including the fan axis, between the surface of said inlet and the direction of the fan axis varies non-monotonically with respect to a surface coordinate which increases with distance along the surface of the inlet.

A compressor stator vane unit includes multiple compressor stator vanes disposed at a certain interval in a circumferential direction; and an annular joint member connected with inner ends of the multiple compressor stator vanes; wherein the annular joint member constitutes an outer diameter side surface of a leakage fluid flow path provided in an inner diameter side of the joint member to communicate a high-pressure space with a low-pressure space respectively located downstream and upstream of the multiple compressor stator vanes in a fluid flow direction, and D/P is set to 0.05≤D/P≤0.2, wherein D is defined as a distance in an axial direction between an upstream end surface of the annular joint member and an upstream edge of the multiple compressor stator vanes in the fluid flow direction and P is defined as a pitch between the adjacent compressor stator vanes in the circumferential direction.

A housing for a fan, in an embodiment for an axial or diagonal fan, with the fan including an impeller and at least one flow-through region, wherein immediately downstream of the impeller or the blades of the impeller in an outer region of the housing and thus in the flow-through region, multiple individual, free-standing guide elements are provided. A fan includes a corresponding housing.