A novel diffuser for a centrifugal turbomachine to reduce or prevent stall. The diffuser includes diffuser vanes arranged around a diffuser axis. Each diffuser vane includes: a leading edge, a trailing edge, a suction side facing radially inwardly, and a pressure side facing radially outwardly. A respective flow passage is defined between the suction side of a first diffuser vane and the pressure side of a second diffuser vane of each pair of adjacently arranged diffuser vanes. The diffuser vanes are arranged with a non-constant pitch around the diffuser axis. The pitch between each pair of adjacently arranged first diffuser vane and second diffuser vane defining a respective flow passage there between is correlated to a chord of one of said first diffuser vane and second diffuser vane.

An electric motor assembly includes an electric motor, a fan assembly coupled to the electric motor and configured to rotate therewith about an axis. The bower assembly also includes a shroud coupled to the electric motor and extending about the fan assembly. The shroud includes a central hub coupled to the electric motor, an inlet ring, and a plurality of arms extending between the central hub and the inlet ring. Each arm of the plurality of arms includes a curved radial portion extending from the central hub and a planar axial portion extending from the radial portion to the inlet ring.

A fan blade (1) has a front inflow edge (2) and a rear outflow edge (3). The fan blade (1) has an at least partially wavy inflow edge (4). The wavy inflow edge (4) forms a wave (W) with a specific three-dimensional waveform.

A rotor blade system includes a rotor, a casing radially spaced apart from the rotor, and a plurality of blades coupled to the rotor and positioned between the rotor and the casing. The one or more of the plurality of blades have a radial length different from a remaining one or more of the plurality of blades so as to vary a tip gap between a tip of the one or more of the plurality of blades and the casing to break up a frequency content of a leakage vortex at the tip to modify natural frequencies of the plurality of blades and mode shapes to reduce or substantially eliminate flutter.

The present invention provides a blower with reduced noise. The blower comprises a blower main body incorporating a centrifugal fan. The blower main body is configured to suck air from both sides of the blower main body by rotation of the centrifugal fan. The centrifugal fan includes a support plate having a rotation center and a plurality of blades provided on each of a first surface and a second surface of the support plate. A position of at least part of the plurality of blades on the first surface and a position of at least part of the plurality of blades on the second surface are misaligned in a circumferential direction, and/or a number of the plurality of blades on the first surface differs from a number of the plurality of blades on the second surface.

A cooling fan and an electronic device are provided. The cooling fan comprises a plurality of blades disposed in a circumferential direction of a rotating shaft. The plurality of blades includes a first blade and a second blade. A windward surface of the first blade includes a first alignment part and a first offset part. The first alignment part is aligned with a windward surface of the second blade, and the first offset part and the windward surface of the second blade are arranged in a staggered manner.

A centrifugal fan includes a housing and an impeller. The housing includes a sidewall, and the sidewall includes a tongue portion. The impeller includes a fan hub and a plurality of blades. The fan hub is rotatably disposed in the housing, and the tongue portion has an inner contour line on a reference plane. The blades connect to the fan hub. Each one of the blades has an end surface facing the sidewall. The end surface has an outer contour line on the section of the blade. Any two adjacent blades have different outer contour lines. The outer contour line of at least one first blade of the plurality of blades is parallel to the inner contour line. The outer contour line of at least one second blade of the plurality of blades is not parallel to the inner contour line.

A fluid pressurizing structure and fan using same are disclosed. The fluid pressurizing structure includes a hub having a plate portion located therearound. The plate portion has a first and a second surface provided with a plurality of first and second hollow protrusions, respectively. Each of the first hollow protrusions has a first fluid inlet and a first fluid outlet, and each of the second hollow protrusions has a second fluid inlet and a second fluid outlet. The first and second fluid outlets extend through the plate portion to communicate the first and second fluid inlets with the second and first surface, respectively. When the fan rotates, fluid drawn thereinto sequentially flows through the first fluid inlets and outlets and the second fluid inlets and outlets in a helical movement in cycles, and is therefore continuously pressurized, which facilitates reduced fan vibration and noise and fan motor power consumption.

A brushless motor comprising a rotor assembly comprising a shaft, an impeller, a bearing assembly and a rotor core; a stator assembly; a frame comprising an outer portion and a support portion radially inward of the outer portion, the support portion supporting at least one of the rotor assembly and the stator assembly; and at least one strut extending between the outer portion and the support portion, wherein the strut and the stator assembly are aligned such that at least part of the strut and at least part of the stator assembly are disposed along a line substantially parallel to a rotation axis of the rotor assembly.

Blades (20a to 20c) of a propeller fan (10) have different circumferential pitches φ1, φ2, and φ3. The blades (20a to 20c) have different masses so that the center of gravity of the propeller fan (10) is positioned on a rotational center axis (11) of the propeller fan (10). Blade body portions (42c) of the blades (20a to 20c) have different thicknesses. In contrast, camber lines of the blades (20a to 20c) in blade cross section have the same shape, projections of the blades (20a to 20c) on a plane perpendicular to the rotational center axis (11) of the propeller fan (10) have the same shape, and leading edge portions (41a to 41c) of the blades (20a to 20c) have the same shape. As a result, a propeller fan (10) having reduced noise and vibrations can be achieved.