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.

Disclosed is a fan. The fan includes a support; a first motor installed on the support, the first motor having a first rotation shaft; a first blade installed on the first rotation shaft; a second motor installed on the support, the second motor having a second rotation shaft and being coaxial with the first motor; a second blade installed on the second rotation shaft, a tilt direction of the second blade being opposite to a tilt direction of the first blade; and an electric control board electrically connected to the first motor and the second motor and configured to control a relative rotation of the first motor and the second motor.

An integral fan blade includes a fan blade connecting disk and a plurality of fan blade bodies arranged around and equidistantly surrounding the fan blade connecting disk. The fan blade bodies and the fan blade connecting disk are integrally formed. This design allows the wind angle to cover a cone-shaped area from top to bottom. Under the same specifications, the wind force is relatively larger than ordinary conventional fan blades, and the coverage area is also larger, thus bringing better blowing effect and better use effect to users.

A centrifugal fan includes an impeller with a base expanded radially, vanes arranged circumferentially, extending from a radially inner side to a radially outer side, and ends thereof at one axial side being connected to the base, and a ring portion connecting ends of the vanes at the other axial side. The vanes include first vanes and second vanes, when viewed axially, the lengths of the second vanes are larger than the lengths of the first vanes, the first vanes and the second vanes are circumferentially arranged alternatingly. Gaps are provided between radially outer ends of the first vanes and the second vanes that are circumferentially adjacent to each other, and sizes of circumferentially adjacent ones of the gaps are different from each other.

A turbomachinery rotor apparatus includes: a rotatable disk having an array of slots spaced around its periphery; an array of blades installed in the slots, wherein the blades have variable weights; and a plurality of connection components installed in the disk, each connection component forming a portion of a mechanical joint between one of the blades and its respective slot, wherein the connection components have variable weights.

A fan includes a frame and an impeller including a hub, a plurality of first blades, a first ring-shaped structure, and a plurality of second blades. The first blades are disposed around the hub. The hub and the first blades are surrounded by the first ring-shaped structure connected with the ends of the first blades, and a central area is structured therebetween. The second blades are connected with an outer rim of the first ring-shaped structure. The frame includes a base, an axle tube portion disposed on the base, and a receiving portion. The impeller is disposed on the axle tube portion. The receiving portion includes plural third blades disposed around the base corresponding to the central area. The first and third blades are matched to each other to be assembled for transforming a tangent velocity into a static pressure to increase the pressure generated by the central area.

A compressor rotor, such as a fan, for a gas turbine engine is described which includes alternating at least first and second blade types. The leading edge of the second blade types includes a leading edge tip cutback extending to the blade tip thereof. The leading edge tip cutback of the second blade type defines a chord length at the blade tip of the second blade types that is less than that of the first blades types. The first and second blade types generate different shock patterns when the fan or compressor rotor operates in supersonic flow regimes.

An integral fan blade includes a fan blade connecting disk and a plurality of fan blade bodies arranged around and equidistantly surrounding the fan blade connecting disk. The fan blade bodies and the fan blade connecting disk are integrally formed. This design allows the wind angle to cover a cone-shaped area from top to bottom. Under the same specifications, the wind force is relatively larger than ordinary conventional fan blades, and the coverage area is also larger, thus bringing better blowing effect and better use effect to users.

The gas turbine compressor for an aircraft gas turbine engine includes a compressor rotor having a plurality of compressor blades circumferentially distributed around a hub. Each of the compressor blades has an airfoil extending radially outward from the hub to a blade tip. A circumferential row of the compressor blades includes two or more different blade types, at least one modified blade of the two or more different blade types having means for generating different shock patterns between adjacent ones of the two or more different blade types when the gas turbine compressor operates in supersonic flow regimes. The means for generating different shock patterns on the modified blade aerodynamically mistune the two or more different blade types.

A fan with increased heat-removing ability and reduced noise in operation includes a hub, a baffle, a first blade layer, and a second blade layer. The first blade layer includes a plurality of first blades, and the second blade layer includes a plurality of second blades. An orthogonal projection of each of the plurality of first blades on the baffle is located between orthogonal projections of adjacent two of the plurality of second blades on the baffle. A length of the plurality of first blades is greater or less than a length of the plurality of second blades to avoid any resonance. An electronic device including the fan is also disclosed.