A modular fan blade includes a first fan blade and a second fan blade. The first fan blade includes a hub and plural first vanes, and the hub has an external periphery, and the first vane is combined with the external periphery, and a flange is formed at the external periphery and a retaining space is formed on a surface of the flange; and the second fan blade includes a fan frame and plural second vanes, and the fan frame is installed at the flange of the hub, sheathed on the hub, and installed in the retaining space, so as to achieve the effects of increasing the wind output of the fan effectively and replacing the blades conveniently.

The first electrode section (7a) and the second electrode section (7b) are formed such that the outer portion connected to the upper portion of the heating section (6) is thinner than the inner portion connected to the lower portion of the heating section (6). The heating section (6) and the first electrode section (7a) are interconnected by an R-shaped first connecting portion (21). The inner circumferential sloping surface of the heating section (6) and the second electrode section (7b) are interconnected by an R-shaped second connecting portion (22). The first and second connecting portions (21)(22) are formed such that R becomes larger from the upper end to the lower end, where the upper portion is thin and the lower portion is thick. The thickness of an intermediate portion (6b) is smaller than the thicknesses of the first and second connecting portions (21)(22).

A compressor wheel of a fluid compression device includes a wheel part, a shaft part and a plurality of connection parts. The wheel part includes a main body formed with a through hole, and a plurality of blades protruded from an outer side of the main body. The shaft part is accommodated in the through hole and configured to connect to a rotor shaft. The plurality of connection parts is connected between an inner side of the main body and the shaft part. Wherein, a fluid passage is formed between the inner side of the main body and the shaft part to allow fluid to flow to a rear side of the compressor wheel from a front side of the compressor wheel via the fluid passage.

An engine assembly includes a crankcase, shaft, blower housing, and cooling fan. The shaft is rotatably coupled to the crankcase and defines a rotational axis. The blower housing includes an internal space. The cooling fan is disposed within the internal space, includes a plate defining an upper surface, and is positioned to rotate with the shaft about the rotational axis. The cooling fan includes a band having an inner band radius and an outer band radius. The cooling fan includes a plurality of reversed fins extending between the band and the upper surface and between a root adjacent to the rotational axis and a tip adjacent to the outer band radius, each fin offset at an angle measured in a counterclockwise direction from a plane passing through the rotational axis and the tip to a plane passing through the root and the tip when viewed from above the cooling fan.

A fan assembly that includes a fan, which has a fan member with a hub and a plurality of fan blades, and an electric motor with a rotor and a stator. The hub is rotatable about an axis and has a front wall and a circumferentially extending wall that cooperate to form a rotor cavity. The rotor has a plurality of first coupling features and a plurality of first snap-fit features formed thereon. The hub has a plurality of second coupling features and a plurality of second snap-fit features formed thereon. The first and second coupling features engage one another to couple the rotor to the hub in a manner that inhibits relative rotation but which permits relative axial movement along the axis. The first and second snap-fit features engage one another to inhibit the rotor from being withdrawn from the rotor cavity.

The invention refers to a fan system (10) comprising a fan shroud (14) and a ring fan (12) having a hub (30), a plurality of fan blades (32), and a ring structure (34). The ring structure (34) has a ring member (46) and a flange member (48), the ring member (46) having a hollow cylindrical shape, the flange member (48) extending radially outwardly from the ring member (46). The fan shroud (14) has an annular shroud flange (54), a shroud body (56) and a plurality of shroud guide vanes (58), the shroud flange (54) extending radially outwardly from the shroud body (56) and being disposed along the rotary axis (A) between the flange member (48) and the shroud body (56), the shroud body (56) being disposed about the ring member (46) and having a first body portion (70), a second body portion (72) and a divergent nozzle (74). A recirculation throttle (88) is formed by the shroud body (56) and the ring member (46) at a location where the first and second body portions (70, 72) of the shroud body (56) intersect one another. The divergent nozzle (74) and a trailing end (50) of the ring member (46) cooperate to form a dynamic sealing feature (90).

Provided in embodiments of the present disclosure are a fan blade assembly and a fan apparatus. The fan blade assembly includes: a primary fan blade, where multiple first blades circumferentially provided are arranged on the primary fan blade; an auxiliary fan blade arranged coaxial and adjacent to the primary fan blade, where multiple second blades circumferentially provided are arranged on the auxiliary fan blade, an air inlet direction of the auxiliary fan blade is an axial direction, an air outlet direction of the auxiliary fan blade is a radial direction, and the first blades and the second blades have different torsion directions; and an motor arranged on one side of the auxiliary fan blade away from the primary fan blade, where the primary fan blade has a maximum outer diameter greater than an outer diameter of the auxiliary fan blade. According to the embodiment of the present disclosure.

A compressor bleed apparatus includes: a compressor comprising one or more rotors mounted for rotation about a central axis and enclosed in a compressor casing; a bleed slot passing through the compressor casing; an outer wall defining, in cooperation with the compressor casing, a plenum surrounding the compressor casing; at least one offtake pipe communicating with the plenum; and wherein at least one of the plenum and the bleed slot has a non-axisymmetric structure.

Methods and apparatus are provided for an axi-centrifugal compressor in a gas turbine engine for a business aviation or rotorcraft propulsion unit. The compressor includes an axial compressor section operable to affect a first pressure ratio along the flow path between a compressor inlet and a first section exit, and a centrifugal compressor section operable to affect a second pressure ratio along the flow path between a second section inlet and the compressor exit. The pressure rise across the axial and centrifugal compressor section is configured to have a tuning factor is in a range between 2.8 and 4.5 and a loading factor in a range between 0.6 and 0.8.

A centrifugal compressor assembly for use in a turbine engine is provided. The assembly includes an impeller that includes a plurality of rotor blades. The assembly also includes a stationary assembly circumscribing the impeller such that a clearance is defined therebetween. The stationary assembly includes at least one articulating seal member positioned adjacent the plurality of rotor blades, and a biasing mechanism configured to cause the at least one articulating seal member to selectively translate relative to the plurality of rotor blades based on an operating condition of the turbine engine.