A compressor has an axial portion and a centrifugal portion. A disk structure is provided to support the centrifugal portion and is connected to the centrifugal portion with a rabbet joint.

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.

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 centrifugal fan that sends out in a radial direction a fluid sucked from an axial direction, includes an impeller rotatable about a center axis extending in a top-bottom direction, and a motor that rotates the impeller. The motor includes a rotor rotatable about the center axis, and a stator that faces at least a portion of the rotor in the radial direction. The impeller includes an impeller hub fixed to the rotor, centrifugal vanes disposed in a circumferential direction on a radial-direction outer side of the impeller hub, and axial flow vanes disposed in the circumferential direction on a radial-direction inner side of the impeller hub. The axial flow vanes are disposed on an axial-direction upper side of the stator.

The invention discloses a high-transmission-ratio suspension shaft centrifugal supercharger which comprises a transmission unit, a fan supercharging unit and a cooling unit; the transmission unit is composed of a belt wheel, a planetary gear mechanism, a friction wheel group and a suspension mainshaft, the planetary gear mechanism comprises a sun gear and a planetary gear both installed in a gearbox, the sun gear and the belt wheel are in coaxial installation and rotate together, the planetary gears are distributed at the periphery of the sun gear in a 120 degree symmetric way and are meshed with and follow up the sun gear; the friction wheel group comprises friction wheels arranged in a sealed box and arranged coaxially with corresponding planetary gears; the suspension mainshaft generates contact friction with surfaces of the friction wheels and is driven to rotate together with the friction wheels; the cooling unit is used to pump out high-temperature lubricating oil in the gearbox and the sealed box, and lubricating oil is returned after cooling is performed. According to the invention, the supercharger is substantially improved in transmission precision and speed increasing ratio at a high speed range, and also possesses characteristics of long safe life, convenience for mounting, good heat dispersion performance, low noise and the like.

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.

An impeller includes a fan frame, a hub, a plurality of axial blades and a plurality of wind guiding blades. The fan frame has a wind inlet, a wind outlet and an inner ring-shaped oblique surface, wherein the wind inlet is opposite to the wind outlet, and the inner ring-shaped oblique surface is formed at an inner side wall of the fan frame and adjacent to the wind inlet. The hub is disposed in the fan frame. The axial blades are connected to the inner side wall of the fan frame and the hub. The wind guiding blades protrude from the inner ring-shaped oblique surface.

A blisk fan is provided for a turbine engine propulsion system. The blisk fan includes a hub configured to rotate about a rotational axis at a maximum rotational speed, and a plurality of blades extending radially outward from the hub to define a fan leading edge tip diameter. Each of the blades has a first vibratory mode at a natural frequency, which is greater than a first fan order and less than a second fan order at the maximum rotational speed. The compression system preferably has a balance factor of the compression system between 1.9 and 3.2.

An intermediate case (IMC) for use in a compressor section of a gas turbine engine includes a bleed duct and an IMC centerbody. The bleed duct is formed via sand casting. The IMC centerbody is formed via investment casting and is fixedly attached to the bleed duct.

A propeller having a plurality of blades extending radially outward from a hub, the blades forming a loop. Each loop having an intake portion, an exhaust portion and a tip portion extending radially outward from the hub and a gap between the intake root and the exhaust root. The tip portion of each of the blades is 30%-75% of the blade, the tip portion beginning at a first deviation from zero of the roll value and extending to 90 degrees, wherein roll value is zero in a plane parallel to the hub axis, and wherein the blades have a vertical angle between ?45 degrees and 45 degrees throughout.