A variable vane fluid system is disclosed with variable stator vanes and a unison actuation structure supported for movement about a longitudinal axis between a first rotational position and a second rotational position to coincidentally rotate the plurality of vanes. The unison actuation structure has a projection. The variable vane fluid system further includes an elongate linkage member having a first portion connected to a stator vane and a second portion with an aperture that receives the projection. The aperture includes an inner surface with a tapered inner surface profile to allow the projection to tilt within the aperture as the unison actuation structure rotates between the first rotational position and the second rotational position.

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 fan assembly includes a hub including a cylindrical portion having an inlet end and an outlet end, the hub further including an inlet surface coupled to the inlet end. The fan assembly also includes a plurality of blades coupled to an outer periphery of the cylindrical portion, wherein the inlet surface is tapered to direct an inlet airflow toward the plurality of blades.

A blower, comprises a blower body, accommodating therein a fan and an electric motor driving the fan to rotate. A rotation shaft of the fan defines a longitudinal axis. A blow pipe is removably attached to the blower body. A tapered member is provided between the electric motor and an air inlet of the blower body, the tapered member gradually narrowing toward the air inlet.

A rotor includes: a hub; and a plurality of blades disposed on the hub. Each of the plurality of blades includes a suction surface, a pressure surface, a leading edge, a trailing edge, a tip-side edge, and a hub-side edge. In a cross-section of each blade at a given chord position between the leading edge and the trailing edge, an angle of at least one of the suction surface or the pressure surface with respect to a blade height direction of the blade increases in a direction from the hub-side edge to the tip-side edge over a region from the hub-side edge to the tip-side edge, in at least a range from the leading edge to a chord position away from the leading edge toward the trailing edge.

A turbine shaft used for a turbocharger including a turbine and a compressor includes a turbine impeller, and a rotor shaft joined on one end side to the turbine impeller. The rotor shaft includes a fitting region configured to fit with a compressor impeller of the compressor by inserting the other end side of the rotor shaft into a through hole formed in the compressor impeller, a fastening region formed between the fitting region and the other end side of the rotor shaft, and configured to allow fastening by a fastening part, and a tapered part having a maximum outer diameter at a position closest to the turbine impeller in the fitting region and formed such that an outer diameter of the rotor shaft decreases from the position closest to the turbine impeller toward a tip side of the compressor impeller.

A gas turbine engine blade according to an example of the present disclosure includes a blade including internal walls defining a blade cooling passage and a tip section at a radially outer end of the blade. The tip section includes a pocket protruding into the tip section from a radially outermost end of the tip section to a pocket floor. The blade further includes a pocket wall defined between the pocket floor and the radially outermost end of the tip section and including a tapered wall cooling passage.

A ceiling fan or similar air-moving device can include a motor for rotating one or more blades to drive a volume of air about a space. The blade can include a body having an outer surface with a flat top surface and a flat bottom surface, and a side edge. A curved transition can extend between one of the flat top surface or the flat bottom surface, and the side edge. The curved transition can include an elliptical curvature.

An assembly of turbine blades or vanes includes a first and a second airfoil extending span-wise from a first and a second platform respectively. The first and the second platform respectively have a first and a second mate face that interface along a platform splitline. The first mate face is proximal to a suction side of the first airfoil the second mate face is proximal to a pressure side of the second airfoil. The first mate face is chamfered or filleted along an aft portion thereof. The chamfered or filleted portion of the first mate face lies in a region in a flow path between the first and second airfoils where a mean velocity of the working medium is directed from the second platform to the first platform.

A turbine includes a stator and a movable rotor, rotating around an axis, in relation to the stator. The rotor comprises at least one disc, the radially outer periphery of which comprises cavities. The rotor further includes blades, each having a blade root axially engaged in a cavity of the disc so as to radially hold the blade on the disc. At least one of the blade roots has an axially flaring shape, with the corresponding cavity having a matching shape so as to axially lock the blade root in the cavity in a first axially oriented direction. Locking means lock the blade root in the cavity in a second axially oriented direction, opposite the first direction.

A turbine rotor blade includes a blade body including a pressure-side blade wall and a suction-side blade wall. The blade body includes: a serpentine passage composed of a cooling passage separated into a plurality of parts by a partition wall that connects the pressure-side blade wall and the suction-side blade wall and extends along a height direction of the blade body; and a first cooling hole communicating at one end with the cooling passage via a first inlet opening formed in an inner wall surface of the pressure-side blade wall or the suction-side blade wall, and communicating at another end with a first outlet opening formed in an outer wall surface of the pressure-side blade wall or the suction-side blade wall of the blade body. The first cooling hole extends in a leading edge direction from the first inlet opening to the first outlet opening.