A set of turbomachine guide vanes including plural vanes arranged around an annulus, each vane having a leading edge extending between root and tip ends, the leading edge offset between these two ends being greater than 10% of the blade height. A tangential stacking of the guide vanes towards the suction face side, the curve of tangential stacking, of the position, in the direction tangential to the annulus, of centers of gravity of successive vane cross sections along the vane height, is a curve that increases constantly towards the suction face side. The curve, near the vane tip end, has an accentuated gradient towards the suction face side compared with the rest of the curve, and has a mean gradient near the vane tip end that is greater than at least 1.2 times the mean gradient of the curve over the portion between 30% and 90% of the vane height.

A ceiling fan or ceiling fan includes a body defining an interior passage having an inlet and an outlet provided on the body. The inlet, outlet, and interior passage can be annular. An impeller is mounted within the interior passage and driven by a motor mounted within the body to draw a volume of air through the interior passage from the inlet to the outlet. A deflector is provided within the body and extending through the outlet including an upper angled surface and a lower angled surface to direct the air in a generally upward or generally downward direction, respectively.

A composite material guide vane for a gas turbine engine, the composite material including fiber reinforcement densified by a matrix, the fiber reinforcement being formed as a single piece by three-dimensional weaving and including an airfoil and at least two fastener flanges extending from a radial end of the vane towards opposite side faces of the airfoil, the fastener flanges being axially offset from each other.

In an operation using a blow operation device driven by an electric motor, fatigue in the arm of an operator is reduced. A blow operation device includes a backpack type frame, a battery attached to the frame, a blower body having an electric motor to which power is fed from the battery and having an axial fan driven by the electric motor, and a blower tube connected to a blow side of the blower body, the blower body being supported pivotally on the frame to be rockable vertically and horizontally.

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.

An actuator system including a harmonic drive operable to drive a variable vane system of a gas turbine engine.

An actuator system including a harmonic drive operable to drive a variable vane system of a gas turbine engine.

A thrust generating apparatus for controlling an attitude of a movable body includes an outer shell body, a first inner shell body and a second inner shell body, a first fan rotating body and a second fan rotating body, an intermediate shell body, and a driving unit. A outer surface of the intermediate shell body has a shape such that an air flow sent from an opening end inside of any one of the first inner shell body and the second inner shell body is accommodated and flowed out to an outer flow path . When the first fan rotating body is rotated, the air flow suctioned from the outside in the axial direction of the first inner shell body passes through the outer flow path defined by the second inner shell body to be jetted from a second opening end of the outer shell body.

An airfoil for a turbomachine such as a gas turbine engine includes a pressure side and a suction side, a flow-distributing forward wall and an inner cooling wall. A switchbacked passage extends through the airfoil, and the flow-distributing forward wall has a plurality of jetting orifices formed therein and connecting the switchbacked passage to a forward cavity. The jetting orifices are oriented to produce wall jets of cooling fluid directed in an upstream direction toward a back side of the leading edge. A second passage extends between the forward cavity and outlets of the airfoil, so as to convey cooling fluid in a downstream direction toward the outlets.

A fan includes a stationary portion, a rotating portion, and an impeller arranged to rotate about a central axis together with the rotating portion to produce an axial air current. The rotating portion includes a rotor holder. The impeller includes a cup portion arranged to cover the rotor holder and a plurality of blades arranged on an outer circumference of the cup portion. The cup portion includes a cup cover portion arranged to extend radially outward from the central axis; a cup cylindrical portion being substantially cylindrical in shape, and arranged to extend in an axial direction from an outer edge portion of the cup cover portion; and a cup through hole arranged to extend through the cup portion at a position overlapping with a portion or boundary between the cup cover portion and the cup cylindrical portion.