A motor assembly having a rotational axis includes a motor housing comprising a plurality of cooling openings extending therethrough and defining a chamber. The motor assembly also includes a stator fixedly coupled to the motor housing and positioned within the chamber. A rotor is coupled to at least one of the motor housing and the stator, wherein the rotor is configured to rotate about the axis and is positioned within the chamber. The motor assembly includes a fan having a first inlet side on a first axial side of the fan and a second inlet side on a second, opposing, axial side of the fan. The fan is configured to draw cooling air in a first direction through the at least one cooling opening into the first inlet side, and the fan is also configured to draw cooling air in a second, opposite direction into the second inlet side.

Discharge grate intended to be mounted inside or at the outlet of a conduit of a discharge valve of a turbine engine of an aircraft, the discharge grate comprising an upstream face intended to receive a gas flow, a downstream face parallel to the upstream face and intended to deliver the gas flow received on the upstream face, and orifices passing through the perforated plate from the upstream face to the downstream face and intended to convey the gas flow through the perforated plate. The discharge grate comprises for each orifice of the perforated plate a tubular channel, coaxial with the orifice with which it is associated, and projecting from the downstream face of the perforated plate.

An exemplary gas turbine engine includes a fan section including a fan rotor and at least one fan blade. A fan pressure ratio across the at least one fan blade is less than 1.45, noninclusive of the pressure across any fan exit guide vane system. The engine further includes a low-pressure compressor having a low-pressure compressor rotor that rotates together with the fan rotor at a common speed in operation, and a geared architecture that drives the low-pressure compressor rotor and the fan rotor. The geared architecture has a gear reduction ratio of greater than 2.5. The engine further includes a high-pressure compressor having a pressure ratio greater than 20, a low-pressure turbine having a pressure ratio greater than 5, and a bypass ratio greater than 10.

An air moving device includes a housing member, an impeller assembly, and a nozzle assembly. The nozzle assembly can include one or more angled vanes set an angle with respect to a central axis of the air moving device. The air moving device can output a column of moving air having an oblong and/or rectangular cross-section. A dispersion pattern of the column of moving air upon the floor of an enclosure in which the air moving device is installed can have an oblong and/or rectangular shape. The dimensions of the dispersion pattern may be varied by moving the air moving device toward or away from the floor, and/or by changing the angles of the stator vanes within the nozzle assembly.

A fan and an electronic device are provided. The fan includes a hub, an outer frame surrounding the hub, and a plurality of blades connected between the hub and the outer frame. The outer frame includes a first side facing an air inlet of the fan, a second side facing an air outlet of the fan, and an inner wall between the first side and the second side. Each of the plurality of blades includes a first end connected to the hub and a second end connected to the outer frame. The second end includes a first region and a second region, the second region is connected to the inner wall. The first region extends from the second region and is disposed above the first side. A first notch is defined among the first regions of two adjacent blades and the first side.

A system for retaining stators and reducing air leakage in a gas turbine engine having an axis includes a stator having an inner platform, an outer platform, a low pressure side, a high pressure side, and at least one foot, and designed to turn air. The system also includes a case positioned radially outward from the stator and having at least one recess designed to interface with the at least one foot to resist movement of the stator relative to the case. The system also includes a bladder positioned between the outer platform of the stator and the case and designed to receive pressurized fluid having a greater pressure than ambient pressures experienced at the low pressure side of the stator and to further resist movement of the stator relative to the case in response to receiving the pressurized fluid.

An aero-propulsion system includes a drive shaft, a low-pressure compressor, a fan shaft driving a fan, a reduction device that couples the drive shaft and the fan shaft, and an inlet channel which extends between the fan and the low-pressure compressor, the inlet having a predetermined mean radius, a ratio between a mean radius of the inlet channel and the mean radius of the low-pressure compressor, on the one hand, and the reduction ratio of the reduction mechanism, on the other hand, being less than 0.35.

The present invention relates to a blower, the blower according to an embodiment of the present invention comprising: a lower case having a suction hole formed therein through which air is introduced; an upper case arranged on the upper side of the lower case and having a discharge hole formed therein through which air is discharged; and a fan arranged in the lower case and including a plurality of blades. Each of the plurality of blades includes a plurality of airfoils respectively extending along different camber lines from one another, and a leading edge of connecting the leading ends of the plurality of airfoils. Entrance angles formed by the respective camber lines of the plurality of airfoils and the rotation directions of the blades are different from one another. Thus, due to the curved shape of the leading edge and the design of a recessed notch, a flow separating from the leading edge is reduced, and thus, there is an advantage in that air volume performance is improved.

A concealed office fan lamp is provided, which includes a stop device, a support and a fan blade. A lamp is arranged at the bottom of the support, a cavity is arranged in the support, the fan blade is electrically connected with a driving mechanism to make it rotatably arranged in the cavity, and the stop device is arranged on the support and/or the fan blade to detect the motion state of the fan blade. According to the motion state, the fan blade is stopped and hidden in the cavity. By providing a stop device on the fan lamp, the fan blade can be accurately stopped and hidden in the cavity, the person under the fan lamp cannot see the fan blade when the fan lamp stops working, making the fan lamp more beautiful as a whole.

A temperature destratification assembly can include an outer housing. An impeller can be positioned within the outer housing between the inlet and outlet of the outer housing. The impeller can have an impeller hub and a plurality of impeller blades extending radially outward from the impeller hub. The assembly can include an impeller motor configured to rotate the impeller blades about an axis of rotation. A stator can be positioned within the outer housing between the impeller and the outlet of the outer housing. The stator can include a plurality of vanes. The stator vanes can include an upstream edge at the upstream end of the stator, a first surface extending from the upstream edge to the downstream edge of the vane, and a second surface opposite the first surface and extending from the upstream edge to the downstream edge of vane. A plurality of the vanes can have a downstream edge at the outlet of the outer housing.