A fan module for an aircraft turbine engine includes a fan with a fan shaft and variable-pitch fan blades. The fan module further includes an oil transfer device transfers oil between a stator and an actuator that controls the pitch of the fan blades the device includes a stator ring having an inner cylindrical surface and internal oil ducts, each of which opens onto the inner cylindrical surface. A shaft is engaged in the stator ring and rotates about an axis inside the ring. The shaft includes an outer cylindrical surface extending inside said inner cylindrical surface. The shaft has internal oil ducts, each of which opens onto said outer cylindrical surface A rolling bearing is mounted between the ring and the shaft, on each side of the plain bearing.

An automatic folding blade type fan mounting frame structure includes a main machine, wherein the main machine is provided with a fan blade mounting frame. The fan blade mounting frame is provided with at least two mounting holes, and fan blade assemblies are arranged on the mounting holes of the fan blade mounting frame. The fan blade assembly includes blades. The fan blade mounting frame is provided with a folding structure. Tie rods are arranged between two adjacent fan blade assemblies. The fan blade mounting frame is provided with reinforcing convex ribs between two adjacent mounting holes. This fan structure improves the structural strength of the product and reduces frame deformation.

The invention discloses a ceiling fan lamp with concealed fan blades, comprising a base plate, an upper motor cover, fan blade reset mechanisms, fan blades and tension springs, wherein a turnplate is fixed on an upper surface of the base plate, and a motor assembly connected to the turnplate is disposed inside the upper motor cover; a fan blade fixed disc, of which a periphery is fastened with the fan blades, is disposed on the turnplate, and a rotary stop plate having arc-shaped grooves thereon is rotationally disposed on the fan blade fixed disc; the fan blade reset mechanisms are matched with and connected to the fan blade fixed disc and the rotary stop plate respectively, and both ends of each tension spring are connected to the turnplate and the rotary stop plate respectively.

A method for reducing the noise level generated by a fan of a turbomachine including a plurality of vanes, said method further including, when the turbomachine is operating and under given flight conditions, the following steps measuring an operational pitch angle for each of the vanes, calculating an offset between the operational pitch angle of each of the vanes and a predetermined reference pitch angle for the given flight conditions so as to produce a controlled noise level at multiple rotation frequencies of the fan, correcting the orientation of the vanes so as to compensate their operational pitch angles depending on the offsets thus calculated.

A fan assembly includes two or more axial flow fans rotatably mounted on a support structure. The fans are of the adjustable pitch type, i.e., each fan includes a pitch adjustment mechanism that is actuatable by axially shifting a positioning rod extending outward from the hub of the fan. The assembly further includes a control member and a plurality of adjustment mechanisms coupled respectively to the positioning rods and to the control member in such a way that the position of the control member determines the axial position of the positioning rods and thereby the pitch of the blades of all the fans of the assembly. A single actuator is configured to actuate a movement of the control member.

A system is described that includes a turbine engine including an engine fan including one or more variable-pitch blades driven by a shaft, which rotates at a rotational speed which depends on a pitch of the one or more variable-pitch blades of the engine fan. The system further includes a generator configured to produce alternating-current (AC) electricity at a particular frequency relative to the rotational speed of the shaft. The system also includes a propulsor, which includes a propulsor motor and a propulsor fan. The propulsor motor is configured to drive, based on the AC electricity produced by the generator, the propulsor fan. The system includes a controller configured to control the particular frequency of the AC electricity by at least controlling the pitch of the one or more variable-pitch blades of the engine fan and thereby the rotational speed of the generator.

Propulsion assembly comprising: an inner casing (13); an outer casing (3); an inter-duct casing (15) delimiting a primary duct (12) between the inner casing (13) and an outer wall (14), and a secondary duct (16) between the outer casing (3) and an outer wall (17); a fan capable of generating an air flow (24) circulating from downstream to upstream in the secondary duct (16); the assembly further comprising: at least one duct (27) for bleeding air from said flow (24), this bleed duct (27) comprising an inlet port (28) in the outer wall (17) and an outlet port (29) in the inner wall (14); an outer flap (30) movable between an open position and a closed position of the inlet port (28); an inner flap (31) movable between an open position and a closed position of the outlet port (29).

A ceiling fan capable of adjusting angles of fan blades includes a hub, a downrod, a rotating motor selectively driving the hub to rotate relative to the downrod, multiple blade assemblies separately mounted on and arranged around the hub, and an adjusting assembly mounted in the hub and including an outer tube, an inner tube, a support, and a driving motor. A driving rod of each of the blade assemblies is mounted in a driving annular recess of the support. When a driving screw of the driving motor rotates, the driving screw drives the outer tube to rotate and drives the inner tube to move upwardly or downwardly accordingly, so as to provide an optimized volume of air current that meets power saving requirement under a constant revolution speed of the rotating motor.

A system is disclosed for measuring displacement of a regulation system for a variable pitch axial fan. The system includes a hub having a plurality of adjustable pitch fan blades. A hydraulic cylinder is connected to the hub. A piston is disposed within the hydraulic cylinder. The piston is coupled to a piston shaft that is axially movable with respect to the hub. The piston shaft is coupled to an actuation assembly for adjusting the pitch of the plurality of adjustable pitch fan blades in response to an axial movement of the piston. A rotating oil union includes a housing and an interior element, the interior element coupled to the hydraulic cylinder so that rotation of the cylinder and the hub causes rotation of the interior element. The rotating oil union includes a static housing and a central probe fixed to the static housing. The central probe extends through respective openings in the interior element, the hydraulic cylinder, and the piston. The central probe is configured to sense an axial position of the piston and to generate a signal representative of said axial position. A method for using the system is also disclosed.

A turboprop control system 10 for use with a turboprop 2 having a turbine engine 12 operably coupled to and rotationally driving a propeller 14 having variable pitch blades 16 to control the engine speed, propeller speed, and propeller pitch. The pilot provides, by a single power control lever 30, the control input used to control the engine and propeller.