The variable pitch propeller assembly includes a hub. The variable pitch propeller assembly also includes a plurality of propeller blade assemblies spaced circumferentially about the hub. Each of the plurality of propeller blade assemblies configured to rotate a respective propeller blade. The variable pitch propeller assembly also includes a hydraulic fluid port assembly integrally formed and including at least three hydraulic fluid ports configured to receive respective flows of hydraulic fluid from a stationary hydraulic fluid transfer sleeve. The variable pitch propeller assembly also includes a pitch actuator assembly coupled in flow communication with at least three hydraulic fluid ports through respective hydraulic fluid transfer tubes. The pitch actuator coupled to the plurality of propeller blade assemblies to selectively control a pitch of the propeller blades. The pitch actuator assembly includes a travel stop configured to limit a rotation of at least one of the pitch actuator assemblies.

A fan module for an aircraft turbine engine, the module including a fan having variable-pitch blades and an oil transfer device for transferring oil between a stator and a rotor, the device including a stator ring having a cylindrical inner surface and internal oil ducts and a shaft engaged in the ring and having a cylindrical outer surface and internal oil ducts; the device includes a plain bearing located between said cylindrical inner surface and the cylindrical outer surface and defined by a single band; and rolling bearings mounted between the ring and the shaft, on either side of the plain bearing, each of these rolling bearings having one of the rings thereof integrated in one of the elements selected from the ring and the shaft.

The invention relates to a fan assembly having a rotatingly driven hub (7) and fan blades (10) which can be pivoted relative to the hub body (29). The fan blades (10) are adjusted by means of a linear drive in the form of a spindle drive (13) or a piston drive (52).

A gas turbine engine includes a core turbine engine and a fan mechanically coupled to the core turbine engine. The fan includes a plurality of fan blades, each fan blade defining a base and an inner end along a radial direction of the gas turbine engine. The fan also includes a hub covering the base of each of the plurality of fan blades. Further, the fan includes one or more bearings for supporting rotation of the plurality of fan blades. The one or more bearings define a fan bearing radius along a radial direction of the gas turbine engine. Similarly, the hub defines a hub radius along the radial direction of the gas turbine engine. The ratio of the hub radius to the fan bearing radius is less than about three, providing for desired packaging of the various components within the fan of the gas turbine engine.

A pitch change mechanism for a bladed rotor includes a driving sleeve, a drive shaft, a first pitch-changing element, a second pitch-changing element, and a plurality of blade drive gears. The driving sleeve has, in axial sequence, a first helical connection portion and a second helical connection portion. The driving sleeve is positioned concentrically with and surrounding the drive shaft. The first pitch-changing element has a first end drivingly engaged with the first helical connection portion, and a first ring gear portion at a second opposite end, while the second pitch-changing element has a first end drivingly engaged with the second helical connection portion, and a second ring gear portion at a second opposite end. The plurality of blade drive gears are arranged in a circumferential array around a longitudinal axis of the drive shaft.

A fan blade is mounted on a shaft or arranged to vary in pitch via rotation about a pitching axis. The fan blade is mounted with a center of mass offset from the shaft or pitching axis. This offset reduces torque around the shaft or pitching axis.

A fan is disclosed. The fan includes a base mountable to a ceiling; a base motor contained in the base; a multi-section shaft operably connected to the base motor and moveable between a collapsed position and an extended position; and a fan assembly connected to the multi-section shaft and including a fan motor and at least one fan blade operably connected to the fan motor, wherein in response to a signal, the base motor raises or lowers the fan assembly by moving the multi-section shaft between the collapsed position and the extended position

A fan of a turbine engine, the fan including a fan disk provided with blades on its periphery, the blades being pivotally mounted on the disk around a pivoting axis and having a center of gravity, and a pitch change mechanism for the blades, each blade being configured so that its center of gravity is positioned on or at a small distance from a fictitious plane which passes through the pivoting axis of the blade and which is perpendicular to the axis of revolution of the fan when the blade is in a minimum drag position.

Apparatus for actuating and controlling the rotation, about their longitudinal axis (Y-Y), of blades (20) of cooling fans (10) for operating machines and/or vehicles, in particular agricultural tractors and off-road vehicles, said fan being mounted on a hub (11) which can be rotationally driven about its axis (X-X) by associated driving means (3,3a) suitable for connection to the heat engine (1) and mounted on a fixed support (5) by means of a bearing (3b) the apparatus comprising a ring (71) provided with a radial seat (71a) inside which a radial pin (72), eccentrically engaged in a base (73) integral with the shank (20a) of the blade (20), is inserted; an electric motor (30) which is coaxial with the axis (X-X) of the hub (11) and the shaft (31) of which is coaxially connected to a reduction gear (40), the kinematic output element (143) of which is coaxially connected by means of a screw (51a)/female thread (76a) coupling to a slider (76) displaceable in both directions along the axis (X-X) and kinematically connected to the ring (71) with an eccentric pin (72) driving the base (73) of the shank of the blade, an electromagnetic clutch (80; 180; 280) being arranged between the pulley (3) and the hub (11) of the fan.

A system for controlling a variable orientation vane of a turbomachine compressor, for example a low-pressure compressor of a turbojet engine. Such a vane is also known as a variable stator vane. The system comprises a support, an orientable vane that is movable in rotation relative to the support and that comprises a lever for controlling the orientation of the orientable vane (26), and a magnetic field source that defines an air gap with the lever. When the source is powered electrically, it forms an electromagnet attracting the lever by induction such that the orientable vane changes orientation.