A radial control shaft for a device for controlling the pitch of fan blades of a turbine engine having an unducted fan, is disclosed. The shaft includes an external portion that is designed to be mounted in the control device from its outside and to be coupled to at least one fan blade in order to adjust its pitch, and an internal portion, independent of the external portion, that is designed to be mounted from the inside of the control device, to be connected to a load transfer bearing in order to pivot the shaft about a radial axis, and to close an oil enclosure in which the bearing is housed, the external and internal portions of the shaft being coupled to each other. A method of mounting such a shaft and a control device including such a shaft are also disclosed.

An after-fan system for a gas turbine engine includes a variable pitch fan exit guide vane array. An after-fan turbine downstream of the variable pitch fan exit guide vane array and a control operable to vary a pitch of the variable fan exit guide vane array. A method of generating thrust for a gas turbine engine includes rotating a fan section with an array of fan blades; rotating an after-fan turbine downstream of the fan section; and varying a pitch of a variable fan exit guide vane array downstream of the fan section and upstream of the after-fan turbine.

A system for controlling the pitch setting of a propeller blade for an aircraft turbine engine is provided. The system generally including a blade having an airfoil connected to a root; a cup having an annular wall extending about a pitch axis of the blade and a lower axial end enclosed by a bottom wall; a locking ring that extends around the root and inside the cup; a safety element that ensures the retention of the root relative to the cup. The at least one safety element can have a generally elongate shape and can pass through aligned holes in the bottom wall of the cup and in the free end of the root.

A gas turbine engine includes a turbomachine comprising a compressor section, a combustion section, and a turbine section arranged in serial flow order; a fan defining a fan axis and comprising a plurality of fan blades rotatable about the fan axis; and a pitch change mechanism operable with the plurality of fan blades to control a pitch of the plurality of fan blades. The pitch change mechanism imparts a torque to each fan blade of the plurality of fan blades via first and second forces imparted in opposite directions to each fan blade of the plurality of fan blades.

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 system having a variable diameter impeller device that is operable for reducing an energy consumption of a rotating fluid or gas pump by increasing said impeller diameter as a speed of said rotating fluid or gas pump increases and decreasing the impeller diameter as the speed decreases. An extendable vane mechanism is configured to move along an elongated curved or sloping slot, said movement along the elongated curved or sloping slot is operable for increasing and decreasing a diameter of the impeller device. A spring mechanism having a first end and a second end extends and retracts to dynamically increase or decrease a diameter of the impeller device.

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.

An assembly for an aircraft turbine engine is provided. The assembly generally includes an un-ducted propeller blade of which the root has a bulbous portion; a system for setting the pitch of the blade about a pitch setting axis, the pitch setting system including a cup, configured to be placed inside the outer casing, has a flared open top end for axial insertion of the root and in which the root of the blade can be axially affixed by a locking member; and at least one radial retention prong in a radial space reserved between the wall of the cup and the root.

Fan module for an aircraft turbine engine, the module including a fan having variable-pitch blades and an oil-transfer device configured to transfer oil between a stator and a rotor. The device includes a stator ring having internal oil ducts, a shaft engaged in the ring and having internal oil ducts, and a plain bearing and rolling bearings which are mounted between the ring and the shaft, the ring including first fluidic-connection ports which are configured to cooperate by male-female engagement with ends of oil-supply sockets during blind assembly of the device by axial translation downstream of the device as a whole.