A hub for a propeller having variable-pitch blades for a turbomachine with longitudinal rotation axis, including a plurality of blade platforms, each one being designed to receive a blade root, the platforms being distributed around the annular outer periphery of the hub concentrically with the longitudinal rotation axis, wherein each blade platform has the general geometric shape of a spherical cap, and wherein, between two adjacent blade platforms around the longitudinal rotation axis, the transverse dimension, in particular the diameter, of the hub can vary axially and radially.

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 aerofoil body for a gas turbine engine is provided. The aerofoil body has leading and trailing edge portions, wherein one of the leading and trailing edge portions is a morphable edge portion having a composite layer structure. The aerofoil body further has a non-morphing central portion which forms pressure and suction surfaces of the aerofoil body between the leading and trailing edge portions. The composite layer structure includes a return spring, one or more shape memory alloy layers, and a flexible cover for the return spring and the one or more shape memory alloy layers. The flexible cover defines pressure and suction surfaces of the aerofoil body at the morphable edge portion. The one or more shape memory alloy layers are electrically heatable to deform the layers against the resistance of the return spring, and thereby alter the pitch of the aerofoil body at the morphable edge portion.

A fan module with variable pitch blades for a longitudinal axis propulsion assembly. The module includes a rotor through which a rotor shaft runs along the longitudinal axis X and carries the blades of the fan. A system for changing the pitch of the blades includes a mechanism connected to the blades of the fan and a controller acting on the mechanism. The controller has a fixed body and a movable body translatable along the longitudinal axis X relative to the fixed body, and a load transfer bearing arranged between the mechanism and the controller. The fan module includes a power shaft driving the rotor shaft via an epicyclic train speed reducer, the speed reducer including a sun gear connected to the power shaft and a satellite carrier including a fixed annular ferrule secured to a fixed casing. The fixed body of the controller is mounted on the annular ferrule.

A rotary machine satisfies at least one of Dr1<Dh1Dr2 or Dc1Dt1>Dc2. Dr1, Dh1, Dr2, Dc1, Dt1, and Dc2 are distances from a rotational center axis of a hub to an upstream end of a first blade-facing surface facing a hub-side end surface of a variable blade, an upstream end of the hub-side end surface when the blade angle is maximum, a downstream end of a first outer peripheral surface adjacent to an upstream side of the blade-facing surface, an upstream end of a second blade-facing surface facing a tip-side end surface of the variable blade, an upstream end of the tip-side end surface when the blade angle is minimum, and a downstream end of a first inner peripheral surface adjacent to an upstream side of the second blade-facing surface, respectively.

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 said impeller diameter as the speed decreases. An extendable vane mechanism is configured to move along an elongated curved or sloping slot, said movement along said elongated curved or sloping slot is operable for increasing and decreasing a diameter of said 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 includes a disc provided with blades at the periphery thereof, the blades being mounted so as to pivot on the disc about a pivot axis, and a mechanism for changing the pitch of the blades. The mechanism is configured to adjust an angular position of each blade around the pivot axis. The angular position is in an angular setting range no greater than 20.

A gas turbine engine includes a fan section. A splitter is downstream of the fan section and at least partially defines a secondary flow path on a radially outer side and an inner flow path on a radially inner side. A variable pitch rotor blade assembly is located at an inlet to the inner flow path and includes a plurality of variable pitch rotor blades.

A vane assembly includes a rotatable airfoil that extends between a radially inner platform and a radially outer platform and has a leading edge and a trailing edge. A thrust projection is fixed relative to the rotatable airfoil. The thrust projection includes a first thrust surface for supporting radial loads in a first radial direction and a second thrust surface for supporting radial loads in a second direction.

A blade retainer adapted for use in a gas turbine engine is configured to block axial movement of a blade. The blade retainer includes a first brace, a second brace, and a web that extends between the first brace and the second brace.