The invention concerns a device (1) for controlling the pitch of the blades of a fan (4) rotor (3), comprising a radial shaft (6) linked to the blade, a connection rod (8) of which the axial movement controls the rotation of the radial shaft (6), characterized in that it comprises:a first part (10) that is mobile in rotation with the rotor (3) about the axis (11) of the fan (4), and on which one end of each connection rod (8) is secured,a second part (12) linked to the first part (10), andat least three cylinders (14) capable of moving said second part (12) in axial translation, and of varying the tilt of said second part, the translation and tilt of the second part (12) driving a corresponding translation and tilt of the first part (10), such that, when the first part (10) rotates, each connection rod (8) is subject to axial displacement of which the amplitude is variable and is a function of the tilt of the first part (10), making it possible to vary the pitch of the blade during the rotation of same. The invention also concerns a fan, and a method for controlling the pitch of blades.

A variable pitch fan for gas turbine engine is provided. The variable pitch fan includes a plurality of fan blades rotatably coupled to a disk and an actuation assembly for changing a pitch of each of the plurality of fan blades. The actuation assembly generally includes an actuation member operably connected to at least one of the plurality of fan blades and a pin. The pin is movable between a first position in which the pin is positioned at least partially in a channel defined in the actuation member, and a second position. The pin blocks movement of the actuation member relative to the pin past a range defined by the channel when in the first position. The actuation assembly further includes a retraction system for selectively engaging the pin in moving the pin from the first position to the second position.

Turbojet engine fan module wheel, including a plurality of blades made of composite material, each blade having a root assembled with a base distinct from the bases of the other blades, each base having a groove extending axially and opening out on the side of the upstream face and on the side of the downstream face, each root cooperating by axial interlocking in a form-fitting manner, for example in the shape of a dovetail, with the groove of the base, whereby the root is retained on the base along the radial and circumferential directions, and each base cooperates with at least one part configured to axially block the root within the groove of the base, whereby the root is retained along the axial direction.

Module for mounting a turbomachine fan blade, including: a blade force take-up device, a blade support able to pivot about a radial axis and configured to be engaged axially inside the device, the support and the device being mutually configured to ensure a clamping of the support against the device and an axial retention of the support inside the device; the support and the device each including, on their respective surfaces in cooperation, an alternation of conical seats and recesses making it possible alternatively, on the one hand, when the recesses of one surface are in geometric correspondence with the seats of the other surface, to axially slide the support relative to the device, and on the other hand, when the seats of both surfaces are in geometric correspondence with each other, to prevent any axial sliding movement of the support relative to the device.

Turbojet engine fan module wheel, including a plurality of blades made of composite material, each blade having a root assembled with a base distinct from the bases of the other blades, each base having a groove extending axially and opening out on the side of the upstream face and on the side of the downstream face, each root cooperating by axial interlocking in a form-fitting manner, for example in the shape of a dovetail, with the groove of the base, whereby the root is retained on the base along the radial and circumferential directions, and each base cooperates with at least one part configured to axially block the root within the groove of the base, whereby the root is retained along the axial direction.

A module having a longitudinal axis, a hydraulic actuator, and a pump for supplying the hydraulic actuator with fluid, the pump can include axial pistons intended to be movable to rotate about the longitudinal axis and configured to transfer the fluid to the hydraulic actuator, a connecting plate connected to the axial pistons and engaging with an annular main plate centered on the longitudinal axis intended to be rotated about the longitudinal axis and tilted relative to the longitudinal axis, the connecting plate being arranged between the main plate and the axial pistons, the axial pistons being movable to rotate in a direction parallel to the longitudinal axis, the tilting of the main plate resulting in the movement of the axial pistons in the direction.

A module having a longitudinal axis, a hydraulic actuator, and a pump for supplying the hydraulic actuator with fluid, the pump can include axial pistons intended to be movable to rotate about the longitudinal axis and configured to transfer the fluid to the hydraulic actuator, a connecting plate connected to the axial pistons and engaging with an annular main plate centered on the longitudinal axis intended to be rotated about the longitudinal axis and tilted relative to the longitudinal axis, the connecting plate being arranged between the main plate and the axial pistons, the axial pistons being movable to rotate in a direction parallel to the longitudinal axis, the tilting of the main plate resulting in the movement of the axial pistons in the direction.

A propeller propulsion system includes: a prime mover having at least one spool, a propeller arranged to be driven by the spool, a pitch adjustment subsystem comprising an electronic control unit and an electronic protection unit, a prime mover speed sensor arranged to detect a rotation speed of the spool; and an additional speed sensor arranged to detect the rotation speed of the spool or arranged to detect a rotation speed of the propeller. A first of the electronic control unit and the electronic protection unit is arranged to use an output from the prime mover speed sensor to determine the rotation speed of the propeller; and a second of the electronic control unit and the electronic protection unit is arranged to use an output from the additional speed sensor to determine the rotation speed of the propeller.

An aircraft propulsion system includes a rotor hub, rotor blades, a rotating frame, and a low-pressure compressor. The rotor hub is configured to rotate about a central axis. The rotor blades are arranged around the rotor hub. Each of the rotor blades is configured to rotate about a radial axis of the rotor hub. The rotating frame is positioned between the rotor hub and the plurality of rotor blades. The rotating frame is configured to allow air to pass without interference of the rotor blades. The low-pressure compressor is configured to receive the air passing through the rotating frame.

An aircraft propulsion system includes a rotor hub, rotor blades, a rotating frame, and a low-pressure compressor. The rotor hub is configured to rotate about a central axis. The rotor blades are arranged around the rotor hub. Each of the rotor blades is configured to rotate about a radial axis of the rotor hub. The rotating frame is positioned between the rotor hub and the plurality of rotor blades. The rotating frame is configured to allow air to pass without interference of the rotor blades. The low-pressure compressor is configured to receive the air passing through the rotating frame.