The invention describes a system for controlling the cyclic setting of blades (1) of a turbine engine propeller, the blades (1) being arranged in a plane normal to the axis of rotation (r) of the propeller, the system comprising: —a plate assembly (40) that can be tilted relative to the normal plane (P), —an articulation system (50) articulating the plate assembly (40) relative to the blades (1) such that tilting the plate assembly (40) modifies the setting of the blades (1), —a force sensor (5) designed to measure a force applied in the normal plane (P) by an air flow at the inlet of the propeller blades (1), —a cylinder (60) suitable for tilting the plate assembly (40) in response to a force measured by the force sensor (5).

A device for controlling the pitch of fan blades in a turbine engine having an unducted fan including at least one set of adjustable pitch fan blades, each fan blade being coupled, for pitch adjustment purposes, to a radial control shaft constrained to rotate with the set of fan blades and suitable for pivoting about a radial pitch axis of the fan blade, the device including a stationary actuator centered on a longitudinal axis of the turbine engine and driving an outer ring of a load transfer bearing in translation, the outer ring of the load transfer bearing being coupled directly to a lever arm of each control shaft via a respective ball joint connection in order to adjust its pivoting.

A lubrication system for a device located between an internal shaft and an external shaft of an aircraft turbine, that are free to rotate, concentric and arranged at least partially one around the other, is provided. The lubrication system includes an annular element provided with an external groove and being mounted integral with the external shaft, the external groove being supplied with lubricant from a fixed part of the turbine; and a grooved element mounted integral with the internal shaft, the grooved element having a relief which directs a lubricant in contact with its external surface along a longitudinal direction when the internal shaft is rotating. The external groove is in fluid communication with an external surface of the grooved element through at least two conduits arranged through the external shaft.

The test rig can be used for testing a blade pitch measurement system of a variable pitch propeller system. The test rig can include a first mount rotatably mounted to the frame and configured to receive the feedback device, a rotation motor drivingly coupled to rotate the ring mount relative to the frame around a rotation axis, a second mount configured to receive the pitch sensor, a mechanism configured for moving the second mount along an orientation parallel to the rotation axis, and a controller configured to control the rotation of the rotation motor to a variable rotation speed, and for controlling the movement of the second mount to variable positions via the mechanism.

A device for controlling pitch of fan blades of a turbine engine including an un-ducted fan, the device including: at least one set of fan blades of adjustable pitch, the set being constrained to rotate with a rotary ring centered on a longitudinal axis and mechanically connected to a turbine rotor, each blade of the set being mounted on a blade root support that is pivotally mounted on the rotary ring; and at least one radial control shaft adjusting pitch of at least two adjacent blades of the set, the control shaft being constrained to rotate with the rotary ring and being configured to pivot about an axis of the shaft, being coupled to the blade root supports of the at least two blades of the set to adjust their pitch via a transmission system including eccentrics connected together by at least one connecting rod.

The invention describes a system for controlling the cyclic setting of blades (1) of a turbine engine propeller, the blades (1) being arranged in a plane normal to the axis of rotation (r) of the propeller, the system comprising: —a plate assembly (40) that can be tilted relative to the normal plane (P), —an articulation system (50) articulating the plate assembly (40) relative to the blades (1) such that tilting the plate assembly (40) modifies the setting of the blades (1), —a force sensor (5) designed to measure a force applied in the normal plane (P) by an air flow at the inlet of the propeller blades (1), —a cylinder (60) suitable for tilting the plate assembly (40) in response to a force measured by the force sensor (5).

The present disclosure is directed to a method for controlling rotors of a rotorcraft system comprising the steps of: receiving air velocity data, first and second rotors rotational angular velocity data, external air temperature data and rotorcraft altitude data by the control module; calculating air velocity over the plurality of blades based on the received data using the control module; calculating, based on the calculated air velocity, if one or more retreating blades of one of the first and second counterrotating rotors are generating insufficient lift; and sending one or more actuation signals from the control module to the electric motor and/or actuators of the other of the first and second counterrotating rotors to maintain a predetermined amount of lift.

An aircraft turbine engine has a pair of rotating and non-ducted propellers. An upstream propeller has an outer diameter D1 and a downstream propeller has an outer diameter D2. The engine further includes a system for varying the diameter D2. The downstream propeller includes an annular row of blades, each of which is configured to be mounted telescopically in the radial direction (R) in an outer fan duct.

The invention relates to a lubrication device for a turbine engine, comprising an oil intake pipe (23) provided with a pump (24) for supplying oil and control means (25) located downstream from the supply pump (24), a supply pipe (26) intended for supplying oil to a member to be lubricated and a recirculation pipe (27), the control means (25) making it possible to direct all or part of the flow of oil from the intake pipe (23) towards the supply pipe (26) and/or towards the recirculation pipe (27), the pump (24) being driven by at least one rotary member of an accessory gearbox of the turbine engine.

An aircraft turbine engine has a pair of rotating and non-ducted propellers. An upstream propeller has an outer diameter D1 and a downstream propeller has an outer diameter D2. The engine further includes a system for varying the diameter D2. The downstream propeller includes an annular row of blades, each of which is configured to be mounted telescopically in the radial direction (R) in an outer fan duct.