A passive centrifugal valve for a gas turbine engine. The passive centrifugal valve includes an inner section with a flow control inlet orifice, a cantilevered valve adjacent to the flow control inlet orifice, and an outer section with a seal land geometry that operates to at least partially support the cantilevered valve in response to a first centrifugal force that deflects the cantilevered valve away from the flow control inlet orifice.

Disclosed herein is a fan module with variable pitch blades for a propulsion unit, the fan module comprising a rotor carrying the blades and comprising an inner shaft and an outer casing defining between them a space, a control device for controlling the pitch of the blades, and a feathering device for feathering the blades. The rotation of the rotor is guided by a bearing, and the module further comprises means for recovering and guiding a liquid lubricant of the bearing, with the recovery and guidance means being configured to recover and guide said lubricant from an axial upstream end of the casing, axially from upstream to downstream and radially from the inside to the outside, under the centrifugal effect.

The invention relates to a method for controlling the speed and the power of a turbine engine propeller, wherein at least two operating modes are implemented: one operating mode, called speed mode, in which the pitch () of the propeller is controlled as a function of the desired propeller speed, while the fuel flow is controlled as a function of the desired torque; the other operating mode, called mode, in which the fuel flow is controlled as a function of the desired propeller speed, the pitch () of the propeller being set to a limit angle (min) that limits the pitch of the propeller in the two operating modes, the pitch angle (min(t)) being continuously computed and updated during a flight on the basis of parameters relating to the flight conditions estimated in real time.

A bistable pitch propeller includes a ball, a spring, and a clutch module where the clutch module has a range of rotational movement between a locked end position and a released end position. The clutch module includes a detent, where the ball sits inside and outside of the detent when the clutch module is in the locked end position and released end position, respectively. In response to an input torque and a spring force from the spring, the clutch module rotates toward the released end position and the locked end position, respectively. The bistable pitch propeller also includes an aircraft blade where the aircraft blade is at the first pitch angle and the second pitch angle when the clutch module is in the locked end position and the released end position, respectively.

A gas turbine engine includes a fan having a plurality of fan blades configured to rotate about a central axis of the gas turbine engine. Each fan blade is configured to pivot about a pivot axis that extends radially away from the central axis to vary a pitch of the fan blade. The fan further includes a counterforce system configured to resist forces that urge the fan blades away from their pitch positions during operation of the gas turbine engine.

Fan module with variable-pitch blades for a propulsion system that includes: a rotor supporting the blades, and including an internal shaft and an external shroud, defining between them a space; a pitch control device (22) of the blades that includes a load transfer bearing; a feathering device of the blades; said feathering device includes at least one lever that is articulated around a fixed axis (A) in relation to the rotor, where said lever features a first end located outside said space and a second end located inside said space, and where a flyweight is fastened to the first end and the second end is coupled to said bearing.

Disclosed herein is a fan module with variable pitch blades for a propulsion unit, the fan module comprising a rotor carrying the blades and comprising an inner shaft and an outer casing defining between them a space, a control device for controlling the pitch of the blades, and a feathering device for feathering the blades. The rotation of the rotor is guided by a bearing, and the module further comprises means for recovering and guiding a liquid lubricant of the bearing, with the recovery and guidance means being configured to recover and guide said lubricant from an axial upstream end of the casing, axially from upstream to downstream and radially from the inside to the outside, under the centrifugal effect.

A bistable pitch propeller includes a ball, a spring, and a clutch module where the clutch module has a range of rotational movement between a locked end position and a released end position. The clutch module includes a detent, where the ball sits inside and outside of the detent when the clutch module is in the locked end position and released end position, respectively. In response to an input torque and a spring force from the spring, the clutch module rotates toward the released end position and the locked end position, respectively. The bistable pitch propeller also includes an aircraft blade where the aircraft blade is at the first pitch angle and the second pitch angle when the clutch module is in the locked end position and the released end position, respectively.

The invention relates to the field of aerial propellers, in particular the field of variable-pitch propellers, specifically for unducted fans. More specifically, the invention relates to a pivot (15) for a blade (14) of a propeller (3a, 3b), the pivot including at least a proximal portion (15a) made of metal and suitable for being retained in a radial orifice of a propeller hub, while being capable of turning in said orifice about a longitudinal axis (Z) of the pivot (15), and a distal portion (15b) including a receptacle (20) suitable for retaining a blade root, and at least one arm (17) of organic matrix composite material extending laterally relative to said longitudinal axis (Z) and supporting a flyweight (16).

The invention relates to the field of aerial propellers, in particular the field of variable-pitch propellers, specifically for unducted fans. More specifically, the invention relates to a pivot (15) for a blade (14) of a propeller (3a, 3b), the pivot including at least a proximal portion (15a) made of metal and suitable for being retained in a radial orifice of a propeller hub, while being capable of turning in said orifice about a longitudinal axis (Z) of the pivot (15), and a distal portion (15b) including a receptacle (20) suitable for retaining a blade root, and at least one arm (17) of organic matrix composite material extending laterally relative to said longitudinal axis (Z) and supporting a flyweight (16).