A control circuit for changing the angle of propeller blades includes a propeller control unit controlling a supply of oil to modify an angle of propeller blades, and a fixed-displacement pump providing the supply of oil from an engine oil return system to the propeller control unit. An oil cooling line extends between an outlet of the pump and the engine oil return system. The oil cooling line defines an oil leakage path leading to the engine oil return system for cooling the oil. A flow regulator between the pump and the propeller control unit is operable between an open position where oil is directed through the oil cooling line to the engine oil return system for cooling the oil, and a closed position blocking the oil cooling line and directing oil toward the propeller control unit to modify the angle of the propeller blades.

A control circuit for changing the angle of propeller blades includes a propeller control unit controlling a supply of oil to modify an angle of propeller blades, and a fixed-displacement pump providing the supply of oil from an engine oil return system to the propeller control unit. An oil cooling line extends between an outlet of the pump and the engine oil return system. The oil cooling line defines an oil leakage path leading to the engine oil return system for cooling the oil. A flow regulator between the pump and the propeller control unit is operable between an open position where oil is directed through the oil cooling line to the engine oil return system for cooling the oil, and a closed position blocking the oil cooling line and directing oil toward the propeller control unit to modify the angle of the propeller blades.

The invention relates to a device (1) for controlling the setting of the blades (2) of a rotor (3) of a propeller, including a radial shaft (6), the rotation of which modifies the setting of the blade (2), a main spring (13), a first end (14) of which is connected to the rotor (3) and a second end (15) of which is connected to a part (8, 10) having an axial movement which drives the rotation of the radial shaft, and has a movement, the travel of which is offset relative to the first end in a direction (7) that is orthogonal to the axial direction (5), the main spring exerting a resilient force which aims to move the parts toward a position in which the cord of the profile of the blade is orthogonal to the plane of rotation of the propeller, in the absence of part control by means of a jack.

A hydraulically adjustable propeller assembly for an aircraft, a land vehicle or a water craft, includes an engine, a propeller unit having a propeller which comprises at least two propeller blades whose pitch is hydraulically settable, a pressure control unit which predetermines a fluid pressure for setting the pitch of the propeller blades and which is hydraulically connected to a pressure chamber of the propeller via a control line, and a pump unit which supplies a hydraulic fluid which is under a base pressure to the pressure control unit. The pump unit is a unit driven independently of the engine and the pressure control unit and includes at least one electrically operated main pump which supplies the hydraulic fluid which is under the base pressure for the pressure control unit.

An hydraulic actuation control module is provided for installation in a pitch change actuator of a propeller assembly. The module comprises a flow metering valve arranged to supply hydraulic fluid flow and pressure to an actuator and an electronic control unit arranged to control the flow metering valve. The flow metering valve is arranged to meter hydraulic fluid flow and pressure to increase and decrease pitch chambers of the pitch change actuator, in accordance with the control of the electronic control unit. The flow metering valve is arranged to receive an hydraulic fluid supply from an entity relative to which the propeller assembly rotates such as an engine driving the propeller assembly or aircraft on which the propeller assembly is installed. A propeller assembly comprising the hydraulic actuation control module is also disclosed, together with a method of installing the module within a propeller assembly.

A method and system are provided for coordinating a propeller with a controller module including a machine having a controller module and a propeller mounted to a propeller shaft at a hub. The shaft is arranged to be received in the machine, and a sensor is mounted to the machine, connected to the electronic controller module, and configured to sense the propeller when the propeller shaft is received in the machine.

The variable pitch propeller assembly includes a hub. The variable pitch propeller assembly also includes a plurality of propeller blade assemblies spaced circumferentially about the hub. Each of the plurality of propeller blade assemblies configured to rotate a respective propeller blade. The variable pitch propeller assembly also includes a hydraulic fluid port assembly integrally formed and including at least three hydraulic fluid ports configured to receive respective flows of hydraulic fluid from a stationary hydraulic fluid transfer sleeve. The variable pitch propeller assembly also includes a pitch actuator assembly coupled in flow communication with at least three hydraulic fluid ports through respective hydraulic fluid transfer tubes. The pitch actuator coupled to the plurality of propeller blade assemblies to selectively control a pitch of the propeller blades. The pitch actuator assembly includes a travel stop configured to limit a rotation of at least one of the pitch actuator assemblies.

An actuation system is provided for varying the pitch of the blades of a variable pitch fan or propeller. The actuation system includes a first actuator and a second actuator. The actuation system further includes a first linkage which operably connects the first actuator to the blades such that operation of the first actuator varies the pitch of the blades via the first linkage. The actuation system further includes a second linkage which operably connects the second actuator to the first actuator such that operation of the second actuator varies the pitch of the blades by series connection of the second linkage to the first linkage.

An actuation system is provided for varying the pitch of the blades of a variable pitch fan or propeller. The actuation system includes a first actuator and a second actuator. The actuation system further includes a first linkage which operably connects the first actuator to the blades such that operation of the first actuator varies the pitch of the blades via the first linkage. The actuation system further includes a second linkage which operably connects the second actuator to the first actuator such that operation of the second actuator varies the pitch of the blades by series connection of the second linkage to the first linkage.

A blade pitch control assembly includes a pitch control actuator having a coarse actuator chamber having a coarse chamber area and a fine actuator chamber having a fine chamber area. The coarse chamber area is biased to a feather position. The assembly also includes a primary pitch control valve configured to control the flow of pressurised fluid to the coarse actuator chamber and the fine actuator chamber, respectively via a coarse fluid line and a fine fluid line. The assembly further includes a hydraulic protection system located between the actuator and the primary pitch control valve, configured to bypass the primary pitch actuator in response to a trigger. The hydraulic protection system has a hydraulic protection system valve located between the fluid lines and when activated fluidly connects the fluid lines to balance fluid pressure between the coarse chamber and the fine chamber.