A propeller assembly of an aircraft includes a hub, a plurality of propeller blades extending from the hub and secured thereto and a propeller blade pitch change system located at at least one propeller blade of the plurality of propeller blades. The propeller blade pitch change system includes a pitch change actuator located in the propeller blade, and a drive mechanism operably connected to the pitch change actuator and to the propeller blade to urge rotation of the propeller blade about a propeller blade axis.

A turbine engine including: a rotor supporting a blade and guided by means of bearings; a control system for controlling the blade, which is solidly connected to the rotor and which includes an actuator driven by energy, the control system being disposed axially upstream of the bearings; and a device for transferring the energy, disposed axially between the bearings and including a stationary member and a moving member. The rotor includes a support ring supporting the blade and a shaft having a frustoconical portion and a cylindrical portion on which the bearings and the moving member are mounted, the frustoconical portion extending about the cylindrical portion.

The invention relates to a fan module having variable-pitch blades for a turbine engine, including a rotor (2) having blades (3), a stationary casing (7), and a system for adjusting and controlling the pitch of the blades (3), the rotor (2) including a central shaft (6) and a ring (9) for supporting the blades surrounding the shaft, a front end of the ring being connected to a front end of the shaft so as to define an annular space between the ring and the shaft which is open towards the rear, said annular space of the rotor (2) housing said system, and the shaft (6) being guided by a first bearing (8) mounted in the stationary casing (7), to the rear of the ring (9), characterised in that the ring (9) is guided by at least one complementary bearing (31) located upstream of the first bearing (8).

Examples described herein provide a computer-implemented method that includes controlling a high spool motor of an aircraft to cause the high spool motor to drive rotation of a high speed spool of a gas turbine engine of the aircraft to maintain a desired compressor pressure and a desired flow within a combustor of the gas turbine engine. The method further includes commanding fuel flow to the combustor responsive to a trigger event to cause the gas turbine engine to start to a fuel-burning mode.

A hybrid propulsion system for use with an aircraft includes a gas turbine engine, at least one propulsor, and an electric power system. The electric power system is coupled to the gas turbine engine to generate electrical energy and the propulsor to provide electrical energy to drive the propulsor. The electric power system includes a thermal management system configured to cool a heat load generated by the electric power system.

A system for controlling a propeller having a plurality of blades having a primary control system and a backup control system. The primary control system including a sensor responsive to a propeller state, and a controller connected to the sensor and to an electrohydraulic control actuator. The electrohydraulic control actuator is connected via a bypass valve to a hydraulic actuator that controls at least a blade angle of a blade of the propeller. The controller generating commands to the electrohydraulic control actuator based on at least the propeller state. The backup control system including a second controller, an electrohydraulic solenoid operably connected to the bypass valve. The backup control system is operable to hydraulically disable the primary control system via the bypass valve upon the occurrence of a selected condition, the second controller modulates the operation of the electrohydraulic solenoid to control the bypass actuator based on the propeller state.

A propulsion system for use with an aircraft includes a gas turbine engine, an electric power system, and at least one propulsor. The gas turbine engine includes a compressor, a combustor, and a turbine. The electric power system includes a generator coupled to the gas turbine engine to generate electrical energy, power electronics connected to the generator to receive the electrical energy from the generator, and a motor configured to produce rotational energy in response to receiving electric energy from the power electronics. The propulsor is configured to use rotational energy received from the motor of the electric power system to generate thrust for propelling the aircraft.

A hybrid propulsion system for use with an aircraft includes a gas turbine engine, at least one propulsor, and an electric power system. The electric power system is coupled to the gas turbine engine to generate electrical energy and the propulsor to provide electrical energy to drive the propulsor. The electric power system includes a thermal management system configured to cool a heat load generated by the electric power system.

In a rotating machine having a fluidic rotor, the rotor comprises at least one blade mounted on an arm rotating about a rotor shaft forming a main axis of the rotor, the rotor being kept by a supporting structure in an orientation such that said axis is substantially perpendicular to the direction of flow of the fluid, the blade being mounted so as to pivot about an axis of rotation of the blade parallel to the main axis. The machine comprises means for generating a relative oscillation movement of the blade with respect to the arm at the axis of rotation of the blade, in order in this way to vary the inclination of the blade during the rotation of the rotor. Said means comprise, at the arm end, a mechanism comprising a first rotating element (A; B) known as the drive element and a second rotating element (B; A) known as the driven element, the elements being mounted on mutually parallel axes of rotation and separated by an inter-axis distance, the orientation of the drive element being controlled depending on the orientation of the rotor shaft while the orientation of the driven element determines the orientation of the blade, one of the rotating elements comprising a finger (D) spaced apart from its axis of rotation and the other rotating element comprising a groove (C) which receives the finger and in which the finger can slide. Application notably to wind turbines, to marine turbines and to nautical and aircraft propellers.

A gas turbine engine including a core having in serial flow order a compressor, a combustor, and a turbine—the compressor, combustor, and turbine together defining a core air flowpath. The gas turbine engine additionally includes a fan section mechanically coupled to the core, the fan section including a plurality of fan blades, and each of the plurality fan blades defining a pitch axis. An actuation device is operable with the plurality fan blades for rotating the plurality fan blades about their respective pitch axes, the actuation device including an actuator located outward of the core air flowpath to, e.g., simplify the gas turbine engine.