Abstract: The present disclosure relates to a system for supplying fuel to a turbomachine. In some embodiments, the system includes a pump, a hydromechanical group, a drive device positioned to drive the pump, and a branch comprising actuators for controlling variable geometry. In some embodiments, the system regulates a fuel flow rate based at least in part on a flow rate set point value. In some embodiments, the system may include a flow rate sensor. A flow rate loop may be arranged to determine a pressure set point value at the outlet of the pump according to the flow rate set point value and a measurement supplied by the flow rate sensor. In some embodiments, a pressure sensor may be positioned in the fuel circuit at the outlet of the pump. In further embodiments, a pressure loop may control the speed of the drive device based at least on a difference between a pressure measurement supplied by the pressure sensor and the pressure set point value.

Abstract: A transmission device drives a fuel pump for a turbomachine using a drive shaft of said turbomachine. The transmission includes a planet reduction gearing with three elements: a central planet gear, an outer ring gear and a planet carrier. A first of the three elements connects to the drive shaft and a second of the three elements couples to a shaft of the pump. The three elements can be rotated about a shaft of the reduction gearing. First electrical means rotatably drive the third element to modify a rotational speed ratio between the first and second elements. Second electrical means are coupled to the first or the second element. The first and second electrical means are arranged to transfer electrical power reversibly from one to the other.

Abstract: A generator starter of a turbomachine, including an asynchronous electric machine configured so as to operate in motor mode during a starting phase of the turbomachine while being supplied by an electrical source, and so as to operate in generator mode after the starting phase of the turbomachine in order to supply an electrical load. An inverter is arranged between the electrical source and the asynchronous machine with at least two alternating current terminals coupled to the asynchronous machine, and a control unit for the inverter configured to supply the asynchronous machine with a starting current in motor mode and a magnetisation current in generator mode. The asynchronous machine includes at least one first stator winding connected to the alternating current terminals to be supplied with the starting current in motor mode and with the magnetisation current in generator mode, and at least one second stator winding connected to the electrical load in generator mode.

Abstract: A transmission device drives a fuel pump for a turbomachine using a drive shaft of said turbomachine. The transmission includes a planet reduction gearing with three elements: a central planet gear, an outer ring gear and a planet carrier. A first of the three elements connects to the drive shaft and a second of the three elements couples to a shaft of the pump. The three elements can be rotated about a shaft of the reduction gearing. First electrical means rotatably drive the third element to modify a rotational speed ratio between the first and second elements. Second electrical means are coupled to the first or the second element. The first and second electrical means are arranged to transfer electrical power reversibly from one to the other.

Abstract: The present disclosure relates to a system for supplying fuel to a turbomachine. In some embodiments, the system includes a pump, a hydromechanical group, a drive device positioned to drive the pump, and a branch comprising actuators for controlling variable geometry. In some embodiments, the system regulates a fuel flow rate based at least in part on a flow rate set point value. In some embodiments, the system may include a flow rate sensor. A flow rate loop may be arranged to determine a pressure set point value at the outlet of the pump according to the flow rate set point value and a measurement supplied by the flow rate sensor. In some embodiments, a pressure sensor may be positioned in the fuel circuit at the outlet of the pump. In further embodiments, a pressure loop may control the speed of the drive device based at least on a difference between a pressure measurement supplied by the pressure sensor and the pressure set point value.

Abstract: A generator starter of a turbomachine, including an asynchronous electric machine configured so as to operate in motor mode during a starting phase of the turbomachine while being supplied by an electrical source, and so as to operate in generator mode after the starting phase of the turbomachine in order to supply an electrical load. An inverter is arranged between the electrical source and the asynchronous machine with at least two alternating current terminals coupled to the asynchronous machine, and a control unit for the inverter configured to supply the asynchronous machine with a starting current in motor mode and a magnetisation current in generator mode. The asynchronous machine includes at least one first stator winding connected to the alternating current terminals to be supplied with the starting current in motor mode and with the magnetisation current in generator mode, and at least one second stator winding connected to the electrical load in generator mode.

Abstract: The invention relates to an electrical conversion and distribution system for an aircraft, the system comprising a synchronous starter-generator (ENG S/G) intended to be coupled to an aircraft engine, a rectifier (R) capable of transforming alternating voltage into direct voltage, an auxiliary synchronous starter-generator (AUX S/G) intended to be coupled to an auxiliary power group, a first, a second and a third power converter (CV1, CV2, CV3) capable of transforming direct voltage into alternating voltage or vice versa, and at least one battery (BATT).

Abstract: An apparatus including a fixed part, a rotary support configured to be driven in rotation relative to the fixed part, at least one item of electrical equipment carried by the rotary support, and a power supply device configured to supply electrical energy to the electrical equipment. The power supply device includes an asynchronous machine including a stator fixed to the fixed part and a rotor carried by the rotary support, and an excitation device. The stator includes an electrical circuit including at least one switch configured to switch between an open state in which the electrical circuit is open and a closed state in which the electrical circuit is closed. The rotor includes at least one winding connected to the electrical equipment. The excitation device is configured to provide a reactive current to the electrical circuit of the stator or to the winding of the rotor.

Abstract: An electrical power supply including an asynchronous machine, an arrangement for driving a rotor of the asynchronous machine in rotation by a rotor of an engine, and an electrical connection for powering electrical equipment by the rotor of the asynchronous machine. The asynchronous machine is configured to receive AC electrical power via a stator of the asynchronous machine, and it presents, over a predetermined range of drive speeds of the rotor of the asynchronous machine under drive by the rotor of the engine, efficiency in transferring electrical power from the stator to the rotor that is privileged relative to the efficiency with which rotary mechanical power is converted into electrical power.

Abstract: The invention relates to an electrical conversion and distribution system for an aircraft, the system comprising a synchronous starter-generator (ENG S/G) intended to be coupled to an aircraft engine, a rectifier (R) capable of transforming alternating voltage into direct voltage, an auxiliary synchronous starter-generator (AUX S/G) intended to be coupled to an auxiliary power group, a first, a second and a third power converter (CV1, CV2, CV3) capable of transforming direct voltage into alternating voltage or vice versa, and at least one battery (BATT).

Abstract: A actuating device includes a fixed portion forming a frame including an inlet intended to receive a fluid, a main outlet and a sampling outlet and a return device for exerting a mechanical force on a movable portion; a movable portion including a shutter moving between an open position and a closed position; a thermostatic device including a conical turning disc, the turning of the disc above a known critical temperature driving the shutter to the closed position of same; a control device allowing a holding force for holding the shutter to be generated, the control device being able to be controlled in such a way that below the critical temperature, the opening or the closing of the valve results from the balance between the holding force and the mechanical force.

Abstract: An aircraft engine including: a stator; a main shaft; a first rotor; a second rotor; a transmission mechanism; a first electrical apparatus supported by the first rotor and a second electrical apparatus supported by the second rotor; at least one first field winding supported by the stator; a control unit configured to circulate direct electric current in the first field winding; at least one first armature winding supported by the first rotor and connected to the first electrical apparatus and at least one second armature winding supported by the second rotor and connected to the second electrical apparatus.

Abstract: An actuator device for actuating a swivel-mounted member carried by a rotor of a propulsion engine including: at least one electricity source; an electric actuator for swiveling the swivel-mounted member; a power supply circuit connecting the electricity source to the actuator; and an inertial device connected to the power supply circuit, the inertial device configured to convert electrical energy coming from the power supply circuit into mechanical energy, to store the mechanical energy, and to convert the mechanical energy into electrical energy for the power supply circuit.

Abstract: An electrical power supply including an asynchronous machine, an arrangement for driving a rotor of the asynchronous machine in rotation by a rotor of an engine, and an electrical connection for powering electrical equipment by the rotor of the asynchronous machine. The asynchronous machine is configured to receive AC electrical power via a stator of the asynchronous machine, and it presents, over a predetermined range of drive speeds of the rotor of the asynchronous machine under drive by the rotor of the engine, efficiency in transferring electrical power from the stator to the rotor that is privileged relative to the efficiency with which rotary mechanical power is converted into electrical power.

Abstract: A actuating device includes a fixed portion forming a frame including an inlet intended to receive a fluid, a main outlet and a sampling outlet and a return device for exerting a mechanical force on a movable portion; a movable portion including a shutter moving between an open position and a closed position; a thermostatic device including a conical turning disc, the turning of the disc above a known critical temperature driving the shutter to the closed position of same; a control device allowing a holding force for holding the shutter to be generated, the control device being able to be controlled in such a way that below the critical temperature, the opening or the closing of the valve results from the balance between the holding force and the mechanical force.

Abstract: An electrical system for starting an engine is provided. The system includes: an AC/DC rectifier powered by an AC power network to deliver a first DC voltage Vdc, a DC/AC converter module for delivering an AC voltage for starting the engine from said first DC voltage Vdc, and k n-phase inverters arranged in parallel (k>1) and each delivering power no greater than half a maximum power Pmax required for starting the engine, and the two power supply lines of each of the inverters are connected to an electronic protection device receiving the first DC voltage Vdc, and the n outputs of each of the inverters delivering the AC voltage for starting the engine via n respective series inductors.

Abstract: A mechanical system including: a shaft rotatably mounted about a primary axis thereof in relation to a structural element; a movable member mounted on the shaft to be fixed to the shaft for rotation therewith about the primary axis and configured to be moved selectively in relation to the shaft; a drive mechanism moving the movable member in relation to the shaft, and including a first fixed portion mounted on the structural element, a second movable portion mounted on the shaft and connected to the movable member, and an air gap electromechanical actuator between the first portion and the second portion.

Abstract: A power supply circuit for supplying electrical energy in an aircraft, the circuit including a power supply generator configured to be driven in rotation by the engine of the aircraft to power electrical equipment of the aircraft engine. The power supply generator includes an asynchronous machine connected to an excitation device. The asynchronous machine includes a rotor configured to be driven in rotation by the engine and a stator connected to the electrical equipment. The excitation device is configured to cause a reactive current of flow in the stator.

Abstract: A polyphase electrical machine controlled by at least two parallel inverters, each including a number of branches equal to a number of phases of the machine and controlled by PWM. When detecting an inverter branch is faulty, the faulty branch is isolated and the phase in question is powered by each corresponding other inverter branch. The PWM is modified to make power switches of each other branch conductive in succession, without switching while absolute value of the current of the phase in question is greater than or equal to a threshold of 80% to 120% of (n?1)Imax/n, n is number of inverters and Imax is maximum magnitude of the phase current. It is thus possible to continue generating substantially sinusoidal voltages on each of the phases, while avoiding overdimensioning the power switches to ensure in event of a fault they can deliver currents of amplitude higher than in normal operation.

Abstract: A turbine engine starter-generator including a main electrical machine including a stator and rotor with a wound rotor inducer and damper bars forming a cage, and an exciter including a stator inducer and rotor with rotor windings connected to the rotor inducer of the main electrical machine via a rotary rectifier. During a first starting stage, the electrical machine operates in asynchronous motor mode by injecting AC into its stator windings, a starting torque being generated by the damper bars, without the rotor inducer of the main electrical machine contributing significantly to generating starting torque. Then in a second starting stage, the main electrical machine operates in synchronous motor mode by injecting AC into its stator windings, while feeding its rotor inducer with DC via the exciter, the change from the first stage to the second stage taking place when rotation speed of the shaft reaches a predetermined value.