Abstract: An aircraft propulsion system includes a turbomachine and at least one electric motor. The motor includes a first half-motor and a second half-motor that include, respectively, a first stator and a second stator cooperating with a common rotor of the motor. The propulsion system further includes at least one first energy source (B) capable of delivering a DC voltage and at least one electric generator (PMG) driven by the turbomachine. The electric generator generates an AC voltage to form a second energy source and is associated with an active rectifier that transforms the AC voltage into a DC voltage. The value of the DC voltage is controlled by the active rectifier, the output of which is connected to the first energy source.

Abstract: Overvoltage protection device for a variable-speed and constant-frequency electrical energy generation system includes at least one DC current generator connected, via a DC current bus to the input terminals of at least one inverter and to at least one regulation module for regulating the output voltage of the at least one inverter. The device includes a circuit including at least one switch in series with a resistor, the circuit being connected between the input terminals of the at least one inverter, at least one measurement sensor for measuring the DC voltage across the input terminals of the at least one inverter, a control circuit connected to the at least one measurement sensor and able to receive a voltage measured by the at least one measurement sensor, compare the measured voltage against a threshold and command the closure of the at least one switch if the measured voltage is greater than the threshold, and command opening thereof if not.

Abstract: A cooling system for a drive device with several electric machines, the cooling system including a hydraulic circuit for a coolant including a cooling part in a gearbox of the drive device for cooling the gearbox, and an air/coolant heat exchanger including cooling walls forming channels for circulating coolant for the cooling thereof, an air cooling circuit including a plurality of fans, rotationally coupled to the gearbox, a cooling part between the cooling walls of the air/liquid heat exchanger, wherein the air sucked in and propelled by the fans circulates by sweeping over the cooling walls in order to cool them.

Abstract: An aircraft propulsion system includes a turbomachine and at least one electric motor. The motor includes a first half-motor and a second half-motor that include, respectively, a first stator and a second stator cooperating with a common rotor of the motor. The propulsion system further includes at least one first energy source (B) capable of delivering a DC voltage and at least one electric generator (PMG) driven by the turbomachine. The electric generator generates an AC voltage to form a second energy source and is associated with an active rectifier that transforms the AC voltage into a DC voltage. The value of the DC voltage is controlled by the active rectifier, the output of which is connected to the first energy source.

Abstract: Overvoltage protection device for a variable-speed and constant-frequency electrical energy generation system includes at least one DC current generator connected, via a DC current bus to the input terminals of at least one inverter and to at least one regulation module for regulating the output voltage of the at least one inverter. The device includes a circuit including at least one switch in series with a resistor, the circuit being connected between the input terminals of the at least one inverter, at least one measurement sensor for measuring the DC voltage across the input terminals of the at least one inverter, a control circuit connected to the at least one measurement sensor and able to receive a voltage measured by the at least one measurement sensor, compare the measured voltage against a threshold and command the closure of the at least one switch if the measured voltage is greater than the threshold, and command opening thereof if not.

Abstract: The invention relates to a device for starting a gas turbine, comprising an initiation system able, on command, to rotate said gas turbine. The starting device comprises means for receiving information representing the rotation speed of the gas turbine, means for calculating a set torque value according to said information representing the rotation speed of the gas turbine, and means for transmitting said set torque value to the initiation system, and the means for calculating the set torque value are suitable for making a comparison of the information representing the rotation speed of the gas turbine with a predetermined speed profile and calculating the set torque value from said comparison.