Abstract: A DC electrical generation system for an aircraft propelled by a turbine engine, such as a turbojet, includes at least one electrical energy storage capacity, at least one generator driven mechanically by a rotation shaft of the turbine engine and electrical connections between the electrical energy storage capacity, the generator and the aircraft equipment for powering the above-mentioned equipment with DC current, also including at least one alternative for supplying DC current to the equipment, which are autonomous in relation to any mechanical driving by a rotation shaft of the turbine engine, and a device that can cut-off power to the generator(s) and simultaneously activate the alternative current supply. The power cut-off device for triggering power cut-off and activating the alternative current supply is controlled by a control or operating parameter of the turbine engine. The alternative current supply is preferably formed by one or more supercapacitors.

Abstract: A DC electrical generation system for an aircraft propelled by a turbine engine, such as a turbojet, includes at least one electrical energy storage capacity, at least one generator driven mechanically by a rotation shaft of the turbine engine and electrical connections between the electrical energy storage capacity, the generator and the aircraft equipment for powering the above-mentioned equipment with DC current, also including at least one alternative for supplying DC current to the equipment, which are autonomous in relation to any mechanical driving by a rotation shaft of the turbine engine, and a device that can cut-off power to the generator(s) and simultaneously activate the alternative current supply. The power cut-off device for triggering power cut-off and activating the alternative current supply is controlled by a control or operating parameter of the turbine engine. The alternative current supply is preferably formed by one or more supercapacitors.

Abstract: A device for producing electrical power in a multi-spool gas turbine engine is disclosed. The device includes at least one first rotary spool and a second rotary spool which drives an electrical machine. The electrical machine is of the twin-rotor type with a first rotor and a second rotor. The first rotor is mechanically connected to the first rotary spool and the second rotor is mechanically connected to the second rotary spool.

Abstract: The invention relates to a device for producing electrical power in a multi-spool gas turbine engine comprising at least one first rotary spool (69), for example a low-pressure spool, and a second rotary spool (24), for example a high-pressure spool, and driving an electrical machine (10). The device is one wherein, with the electrical machine (10) being of the twin-rotor type with a first rotor (13) and a second rotor (14), the first rotor (13) is mechanically connected to the first rotary spool (69) and the second rotor is mechanically connected to the second rotary spool (24).