Snecma

Safran Aircraft Engines

Arnaud Lebrun

Thomas Lepage

Antoine Olivier Francois Colin

Darragh McGrath

Gilles Barjon

Antoine Colin

Darragh Mcgrath

Antoine Olivier Colin

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.

Aircraft load shedding system including supplementary power sources for assuring DC and device for cutting off power to the alternators of a turbine engine during acceleration

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.

Device for producing electrical power in a two-spool gas turbine engine

Growing community of inventors

Noisy sur Ecole, France

Arnaud Lebrun