FIELD: motors and pumps.
SUBSTANCE: system for rapid reactivation of a gas turbine engine of an aircraft contains an electric machine powered by a direct current from the on-board electric power supply network. Also, said system comprises a switch installed between the on-board network and the electric machine, an additional set comprising a plurality of N electric power storage elements, and a device control unit for discharging energy storage elements. Said control unit is configured to parallelly connect the on-board power supply network to a sequential circuit comprising at least one power supply, part of N elements of accumulation of electric energy, so that when the quick reactivation system is activated, the electric machine receives power with a voltage level exceeding the level of its nominal characteristics.
EFFECT: increased reliability of gas turbine engines start-up, including in the standby mode.
10 cl, 7 dwg
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