FIELD: engines and pumps.
SUBSTANCE: invention relates to aircraft engineering, in particular to nacelles of turbojet engines. The power supply circuit of turbojet engine nacelle contains at least one electric generator mechanically connected with the turbojet engine shaft and at least two power devices other than control or monitoring units. The generator is implemented with a possibility of direct power supply, without powering the aircraft mains, of the first and second power devices. One of electric power devices is an electric anti-icing device, and another one - a thrust reversal device. The thrust reversal device contains an input line of electrodynamic braking with a possibility of partial powering of the electric anti-icing device.
EFFECT: simplification of power distribution system, minimizing of its volume and weight.
15 cl, 1 dwg
