ENGINE HAVING POWER BUS FAULT SHORT CIRCUIT CONTROL WITH A DISCONNECTION SWITCH

摘要

An aircraft electrical system comprises a generator to be driven as part of a gas turbine engine. The generator supplies electrical power to a plurality o f accessories associated with the gas turbine engine, and to an aircraft power bus in parallel to the supply to the accessories. A control detects a short circuit on the aircraft power bus. When a short circuit is detected on the aircraft power bus, a switch is driven open to disconnect the aircraft power bus from the generato r. In this manner, the power will continue to be delivered to the plurality of accessories. In a separate feature, a control voltage is provided by an auxiliary permane nt magnet generator to a voltage regulator for the main generator.