An electrical architecture for an aircraft providing power for the aircraft by generating power from a high pressure spool and a low pressure spool of a turbine engine. The spools can be used to drive corresponding generators; the power from which can be used to supply the various loads of the aircraft.
1. An electrical architecture for a turbine engine having a high pressure (HP) spool and a low pressure (LP) spool comprising: a first generator driven by the HP spool and providing a first DC output;a second generator driven by the LP spool and providing a second DC output;a first DC bus connected to the first DC output;a second DC bus connected to the second DC output; andwherein the first and second DC buses are selectively connected. 2. The electrical architecture of claim 1 further comprising an accessory gearbox connecting the HP spool to the first...
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