Systems and methods of power allocation for turboprop and turboshaft aircraft

A method of powering an aircraft system having a first turbine engine, the first turbine engine having a first high pressure (HP) spool and a first low pressure (LP) spool, the first HP spool configured to drive a first generator and provide a first electrical output, the first LP spool coupled to a first propeller configured to drive a second generator, provide a second electrical output, and drive the first propeller, the method comprising:

• splitting a total power from the first turbine engine to the second generator and the first propeller;
• providing the first electrical output from the first generator to an electrical power distribution bus;
• providing the second electrical output from the second generator to the electrical power distribution bus;
• providing a third electrical output from a second high pressure (HP) spool coupled to a second turbine engine, wherein the second HP spool configured to drive a third generator to the electrical power distribution;
• providing a fourth electrical output from a second low pressure (LP) spool coupled to the second turbine engine, wherein the low LP spool configured to drive a fourth generator to the electrical power distribution;
• coupling a first aircraft systems bus, a second aircraft systems bus, and a third aircraft systems bus to the electrical power distribution bus;
• driving a second propeller by the second turbine engine coupled to the second LP spool;
• and
• managing a power allocation among the first generator and the second generator, to the first aircraft systems bus, a second aircraft systems bus, and a third aircraft systems bus from the electrical power distribution bus via a control system having a propulsion system controller (PSC) communicatively coupled to at least one bus power control unit controllers (BPCU) and at least one full authority digital engine control (FADEC).

An electrical system for an aircraft having a first turbine engine, the first turbine engine having a first high pressure (HP) spool and a first low pressure (LP) spool, and a second turbine engine, the second turbine engine having a second high pressure (HP) spool and a second low pressure (LP) spool, the electrical system comprising:

• a first generator coupled to the first HP spool driven by the first turbine engine and providing a first electrical output;
• a second generator coupled to the first LP spool driven by the first turbine engine and providing a second electrical output;
• a third generator coupled to the second HP spool driven by the second turbine engine and providing a third electrical output;
• a fourth generator coupled to the second LP spool driven by the second turbine engine and providing a fourth electrical output;
• a propulsion system defined by a first propeller and driven by the first turbine engine, and a second propeller coupled to the second LP spool, wherein the second propeller is driven by the second turbine engine;
• the first generator the second generator, the third generator, and the fourth generator coupled to an electrical power distribution bus that provides electrical power to a first load, a second load, and a third load;
• a propulsion system controller coupled to the electrical power distribution bus;
• a first aircraft systems bus, a second aircraft systems bus, and a third aircraft systems bus coupled to the electrical power distribution bus;
• the first load, the second load, and the third load coupled to the first aircraft systems bus, the second aircraft systems bus, and the third aircraft systems bus respectively;
• and
• a control system configured to allocate power to at least one of the first load, the second load, and the third load from the first generator and the second generator via the propulsion system controller, the first aircraft systems bus, the second aircraft systems bus, and a third aircraft systems bus.