System for converting and transporting electrical energy for the internal hybridisation of an aircraft turbomachine

An electrical energy conversion and transport system in an aircraft powered by a turbo-engine from which power can be drawn or injected via a high-pressure shaft and/or a low-pressure shaft, wherein the system comprises:

• at least one first electrical rotating machine mechanically connected to the low-pressure shaft via a coupling device,
• a first electrical power module associated with said first electrical machine,
• a second electrical rotating machine mechanically connected to the high-pressure shaft via an accessory box, and a second electrical power module associated with said second electrical rotating machine,
• said first electrical power module and said second electrical power module being electrically connected to an internal electrical network of the turbo-engine,
• a generator coupled with the accessory box and intended to electrically supply an electrical network of the aircraft, said electrical network of the aircraft being electrically isolated from the internal electrical network of the turbo-engine, and
• a control device able to control an assistance for starting the turbo-engine by at least one electrical rotating machine, to compensate for power drawings by the generator, and to carry out a distribution between a power drawn from the high-pressure shaft and a power drawn from the low-pressure shaft as a function of the operating phases of the turbo-engine.