US 12,378,933 B2
System for converting and transporting electrical energy for the internal hybridisation of an aircraft turbomachine
Yann Fefermann, Moissy-Cramayel (FR); Pierre-Alain Jean Philippe Reigner, Moissy-Cramayel (FR); Philippe Naneix, Moissy-Cramayel (FR); and Philippe Delbosc, Moissy-Cramayel (FR)
Assigned to Safran, Paris (FR); Safran Aircraft Engines, Paris (FR); and Safran Electrical & Power, Blagnac (FR)
Appl. No. 18/712,667
Filed by Safran, Paris (FR); Safran Aircraft Engines, Paris (FR); and Safran Electrical & Power, Blagnac (FR)
PCT Filed Oct. 26, 2022, PCT No. PCT/EP2022/079979
§ 371(c)(1), (2) Date May 22, 2024,
PCT Pub. No. WO2023/094101, PCT Pub. Date Jun. 1, 2023.
Claims priority of application No. 2112486 (FR), filed on Nov. 25, 2021.
Prior Publication US 2025/0012201 A1, Jan. 9, 2025
Int. Cl. F01D 15/10 (2006.01); B64D 27/33 (2024.01); B64D 27/357 (2024.01); B64D 31/18 (2024.01)
CPC F01D 15/10 (2013.01) [B64D 27/33 (2024.01); B64D 27/357 (2024.01); B64D 31/18 (2024.01); F05D 2220/76 (2013.01)] 12 Claims
OG exemplary drawing
 
1. 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.