The invention relates to a hybrid propulsion system (2) comprising: a turbine engine (3) comprising a high-pressure spool (4) and a low-pressure spool (5), the low-pressure spool (5) comprising reduction gear (11), the reduction gear (11) forming part of a transmission gearbox (12) which is positioned axially at a front end (13) of the propulsion system (2); - first and second electric machines (14, 15) mechanically and respectively connected to the high-pressure and low-pressure spools (4, 5), the electric machines (14, 15) being configured to operate in modes referred to as motor and generator, the first and second electric machines (14, 15) being fixed to the transmission gearbox (12); - a control system (16) which is configured to allow the transfer of power between the high-pressure and low-pressure spools (4, 5) via the first and second electric machines (14, 15).
SYSTEME PROPULSIF HYBRIDE POUR UN AERONEF
HYBRID PROPULSION SYSTEM FOR AN AIRCRAFT
HYBRIDANTRIEBSSYSTEM FÜR EIN FLUGZEUG
2025-05-28
Patent
Electronic Resource
French