The invention relates to an aircraft turbine engine (101) which comprises, downstream of the low pressure compressor of its low pressure body (104) and upstream of its combustion chamber (102), an electric motor (206) which is configured to rotate a rotor blade ring so as to generate a flow of air. Moreover, the rotational speed of the electric machine rotor is independent of the rotational speed of the compressor rotor.
TURBOMACHINE D'AÉRONEF AVEC UN COMPRESSEUR HYBRIDE
AIRCRAFT TURBINE ENGINE WITH A HYBRID COMPRESSOR
FLUGZEUGTURBINENTRIEBWERK MIT EINEM HYBRIDVERDICHTER
2024-07-24
Patent
Electronic Resource
French
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