AIRCRAFT TURBINE ENGINE WITH A HYBRID COMPRESSOR

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....

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Bibliographic Details
Main Authors PARMENTIER, Nicolas Claude, RIERA, William Henri Joseph
Format Patent
LanguageEnglish
French
German
Published 24.07.2024
Subjects
AIRCRAFT
ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSIONTRANSMISSIONS IN AIRCRAFT
AVIATION
BLASTING
COMBUSTION ENGINES
COSMONAUTICS
EQUIPMENT FOR FITTING IN OR TO AIRCRAFT
FLYING SUITS
HEATING
HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
JET-PROPULSION PLANTS
LIGHTING
MECHANICAL ENGINEERING
PARACHUTES
PERFORMING OPERATIONS
TRANSPORTING
WEAPONS
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Summary: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.
Bibliography:Application Number: EP20210707332