A gas turbine engine is disclosed. In various embodiments, the gas turbine engine includes a low speed spool (208); a first compressor (204), a turbine (206) and a generator (210) rotationally coupled via the low speed spool; a high speed spool (216); and a second compressor (212) and a motor (214) rotationally coupled via the high speed spool.
POWER SYSTEM FOR ROTARY WING AIRCRAFT
ANTRIEBSSYSTEM FÜR DREHFLÜGELFLUGZEUG
SYSTÈME D'ALIMENTATION POUR AÉRONEF À VOILURE TOURNANTE
24.02.2021
Patent
Elektronische Ressource
Englisch
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