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.


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    Title :

    POWER SYSTEM FOR ROTARY WING AIRCRAFT


    Additional title:

    ANTRIEBSSYSTEM FÜR DREHFLÜGELFLUGZEUG
    SYSTÈME D'ALIMENTATION POUR AÉRONEF À VOILURE TOURNANTE


    Contributors:

    Publication date :

    2021-02-24


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    F02C Gasturbinenanlagen , GAS-TURBINE PLANTS / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT




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