An aircraft turbine engine (101) includes an electric motor (206) downstream of a low pressure compressor of a low pressure body (104) of the aircraft turbine engine and upstream of a combustion chamber (102) of the aircraft turbine engine, the electric motor configured to rotate a rotor vane ring to generate an air flow. In addition, the rotating speed of the motor rotor is independent of the rotating speed of the compressor rotor.

    本发明涉及一种飞行器涡轮发动机(101),该飞行器涡轮发动机在飞行器涡轮发动机的低压主体(104)的低压压缩机的下游以及飞行器涡轮发动机的燃烧室(102)的上游包括电动马达(206),该电动马达被构造成使转子轮叶环旋转以产生空气流。此外,该电机转子的转速独立于压缩机转子的转速。


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    Title :

    Aircraft turbine engine with hybrid compressor


    Additional title:

    具有混合动力压缩机的飞行器涡轮发动机



    Publication date :

    2022-10-11


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    Chinese


    Classification :

    IPC:    F02K JET-PROPULSION PLANTS , Strahltriebwerke / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT



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