The invention discloses a distributed hybrid electric propulsion system and a working method thereof. The distributed hybrid electric propulsion system comprises a turbofan engine; the newly-added turbine is arranged at the tail part of a turbine of the turbofan engine; the generator is driven by the newly-added turbine to rotate so as to generate electricity; and the at least one electric fan is arranged at the rear edge of the upper surface of the wing, is powered by the generator, and sucks the boundary layer of the upper surface of the wing after being powered. High-temperature and high-pressure gas exhausted by the turbofan engine is used for generating electricity, so that the electricity is supplied to the electric fans on the wings to enable the electric fans to work and rotate, boundary layers on the surfaces of the wings are sucked, separation of the boundary layers is reduced, the lift-drag ratio of the aircraft is increased, finally, the energy consumption of the engine is reduced, and the fuel efficiency is improved.

    本发明公开了一种分布式混合电力推进系统及其工作方法,该系统包括:涡扇发动机;新增涡轮机,设置于所述涡扇发动机的涡轮尾部;发电机,由所述新增涡轮机带动转动而发电;至少一个电动风扇,设置于机翼上表面的后缘处,由所述发电机供电,供电后对机翼上表面的边界层进行抽吸。通过利用涡扇发动机排出的高温高压气体发电,以供给机翼上的电动风扇,使其工作转动,进而对机翼表面的边界层抽吸,减少边界层的分离,进而增加飞行器的升阻比,最终降低发动机的能耗,提高燃油效率。


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    Title :

    Distributed hybrid electric propulsion system and working method thereof


    Additional title:

    一种分布式混合电力推进系统及其工作方法


    Contributors:

    Publication date :

    2024-11-12


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    Chinese


    Classification :

    IPC:    B64C AEROPLANES , Flugzeuge / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT



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