The invention discloses a boundary layer suction type propulsion system and an aircraft. The propelling system comprises an open type rotor engine and a BLI fan. Wherein one part of energy of fuel combustion of the open type rotor engine is used for driving a rotor of the open type fan to rotate to serve as propelling power, the other part of fuel chemical energy is converted into electric energy and transmitted to the BLI fan installed on the rear portion of the fuselage, and the electric energy drives the BLI fan to rotate to provide the other part of propelling power; wherein the BLI fan comprises a fan hub, a motor and a shunt ring; and the shunting ring is arranged at the upstream end of the fan hub and is used for guiding part of airflow to pass through the motor so as to cool the motor.

    一种边界层吸入式推进系统以及飞机。其中,所述推进系统包括:开式转子发动机,以及BLI风扇;其中,所述开式转子发动机的燃料燃烧的一部分能量用以驱动开式风扇的转子旋转作为推进动力,另一部分燃料化学能转化为电能,传递给安装在机身后部的BLI风扇,电能驱动BLI风扇旋转,用以提供另一部分推进动力;其中,所述BLI风扇包括风扇轮毂、以及电机、分流环;所述分流环设置于所述风扇轮毂的上游端,导引部分气流经过所述电机,以对所述电机冷却。


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    Titel :

    Boundary layer suction type propulsion system and airplane


    Weitere Titelangaben:

    边界层吸入式推进系统、飞机


    Beteiligte:
    LIU HUI (Autor:in) / YANG ZHONG (Autor:in) / LUO JU (Autor:in)

    Erscheinungsdatum :

    06.05.2025


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Chinesisch


    Klassifikation :

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



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