The invention provides an airborne comprehensive cooling system, which comprises a turbine cooler and a heat exchanger, and is characterized in that the turbine cooler comprises a first-stage expansion turbine assembly and a second-stage expansion turbine assembly which are respectively provided with an expansion turbine and a fan; the expansion turbine of the first-stage expansion turbine assembly is connected to an engine air entraining node and the expansion turbine of the second-stage expansion turbine assembly, the fan of the second-stage expansion turbine assembly is connected to an engine exhaust node, an inlet of the heat exchanger is connected to an opening of a machine body, and an outlet of the heat exchanger is connected to the fan of the first-stage expansion turbine assembly.Compared with all systems independently arranged in the prior art, the airborne comprehensive cooling system is higher in integration level and more compact in arrangement, weight reduction, size reduction, energy consumption reduction, heat energy utilization rate improvement and air inlet and outlet number reduction of an airplane structure can be achieved, and therefore the airplane performance is improved.

    本申请提供了一种机载综合冷却系统,所述机载综合冷却系统包括:涡轮冷却器和换热器,其中,所述涡轮冷却器包括均具有膨胀涡轮与风扇的第一级膨胀涡轮组件和第二级膨胀涡轮组件,所述第一级膨胀涡轮组件的膨胀涡轮连接于发动机引气节点及连接于第二膨胀涡轮组件的膨胀涡轮,第二级膨胀涡轮组件的风扇连接于发动机排气节点,换热器的进口连接于机体开口、换热器的出口连接于第一级膨胀涡轮组件的风扇。本申请的机载综合冷却系统与现有技术中独立设置的各系统相比,集成度更高,布置更紧凑,可以实现飞机结构的减重、减小体积、降低能耗、提高热能利用率、减少进排气口数量,从而提高飞机性能。


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    Titel :

    Airborne comprehensive cooling system


    Weitere Titelangaben:

    一种机载综合冷却系统


    Beteiligte:
    YANG ZIZHONG (Autor:in) / BIAN JING (Autor:in) / YU JING (Autor:in)

    Erscheinungsdatum :

    2021-03-12


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Chinesisch


    Klassifikation :

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



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