The invention relates to the technical field of high-temperature thermal protection, and particularly discloses a sleeve passage for cooling high-temperature components of an aircraft, which is used for preventing key components of the aircraft from failing to work in a high-temperature environment. The cooling system comprises a fuel supply system, a sleeve cooling system and a fuel flow regulation and control system. Fuel oil of the fuel tank enters the sleeve cooling channel through the fuel pump, and the flow of large and small passages of the sleeve can be controlled through the automaticadjusting valve. Due to the application of the sleeve cooling passage, the temperature of key parts of the aircraft can be effectively prevented from rising rapidly, the phenomenon of heat transfer deterioration in a traditional cooling passage is prevented, and a new thought is provided for design of an aircraft cooling system.

    本发明涉及高温热防护技术领域,具体公开了一种用以冷却飞行器高温部件的套管通道,用以防止飞行器关键部件在高温环境中工作失效。冷却系统包括燃油供应系统、套管冷却系统和燃油流量调控系统。燃料箱的燃油经燃料泵进入套管冷却通道,套管的大小通道流量可通过自动调节阀控制。套管冷却通道的应用可有效抑制飞行器关键部件温度的快速升高,防止传统冷却通道中传热恶化现象的发生,为飞行器冷却系统的设计提供一种新思路。


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    Titel :

    A sleeve passage for cooling high temperature components of aircraft


    Weitere Titelangaben:

    一种用以冷却飞行器高温部件的套管通道


    Beteiligte:
    XIE GONGNAN (Autor:in) / LI YONG (Autor:in) / ZHANG YINGCHUN (Autor:in) / LI SHULEI (Autor:in)

    Erscheinungsdatum :

    2020-11-10


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Chinesisch


    Klassifikation :

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



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