The invention discloses an aero-engine cabin cooling method and belongs to the field of aero-engine cooling. The temperature control levels of different types of electronic components in an existing engine compartment are different, if the mode of directly ventilating and cooling the engine compartment is adopted to obtain the compartment temperature meeting the temperature control requirement, the cooling air flow needs to be increased or the temperature of cooling air needs to be reduced, and therefore the problem that the ram air heat sink capacity is insufficient is solved. The invention provides an engine compartment cooling method, aiming at the problems that the temperature of electronic components is controlled, and the problems that the performance of the aircraft is lost and the heat sink capacity is insufficient due to the fact that the cooling air flow needs to be increased or the cooling air temperature needs to be reduced are effectively solved.

    一种航空发动机舱室冷却方法,属于航空发动机冷却领域。针对现有发动机舱内,不同种类电子元器件控温水平不一,若采用直接对发动机舱通风冷却的方式,获得满足温控需求的舱温,就需要增加冷却气流量或者降低冷却气的温度,这不仅面临着冲压空气热沉能力不足的问题,同时还会降低飞行器性能等问题,本发明提供了一种发动机舱室冷却方法,保证电子元器件控温的同时,有效的解决了需增加冷却气流量或降低冷却气温度所带来的飞行器性能损失以及热沉能力不足等问题。


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    Titel :

    Aero-engine cabin cooling method


    Weitere Titelangaben:

    一种航空发动机舱室冷却方法


    Beteiligte:
    WANG MINMIN (Autor:in) / WANG KELONG (Autor:in) / ZHONG SHUAI (Autor:in) / TAO XIAOYANG (Autor:in) / LIU JIANG (Autor:in) / TANG LAN (Autor:in)

    Erscheinungsdatum :

    27.12.2024


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Chinesisch


    Klassifikation :

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



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