The invention discloses a self-adaptive porous material sweating and cooling front edge structure based on pyrolysis, which comprises a fuselage and a front edge body connected with the fuselage, the front edge body is covered with a pyrolysis carbonization material layer, a cooling cavity is connected in the front edge body, the cooling cavity is connected with a coolant supply channel, the front edge body is provided with a plurality of coolant channels. The coolant channel is respectively communicated with the pyrolysis carbonization material layer and the cooling cavity, and the coolant supply channel is used for being connected with a coolant supply device. According to the structure, the problems of non-uniform cooling, low cooling efficiency and poor thermal protection effect of different parts of the leading edge in the prior art are solved.

    本发明公开了一种基于热解的自适应多孔材料发汗冷却前缘结构,包括机身、与机身连接的前缘体,所述前缘体外覆盖有热解炭化材料层,所述前缘体内连接有冷却腔,所述冷却腔连接有冷却剂供给通道,所述前缘体上设有若干冷却剂通道,所述冷却剂通道与所述热解炭化材料层、所述冷却腔分别连通,所述冷却剂供给通道用于连接冷却剂供给装置。本发明解决了现有技术存在的前缘不同部位冷却不均匀、冷却效率不高、热防护效果不佳的问题。


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    Titel :

    Self-adaptive porous material sweating cooling front edge structure based on pyrolysis


    Weitere Titelangaben:

    一种基于热解的自适应多孔材料发汗冷却前缘结构


    Beteiligte:
    SHEN BINXIAN (Autor:in) / LI QIANG (Autor:in) / LIU XIAO (Autor:in) / GE QIANG (Autor:in) / ZHOU SHUGUANG (Autor:in)

    Erscheinungsdatum :

    2021-05-07


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Chinesisch


    Klassifikation :

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



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