The invention provides a runner type aircraft nose cone zoning cooling system and an aircraft nose cone, the runner type aircraft nose cone zoning cooling system comprises a liquid inlet cavity, a liquid outlet cavity and a zoning cooling channel, the zoning cooling channel comprises a nose cone end part cooling channel and a nose cone middle-rear part cooling channel, the cooling cavity shape of the nose cone end part cooling channel is matched with the end part of the nose cone, and the cooling cavity shape of the nose cone middle-rear part cooling channel is matched with the end part of the nose cone. A cooling cavity of the cooling channel at the middle-rear part of the nose cone is annularly distributed at the middle-rear part of the nose cone; cooling liquid flows through the head cone end portion cooling channel and the head cone middle rear portion cooling channel from the liquid inlet cavity and flows out from the liquid outlet cavity. Cooling liquid enters the liquid inlet cavity, then is distributed into the central liquid inlet channel and the middle-rear part cooling liquid inlet channel, and then is subjected to partitioned cooling on the end part and the middle-rear part of the nose cone through the end part cooling cavity and the annular cooling unit; and the heated cooling liquid flows back to the liquid outlet cavity through the end part cooling edge liquid outlet channel and the middle-rear part cooling liquid outlet channel and flows out of the cooling system, so that the end part and the middle-rear part of the nose cone can be efficiently cooled in a partitioned manner.

    本发明提供了一种流道式飞行器头锥分区冷却系统及飞行器头锥,包括进液腔、出液腔以及分区冷却通道,分区冷却通道包括头锥端部冷却通道和头锥中后部冷却通道,头锥端部冷却通道的冷却腔形状与头锥的端部相匹配,头锥中后部冷却通道的冷却腔呈环形分布在头锥的中后部;冷却液自进液腔分别流经头锥端部冷却通道、头锥中后部冷却通道,自出液腔流出。本发明通过冷却液进入进液腔后分配进入中心进液通道、中后部冷却进液通道,然后分别通过端部冷却空腔、环形冷却单元对头锥端部、中后部进行分区冷却,升温后的冷却液分别通过端部冷却边缘出液通道、中后部冷却出液通道回流至出液腔并流出冷却系统,能够对头锥端部、中后部进行高效的分区冷却。


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    Titel :

    Flow channel type aircraft nose cone partition cooling system and aircraft nose cone


    Weitere Titelangaben:

    流道式飞行器头锥分区冷却系统及飞行器头锥


    Beteiligte:
    AN GUOCHEN (Autor:in) / GU CUNFENG (Autor:in) / SHEN HAOMIN (Autor:in) / QIANG JIAJIU (Autor:in) / LI QUAN (Autor:in) / GU LONGFEI (Autor:in) / MU WEIMIN (Autor:in) / ZHANG DI (Autor:in)

    Erscheinungsdatum :

    2023-10-24


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Chinesisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge



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