The invention provides a blade, a fan and an aircraft environment control system. The blade comprises a trailing edge (1), a leading edge (2), a rear edge (3) and a blade tip (4), wherein on any wing section of the blade, and the connecting line of the leading edge point of the leading edge (2) and the rear edge point of the rear edge (3) is a wing chord; and the length of the wing chord is the chord length, and the distance between the position, with the maximum airfoil thickness, of the wing section and the leading edge point accounts for 30%-40% of the whole chord length. According to the blade provided by the invention, the fan can be transformed, the airfoil pre-compressed part of the fan is added, the shock loss is weakened, and the isentropic efficiency of the fan is improved.

    本申请提供一种叶片、风扇和飞机环控系统。该叶片包括尾缘(1)、前缘(2)、后缘(3)和叶顶(4),在叶片的任一翼剖面上,前缘(2)的前缘点与后缘(3)的后缘点连线为翼弦,翼弦的长度为弦长,翼剖面的翼型厚度最大位置处与前缘点之间的距离占据整个弦长的30%~40%。根据本申请的叶片,能够从风扇自身进行改造,增加风扇翼型预压缩部分,减弱激波损失,提高风扇等熵效率。


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    Title :

    Blade, fan and aircraft environment control system


    Additional title:

    叶片、风扇和飞机环控系统


    Contributors:
    FU DU (author) / CAO FENG (author) / ZOU JIANHUANG (author) / HE HAOHAO (author)

    Publication date :

    2021-09-10


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    Chinese


    Classification :

    IPC:    F04D Strömungsarbeitsmaschinen , NON-POSITIVE-DISPLACEMENT PUMPS / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT



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