The invention provides a turbine rotor, an expansion machine and an air cycle machine. The turbine rotor comprises a wheel disc (1) and blades arranged in the circumferential direction of the wheel disc (1), the airflow attack angle of the front edge of each blade is 0 degree, the inlet airflow angle alpha of the turbine rotor is the included angle between the airflow direction FD and the axial direction of the turbine rotor, the front edge blade angle beta of the turbine rotor is the included angle between the front edge tangent line of an airfoil mean camber line of each blade and the axial direction of the turbine rotor, and the airflow attack angle i is equal to alpha-beta. According to the turbine rotor, the problem of large separation flow generated by airflow impact on the front edge of the rotor can be solved, so that the airflow loss is reduced, and the efficiency of the turbine rotor is improved.

    本申请提供一种涡轮转子、膨胀机和空气循环机。该涡轮转子包括轮盘(1)和沿轮盘(1)周向设置的叶片,叶片前缘的气流攻角为0°,其中涡轮转子的进口气流角α为气流方向FD与涡轮转子的轴向的夹角,涡轮转子的前缘叶片角β为叶片的翼型中弧线前缘切线与涡轮转子的轴向的夹角,气流攻角i=α‑β。根据本申请的涡轮转子,能够解决转子前缘由气流冲击产生的大分离流动的问题,从而减小气流流动损失,提高涡轮转子效率。


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    Titel :

    Turbine rotor, expansion machine, and air cycle machine


    Weitere Titelangaben:

    涡轮转子、膨胀机和空气循环机


    Beteiligte:
    FU DU (Autor:in) / CAO FENG (Autor:in) / HUANG JIANPING (Autor:in) / YU YANCUI (Autor:in) / ZOU JIANHUANG (Autor:in)

    Erscheinungsdatum :

    2021-09-10


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Chinesisch


    Klassifikation :

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



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