A general eigenvalue theory on flow stability in turbomachinery is proposed with the emphasis on flow-instability onset. Based on this theory, a stall-inception model including the effects of complex solid geometry is developed for a multistage fan/compressors system. The capacity of the present model to predict the stall-inception point is assessed against experimental data of both a low-speed and transonic single rotor. Comparisons with a simplified two-dimensional model are performed to identify the nonnegligible effects of spanwise distribution of flowfield in a general configuration on the unstable mode of the concerned fan/compressors. It is verified that this model is capable of predicting mass flow at the stall-onset point of both subsonic and transonic flow with a reasonable accuracy, and it is sustainable in terms of computation cost for industrial application.


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    Title :

    A General Theory of Flow-Instability Inception in Turbomachinery


    Contributors:
    Sun, Xiaofeng (author) / Liu, Xiaohua (author) / Hou, Ruiwei (author) / Sun, Dakun (author)

    Published in:

    AIAA Journal ; 51 , 7 ; 1675-1687


    Publication date :

    2013-04-09


    Size :

    13 pages




    Type of media :

    Article (Journal)


    Type of material :

    Electronic Resource


    Language :

    English