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本文基于文献[1]提出的建议,即先用流函数方程或势函数方程计算压气机叶栅的跨声速流场,得到大致的通道激波位置后,再对激波的上、下游区分别进行计算;最后通过对激波位置的调整以满足Rankine-Hugoniot条件,得出确切和明晰的激波形状及气流参量通过激波的突跃变化.文中对具有实验数据的一个双圆弧叶栅分别用势函数方法和流函数方法捕获通道激波并将二者所得激波的平均位置作为分区计算时进行通道激波调整的初始波形.在计算结果同实验值的比较中,还考虑了平面跨声速叶栅实验时实际存在的轴向速度密度比和沿流线熵增对计算结果的影响,所得计算结果是接近实验值的。
Based on the suggestion made in [1], this paper first calculates the transonic flow field of the compressor cascade by using the flow function equation or the potential function equation, and after obtaining the rough channel shock position, Finally, the exact and explicit shock shape and the sudden change of the air flow parameters through the shock wave are obtained by adjusting the position of the shock wave to satisfy Rankine-Hugoniot conditions.In this paper, a double circular arc cascade with experimental data The channel shock wave is captured by the potential function method and the stream function method, respectively, and the average position of the shock wave obtained by the two methods is taken as the initial waveform of channel shock wave adjustment in the calculation of the partition. In comparing the calculated result with the experimental value, The actual velocity density ratio and the effect of entropy increase along streamline on the computation of transonic cascades are obtained. The calculated results are close to the experimental values.