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本文对平面叶栅气动计算网格生成方法作了简要评述。在此基础上,根据叶栅槽道流动的特点,提出一种以等比级数为基础,用几何方法构作H网格的数值方法。用这种网格进行流场计算的结果表明,所生成的网格在叶片前后缘区有很高的分辨能力,能够算出速度分布的细微结构。本文的计算结果与亚音速及跨音速叶栅速度图解符合得很好。
In this paper, a brief review is given of the aerodynamic calculation grid generation method for plane cascade. On this basis, according to the characteristics of cascade flow, a numerical method based on geometric progression is proposed based on geometric progression. The results of flow field calculation using this kind of grid show that the generated grids have high resolving power in the leading and trailing edges of the blade and can calculate the fine structure of velocity distribution. The calculated results of this paper are in good agreement with those of subsonic and transonic cascade velocities.