摘要
改进了动静叶级间的掺混面处理方法,提出了用参数分布修正方法来保证参数在掺混面上的周向不均匀性,并使用亚松弛的参数分布系数来解决程序在动静叶轴向间距较小时的计算稳定性和收敛性问题。采用经改进的NAPA软件对NASA37级压气机的设计点和在不同转速下的流场进行了数值模拟,计算结果与试验结果吻合较好。
The modified method for studying inter - row mixing plane between stator and rotor has been described. A parameter distribution correction method is presented to ensure the circumferential parameter nonuniformity in mixing plane. A sub - slack parameter distribution coefficient is used to maintain the stability and convergence of the computation for small axial inter - row gap. Numerical simulation of the flow - field of NASA37 compressor stage is completed using the modified software NAPA at design - point and at different rotor speeds. Comparison of computational and experimental results shows very good agreement.
出处
《航空发动机》
2005年第3期13-16,共4页
Aeroengine
基金
APTD计划
