修正S-A湍流模型在Rotor37计算中的评估

Assessment of Corrected S-A Turbulence Model in the Computation of Rotor37

为评估PMB3D软件中的湍流模型对航空发动机叶轮机的模拟能力,采用二阶Roe格式、LU-SGS时间积分方法和原始一方程S-A湍流模型对NASARotor37压气机进行了计算,基于Van Driest近壁公式对S-A湍流模型进行了修正,并分析了修正对流场的影响。计算结果表明:经过修正的S-A模型计算得到的失速点推迟,对特性线、出口展向平均总压、静压、总温和绝热效率精度低于原始S-A模型,但对切向速度和绝对气流角的计算结果和试验数据吻合更好。该研究工作表明,总体上PMB3D软件中的数值模拟方法对单转子压气机的模拟精度较好,S-A模型的修正方法还需要进一步发展。

For investigation of the prediction capability of turbulence models in PMB3 D software on aero-engine turbomachinery flowfiled,2nd order Roe scheme,LU-SGS time integration method and one equation S-A turbulence model are used to compute the NASA Rotor37 compressor. Correction is made on S-A model based on Van Driest near-wall formula and some analysis of the effects on the flow field are done. The results show that corrected S-A model gives a delayed stall point,and worse results of characteristic lines,outlet spanwise averaged total pressure,static pressure,total temperature and adiabatic effiency. However,tangent velocity and absolute angle are in better agreement with experimental data. This research shows that the numerical methods in PMB3 D software generally predict single-rotor compressor flow well and further improvements shold be done on the correction of S-A model.