一种跨声速轴流压气机性能预测的数值方法

Numerical method of transonic axial compressor performance prediction

采用二维流线曲率法数学方法,考虑到不同因素对落后角和损失的影响,发展了一种适应于跨声速轴流压气机的落后角和损失模型.对轴流跨声速压气机NASA(National Aeronautics and Space Administration)Stage 37进行了数值计算,得到了设计点与非设计点的特性曲线,并与试验数据进行了对比和分析,结果表明:该方法能够较好地预测跨声速轴流压气机特性以及沿径向的气动参数分布,可为压气机设计和优化提供参考.

The deviation and loss models were developed by taking into account different influential factors using two-dimensional streamline curvature mathematic method at off-design conditions.The internal flow field of NASA（National Aeronautics and Space Administration） Stage 37 was calculated,and then the characteristic curves of design and off-design points were obtained.Through comparison between simulation and experimental values,the results show that the predicted characteristics and parameters distribution of compressor are in good agreement with the experimental values.This method can predict the performance and span-wise aerodynamic parameters of transonic axial compressor with better accuracy and can be used for compressor design and optimization.