一种基于全三维数值计算的多级轴流压气机喘振边界预测方法

A Prediction Method based on Full Three-Dimensional Numerical Calculation for Predicting the Surge Margin of the Multistage Axial Compressor

提出一种基于全三维数值计算的多级轴流压气机喘振边界预测方法。该方法采用了NUMECA和ANSYS/CFX两种不同的商业软件,在充分考虑压气机几何结构特征的基础上,根据压气机各级叶片排结构特点,建立了通用的压气机叶片排网格拓扑结构,并从各个方向对压气机叶片排网格节点进行控制来保证压气机叶片排各向网格节点一致。对不同负荷类型、不同结构型式的压气机特性进行了算例分析,并就流量、压比和效率等压气机特性参数进行对比研究。结果表明:该喘振边界预测方法对不同压气机具有较高的适用性,计算结果与试验结果也比较吻合。

A method for predicting the surge boundary of multistage axial compressors based on full three-dimensional numerical calculation is proposed.Two different kinds of commercial software IGG/AutoGrid5 and ANSYS/CFX are used in this method.On the basis of fully considering the geometry characteristics of compressor, according to the structural characteristics of each level of compressor blade row, a general compressor blade grid topology structure is established.The predicted performance based on a variety of compressors with different load types and structure forms was conducted.The performance parameters of these compressors such as massflow, pressure ratio and efficiency were analyzed.The results show that the method proposed has good accuracy and high applicability to different kinds of compressors.The predicted results are in good agreement with the experimental results.