Abstract: In order to study the multistage transonic compressor analysis issue， a throughflow method based on the general throughflow theory and streamline curvature (SLC) approach is presented to calculate the internal flow fields and the performance of transonic axial compressors. The approach includes some semi-empirical correlations established based on previous literatures， such as minimum loss incidence angle model， deviation model and total pressure loss model. In order to improve the prediction accuracy of the semiempirical model， considering the complex three-dimensional flow effect in the real compressor， some reasonable modifications were made for some early models， including a revised deviation model applied to the cascade with large deflection range， as well as a more reasonable prediction model of variable structure shock loss. Two transonic compressors are calculated and verified， and the calibration results are compared with the experimental results and three-dimensional numerical calculation. The comparison shows that the maximum prediction errors at design condition for total pressure ratio and efficiency are 4.1% and 1.1%， respectively. Characteristic prediction and the spanwise flow field parameters can also be calculated in line with the experimental value of the trend at the non-design conditions. In general， this computational method can be used to predict the performance of modern transonic axial multistage compressor.

Key words: Throughflow calculation; Streamline curvature approach; Transonic compressor; Loss and deviation model; Performance prediction

摘要： 为研究多级跨声速压气机的分析问题，以通流理论为基础，采用了一系列适用于跨声速压气机的攻角、落后角和损失等经验模型，发展了一套基于流线曲率法的通流计算程序来预测跨声速压气机流场及其工作特性。为提高经验模型的预测精度，考虑到真实压气机中复杂的三维流动效应，针对部分早期模型进行了合理改进，包括改进了落后角模型使其适用于更大弯度范围叶型，以及采用一种更为合理的可变结构激波损失预测模型。针对两台跨声速压气机算例进行了计算校验，并将校验结果与实验值和三维数值计算进行对比。对比表明，设计工况下总压比最大计算误差为4.1%，效率误差为1.1%，在非设计工况特性预测和展向流场参数计算中也能得到和实验值相符的变化趋势，该通流计算方法可为现代跨声速轴流多级压气机特性分析提供具有参考价值的预测结果。

关键词: 通流计算；流线曲率法；跨声速压气机；损失与落后角模型；特性预测