Performance prediction of transonic axial compressor based on streamline curvature method

Abstract

The streamline curvature (SLC) method is still of great importance for modern compressor performance prediction. The models applied in it, such as minimum incidence, deviation and loss, affect prediction’s accuracy directly. An improved SLC approach is introduced in this paper, which is developed based on the analysis and summary of predecessor’s works. The improvement is embodied mainly in the incidence and loss, which is the result of a combination of the previous models and models’ revisions in order to consider the main effects for modern compressor cascade. A certain isolated stage axial transonic compressor is calculated by SLC method. The speed lines and span-wise aerodynamic parameters are compared with the experiment data to demonstrate the SLC approach presented in this paper.