Efficient Performance Prediction of a one-and-half Stage Axial Compressor based on a Streamline-Curvature Throughflow Method and Stage Characteristics

Abstract

The blade modeling of axial compressor mostly adopts curved and swept design, which results in strong three-dimensional unsteady effects in the compressor. Experiment is the main method to obtain the flow field and characteristics of compressors, but it needs too much time and money. Compared with experiments, throughflow calculation and Computational Fluid Dynamics (CFD) save the cost in the design stage greatly. With the increase of compressor load, compressor blades become lighter and thinner, which leads to the blades deviating from the design profile. The manufacturing deviation may influence the aerodynamic performance and stability boundary of compressors. The key issue is how to predict the influence of manufacturing deviation on the compressor aerodynamic performance in the design stage. As the manufacturing deviations are random, it will occupy a huge amount of computing resources if we add deviations to CFD models directly. To solve this problem, we propose a method based on stage data, which is expected to predict the impact of manufacturing deviations on the aerodynamic performance of the compressor quickly. The reliable loss and deviation models based on stage data can predict the spanwise flow field parameters and performance of the compressor better.