Abstract: Models for computing the losses and deviation angles for multistage axial-flow compressors are proposed. By using the radial line error method, the performance characteristics of two multistage compressors with different flow patterns and airfoil blades are computed and compared with available experimental data. The flow field inside a two stage axial-flow compressor is computed and computed results are in good agreement with experimental data. It shows that the proposed models are accurate and universal. The radial line error method is suitable for single as well as multistage compressors.

Key words: Axial-flow compressor, Characteristics, Model