Aerodynamic Performance Prediction of Highly Loaded Single-Stage Axial-Flow Low-Speed Compressor

Aerodynamic performance of highly loaded low-speed axial-flow compressor stage was computed by means of commercial code Fluent. The computed data were compared with experimental results obtained in test stage with external diameter of 600 mm. At design condition one could observe reasonable agreement. The difference between theoretical and measured characteristics increased with the growing distance of stage working point from design point. This conclusion is supported by the comparison of experimental and computed rotor and stator blade elements performance at three typical working conditions.