Performance prediction and analysis of multi-stage transonic axial compressors

An improved streamline curvature method (SLCM) which approximates the aerodynamic performance of transonic axial compressor through the inverse problem is developed. The loss and deviation model based on NASA low speed cascade test data is modified for a more realistic estimation considering transonic and 3-D flow phenomena. Moreover, a new shock loss estimation method in which the shock structure changes along with working condition is incorporated into the streamline curvature code (SLCC). The design and off-design performance of a two-stage transonic axial fan is predicted and the comparison with NASA original design and experiment data is made. The results show that the calculation error of design point is below 1.1% and consistent trend with test data is obtained at off-design conditions, which indicates that the improved SLCM is capable of overall performance predication for multistage transonic axial compressor efficiently.