Performance Prediction of Transonic Axial Compressors Using Improved Streamline Curvature Approach

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The paper describes an improved streamline curvature approach (SLC) to the flow field analysis and performance prediction of transonic axial compressors. The previous research concerning the incidence angle, deviation angle, and total pressure loss models is discussed. Many semi-empirical correlations and curve fits were based on two-dimensional cascade experiments, resulting in evident discrepancy between the calculated results and the actual experimental data, especially in endwall regions. The approach suggested in this study makes improvements embodied mainly in the deviation revision taking into account the endwall effect, which acts as the combination of aerodynamic and geometry parameters. The program is applied to predict the performance of two transonic axial compressors, a single-stage compressor NASA Stage37 and a two-stage fan TP1493. The characteristic curves and spanwise aerodynamic parameter distributions under design and off-design conditions are illustrated. Moreover, the results acquire satisfactory precision compared with the experimental data. This through-flow method is verified as an reliable and applicable tool for the aerodynamic design and analysis of transonic axial compressors during the design stage.