Stator Blade Row Geometry Modification Influence on Two-Stage, Axial-Flow Compressor Aerodynamic Performance

摘要

The influence of stator row geometry modification on the aerodynamic performance of a two-stage, low-speed, axial-flow research compressor was assessed in the experiments described in this project. Stator geometry modifications tested included stator leading edge forward symmetrical sweep, large-radius blade/annulus wall corner fillets, and stator hub gap sealing (shrouding). Comparisons were made between detailed aerodynamic data associated with baseline and modified configurations. Substantial stator exit flow-field changes attributable to symmetrical sweeping of stator leading edges and to hub clearance sealing were observed with some evidence of corresponding near end wall loss reduction. The effects of large radii filleting were less clear. Interesting conclusions about the off-design flow rate performance of the compressor also resulted from consideration of experimental data. (Author)