Abstract
This numerical study uses a two-stage low speed research compressor with a shrouded stator row to investigate the interaction of non-axisymmetric endwall contouring at the stator hub with the leakage flow emanating from the shroud cavity. It can be shown that the contour is effective in reducing the hub corner stall caused by the separating endwall boundary layer. The leakage flow itself is not reduced. Subsequently, the height of the shroud seal fins is varied. A comparison of the results with and without non-axisymmetric endwalls shows that the effectiveness of the endwall contour in improving stator performance increases with the amount of leakage flow. Consequently, the sensitivity towards shroud leakage is decreased with contoured endwall. This leads to the conclusion that this design feature does not only serve to improve the flow quality in a given case, but also provides a means to the aerodynamic designer to introduce more robustness into the compressor.
Published Version
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