Abstract
Three-dimensional corner separation usually gets worse under the mutual interaction between the boundary layer and shock wave, thus greatly influencing supersonic compressor blades in aerodynamic performance. This study proposed adopting the blade slotting technology to control the serious shock-wave-induced corner separation and investigated the effects of the slot height. The results showed that, the low-energy fluid accumulated in the corner region can be enough re-energized by the slot jet with high momentum, thus effectively reducing its mutual interference with the shock wave and suppressing its separation. The velocity and mass-flow of the slot jet get larger as the slot height increases. But when the momentum contained in the slot jet has been able to enough re-energize the local boundary layer, a larger jet mass-flow will slightly worsen the aerodynamic performance. To better improve the overall aerodynamic performance in a wide inlet airflow angle (β1) range, it is better to choose the slot height that can just resist the migration of hub secondary flow at the maximum β1. In the current study, this suitable slot height can increase the static pressure coefficient by an average of 26.0% and reduce the total pressure loss by 10.8% on average in the β1 range of 57.1°∼61.5°. It is significantly beneficial for the future higher-load compressor to achieve a larger total pressure ratio, higher efficiency, and better working stability.
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