Abstract
This article presents a novel concept for coupled boundary layer control in transonic axial compressors. Proposed control scheme utilizes two steady active methods and couples them creating compact and in principle passive boundary layer control method. Both presented methods (steady suction and steady tangential blowing) are known since many years. In this article they are presented in the context of coupling them on two neighbouring stages. Presented analysis shows that the proposed solution allows for very high stage loadings and pressure ratios. The concept is presented on the set of transonic cascades, where it shows to prevent separation in regions of high adverse pressure gradients (associated both with occurrence of shockwaves and high aerodynamic loading).
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