The increase of the thrust-to-weight ratio of modern gas-turbine engines results in higher
loads and a reduced number of blades and stages for the compressor. The designer must
ensure the acceptable performance of each compressor stage (efficiency and stable
operating range) and control the rising risk of blade boundary layer separation. This can be
obtained using passive or active control devices which act on the behavior of the tip leakage
flows or the endwall corner stall when the operating point gets closer to the stall or surge …