Abstract: Axial compressors are key elements for the performance of modern aero-engines. The main aerodynamic phenomena limiting their operating rage are instabilities known as ‘rotating stall’ and ‘surge’, which can have dramatic effect on the machine or its environment. They deprive the compressor from its higher pressure ratios.
The use of an active flow control system blowing continuous or pulsed jets at the compressor rotor tip to avoid or post-pone rotating stall is introduced and tested on a single stage axial compressor test bench. The effect of the different control parameters on the efficiency of the control system is discussed and an analysis of the effect of the flow physics in the blade passage is proposed.