Abstract
A boundary layer suction strategy is tested in a centrifugal compressor stage designed and built by Safran Helicopter Engines. According to previous numerical results, suction slots are disposed in the radial diffuser at the hub and the shroud near the vane suction side. Experimental results performed in the compressor without any boundary layer suction at partial speed showed a specific feature consisting in a two-channel pattern in the radial diffuser characterized by one stalled passage over two. If throttled the compressor experiences mild surge during which both rotating instabilities and alternate stall co-exist, the latter being then highly unsteady. When the boundary layer suction is activated no surge margin improvement is registered. However, the boundary layer suction allows to revert the pattern in the radial diffuser and to improve the compressor performance both at design and off-design operating points depending on the location of the boundary layer strategy.
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