We investigated a non-steady compressor stator flow of the type that would be expected in a pulsed detonation engine. The effects on the stator vane of the last stator stage were discussed and results from the two-dimensional compressor stator cascade in Berlin are presented. Static pressure measurements showed periodic flow separation phenomena on the measurement blade with respect to the working-phase of a choking-device mounted in the wake of the cascade imposing the non-steady outflow condition. By means of active flow control (AFC) it was possible to avoid flow separation on the measurement blade. Furthermore a figure of merit was defined in order to rate the increase of static pressure recovery with respect to the AFC input. Using an optimized AFC setup the flow-field could be stabilized.
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