ACTIVE CONTROL OF INLET DISTORTED FLOW FIELD IN COMPRESSOR INLET

The feasibility of alleviating the destabilizing effect of the inlet circumferential total pressure distortion on an axial compressor by active control of individually adjustable inlet guide vanes(LAIGV) has been qualitatively analyzed under the parallel compressor hypothesis. The result shows that when the distortion is quasi-steady it is possible to use the actively controlled LA1GV with a relatively simple proportional control scheme to adjust the flow angle, and thus to prevent the compressor entering the unstable state. For a typical blade setting the angular adjustment of LA1GV needed to cope with 10 % total pressure distortion is of only few degrees.