Effects of noise and actuator limits on active control of rotating stall and surge

Operability enhancement is one of the major goals for active control of rotating stall and surge in aeroengines. Based on the Moore Greitzer model (1986), we derive a normal form which gives explicit dependence of the stall and surge inception process on compressor parameters especially the shape of the compressor characteristic. Analysis of the normal form with bleed valve actuator dynamics shows that under certain circumstances the “bang-on” control law gives the largest operability enhancement