Accession Number : ADA320346

Title :   Bifurcation Based Nonlinear Feedback Control for Rotating Stall in Axial Compressors,

Corporate Author : WRIGHT LAB WRIGHT-PATTERSON AFB OH

Personal Author(s) : Gu, Guoxiang ; Sparks, Andrew ; Banda, Siva

PDF Url : ADA320346

Report Date : APR 1996

Pagination or Media Count : 18

Abstract : Classical bifurcation analysis for nonlinear dynamics is used to derive a nonlinear feedback control law that eliminates the hysteresis loop associated with rotating stall and extends the stable operating range in axial compressors. The proposed control system employs pressure rise as output measurement and throttle position as actuating signal for which both sensor and actuator exist in the current configuration of axial compressors. Thus our results provide a practical solution for rotating stall control in axial compressors.

Descriptors :   *ENGINES, *TURBINES, *AXIAL FLOW COMPRESSORS, PRESSURE GRADIENTS, OUTPUT, THROTTLING, MEASUREMENT, POSITION(LOCATION), CONTROL SYSTEMS, AIRCRAFT ENGINES, DYNAMICS, STALLING, NONLINEAR SYSTEMS, FEEDBACK, SIGNALS, CONFIGURATIONS, ACTUATORS, CONTROL THEORY, LOOPS, ROTATION, HYSTERESIS, ACTUATION.

Subject Categories : Jet and Gas Turbine Engines
      Aircraft

Distribution Statement : APPROVED FOR PUBLIC RELEASE