DocumentCode :
1622082
Title :
Rotating stall control via bifurcation stabilization
Author :
Chen, Xiang ; Guoxiang Ga ; Martin, Phillip B. ; Zhou, Kemin
Author_Institution :
Dept. of Electr. & Comput. Eng., Louisiana State Univ., Baton Rouge, LA, USA
Volume :
3
fYear :
1998
Firstpage :
623
Abstract :
Rotating stall is a fundamental aerodynamic instability in axial flow compressors, induced by nonlinear bifurcation. It significantly reduces the performance of aeroengines. In this paper classical bifurcation theory is used to derive output feedback control laws in which throttle position is employed as actuator and pressure rise as output measurement. The challenge to the proposed control system is that the critical mode of the linearized system corresponding to rotating stall is neither controllable nor observable. Using the projection method, it is shown that the proposed control system is effective for elimination of rotating stall for the third-order Moore-Greitzer model
Keywords :
aerodynamics; aerospace engines; aircraft control; bifurcation; feedback; aerodynamic instability; aeroengines; axial flow compressors; bifurcation stabilization; critical mode; linearized system; nonlinear bifurcation; output feedback control laws; pressure rise; projection method; rotating stall control; third-order Moore-Greitzer model; throttle position; Actuators; Aerodynamics; Bifurcation; Compressors; Control system synthesis; Control systems; Output feedback; Position measurement; Pressure control; Pressure measurement;
fLanguage :
English
Publisher :
ieee
Conference_Titel :
Circuits and Systems, 1998. ISCAS '98. Proceedings of the 1998 IEEE International Symposium on
Conference_Location :
Monterey, CA
Print_ISBN :
0-7803-4455-3
Type :
conf
DOI :
10.1109/ISCAS.1998.704089
Filename :
704089
Link To Document :
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