direkt zum Inhalt springen

direkt zum Hauptnavigationsmenü

Sie sind hier

TU Berlin

Inhalt des Dokuments

Publikationen am FG Aerodynamik

Closed-loop active flow control of a non-steady flow field in a highly-loaded compressor cascade
Zitatschlüssel Staats2016
Autor Staats, M. and Nitsche, W. and Steinberg, S. J. and King, R.
Seiten 1–12
Jahr 2016
ISSN 1869-5590
DOI 10.1007/s13272-016-0232-1
Journal CEAS Aeronautical Journal
Zusammenfassung The provision of secure compressor operation under circumstances of a pulsed detonation engine is crucial for the success of pressure gaining combustion processes for turbo machinery applications. This paper discusses active flow control as a possible solution to approach this challenge. The presented experiments were conducted on a highly loaded low speed linear compressor stator cascade operated at $$Re=600,000$$ R e = 600 , 000 and $$Ma =0.07$$ M a = 0.07 . A choking-device which was located in the wake of the cascade simulated the non-steady outflow condition that is expected under the conditions of pressure gaining combustion. In the discussed experiments, the choking-device generated a periodic disturbance to every passage at a typical Strouhal number of $$Sr =0.03$$ S r = 0.03 . The flow structures of the non-steady flow field were strongly correlated to the working-phase of the choking-device. In this paper, an iterative learning controller was used to find an optimized actuation trajectory that was used for closed-loop sidewall-actuation to control the corner separation in the non-steady flow field. The iterative learning controller took advantage of the periodicity of the disturbance to calculate a non-steady actuation trajectory that optimally suppressed the impact of the choking-device on the flow. The active flow control effect was evaluated by means of static pressure rise using five hole probe measurements in the wake of one passage.
Link zur Publikation Download Bibtex Eintrag

Zusatzinformationen / Extras


Schnellnavigation zur Seite über Nummerneingabe