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M. Staats, W. Nitsche, S.J. Steinberg, R. King
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. 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. 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.
Deutscher Luft- und Raumfahrtkongress 2015, Rostock
Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth e.V., Bonn, 2015
21,0 x 29,7 cm, 11 Seiten
Stichworte zum Inhalt:
active flow control, iterative learning controller, linear compressor cascade, non-steady compressor flow