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Reduced Order Modeling for Plasma Aeroelastic Control of Airfoils in Cascade: Dynamic Mode Decomposition
Citation key 2018_neumann_p_iutam
Author Neumann, P. and Motta, V. and Malzacher, L. and Phan, T. D. and Liebich, R. and Peitsch, D. and Quaranta, G.
Year 2018
Location Santorini, Greece
Journal IUTAM Symposium
Month 06
Note Technische Universität Berlin:
P. Neumann, V. Motta, L. Malzacher, T. D. Phan, R. Liebich, D. Peitsch
Politecnico di Milano:
G. Quaranta
Editor IUTAM
Abstract A dynamic mode decomposition is carried out for the flow field of a compressor cascade with plasma actuators employed for aeroelastic control. Numerical assessments carried out in previous works have shown that alternate triggering of pressure side/suction side actuators installed at the trailing edge of the blades can effectively reduce vibratory loads and enlarge the flutter boundaries of a linear compressor cascade. With the twofold aim of having an in depth understanding of the flow physics associated to plasma actuation and of developing an optimized control law for the actuators, the dominant structures of the pressure field are extracted via a dynamic mode decomposition. The decomposition is conducted on the actuated and non actuated pressure fields at several inter blade phase angles. The fundamental effects of plasma actuations on the flow field, and in turn on the blade loading, are identified and discussed. The procedure allows to get an useful picture of the main fluid mechanic phenomena associated to plasma aeroelastic control on turbomachinery bladings.
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