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A Physically Consistent Reduced Order Model for Plasma Aeroelastic Control on Compressor Blades
Citation key 2018_motta_75080-asme
Author Motta, V. and Malzacher, L. and Peitsch, D. and Quaranta, G.
Pages GT2018-75080
Year 2018
ISBN 978-0-7918-5115-9
DOI 10.1115/GT2018-75080
Location Oslo, Norway
Journal ASME Turbo Expo 2018: Turbomachinery Technical Conference and Exposition
Volume Volume 7C: Structures and Dynamics
Month 06
Note V07CT36A004,
Technische Universit├Ąt Berlin:
V. Motta, L. Malzacher, D. Peitsch
Politecnico di Milano:
G. Quaranta
Editor ASME
Series Turbo Expo: Power for Land, Sea, and Air
Abstract Plasma actuators may be successfully employed as virtual control surfaces, located at the trailing edge of blades, both on the pressure and on the suction side, to control the aeroelastic response of a compressor cascade. Actuators generate an induced flow against the direction of the freestream. As a result, actuating on the pressure side yields an increase in lift and nose down pitching moment, whereas the opposite is obtained by operating on the suction side. A properly phased alternate pressure/suction side actuation allows to reduce vibration and to delay the flutter onset. This paper presents the development of a linear frequency domain reduced order model for lift and pitching moment of the plasma-equipped cascade. Specifically, an equivalent thin airfoil model is used as a physically consistent basis for the model. Modifications in the geometry of the thin airfoil are generated to account for the effective chord and camber changes induced by the plasma actuators, as well as for the effects of the neighboring blades. The model reproduces and predicts correctly the mean and the unsteady loads, along with the aerodynamic damping on the plasma equipped cascade. The relationship between the parameters of the reduced order model with the flow physics is highlighted.
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