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Numerical Investigation of Virtual Control Surfaces for Aeroelastic Control on Compressor Blades
Zitatschlüssel 2017_motta_ifasd
Autor Motta, V. and Malzacher, L. and Peitsch, D.
Seiten IFASD-2017-137
Jahr 2017
Ort Como, Italy
Journal IFASD - 17th International Forum on Aeroelasticity and Structural Dynamics
Monat 06
Notiz Technische Universität Berlin:
V. Motta, L. Malzacher, D. Peitsch
Herausgeber IFASD
Zusammenfassung Virtual control surfaces are assessed numerically as a means to enhance the aeroelas- tic response of a compressor cascade. Virtual surfaces are realized with plasma actuators placed on the pressure and on the suction side of the blade trailing edge. Advantages of plasma ac- tuators over mechanical control surfaces are the absence of failure risks when operating under centrifugal and temperature fields typical of compressors used in aero engines. The plasma- induced flow is meant to be against the direction of the freestream. This allows for generating controlled recirculating flow areas and in turn modifying the effective blade camber and enlarg- ing the actual chord. Computational fluid dynamic analyses with the blades at constant angle of attack show that the effects of pressure side actuation on flow field, pressure distribution and integral loads are comparable to those of flap-like devices. On the contrary suction side actua- tion yields effects which are analogous to those of wing spoilers. Traveling wave simulations for the torsion mode show that properly triggering an alternate pressure/suction side actuation during the pitching cycle improves significantly the blade aeroelastic stability. At the same time an effective reduction in the peaks of the oscillating airloads is achieved, with potential benefits for the alleviation of fatigue.
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