Numerical Assessment of Virtual Control Surfaces for Compressor Blades

Dielectric Barrier Discharge Plasma Actuator for Load Alleviation and Instability Control in a Compressor Cascade

“…An accurate estimation of the drag coefficient CD is not a principal objective of this study, because the flow was assumed to be fully turbulent and RANS computations were used. Rough and finer mesh predict similar results, consistently with [15], [16] and [17]. This comparison shows that a mesh independent solution has been achieved and results are accurate.…”

Dynamic mode decomposition analysis of plasma aeroelastic control of airfoils in cascade

“…Conversely, SS actuation will provide effects comparable to those of a trailing edge spoiler, i.e., lift and nose-down pitching moment will be decreased [21,9]. The reliability of the numerical computations has been shown in [8,10,9,11], where space and time convergence studies, as well as comparison with experimental data, are reported.…”

“…Steady simulations showed a different effectiveness of the suction side actuation and the pressure side actuation [8]. That is, to obtain quantitatively comparable effects in the air loads (with opposite sign), a larger body force must be applied on the SS.…”

“…have not yet been thoroughly pursued. In previous works, the authors showed numerically that plasma actuators may be successfully employed as virtual control surfaces to reduce vibration [8,9] and to enlarge the flutter boundaries [10,11] on a linear compressor cascade.…”

“…non-actuated --and the plasma-equipped cascade, capable to reproduce accurately the unsteady behaviour of the blades. The decomposition is applied on the flow field issued by the computational fluid dynamic (CFD) assessments detailed in [8,10,9,11], in the actuated and non-actuated case. The capability of the proposed ROM in reproducing the most relevant flow dynamics is highlighted.…”