The objective of this paper is to investigate the effects of Dielectric Barrier Discharge (DBD) plasma actuators on the aeroelastic control of a subsonic compressor cascade, for unsteady load mitigation and enhancement in the cascade aeroelastic response. Numerical simulations of the blades oscillating in traveling wave mode are performed with the commercial solver Ansys FLUENT®. Results are then validated through comparison with experimental data to assess the stability and convergence of the reference grid. Aeroelastic control is achieved by means of two AC-DBD plasma actuators installed on the trailing edge of the compressor blades, one on the suction side and one on the pressure side. Alleviation of the blade load is realized by operating alternately the actuators through a cosinusoidal function. Moreover, the effect of the actuation force phase on the blade load control is evaluated. Based on the actuation phase, results show that it is possible to manipulate effectively the unsteady lift and moment coefficients, stabilizing the compressor performance, alleviating fatigue phenomena and enlarging the flutter limits of the cascade. Plasma actuators confirm to be a very promising technology for active flow control in turbomachines and aeronautical applications.
Comparison of different plasma actuation strategies for aeroelastic control on a linear compressor cascade
De Giorgi M. G.;Suma A.;
2021-01-01
Abstract
The objective of this paper is to investigate the effects of Dielectric Barrier Discharge (DBD) plasma actuators on the aeroelastic control of a subsonic compressor cascade, for unsteady load mitigation and enhancement in the cascade aeroelastic response. Numerical simulations of the blades oscillating in traveling wave mode are performed with the commercial solver Ansys FLUENT®. Results are then validated through comparison with experimental data to assess the stability and convergence of the reference grid. Aeroelastic control is achieved by means of two AC-DBD plasma actuators installed on the trailing edge of the compressor blades, one on the suction side and one on the pressure side. Alleviation of the blade load is realized by operating alternately the actuators through a cosinusoidal function. Moreover, the effect of the actuation force phase on the blade load control is evaluated. Based on the actuation phase, results show that it is possible to manipulate effectively the unsteady lift and moment coefficients, stabilizing the compressor performance, alleviating fatigue phenomena and enlarging the flutter limits of the cascade. Plasma actuators confirm to be a very promising technology for active flow control in turbomachines and aeronautical applications.I documenti in IRIS sono protetti da copyright e tutti i diritti sono riservati, salvo diversa indicazione.
