Supersonic compressor cascade flow control using plasma actuation at low Reynolds number

To control the supersonic compressor cascade flow at low Reynolds numbers, this paper describes the use of nanosecond dielectric barrier discharge (NS-DBD) plasma actuation for flow control, and presents the results of large-eddy simulations conducted to investigate the corresponding flow control effects. NS-DBD plasma actuation on both the blade pressure surface and suction surface induces a distorted flow structure (DFS) within the blade passage. In the case of NS-DBD plasma actuation on the blade pressure surface, the influence of the DFS on the flow is suppressed by a shock wave. Even so, the DFS can still trigger the instability in the shear layer between the separated flow and the mainstream flow. Shock-wave-induced large-scale flow separation on the blade pressure surface is then suppressed, and the overall total pressure loss of the blade passage is reduced by 7.4%, despite the increased shock wave loss from the reduced flow blockage within the blade passage. In the case of NS-DBD plasma actuation on the blade suction surface, the DFS is less effective in suppressing the shock-wave-induced small-scale flow separation on the blade suction surface. However, the DFS on the blade suction surface enhances the shock wave oscillations within the blade passage, and this suppresses the flow separation on the blade pressure surface. Published under an exclusive license by AIP Publishing.

Automated summary

This paper investigates the flow control effects of nanosecond dielectric barrier discharge (NS-DBD) plasma actuation on the supersonic compressor cascade flow at low Reynolds numbers through large-eddy simulations. The study shows that NS-DBD plasma actuation induces a distorted flow structure (DFS) on both the blade pressure surface and suction surface. Despite being suppressed by shock waves on the blade pressure surface, the DFS still triggers instability in the shear layer. The study also finds that the DFS on the blade pressure surface suppresses shock-wave-induced large-scale flow separation and reduces the overall total pressure loss of the blade passage by 7.4%.