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 ef...

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Bibliographic Details
Published in:Physics of fluids (1994) 2022-02, Vol.34 (2)
Main Authors: Wang, Yizhou, Zhang, Haideng, Wu, Yun, Li, Yinghong, Zhu, Yujie
Format: Article
Language:English
Subjects:
Actuation
Cascade flow
Dielectric barrier discharge
Flow control
Flow separation
Flow stability
Fluid dynamics
Fluid flow
Large eddy simulation
Plasma
Pressure loss
Reynolds number
Separation
Shear layers
Suction
Supersonic compressors
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Summary: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.
ISSN:1070-6631
1089-7666
DOI:10.1063/5.0081685