Journal of Aeronautical Engineering

Journal of Aeronautical Engineering

Experimental Study of the Effect of Dielectric Barrier Discharge Plasma Actuator on the Flow Separation of Linear Cascade Compressor Blades

Document Type : Original Article

Authors
1 Malek-ashtar university of technology
2 Amirkabir university of technology
3 Iran Aviation Industries Organization
10.22034/joae.2024.432759.1214
Abstract
Attention to plasma actuators as a tool for active flow control has been rapidly growing in recent years. This device, by injecting momentum, accelerates the fluid on the surface, which can be used to control flow separation. In the current study, the control of flow separation in an axial compressor cascade by plasma actuator and boundary layer suction, both separately and simultaneously, has been investigated. To study the effects of the plasma actuator and boundary layer suction on flow control, the flow characteristics, such as the static pressure ratio and the total pressure loss coefficient, have been experimentally evaluated with and without the plasma actuator, as well as the effect of boundary layer suction at different suction rates. Experimental results show that the use of plasma actuator at low speeds reduces total pressure loss and hence improves performance. Moreover, this experimental study indicates that the performance of the compressor cascade with the plasma actuator and boundary layer suction simultaneously, at suction rates of 25, 50, 75, and 100 percent at a speed of 10 meters per second, respectively improves by 13.3, 14, 15, and 17 percent, showing better results compared to using only boundary layer suction.
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Volume 26, Issue 2
February 2025
Pages 59-76

  • Receive Date 28 December 2023
  • Revise Date 18 April 2024
  • Accept Date 13 July 2024