Research Papers

Flow Control Over a Circular Cylinder Using Pulsed Dielectric Barrier Discharge Actuators

[+] Author and Article Information
William C. Schneck, III

Turbomachinery and Propulsion Laboratory,
Department of Mechanical Engineering,
Virginia Tech,
Blacksburg, VA 24061
e-mail: wschneck3@gmail.com

Walter F. O'Brien

J. Bernard Jones Professor of Mechanical
Turbomachinery and Propulsion Laboratory,
Department of Mechanical Engineering,
Virginia Tech,
Blacksburg, VA 24061
e-mail: walto@vt.edu

1Corresponding author.

Contributed by the International Gas Turbine Institute (IGTI) Division of ASME for publication in the JOURNAL OF TURBOMACHINERY. Manuscript received July 9, 2014; final manuscript received July 22, 2014; published online August 26, 2014. Editor: Ronald Bunker.

J. Turbomach 137(1), 011001 (Aug 26, 2014) (7 pages) Paper No: TURBO-14-1127; doi: 10.1115/1.4028236 History: Received July 09, 2014; Revised July 22, 2014

Immersed bodies such as struts, vanes, and instrumentation probes in gas turbine flow systems will, except at the lowest of flow velocities, shed separated wakes. These wakes can have both upstream and downstream effects on the surrounding flow. In most applications, surrounding components are designed to be in the presence of a quasi-steady or at least nonvariant flow field. The presence of unsteady wakes has both aerodynamic and structural consequences. Active flow control of wake generation can therefore be very valuable. One means to implement active flow control is by the use of plasma actuation. Plasma actuation is the use of strong electric fields to generate ionized gas that can be actuated and controlled using the electric fields. The controlling device can be based on AC, DC, or pulsed-DC actuation. The present research was conducted using pulsed-DC from a capacitive discharge power supply. The study demonstrates the applicability of, specifically, pulsed-DC plasma flow control of the flow on a circular cylinder at high Reynolds numbers. The circular cylinder was selected because its flow characteristics are related to gas turbine flowpath phenomena, and are well characterized. Further, the associated pressure gradients are some of the most severe encountered in fluid applications. The development of effective plasma actuators at high Reynolds numbers under the influence of severe pressure gradients is a necessary step toward developing useful actuators for gas turbine applications beyond laboratory use. The reported experiments were run at Reynolds numbers varying from 50,000 to 97,000, and utilizing various pulse frequencies. Further the observed performance differences with varying electric field strengths are discussed for these Reynolds numbers. The results show that flow behaviors at high Reynolds numbers can be influenced by these types of actuators. The actuators were able to demonstrate a reduction in both wake width and momentum deficit.

Copyright © 2015 by ASME
Your Session has timed out. Please sign back in to continue.


Lord, W. K., MacMartin, D. G., and Tillman, T. G., 2000, “Flow Control Opportunities in Gas Turbine Engines,” AIAA Paper No. 2000-2234. [CrossRef]
Rethmel, C., Little, J., Takashima, K., Sinha, A., Adamovich, I., and Samimy, M., 2011, “Flow Separation Control Over an Airfoil With Nanosecond Pulse Driven DBD Plasma Actuators,” AIAA Paper No. 2011-487 [CrossRef].
Im, S., Do, H., and Cappelli, M. A., 2011, “Plasma Control of a Turbulent Boundary Layer in an Unstarting Supersonic Flow,” AIAA Paper No. 2011-1143. [CrossRef]
Yamada, S., Shibata, K., Ishikawa, H., Honami, S., and Motoske, M., 2010, “Flow Behavior Behind a Circular Cylinder by DBD Plasma Actuators in Low Reynolds Number,” AIAA Paper No. 2010-549. [CrossRef]
Schlichting, H., and Gersten, K., 2003, Boundary Layer Theory, 8th ed., Springer-Verlag, Berlin.
Thompson, A. C., 2009, “Investigation and Simulation of Ion Flow Control Over a Flat Plate and Compressor Cascade,” Master's thesis, Virginia Tech, Blacksburg, VA.
Richard, M., Dunn-Rankin, D., Weinberg, F., and Carleton, F., 2006, “Maximizing Ion-Driven Gas Flows,” J. Electrostat., 64(6), pp. 368–376. [CrossRef]
Léger, L., Moreau, E., and Touchard, G. G., 2002, “Effect of a DC Corona Electrical Discharge on the Airflow Along a Flate Plate,” IEEE Trans. Ind. Appl., 38(6), pp. 1478–1485. [CrossRef]
Léger, L., Moreau, E., and Touchard, G. G., 2002, “Electrohydrodynamic Airflow Control Along a Flat Plate by a DC Surface Corona Discharge—Velocity Profile and Wall Pressure Measurements,” AIAA Paper No. 2002-2833. [CrossRef]
Matsuno, T., Ota, K., Kanatani, T., and Kawazoe, H., 2010, “Parameter Design Optimization of Plasma Actuator Configuration for Separation Control,” AIAA Paper No. 2010-4983. [CrossRef]
Corke, T. C., and Post, M. L., 2005, “Overview of Plasma Flow Control: Concepts, Optimization, and Applications,” AIAA Paper No. 2005-563. [CrossRef]
Takashima, K., Zuzeek, Y., Lempert, W. R., and Adamovich, I. V., 2010, “Characterization of a Surface Dielectric Barrier Discharge Plasma Sustained by Repetitive Nanosecond Pulses,” AIAA Paper No. 2010-4764. [CrossRef]
Jukes, T. N., and Choi, K., 2009, “Flow Control Around a Circular Cylinder Using Pulsed Dielectric Barrier Discharge Surface Plasma,” Phys. Fluids, 21(8), p. 084103. [CrossRef]
Nishihara, M., Takashima, K., Rich, J. W., and Adamovich, I. V., 2011, “Mach 5 Bow Shock Control by a Nanosecond Pulse Surface DBD,” AIAA Paper No. 2011-1144. [CrossRef]
Golub, V. V., Son, E. E., Saveliev, A. S., Sechenov, V. A., and Tereshonok, D. V., 2011, “Investigation of Vortex Structure Near the Surface of DBD-Actuator,” AIAA Paper No. 2011-154. [CrossRef]
Tkacik, P. T., 1980, “Cascade Perfomance of Double Circular Arc Compressor Blades at High Angles of Attack,” Master's thesis, Virginia Tech, Blacksburg, VA.
Gregory, J. W., Porter, C. O., and McLaughlin, T. E., 2008, “Circular Cylinder Wake Control Using Spatially Distributed Plasma Forcing,” AIAA Paper No. 2008-4198. [CrossRef]
Mertz, B. E., and Corke, T. C., 2011, “Single-Dielectric Barrier Discharge Plasma Actuator Modelling and Validation,” J. Fluid Mech., 669(2), pp. 557–583. [CrossRef]
Durscher, R., and Roy, S., 2011, “Induced Flow From Serpentine Plasma Actuators Acting in Quiescent Air,” AIAA Paper No. 2011-957. [CrossRef]
Wang, C. C., and Roy, S., 2011, “Geometry Effects of Dielectric Barrier Discharge on a Flat Surface,” AIAA Paper No. 2011-732. [CrossRef]
Moreau, E., Sosa, R., and Artana, G., 2008, “Electric Wind Produced by Surface Plasma Actuators: A New Dielectric Barrier Discharge Based on a Three-Electrode Geometry,” J. Phys. D: Appl. Phys., 41(11), p. 115204. [CrossRef]


Grahic Jump Location
Fig. 3

Close up photos of the cylinder actuators

Grahic Jump Location
Fig. 4

Electrical and positioning schematic of the cylinder electrodes. The red electrodes are at high voltage, and the black ones are grounded.

Grahic Jump Location
Fig. 1

Data collection apparatus

Grahic Jump Location
Fig. 5

Power supply schematic

Grahic Jump Location
Fig. 6

Schematic of the instrumentation setup

Grahic Jump Location
Fig. 7

Measured velocity profiles at different Reynolds numbers and reduced frequencies



Some tools below are only available to our subscribers or users with an online account.

Related Content

Customize your page view by dragging and repositioning the boxes below.

Related Journal Articles
Related eBook Content
Topic Collections

Sorry! You do not have access to this content. For assistance or to subscribe, please contact us:

  • TELEPHONE: 1-800-843-2763 (Toll-free in the USA)
  • EMAIL: asmedigitalcollection@asme.org
Sign In