Jet Flow Control by DBD Plasma Actuator: Effect of Electrode Dimensions on Jet Diffusion

ASME-JSME-KSME 2011 Joint Fluids Engineering Conference: Volume 1, Symposia – Parts A, B, C, and D ◽

10.1115/ajk2011-25002 ◽

2011 ◽

Author(s):

Hongyu Jin ◽

Takashi Ono ◽

Motoaki Kimura

Keyword(s):

Flow Control ◽

Barrier Discharge ◽

Jet Flow ◽

Plasma Actuator ◽

Plasma Actuators ◽

Dbd Plasma ◽

Flow Control Devices ◽

Induced Flow ◽

Control Devices ◽

Effective Conditions

Dielectric barrier discharge (DBD) plasma actuators have been investigated by many researchers as flow-control devices. In the present study, we attempt to apply such actuators to a jet flow. In order to achieve enhanced mixing in a jet flow, we focused on the voltage and the frequency of the plasma actuator to examine their effect on the velocity and turbulence of the jet flow. This time, we examined how the induced flow by the plasma actuator electrode dimensions occurred. It was expected that higher velocity would have a larger effect on the jet flow in last year. In this study, we measured the flow velocity for different voltages and frequencies, and determined the most effective conditions for generating the induced flow. We apply that DBD plasma actuators to enhance turbulent intensity and jet flow’s diffusion.

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Dielectric Barrier Discharge (DBD) Plasma Actuators for Flow Control in Turbine Engines: Simulation of Flight Conditions in the Laboratory by Density Matching

International Journal of Turbo and Jet Engines ◽

10.1515/tjj-2018-0021 ◽

2019 ◽

Vol 36 (2) ◽

pp. 157-173

Author(s):

David E. Ashpis ◽

Douglas R. Thurman

Keyword(s):

Flow Control ◽

Dielectric Barrier Discharge ◽

Barrier Discharge ◽

Test Chamber ◽

Plasma Actuators ◽

Chamber Pressure ◽

Turbine Engines ◽

Dbd Plasma ◽

Dielectric Barrier ◽

Actuator Performance

Abstract We address requirements for laboratory testing of AC Dielectric Barrier Discharge (AC-DBD) plasma actuators for active flow control in aviation gas turbine engines. The actuator performance depends on the gas discharge properties, which, in turn, depend on the pressure and temperature. It is technically challenging to simultaneously set test-chamber pressure and temperature to the flight conditions. We propose that the AC-DBD actuator performance depends mainly on the gas density, when considering ambient conditions effects. This enables greatly simplified testing at room temperature with only chamber pressure needing to be set to match the density at flight conditions. For turbine engines, we first constructed generic models of four engine thrust-classes; 300-, 150-, 50-passenger, and military fighter, and then calculated the densities along the engine at sea-level takeoff and altitude cruise conditions. The range of chamber pressures that covers all potential applications was found to be from 3 to 1256 kPa (0.03 to 12.4 atm), depending on engine-class, flight altitude, and actuator placement in the engine. The engine models are non-proprietary and can be used as reference data for evaluation requirements of other actuator types and for other purposes. We also provided examples for air vehicles applications up to 19,812 m (65,000 ft).

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Coherent structures induced by dielectric barrier discharge plasma actuator

Modern Physics Letters B ◽

10.1142/s0217984918500380 ◽

2017 ◽

Vol 31 (32) ◽

pp. 1850038 ◽

Cited By ~ 3

Author(s):

Xin Zhang ◽

Huaxing Li ◽

Kwing So Choi ◽

Longfei Song

Keyword(s):

Flow Control ◽

Dielectric Barrier Discharge ◽

Coherent Structures ◽

High Speed ◽

Barrier Discharge ◽

Plasma Actuator ◽

Dbd Plasma ◽

Peak Voltage ◽

Dielectric Barrier ◽

Piv Measurement

The structures of a flow field induced by a plasma actuator were investigated experimentally in quiescent air using high-speed Particle Image Velocimetry (PIV) technology. The motivation behind was to figure out the flow control mechanism of the plasma technique. A symmetrical Dielectric Barrier Discharge (DBD) plasma actuator was mounted on the suction side of the SC (2)-0714 supercritical airfoil. The results demonstrated that the plasma jet had some coherent structures in the separated shear layer and these structures were linked to a dominant frequency of [Formula: see text] = 39 Hz when the peak-to-peak voltage of plasma actuator was 9.8 kV. The high speed PIV measurement of the induced airflow suggested that the plasma actuator could excite the flow instabilities which lead to production of the roll-up vortex. Analysis of transient results indicated that the roll-up vortices had the process of formation, movement, merging and breakdown. This could promote the entrainment effect of plasma actuator between the outside airflow and boundary layer flow, which is very important for flow control applications.

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Flow Control on a Transport Truck Side Mirror Using Plasma Actuators

Journal of Fluids Engineering ◽

10.1115/1.4030724 ◽

2015 ◽

Vol 137 (11) ◽

Cited By ~ 13

Author(s):

Theodoros Michelis ◽

Marios Kotsonis

Keyword(s):

Flow Control ◽

Guide Vane ◽

Leading Edge ◽

Plasma Actuator ◽

Plasma Actuators ◽

Dbd Plasma ◽

Reference Case ◽

Image Velocimetry ◽

Wind Tunnel Study ◽

Edge Separation

A wind tunnel study is conducted toward hybrid flow control of a full scale transport truck side mirror at ReD=3.2×105. A slim guide vane is employed for redirecting high-momentum flow toward the mirror wake region. Leading edge separation from the guide vane is reduced or eliminated by means of an alternating current -dielectric barrier discharge (AC-DBD) plasma actuator. Particle image velocimetry (PIV) measurements are performed at a range of velocities from 15 to 25 m/s and from windward to leeward angles from -5deg to 5deg. Time-averaged velocity fields are obtained at the center of the mirror for three scenarios: (a) reference case lacking any control elements, (b) guide vane only, and (c) combination of the guide vane and the AC-DBD plasma actuator. The comparison of cases demonstrates that at 25 m/s windward conditions (-5deg) the guide vane is capable of recovering 17% momentum with respect to the reference case. No significant change is observed by activating the AC-DBD plasma actuator. In contrast, at leeward conditions (5deg), the guide vane results in a −20% momentum loss that is rectified to a 6% recovery with actuation. The above implies that for a truck with two mirrors, 23% of momentum may be recovered.

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Optimization and Evaluation of Multiple DBD Plasma Actuators Applied in the Tip Leakage Control for Turbine Cascade

Volume 2D: Turbomachinery ◽

10.1115/gt2019-90208 ◽

2019 ◽

Author(s):

Jianyang Yu ◽

Wenchun Bao ◽

Fu Chen ◽

Yanping Song ◽

Cong Wang

Keyword(s):

Flow Control ◽

Mass Flow ◽

Suction Side ◽

Plasma Actuator ◽

Plasma Actuators ◽

Leakage Flow ◽

Tip Leakage Flow ◽

Dbd Plasma ◽

Tip Leakage ◽

Leakage Control

Abstract The dielectric barrier discharge (DBD) plasma actuator, in which electrodes are asymmetric arranged, has already demonstrated its ability in flow control. In the present work, the configuration of multiple plasma actuators is placed at the suction side of the cascade top to realize the tip leakage control. However, massive configurations appear when the number of plasma actuators increases, resulting in the investigation of actuator configuration for tip leakage flow control becomes a challenge. The surrogate modelling approach provides a cheap and efficient method to investigate the effect of multiple plasma actuators on the tip leakage flow control. By constructing an approximation model, tip leakage mass flow rates of all configuration are obtained in the present work. What’s more, the flow structures in the tip clearance controlled by the plasma actuators are explained in the process of topological analysis. The results show that the tip leakage mass flow rate is decreasing with the number of active plasma actuators increasing. However, the decreasing would reach its limits in the process of adding plasma actuators. In the analysis of flow topology, single actuator would generate a small vortex at the suction side to cause an obstacle in the tip leakage flow. While the continuous arrangements of plasma actuator is beneficial to generate an induced vortex to diminish the tip leakage flow.

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Test Conditions for Performance Characterization of Dielectric Barrier Discharge (DBD) Plasma Actuators for Active Flow Control in Jet Engines

Volume 1: Aircraft Engine; Ceramics; Coal, Biomass and Alternative Fuels; Wind Turbine Technology ◽

10.1115/gt2011-46583 ◽

2011 ◽

Author(s):

David E. Ashpis ◽

Douglas R. Thurman

Keyword(s):

Flow Control ◽

Dielectric Barrier Discharge ◽

Barrier Discharge ◽

Active Flow Control ◽

Plasma Actuators ◽

Dbd Plasma ◽

Dielectric Barrier ◽

Jet Engine ◽

Active Flow

Dielectric Barrier Discharge (DBD) plasma actuators for active flow control in the jet engine need to be tested in the laboratory to characterize their performance at flight operating conditions. DBD plasma actuators generate a wall-jet electronically by creating weakly ionized plasma, therefore their performance is affected by gas discharge properties, which in turn depend on the pressure and temperature at the actuator placement location. Characterization of actuators is initially performed in a laboratory chamber without external flow. It is usually impractical to simultaneously set engine pressures and temperatures in a chamber, and a simplified approach is desired. It is assumed that the plasma discharge depends only on the gas density. Other temperature effects are assumed to be negligible. Therefore, tests can be performed at room temperature with chamber pressure set to yield the same density as in engine operating flight conditions. Engine data was obtained from four generic engine models; 300-, 150-, and 50-Passenger (PAX) aircraft engines, and a military jet-fighter engine. The static and total pressure, temperature, and density distributions along the engine were calculated for sea-level takeoff and altitude cruise, and the chamber pressures needed to test the actuators were calculated. The results show that testing has to be performed over a wide range of pressures from 12.4 to 0.03 atm, depending on the application. For example, if a DBD plasma actuator is to be placed at the compressor exit of a 300 PAX engine, it has to be tested at 12.4 atm for takeoff, and 6 atm for cruise conditions. If it is to be placed at the low-pressure turbine, it has to be tested at 0.5 and 0.2 atm, respectively. These results have implications for the feasibility and design of DBD plasma actuators for jet engine flow control applications. In addition, the distributions of unit Reynolds number, Mach number, and velocity along the engine are provided. The engine models are non-proprietary and this information can be used for evaluation of other types of actuators and for other purposes.

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Experimental and Numerical Analysis of a Micro Plasma Actuator for Active Flow Control in Turbomachinery

Volume 2A: Turbomachinery ◽

10.1115/gt2014-25337 ◽

2014 ◽

Cited By ~ 10

Author(s):

Maria Grazia De Giorgi ◽

Elisa Pescini ◽

Fedele Marra ◽

Antonio Ficarella

Keyword(s):

Flow Control ◽

Active Flow Control ◽

Plasma Actuator ◽

The Body ◽

Plasma Actuators ◽

Compressor Cascade ◽

Barrier Discharge Plasma ◽

Induced Flow ◽

The One ◽

Active Flow

Nowadays several active flow control systems, particularly dielectric barrier discharge plasma actuators, appear to be effective for the control of flow stream separation and to improve performance of turbomachinery. However these applications require high actuation strength, higher than the one generated by conventional macro plasma actuators. Research is actually improving the design of plasma actuator in order to enhance the flow control capability and reduce the power consumption. In this contest, this work concerns the implementation of a micro plasma actuator for the active control in a compressor cascade. For this aim, firstly the micro actuator was developed and an experimental characterization of the flow induced by the device was done. The induced flow field was studied by means of Particle Image Velocimetry and Laser Doppler Velocimetry. The dissipated power was also evaluated. Experimental results were used to validate a multi-physics numerical model for the prediction of the body forces induced by the plasma actuator. Finally, the obtained body force field was used for modeling the separation control by means of the micro plasma actuator in a highly-loaded subsonic compressor stator.

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Plasma Actuators for Boundary Layer Control of Next Generation Nozzles

Volume 1: Advances in Aerospace Technology ◽

10.1115/imece2015-52193 ◽

2015 ◽

Cited By ~ 2

Author(s):

F. Rodrigues ◽

José C. Páscoa ◽

F. Dias ◽

M. Abdollahzadeh

Keyword(s):

Boundary Layer ◽

Dielectric Layer ◽

Jet Flow ◽

Plasma Actuator ◽

Plasma Actuators ◽

Boundary Layer Control ◽

Next Generation ◽

Dbd Plasma ◽

Ionized Air ◽

Layer Control

DBD plasma actuators are simple devices comprising two electrodes separated by a dielectric layer. One of the electrodes is covered by the dielectric layer and is completely insulated from the other one, which is exposed to the atmosphere in the top of the dielectric layer. The DBD plasma actuator operates by applying to the two electrodes an high voltage at high frequency from a power supply. When the amplitude of the applied voltage is large enough, in the exposed electrode, an ionization of the air (plasma) occurs over the dielectric surface which, in the presence of the electric field gradient, produces a body force on the ionized air particles. This induces a flow that draws ionized air along the surface of the actuator and it accelerates this neutral air towards downstream, in a direction tangential to the dielectric. Herein we will present this next generation plasma actuator for boundary layer control, which is demonstrated on the acceleration of the flow in a Coanda nozzle wall, thus contributing to help vectoring the exit jet flow. It will be shown that using only the plasma actuator it will be possible to vectorize the exit jet flow even under pure axial flow at the nozzle exit. Experimental results are obtained using flow visualization and Particle Image Velocimetry.

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Single-dielectric barrier discharge plasma actuator modelling and validation

Journal of Fluid Mechanics ◽

10.1017/s0022112010005203 ◽

2011 ◽

Vol 669 ◽

pp. 557-583 ◽

Cited By ~ 48

Author(s):

BENJAMIN E. MERTZ ◽

THOMAS C. CORKE

Keyword(s):

Flow Control ◽

Dielectric Barrier Discharge ◽

Body Force ◽

Barrier Discharge ◽

Plasma Actuator ◽

Time Dependent ◽

Plasma Actuators ◽

Force Vector ◽

Dielectric Barrier ◽

Flow Simulations

Single-dielectric barrier discharge (SDBD) plasma actuators have gained a great deal of world-wide interest for flow-control applications. With this has come the need for flow-interaction models of plasma actuators that can be used in computational flow simulations. SDBD plasma actuators consist of two electrodes: one uncovered and exposed to the air and the other encapsulated by a dielectric material. An AC electric potential is supplied to the electrodes. When the AC potential is large enough, the air in the region over the encapsulated electrode ionizes. The ionized air in the presence of the electric field results in a space–time dependent body force vector field. The body force is the mechanism for flow control. This study describes a semi-empirical model that has been developed to capture the dynamic nature of the local air ionization and time-dependent body force vector distribution. Validation of the model includes comparisons to experimentally measured space–time charge distribution and the time-resolved and time-averaged body force. Two flow simulations are then used to further validate the SDBD plasma actuator model. These involved an impulsively started plasma actuator in still air, and the flow around a circular cylinder in which plasma actuators were used to suppress the Karman vortex street. In both cases, the simulations agreed well with the experiments.

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