Recommendation of Experimental Setup and use of Standardized Electrohydrodynamic Dimensionless Parameters for Optimization of a Dielectric Barrier Discharge Flow Control Device

2014 ◽  
Author(s):  
Joseph Dygert ◽  
Melissa Morris ◽  
Patrick Browning
Keyword(s):  
Flow Control ◽  
Dielectric Barrier Discharge ◽  
Barrier Discharge ◽  
Control Device ◽  
Experimental Setup ◽  
Dielectric Barrier ◽  
Dimensionless Parameters ◽  
Discharge Flow ◽  
Flow Control Device

Towards In-Flight Applications? A Review on Dielectric Barrier Discharge-Based Boundary-Layer Control

2016 ◽  
Vol 68 (2) ◽  
Author(s):  
Jochen Kriegseis ◽  
Bernhard Simon ◽  
Sven Grundmann
Keyword(s):  
Boundary Layer ◽  
Flow Control ◽  
Dielectric Barrier Discharge ◽  
Barrier Discharge ◽  
Control Device ◽  
Boundary Layer Control ◽  
Detailed Knowledge ◽  
Dielectric Barrier ◽  
Flow Control Device ◽  
Layer Control

Active control of laminar boundary layers with dielectric barrier discharge (DBD) plasma actuators (PAs) has made considerable progress in the last 15 years. First pioneering experiments have motivated numerous researchers to gain a deeper insight into the underlying working principles and corresponding quantification of the actuator performance. These investigations clearly show the strengths but also the weaknesses of the PA as a flow control device. Presently, the boundary-layer control (BLC) with PAs experiences the transition from lab studies to real flight applications. However, the PA community still struggles with the poor fluid mechanic efficiency and the limited momentum flux of the actuator. This review therefore addresses the question how applicable the actuator is as an energy efficient flow control device for future in-flight applications. Since any successful flow control requires detailed knowledge of the actuator’s control authority, this discussion is built upon a careful and comprehensive summary of performance evaluation measures and the interplay with various changes of thermodynamic and kinematic environmental conditions. Consequently, this review for the first time provides a comprehensive discussion of all required steps for successful DBD-based in-flight flow control spanning from the power supply to the achieved flow-control success in one coherent document.

Dielectric Barrier Discharge Flow Control at Very Low Flight Reynolds Numbers

AIAA Journal ◽  
2008 ◽  
Vol 46 (6) ◽  
pp. 1528-1541 ◽  
Author(s):  
David Greenblatt ◽  
Berkant Goksel ◽  
Ingo Rechenberg ◽  
Chan Yong Schule ◽  
Daniel Romann ◽  
...  
Keyword(s):  
Flow Control ◽  
Dielectric Barrier Discharge ◽  
Barrier Discharge ◽  
Reynolds Numbers ◽  
Dielectric Barrier ◽  
Discharge Flow

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

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).

Improved performance of polyimide Cirlex‐based dielectric barrier discharge plasma actuators for flow control

2021 ◽  
Author(s):  
João Nunes‐Pereira ◽  
Frederico Freire Rodrigues ◽  
Mohammadmahdi Abdollahzadehsangroudi ◽  
José Carlos Páscoa ◽  
Senentxu Lanceros‐Mendez
Keyword(s):  
Flow Control ◽  
Dielectric Barrier Discharge ◽  
Discharge Plasma ◽  
Barrier Discharge ◽  
Plasma Actuators ◽  
Dielectric Barrier Discharge Plasma ◽  
Dielectric Barrier ◽  
Barrier Discharge Plasma ◽  
Improved Performance

scholarly journals Coherent structures induced by dielectric barrier discharge plasma actuator

2017 ◽  
Vol 31 (32) ◽  
pp. 1850038 ◽  
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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