Bulletin of the American Physical Society
62nd Annual Gaseous Electronics Conference
Volume 54, Number 12
Tuesday–Friday, October 20–23, 2009; Saratoga Springs, New York
Session GT2: Actuators and Flow Control |
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Chair: David Smith, General Electric Room: Saratoga Hilton Ballroom 2 |
Tuesday, October 20, 2009 10:00AM - 10:15AM |
GT2.00001: Thrust Enhancing Designs for single DBD Plasma Actuators Song Guo, Uwe Kortshagen Dielectric Barrier Discharge (DBD) plasma actuator can be used for the separation control of the air foil applications, whose performance is directly related to the thrust which is generated during the discharge. To obtain more efficient performance, designs which can produce more thrust than the conventional single DBD plasma actuator were made by exploring the asymmetry of the discharge and introducing a semi-conductive layer on the top of the dielectric surface. Direct thrust measurement proved that the new designs can increase the thrust by 70{\%} compared to the traditional plasma actuator, when operated on the same input voltage and discharge frequency. Measurement also showed evidence that by increasing the conductivity of the semi-conductive layer, the thrust will increase. [Preview Abstract] |
Tuesday, October 20, 2009 10:15AM - 10:30AM |
GT2.00002: Experimental investigations of a simple DBD-based flow actuator Yacine Babou, Anna-Elodie Kerlo, Sebastien Paris Optical, electrical and effectiveness measurements of a single dielectric-barrier discharge (DBD)-based flow actuator operating in ambient quiescent air will be presented. actuator is constituted by two thin alumina foil electrodes asymmetrically displayed on both sides of a dielectric (MACOR) plate ($\sim $50 cm$^{2})$ and powered by an AC sinus high frequency ($\sim $10 kHz) high voltage ($\sim $10 kV peak-peak). The experiments were done for a wide range of configurations and operating conditions. The current in the electrical circuit is constituted of a periodic contribution and of short pulses of few ns related to streamers propagation. Thermodynamic state was characterized by means of conventional optical emission spectroscopy technique. A typical gas temperature of 295 K is obtained with the N$_{2}$second positive system rotational bands, whereas vibrational temperature is about 2500 K. The induced flow velocity and the produced thrust were gauged by means of simple techniques and are respectively of order 1 m/s and 0.1 g. Unsteady operations and applications to realistic situations will be presented. [Preview Abstract] |
Tuesday, October 20, 2009 10:30AM - 10:45AM |
GT2.00003: Separation control using plasma actuator: Simulation of plasma actuator Meenakshi Mamunuru, Douglas Ernie, Terry Simon, Uwe Kortshagen We have simulated dielectric barrier discharge in atmospheric pressure air on a two dimensional domain approximating the plasma actuator geometry. The applied voltage to the exposed electrode is a nanosecond range Gaussian pulse with amplitude of 3.5 kV. When a positive pulse was applied, the plasma was intense. A higher thrust was obtained in the downstream direction. When a negative pulse was applied, a weaker plasma and smaller thrust in the opposite direction were seen. The charge accumulation on the dielectric, and the streamer formation process were seen to be drastically different for both the cases. The component of thrust acting perpendicularly down on the actuator surface was seen to be larger than the force in parallel direction for both discharges. We have examined the importance of including photoionization in the air chemistry. A thin semi-conducting layer on the dielectric would drain the charge after a discharge cycle and prevent the occurrence of a reverse discharge, and enhance the time averaged thrust in the downstream direction. We have included a thin conducting layer on the dielectric in our simulations and obtained preliminary results. [Preview Abstract] |
Tuesday, October 20, 2009 10:45AM - 11:00AM |
GT2.00004: Simulations of Thermal Phenomena in Nanosecond Pulsed Plasma Discharged in Supersonic Flows Doug Breden, Laxminarayan Raja The use of nanosecond repetitively pulsed plasmas to ignite and sustain ignition and combustion in supersonic flows has shown promise in recent years. While it is known that radicals produced by the plasma are the primary drivers for enhancing combustion, there is some uncertainty concerning whether radical production is due primarily to electron-impact dissociation or thermal dissociation. We use a self-consistent, multi-species plasma solver is coupled with a compressible Navier-Stokes fluid solver to simulate the temperature field and radical number densities for an H$_{2}$-O$_{2}$ mixture and pure argon. Temperature increases of $\sim $100-1000 K occur in the cathode near-field region for both mixtures where the electron temperature peaks at $\sim $40 eV in H$_{2}$-O$_{2}$ and $\sim $20 eV in argon for voltages of -1000 V and -400 V respectively. Radical production of O, H and OH is observed to occur in streamers separate from thermal heating regions. O radicals are seen with number densities as high as 10$^{21}$ cm$^{-3}$, H densities on the order of 10$^{19}$ cm$^{-3}$ and OH radicals densities of 10$^{17}$cm$^{-3}$. From these results, it can be concluded that radical production is due primarily to electron-impact dissociation in the streamers, while thermal effects are due to electron-joule heating in the cathode sheath. [Preview Abstract] |
Tuesday, October 20, 2009 11:00AM - 11:15AM |
GT2.00005: ABSTRACT WITHDRAWN |
Tuesday, October 20, 2009 11:15AM - 11:30AM |
GT2.00006: ABSTRACT WITHDRAWN |
Tuesday, October 20, 2009 11:30AM - 11:45AM |
GT2.00007: Numerical and Experimental Investigations of Plasma Actuators Based on Magnetogasdynamics Chiranjeev Kalra, Sohail Zaidi, Mikhail Shneider, Richard Miles Numerical and experimental studies were conducted of magnetically driven DC surface plasma discharges. Their application to supersonic boundary layer control is investigated, specifically the shockwave-turbulent boundary layer interaction problem and the induced separation control is shown. This interaction causes incoming boundary layer thickening and localized pressure loads and high heating rates. In the case of scramjet engine inlet this results in reduced effective cross-section and loss of thrust and efficiency. Magnetogasdynamic flow control is achieved by generating a plasma column close to the wall in boundary layer and dragging the gas close to the wall using Lorentz force due to perpendicular (to flow direction as well as current) magnetic field. The surface plasma column appears as a transverse ``arc'' between two slightly diverging electrodes which is driven by j x B forces so that it sweeps the gas near the surface in the separated region or the recirculation zone, either in the downstream direction or in the upstream direction. Depending on the direction of Lorentz force, separation bubble is either induced in the boundary layer or the shockwave induced bubble is reduced in intensity and probably eliminated. It is shown that these interactions between the plasma and the recirculation zone are non-thermal in nature. [Preview Abstract] |
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