成果報告書詳細
管理番号20130000000377
タイトル*平成23年度中間年報 省エネルギー革新技術開発事業先導研究 動的流れ場に対するプラズマ気流制御の最適化の研究開発
公開日2013/6/15
報告書年度2011 - 2011
委託先名株式会社東芝 独立行政法人宇宙航空開発機構
プロジェクト番号P09015
部署名省エネルギー部
和文要約1. 研究開発の内容及び成果等
本研究開発は、流体機械や移動体等、変動する流れ場で使用される幅広い流体機器に対し、空力特性の向上により飛躍的な省エネルギーを達成するために、プラズマ気流制御の要素技術を開発することを目的とし、動的流れ場に対するプラズマ気流制御の最適制御方法を開発するとともに、電源・電極の装置化開発を行って、システムの実用化可能性の見極めを実施する。平成23年度は、各研究項目に関して以下を実施した。
英文要約Title:Research and Development Program for Innovative Energy Efficiency Technology.
Research and development of plasma-flow-control technology in dynamically changing flow conditions (FY2010-FY2011) FY2011 Annual Report
In order to develop plasma-flow-control technology in dynamically changing flow conditions, wide-ranging experimental research and also numerical simulation research were carried out by The University of Tokyo, Tokyo Metropolitan University, Japan Aerospace Exploration Agency (JAXA) and TOSHIBA. TOSHIBA has planned and conducted the whole research as shown below in the last fiscal year.
Characteristics of induced flow accompanied with surface discharge were investigated by TOSHIBA using a dielectric-barrier type discharge electrode mounted on a flat plate. From measurements of average velocity of the induced flow, it was found that both dielectric constant of dielectric-barrier material and waveform of applied voltage were the key parameters which control efficiency of the induced flow.
Characteristics of streamer propagating in the surface discharge were investigated by The University of Tokyo using a high speed camera with an image intensifier. It was found that propagation length of the streamer was affected by both intrinsic capacitance and waveform of applied voltage.
Numerical simulations of the surface discharge were conducted by Tokyo Metropolitan University. The simulation results using a two-dimensional model explained phenomena appearing in the surface discharge qualitatively.
Lift enhancement mechanism by the plasma-flow-control for an oscillating airfoil in dynamic stall was investigated by JAXA using a NACA0012 airfoil of chord length of 200 mm with span length of 1000 mm. Lift coefficient was estimated by integrating surface pressures measured with fast response pressure transducers on the airfoil. Oscillating frequency of the airfoil was changed approximately from 1 Hz to 10Hz. Discharge electrode was located at leading-edge of the airfoil. Discharge voltage was changed form 2.5 kV to 4.25 kV, and duty cycle of the oscillating operation was 10 %. During pulse modulated voltage was applying to the discharge electrode, both a higher cycle-integrated lift and a improvement of lift cycle hysteresis were exhibited. Lift of the oscillating airfoil was improved approximately more than 10 %. It was found that the lift enhancement was correlated strongly with frequency of the oscillating operation. PIV measurement was also conducted to clarify flow control mechanism of the oscillating airfoil in dynamic stall. During pulse modulated voltage was applying to the electrode, clear vortices appeared at the leading-edge at high angle of attack, and moved along the airfoil surface toward trailing edge. These vortices bring entrainment of main flow and the lift enhancement of the oscillating airfoil can be achieved.
In order to investigate an aerodynamic effect of the plasma-flow-control for improving wind turbine performance, wind tunnel experiments were carried out by TOSHIBA using a small wind turbine with a large wind tunnel facility. Discharge electrodes were mounted on the leading edge of each blade of the wind turbine. It was found that output performance was clearly improved in low velocity region.
Investigations for improving the discharge electrode and the power source were also conducted by TOSHIBA. A couple of suitable dielectrics were selected and durability of them was evaluated considering the actual wind turbine environment. Specification of the power source for controlling dynamically changing flow condition was decided.
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