Experimental study for thrust enhancement of stratospheric propeller blade elements by unsteady plasma

doi:10.16568/j.0254-6086.201504013

Abstract

Abstract:

Based on Reynolds similar principles of plasma-induced jet and propeller blade element theory, experiment of propeller blade element wind tunnel was conducted. The effects of constant and unsteady model were compared, effect of different duty cycle and the frequency in unsteady model were studied. The results showed that: at the same voltage, the enhancement of propeller thrust was 9.8% by steady mode, unsteady mode was greater than the steady mode in enhancement of propeller thrust, the enhancement up to 20.4% in unsteady mode. The thrust enhancement of propeller blade elements by plasma was obvious with relative radius between 0.4 and 0.85, in order to improve energy efficiency, plasma actuator could be arranged between blade relative radius of 0.4 and 0.85. At the same frequency, enhancement of propeller thrust increased with duty cycle decreasing, and in duty cycle of 10%, the enhancement was greatest. At the same duty cycle, there existed an optimal frequency, it was 30Hz in which plasma enhanced propeller thrust the most.

Key words: Stratospheric, Propellers, Unsteady, Plasma, Wind tunnel experiment.

摘要：

基于等离子体诱导射流雷诺相似原则和螺旋桨叶素理论，开展了螺旋桨叶素地面风洞实验，比较了定常与非定常两种激励模式对螺旋桨拉力的影响，以及非定常模式下占空比、频率的影响。结果表明：相同电压幅值下，定常模式对螺旋桨拉力增效为9.8%，非定常模式对螺旋桨增效大于定常模式，非定常模式下最大增效 20.4%。螺旋桨桨叶相对半径在0.4 与0.85 之间时，非定常等离子体流动控制对螺旋桨叶素拉力增效较好，将等离子体激励器布置在桨叶相对半径0.4 与0.85 之间可提高能量利用率。相同重复频率下，螺旋桨增效随着占空比的减小而增大，占空比为10%时，增效最大。相同占空比下，重复频率存在一个最优值，频率为30Hz 时，等离子体对螺旋桨的增效最大。

关键词: 临近空间, 螺旋桨, 非定常, 等离子体, 风洞实验

CLC Number:

TL61+2

TIAN Xue-min, TIAN Xi-hui, CHE Xue-ke, NIE Wan-sheng, CHEN Qing-ya, JIANG Jia-wen, ZHOU Si-yin. Experimental study for thrust enhancement of stratospheric propeller blade elements by unsteady plasma[J]. NUCLEAR FUSION AND PLASMA PHYSICS, 2015, 35(4): 361-367.

田学敏，田希晖，车学科，聂万胜，陈庆亚，姜家文，周思引. 临近空间螺旋桨叶素非定常等离子体增效实验研究[J]. 核聚变与等离子体物理, 2015, 35(4): 361-367.

References

[1] Guo X, Zhu M. Ascent trajectory optimization for stratospheric airship with thermal effects[J]. Advances in Space Research, 2013, 52: 1097–1110.
[2] Liu P Q, Duan Z Z, Ma L C. Aerodynamics properties and design method of high efficiency-light propeller of stratospheric airships[A]. International Conference on Remote Sensing, Environment and Transportation Engineering, RSETE, 2011.
[3] 刘志仁, 王福新, 宋文滨, 等. 二维増升装置前缘缝翼的远场噪声分析[J]. 空气动力学报, 2012, 30(3): 388-393.
[4] 许成杰, 杨旭东, 朱敏. 临近空间桨梢小翼螺旋桨布局气动增效研究[J]. 航空计算技术. 2011,41(5): 61- 64.
[5] Yavuz T, Koc E, Kaynak B. Hydrodynamics performance of hydrofoil-slat arrangements in 3D analysis[J]. Energy Conversion and Management, 2013, 75: 44–50.
[6] 聂万胜, 程钰锋, 车学科. 介质阻挡放电等离子体流动控制研究进展[J]. 力学进展, 2012, 42(6): 722-734.
[7] Che X K, Nie W S, Shao T, et al. Study of flow fields induced by surface dielectric barrier discharge actuator in lowpressure air[J]. Physics of Plasmas, 2014, 21: 043508.
[8] Che X K, Shao T, Nie W S, et al. Numerical simulation on a nanosecond-pulse surface dielectric barrier discharge actuator in near space[J]. J. Phys. D: AppliedPhys., 2012, 45, 145201.
[9] 周思引, 车学科, 聂万胜, 等. 等离子体对超燃燃烧室凹腔性能影响的数值研究[J]. 推进技术, 2013, 34(7): 950-955.
[10] 程钰锋, 聂万胜, 车学科, 等. 不同压力下介质阻挡放电等离子体诱导流场演化的实验研究[J]. 物理学报, 2013, 62(10): 295-302.
[11] 李钢, 聂超群, 朱俊强, 等. 介质阻挡放电等离子体流动控制实验研究[J]. 工程热物理学报, 2008, 29(7): 1117-1120.
[12] Wang J J, Choi K S, Feng L H, et al. Recent development in DBD plasma flow control[J]. Progress in Aerospace Sciences, 2013, 62: 52-79.
[13] Corke C, Post M L. Overview of plasma flow control: concepts, optimization, and applications[A]. 43rd AIAA Aerospace Sciences Meeting and Exhibit. Reno, Nevada, 2005.
[14] Benard N, Jolibois J, Moreau E. Lift and drag performances of an axisymmetric airfoil controlled by plasma actuator[J]. J. Electrostatics, 2009, 67:133–139.
[15] Taleghani A S, Shadaram A, Mirzaei M. Effects of duty cycles of the plasma actuators on improvement of pressure distribution above a nlf0414 airfoil[J]. IEEE Transactions on Plasma Science, 2012, 40(5): 1434 -1440.
[16] 李应红, 梁华, 马清源, 等. 脉冲等离子体气动激励抑制翼型吸力面流动分离的实验[J]. 航空学报, 2008, 29(6): 1429-1435.
[17] 冯伟, 聂万胜, 屠恒章, 等. 脉冲等离子体流动控制机理研究[J]. 飞机设计, 2012, 32(6): 60-63.
[18] 刘沛清, 马利川, 段中茹, 等. 平流层飞艇螺旋桨相似准则分析与验证[J]. 北京航空航天大学学报, 2012, 38(7): 957-961.
[19] Cheng Y F, Che X K, Nie W S. Numerical study on propeller flow-separation control by DBD-plasma aerodynamic actuation[J]. IEEE Transactions on Plasma Science, 2013, 41(4): 892-898.
[20] 车学科, 聂万胜, 侯志勇, 等. 地面实验模拟高空等离子体流动控制效果研究[J]. 航空学报, 2015, 36(2): 441-448.
[21] Shao T, Zhang D D, Yu Y, et al. A compact repetitive unipolar nanosecond-pulse generator for dielectric barrier discharge application[J]. IEEE Transactions on Plasma Science, 2010, 38(7): 1651-1655.