一种控制气流分离的无源微脉冲射流技术研究
收稿日期: 2012-10-15
修回日期: 2013-05-17
网络出版日期: 2013-05-20
基金资助
国家自然科学基金(51176072);江苏省普通高校研究生科研创新基金(CXLX11_0216)
Investigation of Technology for Controlling Flow Separation by Micro-pulsed-jet Without External Device
Received date: 2012-10-15
Revised date: 2013-05-17
Online published: 2013-05-20
Supported by
National Natural Science Foundation of China (51176072);Funding of Jiangsu Innovation Program for Graduate Education (CXLX11_0216)
基于压气机在大负荷下发生气流分离的流动特征提出了一种无源引气微脉冲射流控制的概念,并对其核心的脉冲射流器进行了特性实验分析,结果表明脉冲射流器能产生明显的脉冲射流且射流频率无级可调。结合无源脉冲射流控制方式建立了一套仿叶栅通道实验模型,得到了无流动控制时通道内稳态及动态压力特性,在设计状态下通道内分离涡主频为266 Hz。对该分离流场进行了脉冲射流控制通道内气流分离的实验研究,实验测量了频率从60 Hz到600 Hz的微脉冲射流对分离流的控制效果。实验结果表明:从通道总压损失减小的效果来看,当脉冲射流频率接近分离涡主频时控制效果最为明显。此时通道内占主导地位的分离涡的周期性特性得到了明显的改善,其他频率的旋涡对流场的影响程度在脉冲射流的作用下被削弱,流场结构较无控、定常射流控制及其他脉冲射流频率状态更为有序。
朱剑锋 , 黄国平 , 傅鑫 , 付勇 . 一种控制气流分离的无源微脉冲射流技术研究[J]. 航空学报, 2013 , 34(8) : 1757 -1767 . DOI: 10.7527/S1000-6893.2013.0261
Based on the flow separation characteristics in a compressor, a micro pulsed aspirated jet concept is presented and experiments are conducted on them, which shows that an obvious pulsed jet can be generated and the jet frequency can be continuously adjusted.Combined with this new unsteady control method, an imitating cascade channel is established. The steady and dynamic pressure characteristics in the no control state are obtained, and the characteristic frequency of the separated vortex is found to be about 266 Hz. Finally, the experiment of controlling separation flow by pulsed jet is performed, and the frequency of the pulsed jet lies between 60-600 Hz. Results show that when the frequency of the pulsed jet is close to the characteristic frequency of the separated vortex, the control effect is more obvious. Meanwhile, the periodic characteristics of the dominant vortex are significantly improved, while the influence of other vortices on the flow field is weakened. The flow structure is more orderly in comparison to no control, steady control and other frequency pulsed control states.
Key words： pulsed jet; unsteadiness; flow separation; imitating cascade channel; experiment
[1] Rivir R B, Bons J P, Lake J P. Passive and active control of separation in gas turbines. AIAA-2000-2235, 2000.
[2] Hergt A, Meyer R, Engel K. Experimental investigation of flow control in compressor cascades. ASME Paper, GT-2006-90415, 2006.
[3] Guo M, Zheng X Y, Zhou S, et al. BVF application on blowing control of flow separation of a compressor cascade. Journal of Aerospace Power, 2008, 23(8): 1498-1503. (in Chinese) 郭明, 郑晓宇, 周盛, 等. BVF在吹气控制压气机叶栅分离流中的应用. 航空动力学报, 2008, 23(8): 1498-1503.
[4] Schuler B J, Kerrebrock J L, Merchant A. Experimental investigation of a transonic aspirated compressor. Journal of Turbomachinery, 2005, 127(4): 340-348.
[5] Greenblatt D, Wygnanski I J. The control of flow separation by periodic excitation. Progress in Aerospace Sciences, 2000, 36(7): 487-545.
[6] Luo Z B, Xia Z X. Advances in synthetic jet technology and applications in flow control. Advances in Mechanics, 2005, 35(2): 221-234. (in Chinese) 罗振兵, 夏智勋. 合成射流技术及其在流动控制中应用的进展. 力学进展, 2005, 35(2): 221-234.
[7] Zhang P F, Wang J J, Feng L H. Review on the zero-net-mass-flux jet and the application in separation flow control. Science in China Series E: Technological Science, 2008, 51(9): 1315-1344.(in Chinese) 张攀峰, 王晋军, 冯立好. 零质量射流技术及其应用研究进展. 中国科学E辑: 技术科学, 2008, 51(9): 1315-1344.
[8] Zhang P F, Yan B, Dai C F. Lift enhancement method by synthetic jet circulation control. Science in China Series E: Technological Science, 2012, 55(9): 2585-2592.(in Chinese) 张攀峰, 燕波, 戴晨峰. 合成射流环量控制翼型增升技术. 中国科学E辑: 技术科学, 2012, 55(9): 2585-2592.
[9] Hecklau M, Wiederhold O, Zander V, et al. Active separation control with pulsed jets in a critically loaded compressor cascade. AIAA-2010-4252, 2010.
[10] Gmelin C, Zander V, Huppertz A, et al. Active flow control concepts on a highly loaded subsonic compressor cascade: resume of experimental and numerical results. ASME Paper, GT-2011-46468, 2011.
[11] Zheng X Q, Zhou X B, Zhou S. Investigation on a type of flow control to weaken unsteady separated flows by unsteady excitation in axial flow compressors. Journal of Turbomachinery, 2005, 127(7): 489-496.
[12] Zheng X Q, Zhou S, Lu Y J, et al. Flow control of annular compressor cascade by synthetic jets. Journal of Turbomachinery, 2008, 130(2): 021018.1-021018.7.
[13] Hoeger M, Baier R D, Fischer S, et al. High turning compressor tandem cascade for high subsonic flows, Part 1: aerodynamic design. AIAA-2011-5601, 2011.
[14] Müller L, Ko?ulovi?y D, Wulff D, et al. High turning compressor tandem cascade for high subsonic flows-Part 2: numerical and experimental investigations.AIAA-2011-5602, 2011.
[15] Pernod P, Preobrazhensky V, Merlen A, et al. MEMS magneto-mechanical microvalves (MMMS) for aerodynamic active flow control. Journal of Magnetism and Magnetic Materials, 2010, 322(9): 1642-1646.
[16] Hou A P, Zhou S. A study on vortex shessing frequency of blade profile and cylinder in cascade tunnel. Acta Aerodynamica Sinica, 2004, 22(1): 101-108. (in Chinese) 侯安平, 周盛. 对圆柱和二维扩压叶栅在平面叶栅风洞中旋涡脱落的试验研究. 空气动力学学报, 2004, 22(1): 101-108.
[17] Zhang H L. Investigation on application of dihedral/swept blade and boundary layer suction to control vortex configuration in compressor cascades. Harbin: School of Energy Science and Engineering, Harbin Institute of Technology, 2004. (in Chinese) 张华良. 采用叶片弯/掠及附面层抽吸控制扩压叶栅内涡结构的研究. 哈尔滨: 哈尔滨工业大学能源科学与工程学院, 2004.
/
| 〈 |
|
〉 |
CJA