Effects of Plasma Aerodynamic Actuation on Corner Separation in a Highly Loaded Compressor Cascade

WANG Xuede(王学德); ZHAO Xiaohu(赵小虎); LI Yinghong(李应红); WU Yun(吴云); ZHAO Qin(赵勤)

doi:10.1088/1009-0630/16/3/13

Plasma Science and Technology > 2014 > 16(3): 244-250. > DOI: 10.1088/1009-0630/16/3/13

WANG Xuede(王学德), ZHAO Xiaohu(赵小虎), LI Yinghong(李应红), WU Yun(吴云), ZHAO Qin(赵勤). Effects of Plasma Aerodynamic Actuation on Corner Separation in a Highly Loaded Compressor Cascade[J]. Plasma Science and Technology, 2014, 16(3): 244-250. DOI: 10.1088/1009-0630/16/3/13

Citation:

PDF (9567 KB)

Effects of Plasma Aerodynamic Actuation on Corner Separation in a Highly Loaded Compressor Cascade

Science and Technology on Plasma Dynamics Laboratory, Air Force Engineering University, Xi’an 710038, China

Funds: supported by National Natural Science Foundation of China (Nos.50906100, 10972236), Foundation for the Author of National Excellent Doctoral Dissertation of China (No.201172)

More Information

Received Date: September 13, 2012

Graphical Abstract

Abstract

Abstract

This paper reports experimental results on the effects of plasma aerodynamic actua- tion (PAA) on corner separation control in a highly loaded, low speed, linear compressor cascade. Total pressure loss coefficient distribution was adopted to evaluate the corner separation control effect in wind tunnel experiments. Results of pressure measurements and particle image velocime- try (PIV) show that the control effect of pitch-wise PAA on the endwall is much better than that of stream-wise PAA on the suction surface. When both the pitch-wise PAA on the endwall and stream-wise PAA on the suction surface are turned on simultaneously, the control effect is the best among all three PAA types. The mechanisms of nanosecond discharge and microsecond discharge PAA are different in corner separation control. The control effect of microsecond discharge PAA turns out better with the increase of discharge voltage and duty cycle. Compared with microsec- ond discharge PAA, nanosecond discharge PAA is more effective in preventing corner separation when the freestream velocity increases. Frequency is one of the most important parameters in plasma flow control. The optimum excitation frequency of microsecond discharge PAA is 500 Hz, which is different from the frequency corresponding to the case with a Strouhal number of unity.
- plasma aerodynamic actuation,
- corner separation,
- compressor,
- cascade

FullText(HTML)

References (23)

References

1 Dickens T, Day I. 2011, Journal of Turbomachinery,133: 031007;

2 Shabbir A, Adamczyk J J. 2005, ASME Journal of Turbomachinery, 127: 708;

3 Beheshti B H, Teixeira J A, Ivey P C, et al. 2004,ASME Journal of Turbomachinery, 126: 527;

4 Volino R J. 2003, ASME Journal of Turbomachinery,125: 765;

5 Mailach R, Vogeler K. 2004, ASME Jourmal of Tur-bomachinery, 126: 35;

6 Gbadebo S A, Cumpsty N A, Hynes T P. 2008, ASME Journal of Turbomachinery, 130: 011004;

7 Zheng X Q, Hou A P, Zhou S. 2005, Control of un-steady separated °ows inside axial compressors by syn-thetic jets. Presented at the 43rd AIAA Aerospace Sciences Meeting and Exhibit, AIAA Paper No. 2005-0870, Reno, Nevada, American Institute of Aeronau-tics and Astronautics ;

8 Roth J R, Sherman D M. Wilkinson S R. 2000, AIAA Journal, 38: 1166;

9 Corke T C, Post M L. 2005, Overview of plasma °ow control: concepts, optimization, and applications, Pre-sented at the 43rd AIAA Aerospace Sciences Meet-ing and Exhibit, AIAA Paper No. 2005-0563, Reno,Nevada, American Institute of Aeronautics and As-tronautics ;

10 Enloe C L, McLaughlin T, Font G I, et al. 2006, AIAA Journal, 44: 1127;

11 Cristofolini A, Neretti G, Roveda F, et al. 2011, Ex-perimental and numerical investigation on a DBD ac-tuator for air°ow control. Presented at the 42nd AIAA Plasmadynamics and Lasers Conference, AIAA Paper No. 2011-3912, Honolulu, Hawaii, American Institute of Aeronautics and Astronautics ;

12 Belson B A, Meidell K, Hanson R E, et al. 2012, Com-parison of plasma actuators in simulations and experi-ments for control of bypass transition. Presented at the 50th AIAA Aerospace Sciences Meeting, AIAA Paper No. 2012-1141, Nashville, Tennessee, American Insti-tute of Aeronautics and Astronautics;

13 Bisek N J, Poggie J, Nishihara M, et al. 2012, Com-putational and experimental analysis of Mach 5 air °ow over a cylinder with a nanosecond pulse discharge.Presented at the 50th AIAA Aerospace Sciences Meet-ing, AIAA Paper No. 2012-186, Nashville, Tennessee,American Institute of Aeronautics and Astronautics;

14 Rethmel C, Little J, Takashima K, et al. 2011, Flow separation control over an airfoil with nanosecond pulse driven DBD plasma actuators. Presented at the 49th AIAA Aerospace Sciences Meeting, AIAA Paper No. 2011-487, Orlando, Florida, American Institute of Aeronautics and Astronautics ;

15 Poggie J, Bisek N J, Adamovich I V, et al. 2012, Nu-merical simulation of nanosecond-pulse electrical dis-charges. Presented at the 50th AIAA Aerospace Sci-ences Meeting, AIAA Paper No. 2012-1025, Nashville,Tennessee, American Institute of Aeronautics and As-tronautics;

16 Ma C, Li H X, Liu F, et al. 2011, PIV study on steady and periodic-pulsed dielectric barrier discharges, Pre-sented at the 49th AIAA Aerospace Sciences Meeting,AIAA Paper No. 2011-1303, Orlando, Florida, Amer-ican Institute of Aeronautics and Astronautics;

17 Vo H D. 2007, Control of rotating stall in axial com-pressors using plasma actuators. Presented at the 37th AIAA Fluid Dynamics Conference and Exhibit. AIAA Paper No. 2007-3845, Miami, FL, American Institute of Aeronautics and Astronautics ;

18 Wu Y, Li Y H, Zhu J Q, et al. 2007, Experimental in-vestigation of a subsonic compressor with plasma ac-tuation treated casing. Presented at the 37th AIAA Fluid Dynamics Conference and Exhibit. AIAA Pa-per No. 2007-3849, Miami, FL, American Institute of Aeronautics and Astronautics;

19 Li Y H, Wu Y, Zhou M, et al. 2010, Experiments in Fluids, 48: 1015;

20 Zhao X H, Wu Y, Li Y H, et al. 2012, Acta Mechanica Sinica, 27: 1280;

21 Post M L, Corke T C. 2006, AIAA Journal, 44: 3125;

22 Huang J, Corke T C, Thomas F O, et al. 2006, AIAA Journal, 44: 1477;

23 Zhao X H, Li Y H, Wu Y, et al. 2012, Chinese Journal of Aeronautics, 25: 349 (in Chinese)

[1]	Xiaogang YUAN (袁小刚), Haishan ZHOU (周海山), Haodong LIU (刘皓东), Bo LI (李波), Yong WANG (王勇), Lei CHANG (苌磊), Xin YANG (杨鑫), Chuang WANG (汪闯), Lupeng ZHANG (张潞鹏), Guangnan LUO (罗广南). Particle flux characteristics of a compact high-field cascaded arc plasma device[J]. Plasma Science and Technology, 2021, 23(11): 115402. DOI: 10.1088/2058-6272/ac1fd8
[2]	Jier QIU (邱吉尔), Deping YU (余德平), Yihong LI (李裔红), Lei LI (李磊), Tong YANG (杨彤), Yuqing DONG (董宇庆). Design and characteristics of a triple-cathode cascade plasma torch for spheroidization of metallic powders[J]. Plasma Science and Technology, 2020, 22(11): 115503. DOI: 10.1088/2058-6272/aba8ed
[3]	Qianhan HAN (韩乾翰), Chenyu WU (武晨瑜), Ying GUO (郭颖), Jianjun SHI (石建军). Temporal evolution of atmospheric cascade glow discharge with pulsed discharge and radio frequency discharge[J]. Plasma Science and Technology, 2020, 22(3): 34014-034014. DOI: 10.1088/2058-6272/ab6760
[4]	Zheng LI (李铮), Zhiwei SHI (史志伟), Hai DU (杜海), Qijie SUN (孙琪杰), Chenyao WEI (魏晨瑶), Xi GENG (耿玺). Analysis of flow separation control using nanosecond-pulse discharge plasma actuators on a flying wing[J]. Plasma Science and Technology, 2018, 20(11): 115504. DOI: 10.1088/2058-6272/aacaf0
[5]	Yong WANG (王勇), Cong LI (李聪), Jielin SHI (石劼霖), Xingwei WU (吴兴伟), Hongbin DING (丁洪斌). Measurement of electron density and electron temperature of a cascaded arc plasma using laser Thomson scattering compared to an optical emission spectroscopic approach[J]. Plasma Science and Technology, 2017, 19(11): 115403. DOI: 10.1088/2058-6272/aa861d
[6]	Zhigang ZHU (朱志刚), Qiyong ZHANG (张启勇), Yuntao SONG (宋云涛), Ming ZHUANG (庄明), Zhiwei ZHOU (周芷伟), Anyi CHENG (成安义), Ping ZHU (朱平). Present status and one upgrading method with a cold compressor of the EAST sub-cooling helium cryogenic system[J]. Plasma Science and Technology, 2017, 19(5): 55603-055603. DOI: 10.1088/2058-6272/aa58da
[7]	SUN Min (孙敏), YANG Bo (杨波), PENG Tianxiang (彭天祥), LEI Mingkai (雷明凯). Optimum Duty Cycle of Unsteady Plasma Aerodynamic Actuation for NACA0015 Airfoil Stall Separation Control[J]. Plasma Science and Technology, 2016, 18(6): 680-685. DOI: 10.1088/1009-0630/18/6/16
[8]	OU Wei (欧巍), DENG Baiquan (邓柏权), ZENG Xianjun (曾宪俊), GOU Fujun (芶富均), XUE Xiaoyan (薛晓艳), ZHANG Weiwei (张卫卫), CAO Xiaogang (曹小岗), YANG Dangxiao (杨党校), CAO Zhi (曹智). Characteristics of Single Cathode Cascaded Bias Voltage Arc Plasma[J]. Plasma Science and Technology, 2016, 18(6): 627-633. DOI: 10.1088/1009-0630/18/6/08
[9]	LI Cong (李聪), ZHANG Jialiang (张家良), YAO Zhi (姚志), WU Xingwei (吴兴伟), et al.. Diagnosis of Electron, Vibrational and Rotational Temperatures in an Ar/N ₂ Shock Plasma Jet Produced by a Low Pressure DC Cascade Arc Discharge[J]. Plasma Science and Technology, 2013, 15(9): 875-880. DOI: 10.1088/1009-0630/15/9/08
[10]	SONG Huimin, LI Yinghong, ZHANG Qiaogen, JIA Min, WU Yun. Experimental Investigation of the Characteristics of Sliding Discharge Plasma Aerodynamic Actuation[J]. Plasma Science and Technology, 2011, 13(5): 608-611.