射流旋涡发生器控制大折转角扩压叶栅二次流

刘华坪; 陈焕龙; 李德雄; 郭玉杰; 程肖岐; 陈浮

doi:10.13224/j.cnki.jasp.2015.04.010

射流旋涡发生器控制大折转角扩压叶栅二次流

doi: 10.13224/j.cnki.jasp.2015.04.010

哈尔滨工业大学推进理论与技术研究所, 哈尔滨 150001

基金项目:

国家自然科学基金(51306042)

中央高校基本科研业务费专项资金(HIT.NSRIF,2013092)

详细信息

作者简介:
刘华坪(1983-),男,四川峨眉人,讲师,博士,主要从事叶轮机械流动控制研究.

中图分类号: V231.1
计量
- 文章访问数: 1467
- HTML浏览量: 1
- PDF量: 908
- 被引次数: 0
出版历程
- 收稿日期: 2013-11-11
- 刊出日期: 2015-04-28

Secondary flow control in high-turning compressor cascade using vortex generator jet

Institute of Propulsion Theory and Technology, Harbin Institute of Technology, Harbin 150001, China

摘要

摘要: 将射流旋涡发生器引入到某折转角为60°的扩压叶栅端壁二次流控制中,研究了射流方向和射流总压对扩压叶栅气动性能及栅内流动的影响.结果表明:当射流旋涡发生器侧向倾角为0°时,仅采用不足扩压叶栅进口流量0.5%的射流流量,即可显著减少栅内损失.射流旋涡有效阻碍和推迟了通道涡发展,在下洗侧将主流流体卷入端壁附面层内,而在上洗侧将低能流体带入主流中,从而减少了角区低能流体聚积,减弱了吸力面的分离流动.当射流进口总压采用与扩压叶栅进口相同的总压时,总压损失减小21.5%,且射流进口总压越大,其控制效果越明显.
- 射流旋涡发生器 /
- 端壁附面层 /
- 角区分离 /
- 流动损失 /
- 叶栅
Abstract: End wall secondary flow control using vortex generator jet in compressor cascade with the turning angle of 60 degree was performed. The effects of variation of the direction and the total pressure of the jet on aerodynamic performance and flow of compressor cascade were presented. The results indicate that with the skew angle of 0 degree in vortex generator jet and jet mass flow rate less than 0.5% of inlet mass flow rate of compressor cascade, the loss of cascade could be reduced obviously. The vortex induced by the vortex generator jet could weaken or even prevent the development of passage vortex, make the fluid of the main stream involve into the end wall boundary layer in the down-washed region and guide the low energy fluid to the main stream in the up-washed region. Thus the accumulation of the low energy fluid in the corner region was reduced, resulting in the decrease of the separation on the suction surface. Using the same jet total pressure at inlet with that of the compressor cascade inlet, the reduction of 21.5% of total pressure loss can be obtained; this effect can become more obvious with the increase of the jet total pressure at inlet.
- vortex generator jet /
- end wall boundary layer /
- corner separation /
- flow loss /
- cascade

HTML

参考文献(18)

[1]	杨凌, 钟兢军, 韩少冰.不同参数端壁翼刀对跨音速压气机环形叶栅二次流影响的数值研究[J].大连海事大学学报, 2011, 37(4):30-34. YANG Ling, ZHONG Jingjun, HAN Shaobing.Numerical investigation of the secondary flow control in a transonic annual compressor cascade using different parameter endwall fences[J].Journal of Dalian Maritime University, 2011, 37(4):30-34.(in Chinese)
[2]	Yoichi I, Toshinori W, Takehiro H.Effect of endwall contouring on flow instability of transonic compressor[J].International Journal of Gas Turbine, Propulsion and Power Systems, 2008, 2(1):24-29.
[3]	Hecklau M, Gmelin C, Nitsche W, et al.Experimental and numerical results of active flow control on a highly loaded stator cascade[J].Journal of Power and Energy, 2011, 225(7):907-918.
[4]	高光良, 牛楠, 王掩刚.跨音速压气机附面层组合抽吸方案对比分析[J].航空工程进展, 2011, 2(1):105-109. GAO Guangliang, NIU Nan, WANG Yangang.Numerical investigation of combined BLS effect on the performance of a transonic compressor rotor[J].Advances in Areonautical Science and Engineering, 2011, 2(1):105-109.(in Chinese)
[5]	Compton D A, Jonston J P.Streamwise vortex production by pitched and skewed jets in a turbulent boundary layer[J].AIAA Journal, 1992, 30(3):640-647.
[6]	钟易成, 陈晓.涡与涡以及涡与附面层之间相互作用的试验研究[J].航空动力学报, 1999, 14(1):28-31. ZHONG Yicheng, CHEN Xiao.An experimental investigation on interactions among vortices and vortex with boundary layer[J].Journal of Aerospace Power, 1999, 14(1):28-31.(in Chinese)
[7]	沈遐龄, 高歌, 刘宝杰, 等.旋涡发生器对机翼最大升力和失速迎角的影响[J].北京航空航天大学学报, 1998, 24(3):311-314. SHEN Xialing, GAO Ge, LIU Baojie, et al.Effects of vortex generators on maximum lift and stall angle of attack over wings[J].Journal of Beijing University of Aeronautics and Astronautics, 1998, 24(3):311-314.(in Chinese)
[8]	刘沛清, 樊文博, 曹硕.近耦合鸭式布局鸭翼展向吹气涡控技术数值模拟研究[J].飞机设计, 2010, 30(5):7-11. LIU Peiqing, FAN Wenbo, CAO Shuo.Numerical simulation on vortex control technology of canard-spanwise blowing of close-coupled canard wing configuration[J].Aircraft Design, 2010, 30(5):7-11.(in Chinese)
[9]	ZHENG Xinqian, ZHOU Sheng, HOU Anping, et al.Separation control using synthetic vortex generator jets in axial compressor cascade[J].Acta Mechanica Sinica, 2006, 22(6):521-527.
[10]	袁忻, 刘火星.压气机叶栅的涡发生器流动控制研究[J].航空科学技术, 2010(4):30-32. YUAN Xin, LIU Huoxing.Flow control research in compressor cascade with vortex generator[J].Aeronautical Science and Technology, 2010(4):30-32.(in Chinese)
[11]	伊进宝, 乔渭阳, 孙大伟.低压涡轮叶栅流动分离主动控制实验研究[J].航空学报, 2007, 28(5):1055-1061. YI Jinbao, QIAO Weiyang, SUN Dawei.Experimental investigation of active control of flow separation at low-pressure turbine cascade[J].Acta Aeronautica et Astronautica Sinica, 2007, 28(5):1055-1061.(in Chinese)
[12]	Zander V, Hecklau M, Nitsche W, et al.Active flow control by means of synthetic jets on a highly loaded compressor cascade[J].Journal of Power and Energy, 2011, 225(7):897-906.
[13]	Gmelin C, Zander V, Hecklau M, et al.Active flow control concepts on a highly loaded subsonic compressor cascade:resume of experimental and numerical results[R].ASME Paper GT2011-46468, 2011.
[14]	Ortmanns J, Pixberg C, Gummer V.Numerical investigation of vortex generators to reduce cross-passage flow phenomena in compressor stator end-walls[J].Journal of Power and Energy, 2011, 225(7):877-885.
[15]	QI Lei, ZOU Zhengping, WANG Peng, et al.Control of secondary flow loss in turbine cascade by streamwise vortex[J].Computers and Fluids, 2012, 54:45-55.
[16]	刘华坪, 陈焕龙, 杨晓光, 等.基于耗散函数的低速扩压叶栅损失机理探讨[J].航空动力学报, 2011, 26(2):289-296. LIU Huaping, CHEN Huanlong, YANG Xiaoguang, et al.Study of loss mechanism in low speed compressor cascade using dissipation function[J].Journal of Aerospace Power, 2011, 26(2):289-296.(in Chinese)
[17]	Henry F S, Pearcey H H.Numerical model of boundary-layer control using air-jet generated vortices[J].AIAA Journal, 1994, 32(12):2415-2425.
[18]	樊涛, 谢永慧, 张荻.涡旋射流控制扩压器分离流动的大涡模拟[J].中国电机工程学报, 2008, 28(5):57-65. FAN Tao, XIE Yonghui, ZHANG Di.Large-eddy simulation for control of flow separation in conical diffuser by vortex generator jets[J].Proceedings of the Chinese Society for Electrical Engineering, 2008, 28(5):57-65.(in Chinese)