大功率狭缝式活塞激励器流场测量与分析

刘贺; 董金钟; 伍耐明

大功率狭缝式活塞激励器流场测量与分析

1.
清华大学航天航空学院, 北京 100192
2. 北京航空航天大学, 能源与动力工程学院, 北京 100191

详细信息

中图分类号: V 211.3
计量
- 文章访问数: 2065
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- 被引次数: 0
出版历程
- 收稿日期: 2010-07-20
- 网络出版日期: 2012-02-29

Measurements and analysis of high-power slot-type piston actuator flow-field

1.
School of Aeronautics and Astronautics, Tsinghua University, Beijing 100192, China
2. School of Jet Propulsion, Beijing University of Aeronautics and Astronautics, Beijing 100191, China

摘要

摘要: 研制了一种大功率活塞射流激励器,出口瞬时速度峰值可达0.3Hz,通过对活塞激励器射流流场测量,得到激励器出口流场速度、涡量分布,分析得到激励器合成射流流动结构与特征,通过采用活塞激励器控制同轴射流掺混,实验结果证明此种活塞激励器可以用于相对较高的速度流场的主动流动控制.利用提出的设计方法设计合成射流激励器可以在激励器出口形成稳定的对涡结构,采用一定的激励频率即可对喷管气流掺混进行有效控制.研究表明,合成射流激励器作为主动流动的执行机构,在航空动力排气系统具有潜在的重要价值.
- 主动流动控制 /
- 狭缝式 /
- 活塞激励器 /
- 涡对
Abstract: A high-power piston actuator was investigated and peak instantaneous velocity could be up to 0.3 Mach number. Exit velocity and vorticity distribution were obtained through experimental measurements. Synthetic jet flow structure and characters were investigated. Coaxial jet mixing was controlled by piston actuator, indicating which can be used in relative high velocity field to realize active flow control. The results show that the steady vortex pair at export can be formed by using the design methods of synthetic jet actuator presented. The mixing for nozzle flow can be effectively controlled with a certain excitation frequency. It presents that synthetic jet actuator can be used as the implementation of active flow control and has potentially important value to air power exhaust system.
- active flow control /
- slot-type /
- piston actuator /
- vertex pair

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参考文献(16)

[1]	Sefcovic J A,Smith D R.Proportional aerodynamic control of a swept divergent trailing edge wing using synthetic jets .AIAA 2010-92,2010
[2]	Farnsworth J A N,Vaccaro J C,Amitay M.Active flow control at low angles of attack:stingray unmannedaerial vehicle [J].AIAA Journal,2008,46(10):2530-2544
[3]	Shea P R,Smith D R.Aerodynamic control of a rectangular wing using gurney flaps and synthetic jet .AIAA 2009-886,2009
[4]	Slipher C A,Hubbard J E.Exploitation of higher order membrane modes for improved synthetic jet performance [J].AIAA Journal,2009,47(6):1388-1407
[5]	Smith B L,Glezer A.Vectoring and small-scale motions affected in free shear flows using synthetic jet actuators .AIAA 97-0213,1997
[6]	Guo Dahai,Vectoring control of a primary jet with synthetic jets .AIAA 2001-0738,2001
[7]	罗振兵,朱伯鹏,夏智勋,等,合成射流激励器对射流矢量影响研究[J].推进技术,2004,25(5):405-410 Luo Zhenbing,Zhu Bopeng,Xia Zhixun,et al,Jet vectoring using synthetic jet actuators [J].Journal of Propulsion Technology,2004,25(5):405-410 (in Chinese)
[8]	Kral L D.Active flow control technology .ASME FEDSM2001-18196,2001
[9]	Rathnsingham R,Breuer K S.Coupled fluid-structural characteristics of actuators for flow control [J].AIAA Journal,1997,35(5):832-837
[10]	Chen F J.Development of synthetic jet actuators for active flow control at NASA Langley .AIAA 2000-2405,2000
[11]	Kral L D.Numerical simulation of synthetic jet actuators .AIAA 97-1824,1997
[12]	Smith B L.Glezer A.The formation and evolution of synthetic jets [J].Phys Fluids,1998,10(9):2281-2297
[13]	Gilarranz J L.A new class of synthetic jet actuators part I,design,fabrication and characterization[J].Journal of Fluids Engineering,2005,127(2):367-376
[14]	罗振兵,,夏智勋,方丁酉.合成射流影响因素[J].国防科技大学学报,2002,24(3):32-35. Luo Zhenbing,Xia Zhixun,Fang Dingyou.The factors influencing the synthetic jet [J].Journal of National University of Defense Technology,2002,24(3):32-35 (in Chinese)
[15]	罗振兵,夏智勋,胡建新,等,相邻激励器合成射流流场数值模拟及机理研究[J].空气动力学学报,2004,22(1):52-59 Luo Zhenbing,Xia Zhixun,Hu Jianxin,et al.Numerical simulation and mechanism study of the interaction of adjacent synthetic jet actuators [J].ACTA Aerodynamica Sinica,2004,22(1):52-59 (in Chinese)
[16]	罗振兵,夏智勋,方丁酉,等,合成射流激励器初步实验及实验结果分析[J].宇航学报,2004,25(2):201-204 Luo Zhenbing,Xia Zhixun,Fang Dingyou,et al.Experimental investigation on synthetic jet actuator [J].Journal of Astronautics,2004,25(2):201-204 (in Chinese)