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On-line Access: 2022-08-22
Received: 2021-12-07
Revision Accepted: 2022-03-17
Crosschecked: 2022-08-30
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Ru-bing LIU, Xiao-yin MEI, Sheng-hui XUE, Yu-wen LU, Zhe-zhe SU, Qi LIN. Active flow control of S-duct by plasma synthetic jet[J]. Journal of Zhejiang University Science A,in press.Frontiers of Information Technology & Electronic Engineering,in press.https://doi.org/10.1631/jzus.A2100618 @article{title="Active flow control of S-duct by plasma synthetic jet", %0 Journal Article TY - JOUR
基于等离子体合成射流的S形进气道主动流动控制研究机构:1.厦门大学,航空航天学院,中国厦门,361102;2.福建省等离子体与磁共振研究重点实验室,中国厦门,361102 目的:S形进气道内的流动分离和二次流造成进气道出口压力损失和气流畸变较为严重,严重影响发动机的工作性能。为改善其流场特性,本文采用串联式等离子体合成射流主动控制进气道内的流场,抑制进气道内流动分离和出口压力畸变,提高进气道气动性能。 创新点:1.系统探究等离子体合成射流控制位置、布局形式、动量系数和激励频率对控制效果的作用规律,并采用正交实验法确定上述参数的主次和最优组合。2.从流向和出口截面流场及压力分布出发,厘清等离子体合成射流主动控制S型进气道流动的机理。 方法:1.在低速风洞试验中(图2),利用压力扫描阀采集进气道壁面静压分布和出口总压分布,并通过粒子图像测速(PIV)技术测量进气道壁面沿程和出口流场(图5)。2.在壁面布置等离子体合成射流阵列对进气道内的流动分离进行主动控制,改变等离子体合成射流相关参数(图7和9),探究其作用规律,并利用正交实验法确定各参数的影响主次。3.通过对比分析沿程、出口的流场和压力分布(图13),探究等离子体合成射流控制流动分离的机理(图16)。 结论:1.等离子体合成射流能够显著提高静压恢复系数,抑制流动分离并改善出口压力畸变;射流控制位置在分离点附近最佳,而“Λ”型布局形式是最优的。2.本实验中,壁面静压系数提高最大可达127.8%,而出口稳态畸变指数降低了9.15%。3.控制机理是高速射流的直接能量注入及其产生的流向涡间接控制效应;一方面,可提高边界层抵抗逆压梯度的能力,抑制流动分离;另一方面,可有效降低二次流的强度,减弱出口截面回流,降低压力畸变。 关键词组: Darkslateblue:Affiliate; Royal Blue:Author; Turquoise:Article
Reference[1]AmitayM, PittD, GlezerA, 2002. Separation control in duct flows. Journal of Aircraft, 39(4):616-620. [2]AndersonBH, GibbJ, 1992. Application of computational fluid dynamics to the study of vortex flow control for the management of inlet distortion. Proceedings of the 28th Joint Propulsion Conference and Exhibit. [3]BallWH, 1985. Tests of wall suction and blowing in highly offset diffusers. Journal of Aircraft, 22(3):161-167. [4]ChedevergneF, LeonO, BodocV, et al., 2015. Experimental and numerical response of a high-Reynolds-number M=0.6 jet to a plasma synthetic jet actuator. International Journal of Heat and Fluid Flow, 56:1-15. [5]ChenZJ, WangJJ, 2012. Numerical investigation on synthetic jet flow control inside an S-inlet duct. Science China Technological Sciences, 55(9):2578-2584. [6]CybykBZ, SimonDH, LandIII HB, et al., 2006. Experimental characterization of a supersonic flow control actuator. Proceedings of the 44th AIAA Aerospace Sciences Meeting and Exhibit. [7]DebiasiM, HerbergMR, YanZ, et al., 2008. Control of flow separation in S-ducts via flow injection and suction. Proceedings of the 46th AIAA Aerospace Sciences Meeting and Exhibit. [8]DelotAL, GarnierE, PaganD, 2011. Flow control in a high-offset subsonic air intake. Proceedings of the 47th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit. [9]DongXR, ChenYH, DongG, et al., 2016. Research on control of hypersonic shock wave/boundary layer interactions by double micro-ramps. Acta Armamentarii, 37(9):1624-1632 (in Chinese). [10]EmerickT, AliMY, FosterC, et al., 2014. SparkJet characterizations in quiescent and supersonic flowfields. Experiments in Fluids, 55(12):1858. [11]GarnierE, LeplatM, MonnierJC, et al., 2012. Flow control by pulsed jet in a highly bended S-duct. Proceedings of the 6th AIAA Flow Control Conference. [12]GissenAN, VukasinovicB, McMillanML, et al., 2014. Distortion management in a boundary layer ingestion inlet diffuser using hybrid flow control. Journal of Propulsion and Power, 30(3):834-844. [13]GrossmanKR, CybykBZ, VanWieDM, 2003. Sparkjet actuators for flow control. Proceedings of the 41st Aerospace Sciences Meeting and Exhibit. [14]GuRY, ShanY, ZhangJZ, et al., 2018. Numerical study on transport aircraft after-body flow separation control by spark jet. Journal of Aerospace Power, 33(8):1855-1863 (in Chinese). [15]HarrisonNA, AndersonJ, FlemingJL, et al., 2013. Active flow control of a boundary layer-ingesting serpentine inlet diffuser. Journal of Aircraft, 50(1):262-271. [16]HeP, DongJZ, 2015. Effect of slot orientation on synthetic jet-based separation control in a serpentine inlet. Journal of Aerospace Power, 30(2):306-314 (in Chinese). [17]HuangEL, KangJX, WangP, et al., 2013. An investigation of micro-jet control in a compact S-shaped intake. Gas Turbine Technology, 26(3):21-27 (in Chinese). [18]JenkinsLN, GortonSA, AndersSG, 2002. Flow control device evaluation for an internal flow with an adverse pressure gradient. Proceedings of the 40th AIAA Aerospace Sciences Meeting & Exhibit. [19]JiaYH, LiangH, ZongHH, et al., 2022. Flow separation control in S-shaped∼inlet with a nanosecond pulsed surface dielectric barrier discharge plasma actuator. Journal of Physics D: Applied Physics, 55(5):055201. [20]JiangH, LiuJ, LuoSC, et al., 2020. Hypersonic flow control of shock wave/turbulent boundary layer interactions using magnetohydrodynamic plasma actuators. Journal of Zhejiang University-SCIENCE A (Applied Physics & Engineering), 21(9):745-760. [21]LiBB, ChenGKM, GuYS, 2012. Separation flow control of beveled synthetic jet actuator in S-shaped inlet. Journal of Experiments in Fluid Mechanics, 26(2):34-37 (in Chinese). [22]LinQ, GuoRW, 1989. Vortex control investigation of swirl in S-shaped diffuser. Acta Aeronautica et Astronautica Sinica, 10(1):35-40 (in Chinese). [23]LiuRB, NiuZG, WangMM, et al., 2015. Aerodynamic control of NACA 0021 airfoil model with spark discharge plasma synthetic jets. Science China Technological Sciences, 58(11):1949-1955. [24]LiuRB, LinRX, LianGC, et al., 2021. Multichannel plasma synthetic jet actuator driven by Marx high-voltage generator. AIAA Journal, 59(9):3417-3430. [25]MathisR, DukeD, KitsiosV, et al., 2008. Use of zero-net-mass-flow for separation control in diffusing S-duct. Experimental Thermal and Fluid Science, 33(1):169-172. [26]MengT, DongJZ, WuXY, 2016. Active flow control with fluidic in S-shaped inlet. Science Technology and Engineering, 16(32):319-324 (in Chinese). [27]NgYT, LuoSC, LimTT, et al., 2011. Three techniques to control flow separation in an S-shaped duct. AIAA Journal, 49(9):1825-1832. [28]NingL, TanHJ, SunS, 2017. Effects of boundary layer ingestion on flow characteristics of an S-shaped inlet. Journal of Propulsion Technology, 38(2):266-274 (in Chinese). [29]PanJJ, 2014. Research on the Flow Field Characteristics and Flow Control of S-shaped Inlet. MS Thesis, Nanjing University of Aeronautics and Astronautics, Nanjing, China(in Chinese). [30]SahniO, OllesJ, JansenKE, 2009. Simulation of flow control in a serpentine duct. Proceedings of the 47th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition. [31]SaryG, DufourG, RogierF, et al., 2014. Modeling and parametric study of a plasma synthetic jet for flow control. AIAA Journal, 52(8):1591-1603. [32]SchlichtingH, GerstenK, 2017. Boundary-Layer Theory. Springer, Berlin, Germany. [33]ShinJY, KimHJ, KimKH, 2021. Development of one-dimensional analytical model for a SparkJet actuator. AIAA Journal, 59(3):1055-1074. [34]SunJ, NiuZG, LiuRB, et al., 2019. The wind tunnel test of the active flow control on the flying wing model based on the plasma synthetic jet. Journal of Experiments in Fluid Mechanics, 33(4):81-88 (in Chinese). [35]TangMX, WuY, WangHY, et al., 2018. Characterization of transverse plasma jet and its effects on ramp induced separation. Experimental Thermal and Fluid Science, 99:584-594. [36]VaccaroJC, ElimelechY, ChenY, et al., 2015. Experimental and numerical investigation on steady blowing flow control within a compact inlet duct. International Journal of Heat and Fluid Flow, 54:143-152. [37]WangHY, LiJ, JinD, et al., 2018. High-frequency counter-flow plasma synthetic jet actuator and its application in suppression of supersonic flow separation. Acta Astronautica, 142:45-56. [38]WangP, ShenCB, 2019. Characteristics of mixing enhancement achieved using a pulsed plasma synthetic jet in a supersonic flow. Journal of Zhejiang University-SCIENCE A (Applied Physics & Engineering), 20(9):701-713. [39]WengPF, GuoRW, 1992. New method of swirl control in a diffusing S-duct. AIAA Journal, 30(7):1918-1919. [40]WojewodkaMM, WhiteC, ShahparS, et al., 2018. A review of flow control techniques and optimisation in S-shaped ducts. International Journal of Heat and Fluid Flow, 74:223-235. [41]ZhouY, XiaZX, LuoZB, et al., 2018. Experimental characteristics of a two-electrode plasma synthetic jet actuator array in serial. Chinese Journal of Aeronautics, 31(12):2234-2247. [42]ZhouY, XiaZX, LuoZB, et al., 2019. Characterization of three-electrode SparkJet actuator for hypersonic flow control. AIAA Journal, 57(2):879-885. [43]ZhouY, LuoZB, WangL, et al., 2022. Plasma synthetic jet actuator for flow control: review. Acta Aeronauticaet Astronautica Sinica, 43(3):025027 (in Chinese). [44]ZongHH, KotsonisM, 2017a. Interaction between plasma synthetic jet and subsonic turbulent boundary layer. Physics of Fluids, 29(4):045104. [45]ZongHH, KotsonisM, 2017b. Realisation of plasma synthetic jet array with a novel sequential discharge. Sensors and Actuators A: Physical, 266:314-317. [46]ZongHH, KotsonisM, 2018. Formation, evolution and scaling of plasma synthetic jets. Journal of Fluid Mechanics, 837:147-181. [47]ZongHH, ChiattoM, KotsonisM, et al., 2018. Plasma synthetic jet actuators for active flow control. 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