射流涡发生器对激波边界层作用诱导的流体分离控制大涡模拟研究

推进技术 ›› 2016, Vol. 37 ›› Issue (1): 40-48.

射流涡发生器对激波边界层作用诱导的流体分离控制大涡模拟研究

薛大文^1,2,陈志华²,孙晓晖³,张焕好²

浙江海洋学院海运与港航建筑工程学院，浙江舟山 316022; 南京理工大学瞬态物理重点实验室，江苏南京 210094,南京理工大学瞬态物理重点实验室，江苏南京 210094,上海宇航系统工程研究所，上海 201109,南京理工大学瞬态物理重点实验室，江苏南京 210094

发布日期:2021-08-15
作者简介:薛大文，男，博士，讲师，研究领域为流体力学数值模拟。E-mail: dawenjs@163.com 通讯作者:陈志华，男，教授，博导，研究领域为计算流体力学、燃烧推进、爆轰等。
基金资助:
国家自然科学基金(11272156)；中央高校基本科研业务费专项资金(30920130111013)；

Large Eddy Simulation of Flow Separation Control of Shockwave/Boundary Layer by Vortex Generator Jet

School of Shipping and Ports Architecture Engineering，Zhejiang Ocean University，Zhoushan 316022，China; Key Laboratory of Transient Physics，Nanjing University of Science and Technology，Nanjing 210094，China,Key Laboratory of Transient Physics，Nanjing University of Science and Technology，Nanjing 210094，China,Aerospace System Engineering，Shanghai 201109 and Key Laboratory of Transient Physics，Nanjing University of Science and Technology，Nanjing 210094，China

Published:2021-08-15

摘要/Abstract

摘要： 为了研究射流涡发生器对激波边界层作用所诱导的流动分离控制机理及其流场特性，基于大涡模拟(Large eddy simulation)方法和高阶TCD/WENO混合格式，对来流马赫数Ma=2.5情况下，平板上射流涡发生器对激波与边界层相互作用所诱导流场进行了数值模拟。结果表明，射流涡发生器对激波边界层的流体分离有一定的抑制作用，与无控制情况相比，射流作用下进出口总压恢复系数由85.9%提高到94.6%。射流尾涡主要集中于一环状区域内，在该区域内，入射激波与马蹄涡、桶形激波上方的涡管以及剪切涡相互作用，导致整体尾流被激波往下压缩。同时在激波的压缩下，各涡之间相互缠绕、挤压合并，形成多个流向小涡结构，将边界层外的高速流体卷入边界层内，从而增加边界层底层能量，达到抑制流动分离的目的。

关键词: 超声速；射流涡发生器；流动分离控制；大涡模拟

Abstract: In order to investigate the flow separation control mechanism and the flow characteristics induced by vortex generator jet and shock/boundary layer interaction，based on the large eddy simulation method，combined with high order WENO/TCD hybrid scheme，the flow separation control by vortex generator jet has been simulated under the condition of Ma=2.5. The results show that the vortex generator jet suppresses the boundary layer separation，compared with the case without control，the pressure recovery coefficient increases from 85.9 to 94.6% with jet control. The wake of the jet locates mainly in a circular zone，in this area，the incident shock interacted with the horseshoe vortices under the barrel shock and the vortex pipe and shear vortex above the barrel shock，which makes the wake to be compressed by the shock. Meanwhile，due to the shock，the vortices interact with each other including extrustion and coalescence and form many small streamwise tubes，which entangle the high speed main stream into the boundary layer and increase the energy of boundary layer and suppress the flow separation finally.

Key words: Supersonic；Vortex generator jet；Flow separation control；Large eddy simulation

薛大文,陈志华,孙晓晖,张焕好. 射流涡发生器对激波边界层作用诱导的流体分离控制大涡模拟研究[J]. 推进技术, 2016, 37(1): 40-48.

XUE Da-wen^1,2,CHEN Zhi-hua²,SUN Xiao-hui³,ZHANG Huan-haO². Large Eddy Simulation of Flow Separation Control of Shockwave/Boundary Layer by Vortex Generator Jet[J]. Journal of Propulsion Technology, 2016, 37(1): 40-48.

参考文献

[1] Babinsky H, Ogawa H. Shockwave Boundary Layer Interaction Control for Wings and Inlets[J]. Shock Waves, 2008, (18): 89-96.
[2] Kostas J, Foucaut J M, Stanislas M. The Effects of Pulse Frequency and Duty Cycle on the Skin Friction Downstream of Pulsed Jet Vortex Generators in an Adverse Pressure Gradient Turbulent Boundary Layer[J]. Aerospace Science and Technology, 2009, 13: 36-48.
[3] 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[J]. 力学进展, 2005, 35(2).
[4] Cybyk B Z, Simon D H, Land H B. Experimental Characterization of Supersonic Flow Control Actuator [R]. AIAA 2006-478.
[5] Wallis R A. A Preliminary Note on a Modi?ed Type of Air-Jet for Boundary Layer Control[R]. ARCTR 56513.
[6] Johnston J P, Nishi M. Vortex Generator Jets-A Means for Flow Separation Control[J]. AIAA Journal, 1990, 28(6): 989-994.
[7] Zhang X. Co-and Contrarotating Streamwise Vortices in a Turbulent Boundary Layer[J]. Journal of Aircraft,1995, 32(5): 1095-1101.
[8] Gross A, Fasel H F. Simulation of Active Flow Control for a Low Pressure Turbine Blade Cascade[R]. AIAA 2005-869.
[9] Compton D A, Johnston J P. Streamwise Vortex Productionby Pitched and Skewed Jets in a Turbulent Boundary Layer[R]. AIAA-91-0038.
[10] 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.
[11] Zhang X, Collins M W. Nearfield Evolution of Along Itudinal Vortex Generated by an Inclined Jet in a Turbulent Boundary Layer[J]. Journal of Fluids Engineering, 1997, 119: 934-939.
[12] 张荻, 樊涛, 蓝吉兵. 涡旋射流控制逆压梯度平板边界层分离的涡结构研究[J]. 西安交通大学学报, 2012, 46(1): 1-9.
[13] 薛大文, 陈志华, 张焕好. 超声速来流与侧向射流作用下的三维流场结构[J]. 推进技术, 2014, 35(7): 882-890. (XUE Da-wen, CHEN Zhi-hua, ZHANG Huan-hao. 3D Flow Structures Induced by Interaction of Supersoic Flow with a Lateral Jet[J]. Journal of Propulsion Technology, 2014, 35(7): 882-890.)
[14] 罗振兵, 夏智勋, 胡建新. 合成射流流场数值模拟及激励器参数分析[J]. 推进技术, 2004, 25(3): 199-205. (LUO Zhen-bing, XIA Zhi-xun, HU Jian-xin. Numerical Simulation of Synthetic Jet Flow Field and Parameter Analysis of Actuator[J]. Journal of Propulsion Technology, 2004, 25(3): 199-205.)
[15] 王林, 刘冰, 夏智勋. 不同出口倾角合成双射流流动特性及边界层控制[J]. 推进技术. 2010, 31(6): 757-763. (WANG Lin, LIU Bing, XIA Zhi-xun. Flow Characteristic of a Dual Synthetic Jets Actuator with Different Beveled Exit and Boundary Layer Control[J]. Journal of Propulsion Technology, 2010, 31(6): 757-763.)
[16] 郑新前, 侯安平, 周盛. 二维扩压叶栅非定常分离流控制途径探索[J]. 力学学报, 2003, 35(5): 599-605.
[17] Pullin. Vortex-Based Model for Subgrid Flux of a Passive Scalar[J]. Physics of Fluids, 2000, 12(9), 2311-2319.
[18] Hill D J, Pullin D I. Hybrid Tuned Center Difference-WENO Method for Large-Eddy Simulation in the Presence of Strong Shocks[J]. Journal of Computational Physics, 2004, 194(2), 435-450.
[19] 王军旗, 李素循. 超声速多喷流干扰流场特性研究[J]. 力学学报, 2009, 41(4): 575-583.
[20] Huanhao Zhang, Zhihua Chen, Baoming Li. The Secondary Vortex Rings of a Supersonic Underexpanded Circular Jet with Low Pressure Ratio[J]. European Journal of Mechanics B/Fluids, 2014, 46: 172-180.
[21] Zare-Behtash H, Kontis K, Takayama K. Compressible Vortex Loops Studies in a Shock Tube with Various Exit Geometries[R]. AIAA 2008-362.
[22] An R, Kontis K, Edwards J A. Compressible Vortex-ring Interaction Studies with a Number of Generic Body Configurations[R]. AIAA 2005-1044.
[23] Alkislar M B, Choutapalli I, Krothapalli A. The Structure of a Pulsed Jet- a PIV Study[R]. AIAA 2005-1274.(编辑:朱立影)　　　　　　　　　　　　　*　收稿日期:2014-09-25；修订日期:2014-12-02。基金项目:国家自然科学基金(11272156)；中央高校基本科研业务费专项资金(30920130111013)；浙江海洋学院科研启动项目(Q1507)。作者简介:薛大文,男,博士,讲师,研究领域为流体力学数值模拟。E-mail: dawenjs@163.com通讯作者:陈志华,男,教授,博导,研究领域为计算流体力学、燃烧推进、爆轰等。E-mail: chenzh@mail.njust.edu.cn