超声速喷流混合流场大涡模拟

朱志斌; 程晓丽; 潘宏禄

doi:10.13224/j.cnki.jasp.2019.01.024

超声速喷流混合流场大涡模拟

doi: 10.13224/j.cnki.jasp.2019.01.024

中国航天科技集团有限公司中国航天空气动力技术研究院，北京 100074

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出版历程
- 收稿日期: 2018-01-04
- 刊出日期: 2019-01-28

Large eddy simulation of supersonic jet mixing flow

摘要

摘要: 以光学窗口外冷喷流为研究背景，采用大涡模拟方法对后台阶外形切向喷流混合流场进行了研究。数值方法基于隐式亚格子模型，采用高精度WENO格式进行空间离散，并通过超声速平面混合层流动对数值方法进行了考核验证。喷流混合流场计算模型与试验一致，来流和喷流马赫数分别为3.4和2.5。数值模拟清晰地捕捉到了流场波系以及混合剪切层、壁面边界层等典型流场结构，并精细预测了混合层发生失稳、转捩及发展为充分发展湍流的时空发展过程。数值模拟得到的湍流大尺度结构的位置和形态与实验图像一致。通过对瞬时流场、统计平均流场和脉动参数的分析，揭示了流场结构特征及其时空演化规律，并获得了流场密度脉动特性。
- 超声速 /
- 冷却喷流 /
- 剪切层 /
- 转捩 /
- 湍流 /
- 大涡模拟
Abstract: On the background of cooling jet flow on the optical window, the supersonic jet flow over a backward facing step was investigated via large-eddy simulation (LES). Based on the implicit sub-grid model, the numerical method utilized the seventh order WENO scheme for spatial discretion, which was validated by the simulation of the supersonic mixing layer. The computational model for supersonic jet mixing flow was identical to the wind tunnel experiment, and the Mach number of the free flow and jet flow were set as 3.4 and 2.5, respectively. The numerical simulation captured the complex flow structures of compressive and expansive waves, as well as the shearing mixing layer and boundary layers. The process of flow becoming unsteady and transiting to turbulence was predicted subtly. The position and shape of large-scale turbulent structures obtained from numerical simulation agreed with experimental images. By the analysis of instantaneous, averaged, and fluctuant flow field, the temporal and spatial evolution of flow structures were revealed, and the feature of density fluctuation was acquainted.
- supersonic /
- jet cooling flow /
- shear layer /
- transition /
- turbulence /
- large eddy simulation

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参考文献(24)

[1]	李桂春.气动光学［M］.北京:国防工业出版社,2006:7-11.
[2]	STOLLERY J L,EL-EHWANY A A M.A note on the use of a boundary-layer model for correlating film-cooling data［J］.International Journal of Heat and Mass Transfer,1965,8(1):55-65.
[3]	KANDA T,MASUYA G,ONO F,et al.Effect of film cooling/regenerative cooling on scramjet engine perform-ances［J］.Journal of Propulsion and Power,1994,10(5):618-624.
[4]	GOLDSTEIN R J,ECKERT E R G,TSOU F K,et al.Film cooling with air and helium injection through a rearward-facing slot into a supersonic air flow［J］.AIAA Jorunal,1966,4(6):981-985.
[5]	RICHARDS B E,STOLLERY J L.An experimental study of the cooling effectiveness of a laminar two-dimensional tangential film in hypersonic flow［R］.Albuquerque,N M:AIAA 10th Fluid & Plasmadynamics Conference,1977.
[6]	JUHANY K A,HUNT M L,SIVO J M.Influence of in-jectant Mach number and temperature on supersonic film cooling［J］.Journal of Thermophysics and Heat Transfer,1994,8(1):59-67.
[7]	韩启祥,何小明,谈浩元,等.超音速射流气膜冷却效果的实验研究［J］.南京航空航天大学学报,1998,30(5):491-495.HAN Qixiang,HE Xiaoming,TAN Haoyuan,et al.Experimental investigation of supersonic gaseous film cooling effectiveness［J］. Journal of Nanjing University of Aeronautics and Astronautics,1998,30(5):491-495.（in Chinese）
[8]	陈植,易仕和,何霖,等.基于NPLS的超声速层流/湍流后台阶流动精细结构研究［J］.科学通报,2011,56(36):3057-3063.CHEN Zhi,YI Shihe,HE Lin,et al.An experimental study on fine structures of supersonic laminar/turbulent flow over a backward-facing step based on NPLS［J］.Chin Sci Bull,2011,56(36):3057-3063.（in Chinese）
[9]	朱杨柱,易仕和,陈植,等.超声速喷流致冷钝头双锥绕流瞬态与平均结构［J］.气体物理:理论与应用,2013,8(1):72-78.ZHU Yangzhu,YI Shihe,CHEN Zhi,et al.Instantaneous and time-averaged flow structures around a blunt double-cone with supersonic film cooling［J］.Physics of Gases:Theory and Applications,2013,8(1):72-78.(in Chinese)
[10]	朱杨柱,易仕和,陈植,等.带喷流超声速光学头罩流场气动光学畸变试验研究［J］.物理学报,2013,62(8):084219.1-084219.8.ZHU Yangzhu,YI Shihe,CHEN Zhi,et al.Experimental investigation on aero-optical aberration of the supersonic flow passing through an optical dome with gas njection［J］.Acta Phys.Sin,2013,62(8):084219.1-084219.8.（in Chinese）
[11]	朱杨柱,易仕和,孔小平,等.带喷流超声速后台阶流场精细结构及其运动特性研究［J］.物理学报,2015,64(6):064701.1-064701.7.ZHU Yangzhu,YI Shihe,KONG Xiaoping,et al.Fine structures and characteristics on supersonic flow over backward facing step with tangential injection［J］.Acta Phys. Sin.,2015,64(6):064701.1-064701.7.（in Chinese）
[12]	赵学军,魏连风,向星居,等.高速受限混合层结构和效应实验研究［J］.气体物理,2016,1(6):56-63.ZHAO Xuejun,WEI Lianfeng,XIANG Xingju,et al.Experimental study of hypersonic limited mixing layer structure and effectiveness［J］.Physics of Gasses,2016,1(6):56-63.(in Chinese)
[13]	AUPOIX B,BOUVIER F,GAILLARD R,et al.Experimental and numerical study of supersonic film cooling［J］.AIAA Journal,1998,36(6):915-923.
[14]	YANG X B.Numerical study of film cooling in hyper-sonic flows［D］.Glasgow,US:Univerisity of Glasgow,2002:49-100.
[15]	王建,孙冰,魏玉坤.超声速气膜冷却数值模拟［J］.航空动力学报,2008,23(5):865-870.WANG Jian,SUN Bing,WEI Yukun.Numerical simulation of supersonic gaseous film cooling［J］.Journal of Aerospace Power,2008 23(5):865-870.（in Chinese）
[16]	胡娅萍,吉洪湖.平壁气膜冷却流场与温度场的协同分析［J］.工程热物理学报,2004,25(1):94-96.HU Yaping,JI Honghu.Synergetic analysis of velocity and temperature fields of flate film cooling［J］.Journal of Engineering Thermophysics,2004,25(1):94-96.（in Chinese）
[17]	CHILDS E R.Prediction and control of turbulent aero-optical distortion using large eddy simulation［R］.AIAA-93-2670,1993.
[18]	KONOPKA M,MEINKE M,SCHRODER W. Large-eddy simulation of supersonic film cooling at laminar and turbulent injection［R］.AIAA 2011-2260,2011.
[19]	KONOPKA M,MEINKE M,SCHRDER W.Large-eddy simulation of shock/cooling-film interaction［J］.AIAA Journal,2012,50(10):2102-2114.
[20]	AYYALASOMAYAJULA H,ARUNAJATESAN S,KANNEPALLI C,et al.Large eddy simulation of a su-personic flow over a backward-facing step for aero-optical analysis［R］.AIAA 2006-1416,2006.
[21]	BORIS J P,GRINSTEIN F F,ORAN E S,et al.New insights into large eddy simulation［J］.Fluid Dynamics Research,1992,10(4):199-228.
[22]	GARNIER E,ADAMS N,SAGAUT P.Large eddy simulation for compressible flows［M］.Berlin:Springer Netherlands,2009:93.
[23]	JIANG G S,SHU C W.Efficient implementation of weighted ENO schemes［J］.Journal of Computational Physics,1996,126:202-228.
[24]	GOEBEL S G,DUTTON J C.Experimental study of compressible turbulent mixing layers［J］.AIAA Journal,1990,29(4):538-546.