超声速气流中横向射流雾化实验和数值模拟
Experimental and numerical simulation of atomization of liquid jet in supersonic crossflow
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摘要: 为了对超声速气流中的横向射流雾化过程进行研究,在直连式实验台上进行了超声速气流中的横向射流雾化实验,并对实验工况进行了数值模拟.超声速来流的马赫数为2,实验喷雾的动压比范围为1.~11.7,实验工质为水.采用纹影法对射流雾化过程进行了拍摄,得到了有雾化的超声速流场结构和穿透深度拟合公式.同时采用欧拉-拉格朗日两相流计算方法对实验工况进行了数值模拟,雾化模型采用了一种新型K-H(Kelvin-Helmholtz)和R-T(Rayleigh-Taylor)混合模型,数值模拟与实验结果符合较好.Abstract: The liquid jet atomization in supersonic crossflow was investigated experimentally in a supersonic wind tunnel and the present experiment was numerically simulated.The Mach number of the supersonic flow was 2 and dynamic pressure ratio varied from 1.6 to 11.7,and water was used as test liquid.Schlieren method was used to study the structure of liquid jet in supersonic flow field and the correlation for penetration height was developed.Numerical simulation used EulerianLagrangian method to describe the two-phase flow.Anew hybrid K-H(Kelvin-Helmholtz) and R-T(Rayleigh-Taylor) atomization model was used to describe the atomization process.
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Key words:
- aerospace propulsion system /
- supersonic /
- atomization /
- experiment /
- numerical simulation /
- two-phase flow
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[1] Kolpin M A,Horn K P,Reichenbach R E.Study of penetration of a liquid injectant into a supersonic flow[J].AIAA Journal,1968,6(5):853-858. [2] Allan S,Joseph S.Breakup of liquid sheets and jets in a supersonic gas stream[J].AIAA Journal,1971,9(4):666-673. [3] Kush E A Jr,Schetz J A.Liquid jet injection into a supersonic flow[J].AIAA Journal,1973,11(9):1223-1224. [4] Prakash B J,Schetz J A.Effect of injector shape on penetration and spread of liquid jet[J].AIAA Journal,1975,13(9):1137-1138. [5] Schetz J A,Kush E A Jr,Joshi P B.Wave phenomena in liquid jet breakup in a supersonic crossflow[J].AIAA Journal,1980,18(7):774-778. [6] Nejad A S,Schetz J A.Effects of properties and locations in the plume on droplet diameter for injection in a supersonic stream[J].AIAA Journal,1983,21(7):956-961. [7] Nejad A S,Schetz J A,Jakubowski A K.Mean droplet diameter resulting from atomization of a transverse liquid jet in a supersonic air stream[R].AIAA-80-0899,1980. [8] Lin K C,Kennedy P J,Jackson T A.Structures of water jets in a Mach 1.94 supersonic crossflow[R].AIAA2004911,2004. [9] Wang L X,Chang Y,Chin J S.Experimental study on the atomization of plain orifice injector in supersonic crossflow air stream[R].AIAA87-1959,1987. [10] 徐胜利,Archer R D,Milton B E,等.煤油在超声速气流中非定常横向喷射的实验观察[J].空气动力学学报,2000,18(3):272-279.XU Shengli,Archer R D,Milton B E,et al.Experimental investigation on unsteady transverse injection of kerosene into a supersonic flow[J].ACTA AERODYNAMICA SINICA,2000,18(3):272-279. [11] 陈文彤.超声速气流中喷嘴雾化的试验与理论研究[D].安徽合肥:国防科学技术大学.2002.CHEN Wentong.An experimental and theoretical study of nozzle atomization in supersonic flow[D].Anhui Hefei:National University of Defense Technology,2002. [12] 俞刚,张新宇,李建国.超声速气流中的煤油喷雾研究[J].流体力学实验与测量,2001,15(4):12-14.YU Gang,ZHANG Xinyu,LI Jianguo.Investigation of kerosere spray atomization in supersonic flow[J].Experiments and Measurements in Fluid Mechanics,2001,15(4):12-14. [13] 赖林.带空腔超燃发动机燃烧室内流场实验和仿真研究[D].安徽合肥:国防科学技术大学,2003.LAI Lin.Combustion chamber flow field experiment and simulation in scramjet with cavity[D].Anhui Hefei:National University of Defenste Technology,2003. [14] Reitz R D,Diwakar R.Structure of high-pressure fuel sprays[R].SAE870598,1987. [15] Patterson M A,Reitz R D.Modeling the effects of fuel spray characteristics on diesel engine combustion and emission[R].SAE980131,1998.
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