气体伴随射流对液体射流穿透深度影响研究
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摘要
在来流Ma2.85条件下,对气体伴随射流喷注方案进行研究。通过改变气体喷注压降、气体喷孔孔径以及气液喷注间距,研究这些喷注参数对射流穿透深度的影响。同时采用数值仿真的方法得到气体射流流场结构,对气体伴随射流的作用机理进行解释。结果表明,增加气体喷注压降和孔径都能够有效增大其下游液体射流出口的液气动量通量比,从而增大液体射流的穿透深度及其增长比率;对于固定的气体喷注压降,气液喷注间距与气体孔径的比值在4～8范围内,液体射流前的液气动量通量比最大。文中根据实验结果拟合出了纯液体射流及气体伴随射流穿透深度经验公式。
Researches are carried out to study air-accompanied injection scheme in the condition of Mach 2.85.By changing gas injection pressure,gas injection orifice,and distance between gas and liquid jet orifices,the effects of these parameters on jet penetration are investigated.Simulation is also adopted to obtain the flow field of gas injection,which could analyze acting mechanism of air-accompanied injection.Experimental results indicate that increasing gas injection pressure drop and orifice could both increase the enhancement that air-accompanied injection exerts on liquid jet penetration.Results of simulation show that the ratio of distance between gas and liquid jet orifices to gas injection orifice has an optimal value,which could make liquid to gas momentum flux ratio maximum.Empirical equations of liquid jet penetration with and without gas injection are obtained according to test data in this paper.
Researches are carried out to study air-accompanied injection scheme in the condition of Mach 2.85.By changing gas injection pressure,gas injection orifice,and distance between gas and liquid jet orifices,the effects of these parameters on jet penetration are investigated.Simulation is also adopted to obtain the flow field of gas injection,which could analyze acting mechanism of air-accompanied injection.Experimental results indicate that increasing gas injection pressure drop and orifice could both increase the enhancement that air-accompanied injection exerts on liquid jet penetration.Results of simulation show that the ratio of distance between gas and liquid jet orifices to gas injection orifice has an optimal value,which could make liquid to gas momentum flux ratio maximum.Empirical equations of liquid jet penetration with and without gas injection are obtained according to test data in this paper.
引文
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[16]Ogawa H.Effects of Injection Angle and Pressure on Mixing Performance of Fuel Injection via Various Geometries for Upstream-Fuel-Injected Scramjets[J].Acta Astronautica,2016,128:485-498
[2]陈亮,乐嘉陵,宋文艳,等.超声速冷态流场液体射流雾化实验研究[J].实验流体力学,2011,25(2):29-34CHEN Liang,LE Jialing,SONG Wenyan,et al.Experimental Investigation of Liquid Jets Atomization in Supersonic Cold Crossflow[J].Journal of Experiments in Fluid Mechanics,2011,25(2):29-34
[3]Rogers R C,Capriotti D P,Guy R W.Experimental Supersonic Combustion Research at NASA Langley[C]//20th AIAA Advanced Measurement and Ground Testing Technology Conference,USA,AIAA,1998:1-23
[4]王应洋,李旭昌,王宏宇,等.超声速燃烧室小支板对射流作用的数值分析[J].航空动力学报,2016,31(1):211-218WANG Yingyang,LI Xuchang,WANG Hongyu,et al.Numerical Analysis on Effect on Injection for Supersonic Combustor Pylon[J].Journal of Areospace Power,2016,31(1):211-218
[5]Tam C J,Hsu K Y,Gruber M R,et al.Fuel/Air Mixing Characteristics of Strut Injections for Scramjet Combustor Applications[C]//26th AIAA Applied Aerodynamics Conference,USA,AIAA,2008:1-15
[6]Masuya G,Komuro T,Murakami A,et al.Ignition and Combustion Performance of Scramjet Combustors[J].Journal of Propulsion and Power,1995,11(2):301-307
[7]Lin K C,Kennedy P J,Jackson T A.Spray Penetration Heights of Angle-Injected Aerated-Liquid Jets in Supersonic Crossflows[C]//38th Aerospace Sciences Meeting and Exhibit,USA,AIAA,2000:1-13
[8]Lin K C,Kennedy P J,Jackson T A.Structures of Water Jets in a Mach 1.94 Supersonic Crossflow[C]//42nd AIAA Aerospace Sciences Meeting and Exhibit,USA,AIAA,2004:1-19
[9]Cox-Stouffer S K,Gruber M R.Effects of Spanwise Injection Spacing on Mixing Characteristics of Aerodynamic Ramp injectors[C]//34th AIAA/ASME/SAE/ASEE Joint Propulsion Conference&Exhibit,USA,AIAA,1998:1-11
[10]Cox-Stouffer S K,Gruber M R.Effects of Injector Yaw on Mixing Characteristics of Aerodynamic Ramp Injectors[C]//37th Aerospace Sciences Meeting and Exhibit,USA,AIAA,1999:1-12
[11]Cox-Stouffer S K,Gruber M R.Further Investigation of the Effects of Aerodynamic Ramp Design upon Mixing Characteristics[C]//35th Joint Propulsion Conference and Exhibit,USA,AIAA,1999:1-11
[12]Olmstead D T,Gruber M R,Collatz M J,et al.Cavity Coupled Aeroramp Injector Combustion Study[C]//45th AIAA/ASME/SAE/ASEE Joint Propulsion Conference&Exhibit,USA,AIAA,2009:1-16
[13]仝毅恒,李清廉,吴里银,等.超声速气流中液体横向射流组合喷注特性实验[J].国防科技大学学报,2014,36(2):73-80TONG Yiheng,LI Qinglian,WU Liyin,et al.Experimental Investigation on Injection Characteristics of Assembled Transverse Injectors in Supersonic Crossflow[J].Journal of National University of Defense Technology,2014,36(2):73-80
[14]吴里银.超声速气流中液体横向射流破碎与雾化机理研究[D].长沙:国防科学技术大学,2016WU Liyin.Breakup and Atomization Mechanism of Liquid Jet in Supersonic Crossflows[D].Changsha:National University of Defense Technology,2016
[15]Zhao M,Ye T,Cao C,et al.Study of Sonic Injection from Circular Injector into a Supersonic Cross-Flow Using Large Eddy Simulation[J].International Journal of Hydrogen Energy,2016,41(39):17657-17669
[16]Ogawa H.Effects of Injection Angle and Pressure on Mixing Performance of Fuel Injection via Various Geometries for Upstream-Fuel-Injected Scramjets[J].Acta Astronautica,2016,128:485-498
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