扰流环对粉末发动机燃烧流动影响的数值模拟
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摘要
为了提高粉末火箭发动机的燃烧效率,通过数值模拟方法研究了扰流环的有无、通径及位置对燃烧室燃烧流动特性的影响。结果表明:扰流环会增强Al颗粒和气相的掺混和换热程度,促进Al颗粒蒸发和燃烧,从而提高粉末火箭发动机的燃烧效率。当扰流环通径比在0.538～0.846范围内时,扰流环的通径越小,燃烧效率越高;当扰流环头部距离比在0.3～0.8范围内时,扰流环位置离头部越近,燃烧效率越高。设计扰流环时,应在距离燃烧室头部30%～40%的位置布置小通径的扰流环。
In order to improve the combustion efficiency of powdered rocket motor,the effects of spoiler ring's existence,flowing diameter and position on the combustion and flow characteristics in the chamber were studied by numerical simulation.Result showed that the spoiler ring can increase mixing and heat transfer intensity between particle and gas species,and improve the evaporation and combustion of Al particle,which resulting in the increase of combustion efficiency of the powdered rocket motor.When the ratio of spoiler ring flowing diameter to the combustion chamber diameter was between 0.538 and 0.846,the combustion efficiency increased with the reducing flowing diameter of spoiler ring.When the ratio of spoiler ring's distance from the chamber's head position to the chamber's total length was between 0.3 and 0.8,the combustion efficiency increased as the spoiler ring moved toward the chamber's head.The spoiler ring with small flowing diameter and distance from the head between 30%and 40%of the chamber length could be better for the spoiler ring design of powdered rocket motor.
In order to improve the combustion efficiency of powdered rocket motor,the effects of spoiler ring's existence,flowing diameter and position on the combustion and flow characteristics in the chamber were studied by numerical simulation.Result showed that the spoiler ring can increase mixing and heat transfer intensity between particle and gas species,and improve the evaporation and combustion of Al particle,which resulting in the increase of combustion efficiency of the powdered rocket motor.When the ratio of spoiler ring flowing diameter to the combustion chamber diameter was between 0.538 and 0.846,the combustion efficiency increased with the reducing flowing diameter of spoiler ring.When the ratio of spoiler ring's distance from the chamber's head position to the chamber's total length was between 0.3 and 0.8,the combustion efficiency increased as the spoiler ring moved toward the chamber's head.The spoiler ring with small flowing diameter and distance from the head between 30%and 40%of the chamber length could be better for the spoiler ring design of powdered rocket motor.
引文
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[2]LOFTUS H,MONTANINO L,BRYNDLE R.Powder rocket feasibility evaluation[R].AIAA 72-1162,1972.
[3]WICKMAN J.In-situ Mars rocket and jet engines burning carbon dioxide[R].AIAA 99-2409,1999.
[4]SZABO J,MILLER T,HERR J,et al.Magnesium bipropellant rockets for martian ascent vehicles[R].AIAA-2011-5834,2011.
[5]李悦,胡春波,孙海俊,等.粉末火箭发动机燃烧室燃烧流动特性研究[J].固体火箭技术,2014,37(6):792-797.LI Yue,HU Chunbo,SUN Haijun,et al.Study on flow and combustion characteristics in the thrustchamber of powder rocket[J].Journal of Solid Rocket Technology,2014,37(6):792-797.(in Chinese)
[6]李超,胡春波,武冠杰,等.喷注压降对Al/AP粉末火箭发动机工作特性影响研究[J].推进技术,2018,39(12):2873-2880.LI Chao,HU Chunbo,WU Guanjie,et al.Investigation on effects of injection pressure drop on Al/AP powder rocket motor operation characteristics[J].Journal of Propulsion Technology,2018,39(12):2873-2880.(in Chinese)
[7]孙海俊,胡春波,徐义华.粉末推进剂流化过程及高压流化机制分析[J].推进技术,2018,39(12):2853-2862.SUN Haijun,HU Chunbo,XU Yihua.Analysis on fluidization process and mechanismof powder propellant at high pressure[J].Journal of Propulsion Technology,2018,39(12):2853-2862.(in Chinese)
[8]朱小飞,胡春波,胡加明,等.氧化剂气量配比对Mg/CO2发动机性能影响实验[J].航空动力学报,2019,34(2):479-485.ZHU Xiaofei,HU Chunbo,HU Jiaming,et al.Exiperiments on influence of oxygen gas intake plan on performance of Mg/CO2engine[J].Journal of Aerospace Power,2019,34(2):479-485.(in Chinese)
[9]银仁亮,周进,张光中,等.双组元液体远地点火箭发动机扰流环的设计方法研究[J].火箭推进,2004,30(1):11-15.YIN Renliang,ZHOU Jin,ZHANG Guangzhong,et al.Design method of spoiler ring for bipropellant liquid apogee rocket engine[J].Journal of Rocket Propulsion,2004,30(1):11-15.(in Chinese)
[10]杨玉新,胡春波,秦飞,等.固液发动机固体燃料瞬态退移速率[J].推进技术,2008,29(5):533-538.YANG Yuxin,HU Chunbo,QIN Fei,et al.Study of instantaneous regression rate in hybrid rocket motor[J].Journal of Propulsion Technology,2008,29(5):533-538.(in Chinese)
[11]王鹏飞,田辉,俞南嘉,等.药柱含扰流板H2O2/HTPB固液火箭发动机两相流数值计算[J].航空动力学报,2013,28(11):533-538.WANG Pengfei,TIAN Hui,YU Nanjia,et al.Two-phase flow numerical calculation of H2O2/HTPB hybrid rocket engine with diaphragm in grain[J].Journal of Aerospace Power,2013,28(11):533-538.(in Chinese)
[12]LAZZARIN M,FAENZA M,BARATO F.Computational fluid dynamics simulation of hybrid rockets of different scales[J].Journal of Propulsion and Power,2015,31(5):1458-1469.
[13]胡松启,李葆萱.固体火箭发动机燃烧基础[M].西安:西北工业大学出版社,2014.
[14]KIM K,KIM C,YOO J.Test-based thermal decomposition simulation of AP/HTPB and AP/HTPE propellants[J].Journal of Propulsion and Power,2011,27(4):822-827.
[15]BROOKS K P,BECKSTEAD M W.Dynamics of aluminum combustion[J].Journal of Propulsion and Power,1995,11(4):769-780.
[16]BECKSTEADM W.A summary of aluminum combustion[M].Provo,Utah:Brigham Young University Press,2004.
[17]LI Yue,HU Chunbo,DENG Zhe,et al.Experimental study on multiple-pulse performance characteristics of ammonium perchlorate/aluminum powder rocket motor[J].Acta Astronautica,2017,133:455-466.
[18]陈斌斌,夏智勋,王德全,等.固冲发动机补燃室掺混过程评估方法研究[J].固体火箭技术,2013,36(6):731-735.CHEN Binbin,XIA Zhixun,WANG Dequan,et al.Study on mixing process assessment method in solid ramjet[J].Journal of Solid Rocket Technology,2013,36(6):731-735.(in Chinese)
[19]何洪庆,张振鹏.固体火箭发动机气体动力学[M].西安:西北工业大学出版社,1988.
[20]鲍福庭,刘旸,惠卫华,等.固体火箭发动机设计[M].西安:西北工业大学出版社,2013.