超声速自引射装置的工作过程研究

张民庆; 张忠利; 周立新; 张蒙正

超声速自引射装置的工作过程研究

1.
西北工业大学航天学院,西安 71007
2.
中国航天科技集团公司西安航天动力研究所,西安 710100

计量
- 文章访问数: 1604
- HTML浏览量: 86
- PDF量: 473
- 被引次数: 0
出版历程
- 收稿日期: 2011-04-16
- 修回日期: 2011-11-19
- 刊出日期: 2012-01-28

Investigation on working course of supersonic self-ejector

1.
School of Astronautics, Northwestern Polytechnical university, Xi'an 71007
2.
Xi'an Aerospace Propulsion Institute, China Aerospace Science and Technology Corporation, Xi'an 710100, China

摘要

摘要: 应用湍流κ-ε双方程模型,分析了液体火箭发动机自引射工作过程所用的超声速自引射装置(简称引射器,包括圆柱型和二次喉道型引射器)在相同二次流入口面积时的流场分布,依据流场分析值确定了激波在引射器内的位置,结果表明喷管内的气流达到满流状态,并根据有关参数计算了引射系数.对比引射器真空舱内压力仿真值和试车测量值,两者基本一致.
- 液体火箭发动机 /
- 引射器 /
- 流场 /
- 数值模拟 /
- 引射系数
Abstract: The analysis model of self-ejector(ejector for short,including cylindrical ejector and second-throat ejector) was set up in liquid rocket engine.The two equation κ-ε model was employed to simulate the turbulence.The performances and the flow field features of cylindrical and second-throat ejector were gained in same gap.According as these flow fields,the site of the shock wave,the full flow in nozzle,the coefficients of ejecting were calculated.The numerical value was compared with hot fire test value in vacuum cabin,both are same.
- liquid rocket engine /
- ejector /
- flow fields /
- numerical simulation /
- coefficients of ejecting

HTML

参考文献(12)

[1]	徐万武,王振国.环型超声速空气引射器零二次流流场数值研究[J].推进技术,2003,24(1):36-39. XU Wanwu,WANG Zhenguo.Numerical study on flow-fields of the zero-second-flow annular supersonic air ejector[J].Journal of Propulsion Technology,2003,24(1):36-39.(in Chinese)
[2]	邱义芬,王俊清,袁修干,等.多喷嘴引射器性能计算模型[J].北京航空航天大学学报,1997,23(5):621-626. QIU Yifen,WANG Junqing,YUAN Xiugan,et al.Multiple nozzle ejector performance calculating model[J].Journal of Beijing University of Aeronautics and Astronautics,1997,23(5):621-626.(in Chinese).
[3]	吴继平,陈健,王振国.带二次流的多喷管超声速引射器性能实验研究[J].强激光与粒子束,2007,19(9):1439-1443. WU Jiping,CHEN Jian,WANG Zhenguo.Experimental investigation on performance of multi-nozzle supersonic ejector with secondary flow[J].High Power Laser and Particle Beams,2007,19(9):1439-1443.(in Chinese)
[4]	张忠利.超音速二次喉道扩压器气动特性研究[J].火箭推进,2001,27(3):14-22. ZHANG Zhongli.Investigation on supersonic secondary throat ejector[J].Journal of Rocket Propulsion,2007,27(3):14-22.(in Chinese)
[5]	吴继平,王振国.第二喉道超声速引射器启动性能理论研究[J].航空动力学报,2008,23(5):803-809. WU Jiping,WANG Zhenguo.Theoretical investigation on starting performance of supersonic ejector with second throat[J].Journal of Aerospace Power,2008,23(5):803-809.(in Chinese)
[6]	Lu K T,Kou H S,Lan T H.Geometrically and thermally non-optimum ejector heat pump analysis[J].Energy Conversion and Management,1993,34(12):1287-1297.
[7]	Hsu C T.Investigation of an ejector heat pump by analytical methods.Oak Ridge,TN:Oak Ridge National Laboratory,ORNL/CON-144,1984.
[8]	Hammer R M.An investigation of an ejector compression refrigeration cycle and its application to heating,cooling and energy conservation.Alabam:The University of Alabam,1978.
[9]	Keenan J H,Neumann E P,Lustuerk F.An investigation of ejector design by analysis and experiment[J].Journal of Applied Mechanics,1950(72):299-309.
[10]	魏超,张忠利.深空探测发动机热环境研究[J].航空动力学报,2010,25(5):1139-1144. WEI CHao,ZHANG Zhongli.Investigation on thermal environment for deep-space-exploration liquid rocket engine[J].Journal of Aerospace Power,2010,25(5):1139-1144.(in Chinese)
[11]	陈建华,卢钢,张贵田,等.冷却环带喷注结构对煤油超临界液膜的影响研究[J].航空动力学报,2008,23(2):336-341. CHEN Jianhua,LU Gang,ZHANG Guitian,et al.Investigation on the effects of injection structure on kerosene supercritical cooling film[J].Journal of Aerospace Power,2008,23(2):336-341.(in Chinese)
[12]	张忠利.高空滑行期间燃烧室温度仿真方法研究[J].火箭推进,2001,27(6):14-18. ZHANG ZHongli.Investigation on the method of numerical simulation of temperature distribution combustion chamber during coast[J].Journal of Rocket Propulsion,2001,27(6):14-18.(in Chinese)