期刊文献+

旋转条件下长尾喷管发动机三维两相流场数值模拟 被引量:2

Three Dimension Two Phase Flow Field Numerical Simulation on Tail-Pipe Nozzle SRM under Spinning Condition
下载PDF
导出
摘要 针对旋转条件下长尾喷管发动机的三维两相流场开展了一体化数值模拟,进行了旋转速度为0、100 r/min、300 r/min、500 r/min和1 000 r/min,颗粒直径为10μm、40μm、70μm和100μm条件下颗粒运动轨迹和聚集浓度分布影响的研究。研究结果表明:①与无旋转条件下的颗粒运动轨迹以及聚集分布规律相比,在本旋转条件下,颗粒的运动历程增加,滞留时间增加,颗粒的聚集部位发生改变;②随着旋转速度增大,颗粒加入主流后首先贴着壁面作周向环绕运动,旋转速度越大,颗粒的旋转环绕轨迹越长;颗粒环绕运动的区域也随着旋转速度的增大而增大;颗粒所滞留的时间总体上是增大的;③随着颗粒直径的增大,由于颗粒本身运动惯性的增大,随流性变弱,受旋转作用影响的程度变差,滞留时间减小;④随着旋转速度的增大,锥台型装药壁面和后封头处的颗粒聚集浓度呈现增加趋势,翼槽表面的颗粒聚集带由翼槽顶部向根部移去;轴线处的颗粒聚集浓度随旋转速度增大而逐渐减弱。 Numerical simulations of three dimensions two - phase flow field of tail - pipe SRM under spinning condition are carried out. The differences of the particle trace and particle concentration along the wall of tail - pipe nozzle between the different diameters 10 μm, 40 μm, 70 μm, 100 μm and different spinning velocities 0, 100 r/min, 300, r/min, 500 r/min, l 000 r/min are studied. The results show that :①in comparison with the particle movement trace and particle concentration distributing rule under the no - spinning condition, the particle movement path and time are increased and the change of particle movement rule is obvious under the spinning condition;② With the increase of the spinning velocity, the movement path and area of particles and residence time are increased;③With the increase of the particle diameter, the particle residence time is shortened because the particle inertia has more effects than the trend to revolving effect; ④With the increase of the spinning velocity, the particle concentration in surface of conocyl grain is increased, and the particle congregation area is transferred from the fin top to the root of finocyl grain. The particle concentration is reduced in axis of flow path with the increase of spinning velocity.
出处 《空军工程大学学报(自然科学版)》 CSCD 北大核心 2009年第5期10-15,共6页 Journal of Air Force Engineering University(Natural Science Edition)
基金 国家自然科学基金资助项目(50776073)
关键词 固体火箭发动机 长尾喷管 两相流 数值模拟 旋转条件 solid rocket motor tail-pipe nozzle two phase numerical simulation spinning condition
  • 相关文献

参考文献6

二级参考文献26

  • 1张为华,曹泰岳,万章吉.固体火箭发动机旋转对燃速的影响[J].航空动力学报,1994,9(1):67-70. 被引量:11
  • 2陶文栓.数值传热学[M].西安:西安交通大学出版社,1988..
  • 3张健 周力行.强旋湍流流动和煤粉燃烧的模拟:博士论文[M].北京:清华大学,1992..
  • 4曹泰岳,固体火箭发动机燃烧过程理论基础,1992年
  • 5张如洲,兵工学报,1988年,2期
  • 6李宜敏,固体火箭发动机原理,1991年
  • 7蔡国飙,推进技术,1999年,20卷,1期
  • 8邵爱民,固体火箭技术,1998年,3期
  • 9张健,学位论文,1992年
  • 10陶文栓,数值传热学,1988年

共引文献20

同被引文献21

  • 1刘静,徐旭.随机轨道模型在喷管两相流计算中的应用[J].固体火箭技术,2006,29(5):333-336. 被引量:6
  • 2Strykpwski P J, Krothapaijj A, Forliti D J. Counterflow thrust vectoring of supersonic jets [J]. AIAA Journal, 1996,34(11) :2306-2314.
  • 3Kowal H J. Advances in thrust vectoring and the applica- tion of flow-control technology[J]. Canadian Aeronautics and Space Journal, 2002,48 ( 1 ) : 145-151.
  • 4Lloyd S R,Thorp G R. A review of thrust vector control systems for tactical missiles [ R]. Las Vegas, Nevada: AIAA/SAE 14th Joint Propulsion Conference,1978.
  • 5Anderson C J,Giuliano V J, Wing D J, et al. Investigation of hybrid fluidic/mechanical thrust vectoring for fixed:exit exhaust nozzles[R]. AIAA 97-3148,1997.
  • 6Deere K A,Berrier B L,Flamm J D. A computational study of a new dual throat fluidic thrust vectoring nozzle concept [R]. AIAA 2005-3502,2005.
  • 7Deere K A. Summary of fluidic thrust vectoring research conducted at NASA Langley research center[R]. AIAA- 2003-3800,2003.
  • 8Waithe K A, Deere K. Experimental and computation in vestigation of multiple injection ports in a convergent-all vergent nozzle for fluidic thrust vectoring[R]. AIAA 2003 3802,2003.
  • 9李志杰,王占学,蔡元虎.自由流Ma对流体推力矢量喷管气动性能影响的数值模拟[C]//第三届中国航空学会青年科技论坛文集.贵阳:中国航空学会,2008:248-256.
  • 10Mangin B,Chpoun A,Jaequin L. Experimental and numer- ical study of the fluidic thrust vectoring of a two dimen- sional supersonic nozzle[R]. AIAA 2006-3666,2006.

引证文献2

二级引证文献15

相关作者

内容加载中请稍等...

相关机构

内容加载中请稍等...

相关主题

内容加载中请稍等...

浏览历史

内容加载中请稍等...
;
使用帮助 返回顶部