期刊文献+

两步起爆过程中爆震波衍射特性研究

Investigation on Diffraction of Detonation in Two-step Detonation Initiation Process
下载PDF
导出
摘要 为了研究两步爆震起爆过程,通过数值模拟研究了填充条件和预爆管出口伸进扩张过渡段的长度L对爆震波衍射特性的影响规律。结果表明:L越小扩张过渡段对爆震起爆的加强作用越明显,但预爆管与扩张过渡段间的渐扩通道对爆震波回传的阻滞作用越弱;L越大,则结果相反。因此,应选择合适的L使扩张过渡段与渐扩通道对爆震波传播的增强作用达到最大。同时,在L=35 mm时,爆震波能够较早地与扩张过渡段壁面作用形成高温、高压区,从而加强了爆震波的传播,且预爆管与扩张过渡段之间的渐扩通道能对回传的爆震形成一定的阻滞作用。 In order to investigate two - step detonation initiation process, the pre - detonators with different L ( distance between transition section inlet and pre -detonator outlet) inserted transition section are simulated. The results indicate that the smaller the L, the more obvious the enhanced effect of the transition section is, but the effect caused by gradually outspread passage is weaker. When L turns longer, the trend is opposite. So it is necessary to choose a suitable L for the transition section and the gradually outspread passage to optimize the enhanced effect of detonation wave transition. When L is equal to 35 mm, the numerical simulated results indicate that the high ternperature and high pressure area can be formed earlier to reinforce the detonation wave transition. The gradually out- spread passage between pre -detonator and area expansion can form a better retardant effect on the return detonation wave, which prevents the excessively augment of the pressure in blender of the main combustor tube, then the two - step initiation of detonation can be successfully achieved.
出处 《空军工程大学学报(自然科学版)》 CSCD 北大核心 2010年第5期6-10,共5页 Journal of Air Force Engineering University(Natural Science Edition)
基金 空军工程大学学术基金资助项目(XS0901009)
关键词 脉冲爆震发动机 两步爆震起爆 预爆管 衍射特性 pulse detonation engine two - step initiation pre - detonator diffraction characteristic
  • 相关文献

参考文献8

  • 1Brophy C M, Sinibaldi I O. Operation of A JP - 10/Air Pulse Detonation Engine[ R]. AIAA 2000 -3591.
  • 2Anderson S D, Tonouchi J H, Lidstone G L. Performance Trends for A Product Scale Pulse Detonation Engine[ R]. AIAA 2004 - 3402.
  • 3Piton Dominique, Prigent Alban, Serre Laurent. Performance of A Valveless Air Breathing Pulse Detonatiron Engine [ R ]. AIAA 2004 - 3749.
  • 4Panicker Philip K, Li Jiun -Ming, Lu Frank K, et al. Development of A Compact Liquid Fueled Pulsed Detonation Engine with Predetonator [ R ]. AIAA 2007 - 0237.
  • 5Brophy C M, Sinibaldil J O, Damphousse P. Initiator Performance for Liquid -Fueled Pulse Detonation Engines [ R]. AIAA 2002 - 0472.
  • 6Brophy C M, Wemer L T S, Sinibaldi J O. Performance Characterization of A Valveless Pulse Detonation Engine[ R]. AIAA 2003 - 1344.
  • 7韩启祥,王家骅.预混气爆震波在不同直径管间的传播特性[J].航空动力学报,2005,20(2):225-229. 被引量:5
  • 8Kailasanath K. Recent Developments in the Research on Pulse Detonation Engines[ R]. AIAA 2002 -0470.

二级参考文献4

  • 1Brophy C,Sinibaldi J.Operation of a JP-10/Air Pulse Detonation Engine[R].AIAA 00-3591.
  • 2Zeldovich IaB,Kogarko S M,Simonov N N.An Experimental Investigation of Spherical Detonation in Gases[J].Soviet Phys Tech Phys,1956,1:1689~1713.
  • 3Desbordes D, Critical initiation conditions for gaseous diverging spherical detonations[J].Journal de Physique,1995,5(4):155~162.
  • 4Sugimura.Behavior of Detonations Passing Through Reflection Nozzles[J].JSME International,Journal B,1995,38(3):353~359.

共引文献4

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