Journal of Projectiles, Rockets, Missiles and Guidance >
The Investigation on the Influence of Distance between Jet Inlet and Concave Exit Plane on Detonation Initiation by Shock Wave Focusing
Received date: 2011-05-27
Online published: 2025-05-29
In order to investigate the influence of the distance between jet inlet and concave exit plane on detonation initiation via shock wave focusing in a 2-stage PDE, detonation initiation with different L (the distance between jet inlet and concave exit plane) was simulated and hydrogen-air mixture was used in this paper. The results indicate that in the hemisphere concave cavity, the appropriate length of L can improve the incidence of leading shock at the concave wall to increase the reflected shock wave area and Aprrease the incidence angle and thus improve the reflecting effect. As L increases, the distance between the focus and concave wall is enlarged. Further more, when L = 1d, the impulse on unit concave area is the largest during a detonation cycle.
ZHANG Rongli , HE Liming , RONG Kang , CHEN Xin , ZENG Hao . The Investigation on the Influence of Distance between Jet Inlet and Concave Exit Plane on Detonation Initiation by Shock Wave Focusing[J]. Journal of Projectiles, Rockets, Missiles and Guidance, 2012 , 32(2) : 137 -140,161 . DOI: 10.15892/j.cnki.djzdxb.2012.02.023
| [1] | Roy GD, Frolov S M, Borisov A A, et al. Pulsed detona-tion propulsion: challenges, current status, and future per-spective[J]. Progress in Energy and Combustion Science, 2004, 30 (6): 545- 672. |
| [2] | Levin V A, Nechaev JN, Tarasov A I. A new approach toorganizing operation cycles in pulse detonation engines, ADA406683[R]. |
| [3] | Ivett A Leyva, Venkat Tangirala, Anthony J Dean. Investiga-tion of unsteady flow field in a 2 - Stage PDE resonator, ΑΙΑΑ-2003-0715[R]. 2003. |
| [4] | Keith R McManus, Anthony J Dean. Experimental evalua-tion of a two-stage pulse detonation combustor, AIAA2005-3773[R]. 2005. |
| [5] | 王栋. 脉冲爆震发动机工作过程数值模拟研究[D]. 南京: 南京理工大学, 2007. |
| [6] | 姜日红, 武晓松, 王栋. 共振型 PDE 谐振腔喷嘴匹配关系研究. 航空动力学报, 2009, 24 (5): 56– 60. |
| [7] | 李海鹏, 何立明, 陈鑫, 等. 不同结构形式凹面腔内的激波聚焦起爆爆震波数值研究[C]// 第九届全国冲击动力学学术会议, 2009. |
| [8] | 李海鹏, 何立明, 陈鑫, 等. 凹面腔內激波聚焦起爆爆震波过程的数值模拟[J]. 推进技术, 2010, 31 (1): 87– 91. |
| [9] | KONNOV A A. Refinement of the kinetic mechanism of hy-drogen combustion[J]. Khimicheskaya Fizika, 2004, 23 (8): 5- 18. |
| [10] | KONNOV A A. Remaining uncertainties in the kineticmechanism of hydrogen combustion[J]. Combust.Flame, 2008, 152 (4): 507- 528. |
| [11] | Achasov O V, Penyazkov O G. Some gasdynamic methodfor control of detonation initiation and propagation, AIAA2001-3614 R. 2001. |
/
| 〈 |
|
〉 |