脉冲爆震火箭发动机收敛扩张喷管数值模拟

李强; 范玮; 严传俊

脉冲爆震火箭发动机收敛扩张喷管数值模拟

西北工业大学动力与能源学院, 西安 710072

基金项目: 国家自然科学基金资助项目(50106012,50336030); 新世纪优秀人才计划资助项目(NCET-04-0960)

详细信息

中图分类号: V 231
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- 被引次数: 5
出版历程
- 收稿日期: 2006-03-30
- 网络出版日期: 2007-07-31

Numerical simulation of converging-diverging nozzle flow in pulse detonation rocket engine

School of Power and Energy, Northwestern Polytechnical University, Xi-an 710072, China

摘要

摘要: 排气喷管是脉冲爆震火箭发动机(PDRE)的重要部件,对提高发动机的推进性能起着重要的作用.应用特征线法给出一维CJ爆震波在理想爆震管内传播过程的解析解.对爆震波到达爆震管口后,发动机的非定常排气过程进行了二维轴对称数值模拟.数值模拟结果形象地反应了非定常流场的演变,详细讨论了激波和涡等的发展变化过程.所选用的收敛扩张喷管能够提高发动机性能达到18.24％.
- 脉冲爆震火箭发动机 /
- 爆震 /
- 喷管 /
- 数值模拟
Abstract: Exhaust nozzle is one of the key components of pulse detonation rocket engine (PDRE). Exhaust nozzle can be used to improve the propulsion performance of PDRE. Method of characteristic (MOC) was used to calculate one-dimensional CJ(Chapman-Jouguet)detonation wave propagating in the ideal detonation tube. The unsteady blowdown process after the CJ detonation wave reach the exit of detonation tube was two-dimensional axisymmetric numerical simulated. The results of numerical simulation demonstrated the development of the unsteady flow field, and the unsteady waves and vortexes were discussed. Contrary to PDRE without nozzle, the CD nozzle can augment propulsive performance by 18.24%.
- pulse detonation rocket engine /
- detonation /
- nozzle /
- numerical simulation

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参考文献(1)

[1] Bratkovich T E, Aarnio M J, Williams J T, et al. An introduction to pulse detonation rocket engines (PDREs) . AIAA 97-2742, 1997 [2] Kailasanath K. Review of propulsion applications of detonation waves [J]. AIAA Journal ,2000, 38(9):1698-1708 [3] McBride B J, Gordon S. Computer program for calculation of complex chemical equilibrium compositions and applications . NASA Reference Publication 1311, 1996 [4] Matsutomi Y, Meyer S E, Heister S D , et al. Impulse measurements and analytical studies on a cyclic pulse detonation engine . AIAA2003-4824, 2003

施引文献

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