突扩管爆轰推进及其喷管推力性能数值模拟

张焕好; 陈志华; 孙晓晖; 范宝春

doi:10.11858/gywlxb.2010.06.003

突扩管爆轰推进及其喷管推力性能数值模拟

doi: 10.11858/gywlxb.2010.06.003

南京理工大学瞬态物理重点实验室，江苏南京 210094

详细信息

通讯作者:
陈志华

计量
- 文章访问数: 7804
- HTML全文浏览量: 406
- PDF下载量: 639
出版历程
- 收稿日期: 2009-10-13
- 修回日期: 2010-03-19
- 发布日期: 2010-12-15

Numerical Simulations on the Thrust Performance of Nozzles and Detonation Propulsion of a Sudden Area Change Tube

Science and Technology on Transient Physics Laboratory, Nanjing University of Science & Technology, Nanjing 210094, China

More Information

Corresponding author: CHEN Zhi-Hua

摘要

摘要: 基于均相反应流N-S方程以及k-湍流模型与EBU燃烧模型，对爆轰波在突扩管内传播，以及主爆轰管加装不同形状喷管后对推力性能的影响进行了数值模拟。结果表明，爆轰波从预爆管进入主管后，能迅速诱发新的爆轰。另外，主管加装各类喷管后，单次爆轰所得的平均推力发生变化。其中，发动机端部推力随喷管收敛角度的增大而提高，并随扩张角度的增大而降低，但平均总推力却随扩张角度的增大而提高，随收敛角度的增大而降低，并存在一个最佳扩张角。
- 爆轰波 /
- 燃烧 /
- 推进 /
- 喷管形状
Abstract: Based on the homogenous fluid reaction N-S equations, the k- turbulent model and the EBU combustion model, the propagation of detonation wave in a sudden area change tube and the influences on the thrust performance of the main tube with different nozzles were investigated. Our results show that, a new detonation can be initiated promptly when the detonation wave of the pre-detonator injects into the main tube. In addition, with the mount of nozzle, the average thrust of single detonation varies. The head-end thrust increases with the raise of the contracting angle of nozzle, and decreases with the raise of its diverging angle. But the average total thrust increases with the diverging angle, and decreases with the raise of converging angle. There also exists an optimal diverging angle which can generate maximum average total thrust.
- detonation wave /
- combustion /
- propulsion /
- nozzle shape

HTML全文

参考文献(23)

Bussing T, Pappas G. An Introduction to Pulse Detonation Enignes [R]. AIAA 94-0263, 1994.

Eidelman S. Pulse Detonation Engine: A Status Review and Technology Development Road Map [R]. AIAA 97-2740, 1997.

Kailasanath K. A Review of PDE Research-Performance Estimates [R]. AIAA 2001-0474, 2001.

Roy G D, Frolov S M, Borisov A A, et al. Pulse Detonation Propulsion: Challenges, Current Status, and Future Perspective [J]. Progress in Energy and Combustion Science, 2004, 30: 545-672.

New T H, Panicker P K, Lu F K, et al. Experimental Investigations on DDT Enhancements by Schelkin Spirals in a PDE [R]. AIAA, 2006-552, 2006.

Frolov S M, Semenov I V, Utkin P S, et al. Enhancement of Shock-to-Detonation Transition in Channels with Regular Shaped Obstacles [A]//21st ICDERS [C]. Poitiers, France, 2007.

Li C, Kailasanath K. Detonation Diffraction in Pulse Detonation Engines [R]. AIAA 2000-3470, 2000.

Han Q X, Wang J H. Investigation on Characteristics of Detonation Wave Propagation in Tubes with Different Diameter [J]. Journal of Aerospace Power, 2005, 20(2): 225-229. (in Chinese)

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.

Nikitin V F, Dushin V R, Phylippov Y G, et al. Pulse Detonation Engines: Technical Approaches [J]. Acta Astronautica, 2009, 64: 281-287.

Kailasanath K. A Review of Research on Pulse Detonation Engine Nozzles [R]. AIAA 2001-3932, 2001.

Tangirala V E, Dean A J. Performance Estimations of a Pulse Detonation Engine with Exit Nozzle [R]. AIAA 2006-4792, 2006.

Li M, Yan C J, Zheng L X, et al. Experimental Investigation on Pulse Detonation Engine Nozzles [J]. Journal of Experiments in Fluid Mechanics, 2006, 20(3): 13-17. (in Chinese)

李牧, 严传俊, 郑龙席, 等. 脉冲爆震发动机喷管实验研究 [J]. 实验流体力学, 2006, 20(3): 13-17.

Eidelman S, Yang X. Analysis of the Pulse Detonation Engine Efficiency [R]. AIAA 1998-3877, 1998.

Mohanraj R, Merkle C L. A Numerical Study of Pulse Detonation Engine Performance [R]. AIAA 2000-0315, 2000.

Danieu, Z R, Desbordes D. Effects of Nozzles of Different Length and Shape on Propulsive Performance of Pulsed Detonation Engines [A]//International Colloquium on the Control of Detonation Processes [C]. Moscow, 2000.

Eidelman S, Yang X. Analysis of the Pulse Detonation Engine Efficiency [R]. AIAA 1998-3877, 1998.

Fan W, Yan C J, Li Q, et al. Experiment on Pulse Detonation Rocket Engines [J]. Journal of Propulsion Technology, 2006, 27(5): 385-389. (in Chinese)

范玮, 严传俊, 李强, 等. 脉冲爆震火箭发动机试验 [J]. 推进技术, 2006, 27(5): 385-389.

Chen Z H, Fan B C, Li H Z. Numerical Simulation of the Flame Acceleration for Homogeneous Turbulent in a Large Tube [J]. Explosion and Shock Waves, 2003, 23(4): 337-342. (in Chinese)

陈志华, 范宝春, 李鸿志. 管内均相湍流燃烧加速的数值模拟 [J]. 爆炸与冲击, 2003, 23(4): 337-342.

Owens Z C, Hanson R K. Unsteady Nozzle Design for Pulse Detonation Engines [R]. AIAA 2005-3649, 2005.

施引文献

资源附件(0)

访问统计