航天推进技术研究院主办
[1]李自然,林志勇.来流状态对超声速气动斜劈诱导爆震起爆过程的影响[J].火箭推进,2015,41(01):29-35.
LI Zi-ran,LIN Zhi-yong.Influence of flow state on initiation process of oblique detonation wave induced by hydrodynamic wedge in supersonic combustible flow[J].Journal of Rocket Propulsion,2015,41(01):29-35.
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LI Zi-ran,LIN Zhi-yong.Influence of flow state on initiation process of oblique detonation wave induced by hydrodynamic wedge in supersonic combustible flow[J].Journal of Rocket Propulsion,2015,41(01):29-35.
来流状态对超声速气动斜劈诱导爆震起爆过程的影响
《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]
卷:
41
期数:
2015年01期
页码:
29-35
栏目:
研究与设计
出版日期:
2015-04-30
- Title:
- Influence of flow state on initiation process of oblique detonation wave induced by hydrodynamic wedge in supersonic combustible flow
- Keywords:
- supersonic combustionoblique detonationlow-speed thermojetinitiation processinfluence fact
- 分类号:
- V434-34
- 文献标志码:
- A
- 摘要:
- 超声速斜爆震热射流起爆特性受到气流状态参数的影响。针对低速持续热射流，采用高速激光纹影技术和压力传感器测压技术，研究低速热射流预混气来流当量比、温度和速度等状态参数的影响。实验发现，当量比对起爆过程的影响具有一定的随机性，但一般情况下，当量比的增加，有利于爆燃向爆震转变（Deflagration to Detonation, DDT）过程；提高来流温度，将缩短DDT时间，有利于起爆；而提高来流速度，则将阻碍剪切层发展，导致混合效果变差，不利于起爆。
- Abstract:
- The initiation characteristics of supersonic-speed oblique detonation thermojet are influenced by the airflow status parameters. The high speed laser schlieren technology and pressure sensor technology are adopted to study the influence of state parameters such as the thermojet premixed combustible gas equivalence ratio, inlet flow temperature and velocity on the low-speed continuous thermojet. It is found in the experiment that the influence of equivalence ratio on the initiation process has a certain randomness, but under general condition, increase of the fuel equivalence ratio will benefit DDT (deflagration to detonation), increase of the inlet flow temperature will reduce the DDT time and benefit the initiation, and increase of the inlet flow velocity will result in poor mixing effect and will not benefit the initiation.
参考文献/References:
[1]LU F K. Prospects for detonations in propulsion[C]//Proceedings of the 9th International Symposium on Experimental and Computational Aerothermodynamics of Internal Flows. Gyeongju, Korea: [s.n.], 2009: 11-14.
[2]HARRIS P G. Structure of conical oblique detonation waves[C]//44th AIAA/ASME/ SAE/ASEE Joint Propulsion Conference & Exhibit. Harvard, CT: AIAA, 2008: 111-115.
[3]OSTRANDER M J, HYDE J C, YOUNG M F, et al. Standing oblique detonation wave engine performance, AIAA 1987-2002[R]. USA: AIAA, 1987.
[4]SISLIAN J P. Propulsive performance of hypersonic oblique detonation wave and shock-induced combustion ramjets[J]. Journal of Propulsion and Power, 2001, 17(3): 599-604.
[5]FUSINA G. Formation and stability of near chapman- jouguet standing oblique detonation waves[J]. American Institute of Aeronautics and Astronautics, 2005, 43(7): 1591-1604.
[6]HARRIS P G. Structure of conical oblique detonation waves[C]//44th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit. Harvard, CT: AIAA, 2008: 222-228.
[7]FUSINA G, PARENT B. Numerical study of structure and stability of oblique detonation waves[C]//42nd AIAA Aerospace Sciences Meeting and Exhibit, AIAA 2004-1125. Reno, Nevada: AIAA, 2004: 123-128.
[8]CARRIER G F, FENDELL F E. Nonintrusive stabilization of a conical detonation wave for supersonic combustion [J]. Combustion and Flame, 1995, 103(4): 281-295.
[9]LEE J H S. Initiation of gaseous detonation[J]. Annual Review of Physical Chemistry, 1977, 28: 75-104.
[10]CHOI J Y. Capturing unstable wrinkled oblique detonation wave front by Hi-Fi numerical simulation, AIAA 2006-5100[R]. USA: AIAA, 2006.
相似文献/References:
[1]李自然,林志勇,韩 旭.超声速斜爆震发动机起爆过程研究综述[J].火箭推进,2013,39(03):1.
LI Zi-ran,LIN Zhi-yong,HAN Xu.Investigation for initiation process of supersonic oblique detonation engine[J].Journal of Rocket Propulsion,2013,39(01):1.
[2]杜炜强,吴宝元.带不同长度凹腔超声速燃烧数值研究[J].火箭推进,2005,31(04):26.
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备注/Memo
收稿日期：2014-10-13；修回日期：2014-12-02 基金项目：国家自然科学基金资助项目（51206182） 作者简介：李自然（1977—），男，博士，讲师，研究领域为先进火箭推进技术、高等教育研究
更新日期/Last Update:
1900-01-01