航天推进技术研究院主办
[1]姚照辉,李光熙,张蒙正,等.燃油分配对超燃冲压发动机的性能影响仿真分析[J].火箭推进,2013,39(04):30-35.
YAO Zhao-hui,LI Guang-xi,ZHANG Meng-zheng,et al.Simulation and analysis for influence of fuel distribution on scramjet performance[J].Journal of Rocket Propulsion,2013,39(04):30-35.
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YAO Zhao-hui,LI Guang-xi,ZHANG Meng-zheng,et al.Simulation and analysis for influence of fuel distribution on scramjet performance[J].Journal of Rocket Propulsion,2013,39(04):30-35.
燃油分配对超燃冲压发动机的性能影响仿真分析
《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]
卷:
39
期数:
2013年04期
页码:
30-35
栏目:
研究与设计
出版日期:
2013-08-30
- Title:
- Simulation and analysis for influence of fuel distribution on scramjet performance
- 文章编号:
- 1672-9374(2013)04-0030-06
- 分类号:
- V434+.13-34
- 文献标志码:
- A
- 摘要:
- 针对超燃冲压发动机两级燃油分配对内流道流动过程、燃烧模态、发动机性能及调节特性的影响问题，建立了发动机一维流动分析模型；对马赫数6/当量比1，马赫数6/当量比0.6，马赫数4/当量比1三种工况不同的一级/二级燃烧室燃油分配比例下的流动过程进行了仿真，并获得了不同燃油分配规律下的发动机性能。通过分析表明：超燃冲压发动机的两级燃油分配比例直接影响发动机内流道内的流动参数分布、燃烧模态及发动机比冲等性能参数。对于马赫数6/当量比1工况，当一级燃烧室的燃油分配比例为30%~70%时，可在全流道内组织纯超声速燃烧，
- Abstract:
- Aiming at the influence of the fuel distribution on the flow mechanism in scramjet duct, combustion mode, engine performance and adjustment characteristic, a one-dimensional scramjet analysis model was established. Simulation of flow process in one-stage/two-stage fuel distribution percent is carried under three different cases, including Ma 6/ψ 1, Ma 6/ψ 0.6, Ma 4/ψ 1. Scramjet performance in different fuel distribution is obtained. The analysis results show that the flow mechanism, combustion mode and engine performance are strongly dependent on the one-stage/two-stage fuel distribution percent. For the case of Ma 6/ψ 1, combustion in the duct can be organized in supersonic flow when one-stage combustor fuel distribution is at the range of 30%~70%, whose maximum specific impulse exceeds 800 s. For the case of Ma 6/ψ 0.6, combustion is always organized in supersonic flow even if all the fuel is injected in one-stage combustor, because the total fuel amounts are too small to choke the combustor duct, whose maximum specific impulse exceeds 800 s. For the case of Ma 4/ψ 1, combustion can be organized in subsonic flow and its maximum specific impulse is 1 031.9 s. Furthermore, the one-stage fuel distribution should not be too high, so as to avoid a subsonic combustion disturbance diffusing outside the combustor entrance.
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备注/Memo
收稿日期：2013-03-28；修回日期：2013-05-28
基金项目：总装备部预研项目（2007AA05306）
作者简介：姚照辉（1982—），男，博士，工程师，研究领域为吸气式高超声速推进技术
更新日期/Last Update:
1900-01-01