航天推进技术研究院主办
[1]李茂,高玉闪,金平,等.富氢/富氧燃气温度对同轴直流气-气喷嘴性能的影响[J].火箭推进,2010,36(01):19-24.
Li Mao,Gao Yushan,Jin Ping,et al.Effects of temperature of hydrogen-rich/oxygen-rich hot gas on performance of a shear coaxial injector[J].Journal of Rocket Propulsion,2010,36(01):19-24.
点击复制
Li Mao,Gao Yushan,Jin Ping,et al.Effects of temperature of hydrogen-rich/oxygen-rich hot gas on performance of a shear coaxial injector[J].Journal of Rocket Propulsion,2010,36(01):19-24.
富氢/富氧燃气温度对同轴直流气-气喷嘴性能的影响
《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]
卷:
36
期数:
2010年01期
页码:
19-24
栏目:
研究与设计
出版日期:
2010-02-15
- Title:
- Effects of temperature of hydrogen-rich/oxygen-rich hot gas on performance of a shear coaxial injector
- 文章编号:
- (2010)01-0019-06
- 分类号:
- V434
- 文献标志码:
- A
- 摘要:
- 通过求解使用k-ε湍流模型的Navier-Stokes方程组对采用同轴直流气-气单喷嘴燃烧室的燃烧流场进行数值模拟，对比分析了富氢/富氧燃气推进剂与常温氢气/氧气推进剂条件下的燃烧流场、燃烧室室壁和喷注面板处的燃气温度，研究了富氢/富氧燃气温度变化对燃烧流场和燃烧室热载的影响。数值结果表明：富氢/富氧燃气气-气喷嘴的燃烧性能较好，但热载较高；富氢/富氧燃气温度一定范围内提高对燃烧性能影响不明显，而热载增加。
- Abstract:
- The turbulent Navier-Stokes equations in combination with the two equation k-ε turbulence model were used to simulate the flow field in the chamber of a shear coaxial gas-gas injector. Combustion performance and heat load were compared between the gas-gas injector of the hydrogen-rich/oxygen-rich hot gas and the gas-gas injector of the ambient hydrogen/oxygen. The influence of the temperature of the hydrogen-rich/oxygen-rich hot gas on the performance of gas-gas injector was studied. The results show that the combustion performance of the gas-gas injector of the hydrogen-rich/oxygen-rich hot gas was better than the gas-gas injector of the ambient hydrogen/oxygen, but the heat load of the faceplate and the chamber were increased. The combustion performance was indistinctive to the temperature of the hydrogen-rich/oxygen-rich hot gas products, but the heat load of the faceplate and the chamber were increased.
参考文献/References:
[1]Cai Guobiao, Wang Xiaowei, Jin Ping, et al. Experimental and Numerical Investigation of Large Mass Flow Rate Gas-Gas Injectors[R]. AIAA-2008-4562. [2]Vaidyanathan A, Gustavsson J, Segal C. Heat Fluxs/OH PLIF Measurements in a GO2/GH2 Single-element, Shear Injector[R]. AIAA-2007-5591. [3]Conley A, Vaidyanathan A, Segal C. Heat Flux Measurements for a GO2/GH2 Single-Element, Shear Injector[J]. Journal of Spacecraft and Rockets. Vol.44, No.3, May-June 2007. [4]Vaidyanathan R, Tucker P. K, Papila N, et al. Computational-fluid-dynamics-based Design Optimization for Single-Element Rocket Injector. Journal of Propulsion and Power[J]. Vol.20, No.4, July-August 2004. [5]Shyy W, Kevin T P, Vaidyanathan R. Response Surface and Neural Network Techniques for Rocket Engine Injector Optimization [J]. Journal of Propulsion and Power. 2001, 7(2): 391-401. [6]Lin J, West J S, Williams W R, et al. CFD Code Validation of Wall Heat Flux Heat Fluxes for a GO2/GH2 Single Element Combustor[R]. AIAA-2005-4524. [7]Marshall W M., Pal S. Benchmark Wall Heat Flux Data for a G02/GH2 Single Element Combustor[R]. AIAA 2005-3572. [8]中国航天工业总公司.世界导弹与航天发动机大全[M]. 北京: 军事科学出版社, 1999. [9]Sozer E, Vaidyanathan A, Segal C, et al. Computational Assessment of Gaseous Reacting Flows in Single Element Injector[R]. AIAA 2009-449. [10]Shang M, Chen Y, Paul L. Investigation of Chemical Kinetics Integration Algorithms for Reacting Flows[R]. AIAA 95-0806.
备注/Memo
收稿日期：200９-０9-１1；修回日期：2010-01-04。基金项目：国家“863”计划资助项目（2008702504）。
基金项目：国家“863”计划资助项目（2008702504）。
作者简介： 李茂（1983—），男，博士研究生，研究领域为全流量补燃循环发动机气-气燃烧技术。
更新日期/Last Update:
1900-01-01