航天推进技术研究院主办
[1]杨丹奇,卓丹晨,吴润生,等.NTO/UDMH燃烧机理构建与着火特性分析[J].火箭推进,2024,50(05):82-95.[doi:10.3969/j.issn.1672-9374.2024.05.008]
YANG Danqi,ZHUO Danchen,WU Runsheng,et al.Construction of NTO/UDMH combustion mechanism and analysis of ignition characteristics[J].Journal of Rocket Propulsion,2024,50(05):82-95.[doi:10.3969/j.issn.1672-9374.2024.05.008]
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YANG Danqi,ZHUO Danchen,WU Runsheng,et al.Construction of NTO/UDMH combustion mechanism and analysis of ignition characteristics[J].Journal of Rocket Propulsion,2024,50(05):82-95.[doi:10.3969/j.issn.1672-9374.2024.05.008]
NTO/UDMH燃烧机理构建与着火特性分析
《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]
卷:
50
期数:
2024年05期
页码:
82-95
栏目:
目次
出版日期:
2024-11-13
- Title:
- Construction of NTO/UDMH combustion mechanism and analysis of ignition characteristics
- 文章编号:
- 1672-9374(2024)05-0082-14
- Keywords:
- unsymmetrical dimethyl hydrazine; nitrogen tetroxide; construction of reaction mechanism; simplify the mechanism
- 分类号:
- V511.4
- 文献标志码:
- A
- 摘要:
- 为提高自燃推进剂液体火箭发动机燃烧流场的CFD数值计算精度,基于分级法思想构建了63组分357基元反应的四氧化二氮(NTO)/偏二甲肼(UDMH)详细燃烧机理。分别采用单一简化方法与综合多种简化方法对详细机理进行简化,得到与详细机理吻合较好的35组分149基元反应和23组分19基元反应。在此基础上,研究了不同压力、温度与氧燃比对详细机理与简化机理着火特性的影响规律:增大初始压力整体会增加系统平衡温度与着火延迟时间,初始压力越大,系统平衡温度增加越慢,从1 035～1 320 K/MPa减小至170～320 K/MPa; 初始温度的升高会增加系统平衡温度但缩短了着火延迟时间,初始温度增加1 K,系统平衡温度约增大3 K; 增大氧燃比会降低系统平衡温度、增大着火延迟时间,氧燃比越大,着火延迟时间增加越多。获得的规律为NTO/UDMH反应动力学研究提供了重要的参考依据与理论基础,构建得到的详细及简化机理有助于建立更加准确的发动机燃烧流场仿真模型。
- Abstract:
- To improve the CFD numerical calculation accuracy of the combustion of hypergolic propellant liquid rocket engines, a detailed combustion mechanism of nitrogen tetroxide(NTO)/unsymmetrical dimethylhydrazine(UDMH)with 63 components 357 elementary reactions was constructed based on the hierarchical method. The detailed mechanism was simplified using a single simplification method and a combination of multiple simplification methods, resulting in 35 components 149 elementary reactions and 23 components 19 elementary reactions that were in good agreement with the detailed mechanism. Based on this, the influence of different pressures, temperatures, and the ratios of oxygen and fuel on the ignition characteristics of the detailed mechanism and simplified mechanism was studied. Increasing the initial pressure will integrally increase equilibrium temperature and ignition delay time of the system. And the higher initial pressure leads to the slower the system equilibrium temperature increment: decreasing from 1 035-1 320 K/MPa to 170-320 K/MPa. Meanwhile, the increase in initial temperature will increase the equilibrium temperature of the system but shorten the ignition delay time. When the initial temperature increases by 1 K, the equilibrium temperature of the system will increase by about 3 K. The growth of the oxygen fuel ratio will lower the system equilibrium temperature and raise the ignition delay time. Larger oxygen fuel ratio results in a rapid increase in ignition delay time. The law provides an important reference and theoretical basis for the study of NTO/UDMH reaction kinetics. The detailed and simplified mechanism constructed helps to establish a more accurate simulation model of engine combustion flow field.
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相似文献/References:
[1]尹 婷,聂万胜,何浩波.偏二甲肼液滴燃烧特性及影响因素实验研究[J].火箭推进,2014,40(05):29.
YIN Ting,NIE Wan-sheng,HE Hao-bo.Experimental study on combustion characteristics of UDMH droplet and influence factors on combustion[J].Journal of Rocket Propulsion,2014,40(05):29.
[2]禹天福.偏二甲肼胶体流变学研究[J].火箭推进,2004,(03):36.
[3]尹继辉,胡洪波,李远远,等.MMH/NTO双组元自燃推进剂反应机理简化[J].火箭推进,2021,47(02):40.
YIN Jihui,HU Hongbo,LI Yuanyuan,et al.Investigation of reduced chemical kinetic model of MMH/NTOhypergolic propellants[J].Journal of Rocket Propulsion,2021,47(05):40.
备注/Memo
收稿日期:2023- 11- 21修回日期:2023- 12- 22
基金项目:国家重点项目; 载人航天工程科技创新团队课题
作者简介:杨丹奇(1996—),女,博士,研究领域为液体火箭发动机热过程仿真。
更新日期/Last Update:
1900-01-01