火箭推进

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。

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.

引言
1 NTO/UDMH详细燃烧机理构建及验证
2 NTO/UDMH详细燃烧机理分析
3 NTO/UDMH详细燃烧机理简化
4 结论

图1 NTO/UDMH详细燃烧机理构建主要起始反应<br/>Fig.1 Detailed combustion mechanism construction of NTO/UDMH and main initial reactions

图1 NTO/UDMH详细燃烧机理构建主要起始反应
Fig.1 Detailed combustion mechanism construction of NTO/UDMH and main initial reactions

表1 NTO/UDMH起始过程10组分42步基元反应<br/>Tab.1 NTO/UDMH initiation process, 10 components, 42 step elementary reactions

表1 NTO/UDMH起始过程10组分42步基元反应
Tab.1 NTO/UDMH initiation process, 10 components, 42 step elementary reactions

图2 构建NTO/MMH机理与文献[10]对比结果<br/>Fig.2 Mechanism of constructing NTO/MMH and comparison results with reference[10]

图2 构建NTO/MMH机理与文献[10]对比结果
Fig.2 Mechanism of constructing NTO/MMH and comparison results with reference[10]

图3 构建的NTO/UDMH详细机理与文献[10]对比结果<br/>Fig.3 Comparison of detailed mechanism of constructed NTO/UDMH with reference[10]

图3 构建的NTO/UDMH详细机理与文献[10]对比结果
Fig.3 Comparison of detailed mechanism of constructed NTO/UDMH with reference[10]

表2 温度敏感性前50基元反应<br/>Tab.2 Temperature sensitivity of top 50 primitive reactions

表2 温度敏感性前50基元反应
Tab.2 Temperature sensitivity of top 50 primitive reactions

图4 温度敏感性前20反应数值<br/>Fig.4 Temperature sensitivity of top 20 reaction values

图4 温度敏感性前20反应数值
Fig.4 Temperature sensitivity of top 20 reaction values

图5 初始压力对详细机理着火特性影响<br/>Fig.5 Effect of initial pressure on detailed mechanism ignition characteristics

图5 初始压力对详细机理着火特性影响
Fig.5 Effect of initial pressure on detailed mechanism ignition characteristics

图6 初始温度对详细机理着火特性影响<br/>Fig.6 Effect of initial temperature on detailed mechanism ignition characteristics

图6 初始温度对详细机理着火特性影响
Fig.6 Effect of initial temperature on detailed mechanism ignition characteristics

图7 氧燃比对详细机理着火特性的影响<br/>Fig.7 Impact of the ratio of oxygen and fuel on detailed mechanism ignition characteristics

图7 氧燃比对详细机理着火特性的影响
Fig.7 Impact of the ratio of oxygen and fuel on detailed mechanism ignition characteristics

图8 详细机理及3种简化机理着火温升曲线<br/>Fig.8 Detailed mechanism and three simplified ignition temperature rise curves

图8 详细机理及3种简化机理着火温升曲线
Fig.8 Detailed mechanism and three simplified ignition temperature rise curves

图9 不同压力、温度和氧燃比对简化机理A着火特性影响<br/>Fig.9 Effect of pressures, temperatures, and oxygen fuel ratios on the ignition characteristics of simplified mechanism A

图9 不同压力、温度和氧燃比对简化机理A着火特性影响
Fig.9 Effect of pressures, temperatures, and oxygen fuel ratios on the ignition characteristics of simplified mechanism A

图10 敏感性分析法简化机理与详细机理着火温升曲线<br/>Fig.10 Sensitivity analysis method simplified mechanism and detailed mechanism ignition temperature rise curve

图10 敏感性分析法简化机理与详细机理着火温升曲线
Fig.10 Sensitivity analysis method simplified mechanism and detailed mechanism ignition temperature rise curve

图11 生成速率分析法简化机理与详细机理着火温升曲线<br/>Fig.11 Simplified and detailed mechanism of the generation rate analysis method ignition temperature rise curve

图11 生成速率分析法简化机理与详细机理着火温升曲线
Fig.11 Simplified and detailed mechanism of the generation rate analysis method ignition temperature rise curve

图12 详细机理与简化机理A、B温升曲线<br/>Fig.12 Detailed and simplified mechanisms A and B temperature rise curves

图12 详细机理与简化机理A、B温升曲线
Fig.12 Detailed and simplified mechanisms A and B temperature rise curves

表3 不同机理着火延迟时间及平衡温度对比<br/>Tab.3 Comparison of ignition delay time and equilibrium temperature for different mechanisms

表3 不同机理着火延迟时间及平衡温度对比
Tab.3 Comparison of ignition delay time and equilibrium temperature for different mechanisms

图13 不同压力、温度和氧燃比对简化机理B着火特性影响<br/>Fig.13 Effect of different pressures, temperatures, and oxygen fuel ratios on the ignition characteristics of simplified mechanism B

图13 不同压力、温度和氧燃比对简化机理B着火特性影响
Fig.13 Effect of different pressures, temperatures, and oxygen fuel ratios on the ignition characteristics of simplified mechanism B

[1] 何博, 丰松江, 聂万胜. 液体火箭自燃推进剂化学着火延迟数值模拟[J]. 系统仿真学报, 2013, 25(4): 612-615.
[2]杨 V, 安德松W E. 液体火箭发动机燃烧不稳定性[M]. 张宝炯, 洪鑫, 陈杰, 译. 北京: 科学出版社, 2001.
[3]杨建文, 胡海峰, 李钰航, 等. 液体火箭发动机热过程仿真技术发展概述[J]. 中国航天, 2023(5): 46-52.
[4]TUAZON E C, CARTER W P L, BROWN R V, et al. Gas-phase reaction of 1, 1-dimethylhydrazine with nitrogen dioxide[J]. The Journal of Physical Chemistry, 1983, 87(9): 1600-1605.
[5]徐亚飞. 偏二甲肼与羟基自由基降解反应机理的理论研究[D]. 重庆: 重庆大学, 2008.
[6]黄丹, 刘祥萱, 王煊军, 等. 偏二甲肼大气氧化生成亚硝基二甲胺(NDMA)的机理[J]. 含能材料, 2019, 27(1): 35-40.
[7]何博, 聂万胜, 庄逢辰. 偏二甲肼有机凝胶液滴蒸发燃烧模型展望[J]. 化学学报, 2013, 71(3): 302-307.
[8]HE B, NIE W S, HE H B. Unsteady combustion model of nonmetalized organic gel fuel droplet[J]. Energy & Fuels, 2012, 26(11): 6627-6639.
[9]HE B, NIE W S, FENG S J, et al. Effects of NTO oxidizer temperature and pressure on hypergolic ignition delay and life time of UDMH organic gel droplet[J]. Propellants, Explosives, Pyrotechnics, 2013, 38(5): 665-684.
[10]娄德全. 非设计工况下自燃推进剂推力室燃烧流动模拟[D]. 北京: 北京航空航天大学, 2010.
[11]CATOIRE L, CHAUMEIX N, PAILLARD C. Chemical kinetic model for monomethylhydrazine/nitrogen tetroxide gas phase combustion and hypergolic ignition[J]. Journal of Propulsion and Power, 2004, 20(1): 87-92.
[12]CATOIRE L, BASSIN X, DUPRE G, et al. Experimental study and kinetic modeling of the thermal decomposition of gaseous monomethylhydrazine: Application to detonation sensitivity[J]. Shock Waves, 1996, 6(3): 139-146.
[13]CATOIRE L, LUDWIG T, BASSIN X, et al. Kinetic modeling of the ignition delays in monomethylhydrazine/oxygen/argon mixtures[J]. Symposium(International)on Combustion, 1998, 27(2): 2359-2365.
[14]CATOIRE L, SWIHART M T. Thermochemistry of species produced from monomethylhydrazine in propulsion and space-related applications[J]. Journal of Propulsion and Power, 2002, 18(6): 1242-1253.
[15]SUN H Y, CATOIRE L, LAW C K. Thermal decomposition of monomethylhydrazine: Shock tube experiments and kinetic modeling[J]. International Journal of Chemical Kinetics, 2009, 41(3): 176-186.
[16]KNAB O, PRECLIK D, ESTUBLIER D. Flow field prediction within liquid film cooled combustion chambers of storable bi-propellant rocket engines[C]//34th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit. Reston, Virginia: AIAA, 1998.
[17]ZHANG L B, XU X. Performance prediction of apogee attitude and orbit control thruster for MMH/NTO hypergolic bipropellant[C]//50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference. Reston, Virginia: AIAA, 2014.
[18]巴延涛, 侯凌云, 毛晓芳, 等. 甲基肼/四氧化二氮反应化学动力学模型构建及分析[J]. 物理化学学报, 2014, 30(6): 1042-1048.
[19]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(2): 40-46.
[20]王镜淇,王成刚,陈雪娇,等.RBCC组合动力用液体推进剂研究进展[J].火箭推进,2022,48(6):101-112.
[21]HOU L Y, FU P F, BA Y T. Chemical mechanism of MMH/NTO and simulation in a small liquid rocket engine[J]. Combustion Science and Technology, 2019, 191(12): 2208-2225.
[22]LEE K H. Numerical simulation on thermal and mass diffusion of MMH-NTO bipropellant thruster plume flow using global kinetic reaction model[J]. Aerospace Science and Technology, 2019, 93: 104882.
[23]LABBE N J. Determining detailed reaction kinetics for nitrogen and oxygen containing fuels[D]. Massachusetts: University of Massachusetts Amherst, 2013.
[24]陈晨. UDMH和NTO双组元液体推进剂反应机理及燃烧特性研究[D]. 北京: 北京航空航天大学, 2016.
[25]郭俊江, 唐石云, 李瑞, 等. 高碳烃宽温度范围燃烧机理构建及动力学模拟[J]. 物理化学学报, 2019, 35(2): 182-192.
[26]肖虹,房喜荣,李悦,等.常规推进剂发动机高压富氧燃气燃烧处理方法与试验[J].火箭推进,2023,49(1):84-92.
[27]王丹,刘臻丽,周康,等.常温推进剂发生器低压点火动态特性分析[J].火箭推进,2023,49(2):35-41.

备注

引言

1 NTO/UDMH详细燃烧机理构建及验证

2 NTO/UDMH详细燃烧机理分析

3 NTO/UDMH详细燃烧机理简化

4 结论

期刊信息