航天推进技术研究院主办
[1]孙得川,杨建文.液体火箭发动机喷管仿真模型[J].火箭推进,2022,48(02):56-65.
SUN Dechuan,YANG Jianwen.Nozzle simulation model of liquid rocket engine[J].Journal of Rocket Propulsion,2022,48(02):56-65.
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SUN Dechuan,YANG Jianwen.Nozzle simulation model of liquid rocket engine[J].Journal of Rocket Propulsion,2022,48(02):56-65.
液体火箭发动机喷管仿真模型
《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]
卷:
48
期数:
2022年02期
页码:
56-65
栏目:
目次
出版日期:
2022-04-30
- Title:
- Nozzle simulation model of liquid rocket engine
- 文章编号:
- 1672-9374(2022)02-0056-10
- 分类号:
- V430
- 文献标志码:
- A
- 摘要:
- 基于量热完全气体、组分冻结的热完全气体、化学非平衡气体模型建立了喷管性能仿真物理模型,采用三阶精度的WENO格式进行了不同气体模型的喷管流场计算。根据流场计算分析了四氧化二氮/甲基肼发动机和液氧/煤油发动机喷管的性能,并针对液氧/煤油发动机分析了室压和不同喷管扩张段型面对性能的影响。结果表明,采用量热完全气体模型所计算的比冲高于用热完全气体模型的计算值,这两种气体模型给出的计算偏差较大,且没有规律性 二维化学动力学计算结果更接近实测值 提高室压不仅能提高燃烧效率,也能减小化学动力学损失,使喷管性能提高 对Rao方法设计的喷管型面进行附面层修正可略提高性能,或在同样性能要求下略减小喷管长度。
- Abstract:
- Based on the models of calorically perfect gas, thermally perfect gas with frozen species,and chemical non-equilibrium gas, a physical model of nozzle performance simulation was established.A WENO scheme with third-order precision was used to calculate the nozzle flow field for these different gas models.According to the calculation of the flowfield, the nozzle performances of the nitrous oxide/methylhydrazine engine and the liquid oxygen/kerosene engine were analyzed. The effects of the chamber pressure and the nozzle expansion contour on the performance of liquid oxygen/kerosene engine were analyzed by the flowfield calculation.The results show that the specific impulse calculated by the caloric perfect gas model is higher than that calculated by the thermal perfect gas model.The calculation deviation given by the two gas models is large and has no regularity,and the calculated results of the two-dimensional chemical kinetics are closer to the real values.Increasing the chamber pressure can not only improve the combustion efficiency, but also reduce the chemical kinetic loss and thus improve the nozzle performance.Modifying the boundary layer of the nozzle contour designed by Raos method can slightly improve the performance, or slightly reduce the nozzle length under the same performance requirements.
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备注/Memo
收稿日期:2021-10-06 修回日期:2021-12-29
基金项目:国家重点实验室基金(6142704180202)
作者简介:孙得川(1973—),男,博士,教授,研究领域为火箭发动机仿真。
更新日期/Last Update:
1900-01-01