航天推进技术研究院主办
[1]熊莉芳,林 源,王鹏武,等.汽蚀管两相流数值仿真及内型面参数影响研究[J].火箭推进,2015,41(02):79-86.
XIONG Li-fang,LIN Yuan,WANG Peng-wu,et al.Numerical simulation of two-phase flow and study on effect of interior structure parameter of cavitation nozzle[J].Journal of Rocket Propulsion,2015,41(02):79-86.
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XIONG Li-fang,LIN Yuan,WANG Peng-wu,et al.Numerical simulation of two-phase flow and study on effect of interior structure parameter of cavitation nozzle[J].Journal of Rocket Propulsion,2015,41(02):79-86.
汽蚀管两相流数值仿真及内型面参数影响研究
《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]
卷:
41
期数:
2015年02期
页码:
79-86
栏目:
研究与设计
出版日期:
2015-07-30
- Title:
- Numerical simulation of two-phase flow and study on effect of interior structure parameter of cavitation nozzle
- 分类号:
- V433.9-34
- 文献标志码:
- A
- 摘要:
- 在液体火箭发动机中广泛采用汽蚀管来控制和调节流量。针对某液体火箭发动机汽蚀管实际选配过程中经常出现选配困难的问题，应用CFD两相流数值仿真方法，研究了该汽蚀管水试中气泡生长、溃灭等现象，得到了该汽蚀管的工作特性，而且与水试试验结果进行了对比，数值仿真结果与试验结果偏差较小，为解决实际选配问题提供了理论技术支撑。并且对该汽蚀管喉部设置直线段后的汽蚀特性进行了仿真研究，得出该汽蚀管喉部设置直线段后，相对压力损失能降低2%左右。最后分析了汽蚀管内型面参数对流阻系数和相对压力损失系数的影响，总结了成熟的设计经验。
- Abstract:
- The cavitation nozzle is widely used in controlling and adjusting the liquid flux of the liquid rocket engine. According to the difficulty occurred in practice apolegamy of cavitation nozzle in a liquid rocket engine, the growth process and break phenomenon of the water bubble in the cavitation nozzle was studied, and the operating characteristics of the cavitation nozzle was attained by means of CFD two-phase flow numerical simulation method. The simulation results and the water test results are compared. The difference between them is small, which provides the theoretical and technical support for solving the actual question. The cavitation characteristics of the cavitation nozzle throat after setting beeline segment in it was simulated. The relative pressure loss can be reduced about 2% by the beeline segment in it. The effect of the cavitation nozzle's interior structure parameter on
参考文献/References:
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备注/Memo
收稿日期：2014-07-20；修回日期：2014-12-08 基金项目：中国航天科技集团公司支撑项目（2011JY011） 作者简介：熊莉芳（1982—），女，硕士，研究领域为液体火箭发动机系统设计
更新日期/Last Update:
1900-01-01