航天推进技术研究院主办
[1]吴高杨,苏凌宇,聂万胜,等.螺旋离心式喷嘴雾化特性试验与仿真研究[J].火箭推进,2015,41(06):21-26.
WU Gaoyang,SU Lingyu,NIE Wansheng,et al.Experiment and simulation on atomization characteristics of screw centrifugal nozzle[J].Journal of Rocket Propulsion,2015,41(06):21-26.
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WU Gaoyang,SU Lingyu,NIE Wansheng,et al.Experiment and simulation on atomization characteristics of screw centrifugal nozzle[J].Journal of Rocket Propulsion,2015,41(06):21-26.
螺旋离心式喷嘴雾化特性试验与仿真研究
《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]
卷:
41
期数:
2015年06期
页码:
21-26
栏目:
研究与设计
出版日期:
2015-12-31
- Title:
- Experiment and simulation on atomization characteristics of screw centrifugal nozzle
- 分类号:
- V434-34
- 文献标志码:
- A
- 摘要:
- 为了研究螺旋离心式喷嘴液膜形态及锥角变化规律，运用高速摄影仪与VOF方法对该型喷嘴进行了不同喷注压降及不同背压下的雾化特性试验与数值仿真研究。试验与数值仿真结果分析表明：提高喷注压降能明显加剧液膜一次破碎，缩短破碎长度，而提高背压对二次破碎的影响更明显，更有助于改善雾化效果；随着喷注压降与背压的提高，液膜锥角均逐渐增大，但改变背压对液膜锥角的影响明显小于改变喷注压降；液膜锥角沿轴向增大且变化率逐渐减小，最后锥角基本保持定值。数值仿真所得到的液膜形态及锥角与试验结果吻合较好。
- Abstract:
- The spray morphology and angle variation law of screw centrifugal nozzle were researched via high-speed camera and volume of fluid (VOF) model at different injection pressure and back pressure. The results show that the primary breakup of drop can be exacerbated significantly and the broken length of drop can be shortened at higher injection pressure drop, and the greater impact on secondary breakup of drop will appear at the higher back pressure and it is helpful to improve atomization quality; with higher back pressure and injection pressure drop, the spray angle increases gradually to a constant value, but the increase of back pressure will have much smaller contribution to the angle gradient than the increase of injection pressure drop, it means that the influence of the former on spray angle is more significantly. The numerical simulation results of spray morphology and angle agree well with those of the experiment.
参考文献/References:
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[4]杨立军, 葛明和, 张向阳, 等. 喷口长度对离心喷嘴雾化特性的影响[J]. 推进技术, 2005, 26(3): 209-214.
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备注/Memo
收稿日期：2015-03-20；修回日期：2015-06-03 基金项目：国家自然科学基金（91441123, 51206185） 作者简介：吴高杨（1991—），男，硕士，研究领域为液体火箭发动机
更新日期/Last Update:
1900-01-01