航天推进技术研究院主办
[1]吴凌峰,杨成虎,姚 锋,等.单股自由圆射流撞壁雾化实验[J].火箭推进,2020,46(01):44-51.
WU Lingfeng,YANG Chenghu,YAO Feng,et al.Atomization experiment of single free circular jet impinging against wall[J].Journal of Rocket Propulsion,2020,46(01):44-51.
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WU Lingfeng,YANG Chenghu,YAO Feng,et al.Atomization experiment of single free circular jet impinging against wall[J].Journal of Rocket Propulsion,2020,46(01):44-51.
单股自由圆射流撞壁雾化实验
《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]
卷:
46
期数:
2020年01期
页码:
44-51
栏目:
研究与设计
出版日期:
2020-02-29
- Title:
- Atomization experiment of single free circular jet impinging against wall
- Keywords:
- atomization law; spluttering against wall; circular jet; mechanism analysis; atomization characteristics
- 分类号:
- V433.9文献标识码:A 文章编号:1672-9374(2020)01-0044-08
- 摘要:
- 利用直流撞击式喷注器组织燃烧的发动机推力室喉部材料耐温极限制约了发动机燃烧效率提升,一种新型高性能直流冷壁式喷注器可以解决这一问题,为了指导这种新型喷注器的设计,从射流撞击雾化实验出发,探索了圆射流撞壁雾化规律。采用高速摄影捕获溅射雾化场整体形态,利用收集法测量溅射雾化率,选用PDA和PIV分别测量溅射液滴粒径及速度矢量。研究结果表明:射流撞壁后存在溅射,溅射液滴局部呈现螺旋状,液滴粒径为几十微米量级,溅射雾化率随撞击距离的变化规律可分为4个典型阶段:初始段、发展段、稳定段、衰减段,湍流动能为溅射雾化率的决定因素。
- Abstract:
- The temperature resistance limit of the throat material of the engine thrust chamber, which applies the simple orifice injector to organize the combustion, restricts the improvement of engine combustion efficiency. A new high-performance cold wall injector can be used to solve this problem. In order to guide the design of this new type of injectora, a jet impact atomization experiment was carried out to investigate the atomization law of the circular jet against wall. High-speed photography was used to capture the phenomenon of spluttering atomization field, and the sputtering atomization rate was measured with the collection method. In addition, PDA and PIV were used to measure the particle sized and velocity vector of the sputtering droplets. The results show that there is sputtering after the jet impinges against the wall, and of the spluttering drops are spiral in part, and the droplet size is at the range of several tens of microns. The variation of the sputtering atomization rate with the impact distance can be divided into four typical stages: the initial stage, the development stage, the stable stage and the attenuation stage. The turbulent kinetic energy is the determinant of sputtering atomization rate.
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备注/Memo
收稿日期:2019-04-27; 修回日期:2019-06-01基金项目:国家装备预先研究项目(30508040301)作者简介:吴凌峰(1993—),男,硕士,研究领域为液体火箭发动机雾化
更新日期/Last Update:
2020-02-25