航天推进技术研究院主办
[1]刘晓伟,胡伟,曹晶,等.鲁泊数和孔径比对直流互击式喷注器性能的影响[J].火箭推进,2010,36(03):24-27.
Liu Xiaowei,Hu Wei,Cao Jing,et al.Effects of Rupe number and ratio of injection orifice diameter on unlike impinging injector performance[J].Journal of Rocket Propulsion,2010,36(03):24-27.
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Liu Xiaowei,Hu Wei,Cao Jing,et al.Effects of Rupe number and ratio of injection orifice diameter on unlike impinging injector performance[J].Journal of Rocket Propulsion,2010,36(03):24-27.
鲁泊数和孔径比对直流互击式喷注器性能的影响
《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]
卷:
36
期数:
2010年03期
页码:
24-27
栏目:
出版日期:
2010-06-15
- Title:
- Effects of Rupe number and ratio of injection orifice diameter on unlike impinging injector performance
- 文章编号:
- (2010)03-0024-04
- 分类号:
- V434
- 文献标志码:
- A
- 摘要:
- 设计高性能喷注器、提高发动机比冲性能是发动机设计者一直追求的目标。对于直流互击式喷注器，鲁泊数和孔径比是影响喷注器性能的两个关键参数，而且两者之间有一定关联。为了初步研究鲁泊数和孔径比参数对直流互击式喷注器性能的影响，合理匹配两者的关系，设计了三种状态的喷注器，进行了混合比分布试验和热试车考核。结果表明，兼顾鲁泊数和孔径比才能使氧化剂和燃料达到最佳混合效果，提高燃烧效率。
- Abstract:
- To design a high performance injector and to improve engine impulse performance are the permanent goals of engine designers. The Rupe number and the ratio of injection orifice diameter are two key parameters affecting unlike impinging injector performance, and they are closely interrelated. To study the effect of Rupe number and ratio of injection orifice diameter on unlike impinging injector performance and to match reasonably the relationship between Rupe number and ratio of injection orifice diameter, three kinds of injectors were designed, and relevant mixture ratio distribution tests and hot fire tests were performed. The results show that mixture characteristics of oxidizer and fuel can be improved only by taking into account both Rupe number and ratio of injection orifice diameter，and thus combustion
参考文献/References:
[1]Larry C Liou, John W Dankanich, Leslie L Alexander.NASA In-Space Advanced Chemical Propulsion Development in Recent Years[R]. AIAA 2009-5126. [2]Dickerson R A. Like and unlike Impinging Injection Element Droplet Sizes[J]. J Spacecraft, V.6,N 11,1969. [3]张蒙正, 傅永贵. 两股互击式喷嘴雾化研究及应用[J]. 推进技术, 1999, 20(2): 73-76. [4]庄逢辰. 液体火箭发动机喷雾燃烧的理论、模型及应用[M]. 长沙: 国防科技大学出版社, 1995. [5]杜正刚, 高玉闪, 蔡国飙. 气－气喷嘴结构分析[J]. 火箭推进, 2009, 35(3): 6-11. [6]高玉闪, 杜正刚, 金平, 等. 气氧/甲烷同轴剪切喷注器燃烧特性数值模拟[J]. 火箭推进, 2009, 35(5): 18-24.
备注/Memo
收稿日期：2010-０1-06；修回日期：2010-02-12。
作者简介： 刘晓伟（1978—），男，工程师，研究领域为轨姿控推力室设计。
更新日期/Last Update:
1900-01-01