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Effects of Rupe number and ratio of injection orifice diameter on unlike impinging injector performance(PDF)

《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]

Issue:
2010年03期
Page:
24-27
Research Field:
Publishing date:

Info

Title:
Effects of Rupe number and ratio of injection orifice diameter on unlike impinging injector performance
Author(s):
Liu Xiaowei; Hu Wei; Cao Jing; Xia Kaihong; Chang Xiaoqing
Xi'an Aerospace Propulsion Institute, Xi'an 710100, China
Keywords:
-
PACS:
V434
DOI:
-
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

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.

Memo

Memo:
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Last Update: 1900-01-01