Study on Characters of Kerosene/O2 HVO Jet

  • WANG Dewen ,
  • YU Chunming ,
  • MENG Dongrong ,
  • QU Juxin
Expand
  • Xijing University, Xi'an 710123, China

Received date: 2017-12-21

  Online published: 2025-05-29

Abstract

The aviation kerosene and O2 were ignited in the chamber in order to obtain the distribution characteristics of the high velocity jet, which was accelerated and sprayed from the exit. The distribution characteristics of the temperature and velocity on the axis at the exit were obtained by calculation The distribution of the field was obtained by FLUENT numerical simulations. Measuring the temperature and velocity at different distances with particle tester and metal-melt method, the jet characteristics will change with the change of kerosene O2 ratio The results show that the temperature is about 2 800 K and the velocity is about 2 150 m/s at the exit. The temperature and velocity reduce with the distance increase What's more, with the increase of oxygen-enriched degree, the temperature and velocity in the jet field reduce obviously.

Cite this article

WANG Dewen , YU Chunming , MENG Dongrong , QU Juxin . Study on Characters of Kerosene/O2 HVO Jet[J]. Journal of Projectiles, Rockets, Missiles and Guidance, 2018 , 38(5) : 91 -94,101 . DOI: 10.15892/j.cnki.djzdxb.2018.05.022

References

[1]
李斌, 谭永华. 液氧/煤油富氧补燃发动机[J]. 火箭推进, 2003, 29(2): 1-6.
[2]
READ R W, ROGERSON J W, HOCGREB S. Relight imaging at low temperature,low pressure conditions: AIAA 2008-0957[R]. [S. l.]:AIAA,2008.
[3]
Vasu S S, Davidon D F. Jet fuel ignition delay times: shock tube experiments over wide conditions and surrogate model predictions[J]. Combustion and Flame, 2008, 152(1/2): 125-143.
[4]
雷向东, 余协正, 杨京军, 等. 氧气/煤油点火装置高空点火试验研究[J]. 火箭推进, 2014, 40(6): 37-43.
[5]
梁金虎, 王苏, 张灿, 等. RP-3 航空煤油点火特性研究[J]. 力学学报, 2014, 46(3): 352-360.
[6]
吴宝元, 张民庆. 液氧/煤油富氧预燃室的理论分析和试验研究[J]. 推进技术, 1999, 20(5): 11-16.
[7]
雷震, 代玉东. 液氧/煤油发动机试车热敏电阻测温技术[J]. 火箭推进, 2003, 29(4): 35-39.
[8]
王爱玲, 吴建军. 气氧/煤油发动机电点火技术研究[J]. 上海航天, 2006(6): 14-17.
[9]
赵正社. 液氧/煤油发动机试验低温测量系统的设计与实现[J]. 火箭推进, 2001, 27(2): 36-41.
[10]
张福祥. 火箭燃气射流动力学[M]. 哈尔滨: 哈尔滨工程大学出版社, 2004.
[11]
曹再勇, 蔡体敏, 谭永华. 富氧燃气发生器三维燃烧流场的数值模拟[J]. 西北工业大学学报, 2005, 23(5): 557-561.
[12]
翟鹏, 杨月诚. 基于FLUENT 的烧蚀喷枪两相流流场数值模拟[J]. 弹箭与制导学报, 2012, 32(3):133-136.
[13]
程钰锋, 聂万胜, 丰松江. 氢氧火箭发动机不稳定燃烧数值研究[J]. 装备指挥技术学院学报, 2009, 20(4): 69-73.
[14]
饶琼, 周香林, 张济山, 等. 超音速喷涂技术及其应用[J]. 热加工工艺, 2004(10):49-52.
[15]
于永志. 固体火箭发动机尾焰温度场特性研究[D]. 沈阳: 沈阳理工大学, 2016.
Outlines

/

tom_en.htm"-->