火箭技术

乙烯超燃燃烧室菱形孔射流的数值优化

  • 张涵 ,
  • 吴达 ,
  • 王应洋 ,
  • 王旭东
展开
  • 空军工程大学防空反导学院,西安 710051

张涵(1992-),男,山东菏泽人,硕士研究生,研究方向:航空宇航。

收稿日期: 2015-07-07

  网络出版日期: 2025-05-30

基金资助

航空科学基金(20130196004)

Numerical Optimization on Supersonic Combustion using Ethylene with Diamond-shaped Orifices

  • ZHANG Han ,
  • WU Da ,
  • WANG Yingyang ,
  • WANG Xudong
Expand
  • Air and Missile Defense College, Air Force Engineering University, Xi'an 710051, China

Received date: 2015-07-07

  Online published: 2025-05-30

摘要

为分析相同面积条件下菱形孔的不同长宽比、不同偏转角度对超燃燃烧室中的流动特性影响,对低动压喷射的超声速流场进行了数值模拟。研究结果表明:在计算的6种长宽比构型中,长宽比为5构型燃料穿透能力和掺混特性最强,但此时对称面上总压损失变大;在计算的3种偏转角构型中,偏转角度为30°构型的燃料掺混特性和燃料的穿透能力最强,但此构型在远流场处抬升能力变弱,羽流质量中心高度出现下降。

本文引用格式

张涵 , 吴达 , 王应洋 , 王旭东 . 乙烯超燃燃烧室菱形孔射流的数值优化[J]. 弹箭与制导学报, 2016 , 36(3) : 60 -64 . DOI: 10.15892/j.cnki.djzdxb.2016.03.017

Abstract

Based on investigation of influence of diamond-shaped orifices with different length-width ratio and various deflection angle on cold flow characteristics of supersonic combustion, numerical simulation was done for evaluating several patterns for mixing enhancement.It is found that the diamond-shaped orifice whose length-width ratio is 5 behaves the best in mixing efficiency and fuel penetration among these different models, but this kind of diamond-shaped orifice heightens total pressure loss.With increase of deflection angle of injector, penetration height of the fuel and mixing efficiency firstly increase and then decrease.The model with 30 degree deflection angle of injector has the best characteristics, but the distance between the flow field and the injector is longer, the effect on increasing penetration height of the fuel is weaker.

参考文献

[1]
CURRAN E T, MURTHY S N B. Scramjet propulsion[M].Progress in Astromautics and Aeronautics, 2002: 42-43.
[2]
占云. 超燃冲压发动机的第一个40 年[J]. 飞航导弹, 2002 (9): 32-40.
[3]
CORIN Segal. The scramjet engine processes and charac-teristics[M]. Cambridge, Eng Lang, U.K.: Cambridge University, 2009: 85-86.
[4]
刘伟凯, 陈林泉, 杨向明. 固体燃料超燃冲压发动机燃烧室掺混燃烧数值研究[J]. 固体火箭技术, 2012, 35(4): 457-462.
[5]
杨银军, 窦志国, 段立伟. 超声速来流中横向喷流角度对流动与混合特性的影响[J]. 现代电子技术, 2013, 36(17): 151-154.
[6]
OGAWA H, SUNAMI T, KUBOTA H, BOYCE R R. Numerical investigation of mixing characteristics of various wall injection into a hypersonic crossflow in scramjet engines:AIAA 2013-0115[R]. 2013.
[7]
BARBER M J, SCHETZ J A, ROE L A. Normal, sonic helium injection through a wedge-shaped orifice into super-sonic flow[J]. Journal of Propulsion and Power, 1997, 13(2): 257-263.
[8]
张丁午, 王强, 胡海洋. 菱形孔射流在超声速流场中的气动特性[J]. 航空动力学报, 2012, 27(10): 2378-2383.
[9]
MITCHELLI R, ROBERT B. Critical design parameters for pylon-aided gaseous fuel injection:AIAA 2009-1422[R]. 2009.
[10]
MONTES D R, KING P I, Gruber M R, et al. Mixing effects of pylon-aided fuel injection located upstream of flame holding cavity in supersonic flow:AIAA 2005-3913[R]. 2005.
[11]
闫明磊, 韦宝禧, 徐旭,等. 应用气动斜坡和燃气发生器的超然燃烧室[J]. 北京航空航天大学学报, 2011, 37(7): 782-788.
[12]
SONG Ganglin, ZHANG Yan, WEI Baoxi. Performance comparison of aero-ramp and transrerse injector based on gaspilot flame[J]. Journal of Aerospace Power, 2014, 29(2): 406-419.
[13]
张岩, 李崇香, 韦宝喜. 超燃冲压发动机燃料喷注方案综述[J]. 飞航导弹, 2014 (2): 61-67.
文章导航

/

tom_cn.htm"-->