超声速燃烧室小支板对射流作用的数值分析

王应洋; 李旭昌; 王宏宇; 张涵

doi:10.13224/j.cnki.jasp.2016.01.027

超声速燃烧室小支板对射流作用的数值分析

doi: 10.13224/j.cnki.jasp.2016.01.027

空军工程大学防空反导学院, 西安 710051

基金项目:

航空科学基金项目(20130196004)

详细信息

作者简介:
王应洋(1990-),男,四川隆昌人,硕士生,研究方向为超声速燃烧.

中图分类号: V235.11
计量
- 文章访问数: 820
- HTML浏览量: 1
- PDF量: 400
- 被引次数: 0
出版历程
- 收稿日期: 2014-05-19
- 刊出日期: 2016-01-28

Numerical analysis on effect on injection for supersonic combustor pylon

Air and Missile Defense College, Air Force Engineering University, Xi'an 710051, China

摘要

摘要: 为分析小支板前/后喷射在超声速燃烧室中的流动特性,运用数值模拟方法研究了小支板对乙烯喷射冷流场的作用规律.对比分析了有无小支板、不同喷射位置、不同喷射角对流场的影响.研究发现小支板增强掺混的机制主要在于在小支板后端形成了流向涡与低压区;在一定范围内,喷孔距离支板尾部越远越处于湍流强度较大的流向涡中,更有利于掺混增强,但同时也距离小支板后缘的低压区更远,这将导致总压损失变大;综合考虑,小支板与喷孔的距离为2.2d,喷射角为90°时燃料穿透深度、混合效率较好,总压损失也相对较小.
- 超声速燃烧 /
- 小支板 /
- 掺混增强 /
- 乙烯 /
- 横向射流
Abstract: To analyze of flow characteristics of the pylon before/after injection in supersonic combustion,the numerical simulation was carried out to investigate the effect rules of pylon on ethylene injection cold flow field.The influence of several conditions on flow field was contrastive analyzed,such as: with and without pylon, different injection locations and different injection angles. It is found that the streamwise vortex zone and low pressure depression behind the pylon are the paramount mechanism for mixing enhancement. Further distance between the pylon and injector is good for mixing enhancement for stronger wise vortex zone, but leads to higher total pressure loss for less low pressure depression. Moreover, injection with the distance between pylon and injector of 2.2d, injection angle of 90 degree is recommended regarding high mixing efficiency and less total pressure loss.
- supersonic combustion /
- pylon /
- mixing enhancement /
- ethylene /
- transverse injection

HTML

参考文献(18)

[1]	Segal C,Michael J R.The scramjet engine processes and characteristics[M].Cambridge,England:Cambridge University Press,2009.
[2]	陈方,陈立红,张新宇.超声速燃烧室凹腔火焰稳定器的数值模拟[J].推进技术,2007,28(2):135-140. CHEN Fang,CHEN Lihong,ZHANG Xinyu.Numerical studies on cavity holders for supersonic combustors[J].Journal of Propulsion Technology,2007,28(2):135-140.(in Chinese)
[3]	徐旭,陈兵,徐大军.冲压发动机原理及技术[M].北京:北京航空航天大学出版社,2014.
[4]	蔡国彪,徐大军.高超声速飞行器技术[M].北京:科学出版社,2012.
[5]	苏义.支板超声速混合增强技术及其阻力特性研究[D].长沙:国防科学技术大学,2006. SU Yi.Investigations of supersonic mixing enhancement technology and drag ofstrut[D].Changsha:National University of Defense Technology,2006.(in Chinese)
[6]	高峰,王宏宇,张涵.超燃冲压发动机燃烧室数值流场分析研究综述[J].飞航导弹,2014(1):80-84.
[7]	Daniel L R,King P.Mixing effects of pylon-aided fuel injection located upstream of flame holding cavity in supersonic flow[R].AIAA-2005-3913,2005.
[8]	Pohlman M R,Greendyke R B.Critical design parameters for pylon-aided gaseous fuel injection[R].AIAA-2009-1422,2009.
[9]	金劲睿,刘玉英,洪燕.前置肋片对凹槽火焰稳定器混合特性的影响[J].航空动力学报,2011,26(12):2716-2721. JIN Jinrui,LIU Yuying,HONG Yan.Effects of injection fin on flow and mixing characteristics of cavity flame holder[J].Journal of Aerospace Power,2011,26(12):2716-2721.(in Chinese)
[10]	Gruber M R,Carter C D,Monters D R.Experimental studies of pylon-aided fuel injection into a supersonic cross flow[J].Journal of Propulsion and Power,2008,24(3):460-470.
[11]	Aguilera C,Pang B,Ghosh A.Scramjet mixing control using fin-guided fuel injection[R].AIAA-2009-5415,2009.
[12]	Aguilera C,Pang B,Ghosh A.Supersonic mixing enhancement and optimization using fin-guided fuel injection[R].AIAA-2010-1526,2010.
[13]	Takahashi H,Tu Q,Segal C.Effects of pylon-aided fuel injection on mixing in a supersonic flow field[J].Journal of Propulsion and Power,2010,26(5):1092-1099.
[14]	Balar R A,Gupta A K,Yu K H.Pylon-aided fuel injection into supersonic flow[R].AIAA-2007-834,2007.
[15]	Bagg C M G,Greendyke R.Computational analysis of strut induced mixing in a scramjet[R].AIAA-2009-1253.
[16]	郭金鑫,刘金林,朱卫兵.乙烯超燃燃烧室支板/凹腔结构组合的数值研究[J].固体火箭技术,2012,33(2):602-607. GUO Jinxin,LIU Jinlin,ZHU Weibing.Numerical study on supersonic combustor using ethane with strut and cavity combination[J].Journal of Rocket Technology,2012,33(2):602-607.(in Chinese)
[17]	张弯洲,乐嘉陵,田野.超燃发动机混合效率评估方法探讨[J].航空动力学报,2012,27(9):1958-1965. ZHANG Wanzhou,LE Jialing,TIAN Ye.Evaluations of the fuel mixing efficiency for scramjet[J].Journal of Aerospace Power,2012,27(9):1958-1965.(in Chinese)
[18]	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. YANG Yinjun,DOU Zhiguo,DUAN Liwei.Influence of lateral injection angle in supersonic inflow on flow and mixed characteristics[J].Modern Electronics Technique,2013,36(17):151-154.(in Chinese)