弹药技术

双凹腔开口先进旋涡燃烧室燃烧特性研究

  • 王志凯 ,
  • 曾卓雄 ,
  • 徐义华
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  • 南昌航空大学飞行器工程学院,南昌 330063

王志凯(1989-),男,山西朔州人,硕士研究生,研究方向:航空宇航推进理论与工程。

收稿日期: 2013-11-04

  网络出版日期: 2025-05-30

基金资助

国家自然科学基金(51066006;51266013);航空科学基金(2013ZB56002; 2013ZB56004)资助

Research on Combustion Characteristics of Double-cavity Slotted Advanced Vortex Combustor

  • WANG Zhikai ,
  • ZENG Zhuoxiong ,
  • XU Yihua
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  • School of Aircraft Engineering, Nanchang Hangkong University, Nanchang 330063, China

Received date: 2013-11-04

  Online published: 2025-05-30

摘要

为了确定先进旋涡燃烧室后钝体开口结构参数(开口角度100°、开口尺寸2mm)下燃烧室最佳匹配长度,通过研究燃烧室长度对燃烧效率、出口温度分布及出口径向温度分布的影响,得出燃烧室最佳匹配长度为800mm。在此结构基础上,增加第三钝体形成双凹腔AVC(advancedvortexcombustor),对其燃烧流场进行数值模拟,结果表明当第二凹腔长度L₂及第三钝体开口尺寸L3满足L₂/L₁=1.2,L3/H=0.6时双凹腔开口AVC具有流场流动性好、燃烧稳定性好、温度分布高等优点。

本文引用格式

王志凯 , 曾卓雄 , 徐义华 . 双凹腔开口先进旋涡燃烧室燃烧特性研究[J]. 弹箭与制导学报, 2014 , 34(5) : 117 -122 . DOI: 10.15892/j.cnki.djzdxb.2014.05.030

Abstract

In order to determine the best match length of slotted AVC (opening angle is 100°, slot size is 2mm), the effect of combustor length on combustion efficiency, the outlet temperature distribution and radial temperature distribution were numerically calculated. The results show the best match length of combustor is 800 mm, on the basis of this structure, the third blunt body was added for forming the double-cavity AVC, studies suggest that when the length of the second cavity is L2/L₁ = 1.2, slot size of the third blunt body is L3/H = 0. 6, AVC has advantages of good flow field, stable combustion, high temperature distribution.

参考文献

[1]
Ben-Yaker A, Hanson R K.Cavity flameholders for ignition and flame stabilization in scramjets:review and experimental study, AIAA-98-35018[R].1998.
[2]
杨事民, 唐豪, 黄玥.超燃冲压发动机凹腔稳焰的数值模拟[J].飞机设计, 2007, 27(6):47-51.
[3]
Hsu K Y, Goss L P, Trump D D, et al.Performance of a trapped-vortex combustor, AIAA-95-0810[R].1995.
[4]
Roquemore W M, Shousese D, Burrus D, et al.Trapped vortex combustor concept for gas turbine engines, AIAA2001-0483[R].2001.
[5]
邓洋波, 刘世青, 钟兢军.先进旋涡燃烧室燃烧特性数值模拟[J].大连海事大学学报, 2008, 34(3):21-24.
[6]
邓洋波, 孙海涛, 王玉龙, 等.氢燃料先进旋涡燃烧室流动和燃烧特性[J].航空动力学报, 2013, 21(1):120-128.
[7]
Katta V R, Roquemore W M.Numerical studies on trapped vortex concepts for stable combustion[J].Gas Turbines Power, 1998, 120(1):60-68.
[8]
Dobbeling K, Eroglu A, Winkler D, et al.Low NOx premixed combustion of MBtu fuels in a research burner[J].ASME Engineering for Gas Turbines and Power, 1997, 119(3):553-558.
[9]
孙海俊, 曾卓雄, 徐义华.先进旋涡燃烧室钝体结构参数选择的数值分析[J].弹箭与制导学报, 2012, 32(6):99-102.
[10]
孙海俊, 曾卓雄, 徐义华, 等.AVC预混燃烧流动特性的数值模拟[J].科学技术与工程, 2013, 13(17):4843-4848.
[11]
王志凯.先进旋涡燃烧室流场的数值研究[D].南昌:南昌航空大学, 2013.
[12]
王玉龙.三对钝体布置先进旋涡燃烧室流动特性研究[D].大连:大连海事大学, 2013.
[13]
林宇震, 许全宏, 刘高恩.燃气轮机燃烧室[M].北京:国防工业出版社, 2008:11-12.
[14]
刘世青, 钟兢军, 程平.喷射孔径影响驻涡燃烧室性能冷态数值研究[J].汽轮机技术, 2010, 52(2):107-111.
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