航天推进技术研究院主办
[1]丁兆波,金 捷.某型蒸发式稳定器气动及燃烧特性研究[J].火箭推进,2013,39(03):27-31.
DING Zhao-bo,JIN Jie.Investigation on aerodynamic and combustion characteristics of an evaporating flame-holder[J].Journal of Rocket Propulsion,2013,39(03):27-31.
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DING Zhao-bo,JIN Jie.Investigation on aerodynamic and combustion characteristics of an evaporating flame-holder[J].Journal of Rocket Propulsion,2013,39(03):27-31.
某型蒸发式稳定器气动及燃烧特性研究
《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]
卷:
39
期数:
2013年03期
页码:
27-31
栏目:
研究与设计
出版日期:
2013-06-30
- Title:
- Investigation on aerodynamic and combustion characteristics of an evaporating flame-holder
- 文章编号:
- 1672-9374(2013)03-027-05
- Keywords:
- ramjet engine; evaporating flame-holder; V-gutter flame-holder; aerodynamic characteristic; combustion characteristic
- 分类号:
- V439-34
- 文献标志码:
- A
- 摘要:
- 为解决亚燃冲压发动机在高速低温来流条件下的可靠点火、火焰稳定和高效燃烧问题，对某型蒸发式火焰稳定器分别进行了冷态流场和燃烧流场的数值研究，并与常规V型火焰稳定器进行了对比分析。研究结果表明：在给定范围内，蒸发式稳定器随来流速度的增大，总压恢复系数和停留时间明显减小，回流区长度、回流率和燃烧效率变化不大；与相同槽宽的常规V型火焰稳定器相比，回流率明显减小，总压恢复系数、回流区长度和停留时间略有减小。蒸发式稳定器后部形成明显的回流区，且基本上不受外部主流流动的干扰，通过单独控制稳定器局部供油，可以使稳定器在最
- Abstract:
- To realize reliable ignition, flame stabilization and effective combustion of a ramjet engine under the condition of low-temperature and high-velocity incoming flow, numerical analysis of cold-state and combustion flow fields for an evaporating flame-holder was completed, and contrastive analysis with the V-gutter flame-holder was performed. The results show that, in a given scope, with the increase of inlet velocity, the total pressure recovery coefficient and retention time are reduced obviously, and recirculation zone length, recirculation ratio and combustion efficiency change a little. Compared to the V-gutter flame-holder, the recirculation ratio is reduced more significantly, and the total pressure recovery coefficient, recirculation zone length, and retention time are decreased a little bit. Recirculation zone happens in downriver of evaporating flame-holder, and is not interfered by main-flow. The flame-holder can work at the best fuel-air mass ratio by local fuel supply and adapt to low-temperature high-velocity inlet environment.
参考文献/References:
[1]郑殿峰, 张会强, 林文漪, 等. 蒸发式稳定器常压和低压燃烧性能试验研究[J]. 哈尔滨工业大学学报, 2004, 36(12): 1724-1728.
[2]郑殿峰, 张会强, 林文漪, 等. 蒸发式稳定器气态燃料掺混特性和蒸发管的流量系数[J]. 燃烧科学与技术, 2004, 10(1): 28 -31.
[3]刘鸿, 王家骅. 特种V型蒸发式火焰稳定器的总压损失试验研究[J]. 江苏石油化工学院学报, 2002, 14(3): 40-42.
[4]刘鸿, 王家骅. 特种V型蒸发式火焰稳定器的低压性能试验研究[J]. 江苏工业学院学报, 2004, 16(1): 12-14.
[5]王方, 许春晓, 王家骅. 稳定器流动、燃烧实验及冷态大涡模拟研究[J]. 航空动力学报, 2006, 21(3): 502-506.
[6][美]约翰. 霍普金斯大学应用物理实验所. 冲压发动机技术[M]. 北京: 国防工业出版社, 1980.
[7]刘兴洲. 飞航导弹动力装置[M]. 北京: 宇航出版社, 1992.
[8]LONGWELL J P, FROST E E, WEISS M A. Flame stability in bluff body recirculation[J]. Journal of Industrial and Engineering Chemistry, 1953, 45(8): 1629-1633.
[9]许胜. 多孔介质钝体火焰稳定特性实验研究[D]. 中国科学技术大学, 2011.
[10]丁兆波, 金捷. 某型蒸发式火焰稳定器燃烧特性及供油匹配数值研究[J]. 火箭推进, 2012, 38(4): 43-48.
[11]王家骅. 一个预燃式稳定器的稳焰机理研究[J]. 工程热物理学报, 1981, 2(4): 23-28.
[12]王家骅. 蒸发式火焰稳定器的稳定机理研究[J]. 南京航空学院学报, 1980 (1): 69-84.
[13]KUNDU K M, DBANERJEE D. Theoretical analysis on flame stabilization by a Bluff-body[J]. Combustion Science and Technology, 1977, 17(3/4): 153-162.
[14]李宁, 宋文艳, 罗飞腾, 等. 基于先锋氢点火和双凹腔火焰稳定的煤油超声速燃烧特性[J]. 推进技术, 2012 (2): 205-210.
[15]潘亮, 聂嵩, 刘业奎. 环槽式过氧化氢/煤油气液喷注器研究[J]. 火箭推进, 2012 (3): 23-28.
[16]冮强, 王辽, 郭金鑫, 等. 基于总温测量的超燃冲压发动机燃烧效率研究[J]. 实验流体力学, 2012 (4): 1-5.
[17]税琳棋, 高建民, 刘加增, 等. 不同冷却工况下90°带肋通道中蒸汽的强化换热特性研究[J]. 西安交通大学学报, 2012 (9): 6-11.
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备注/Memo
收稿日期：2013-01-１5；修回日期：2013-02-12
基金项目：国家863项目（2006AA705308）
作者简介：丁兆波（1980—），男，博士研究生，研究领域为发动机燃烧装置
更新日期/Last Update:
1900-01-01