Experimental Investigation of Hydrocarbon-fuel Ignition in Scramjet Combustor

The direct-connected supersonic combust or experiment is finished for kerosene fuel ignition in H2/O2 preheated impulse facility. The entrance parameter of combustor corresponds to scram jet flight Mach number 3.5. Kerosene ignition is realized by using hydrogen as pilot flame. Wall pressure distrib...

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Published inChinese journal of aeronautics Vol. 17; no. 2; pp. 65 - 71
Main Author 宋文艳 黎明 蔡元虎 刘伟雄 白菡尘
Format Journal Article
LanguageEnglish
Published Elsevier Ltd 01.05.2004
Subjects
ignition
impulse wind tunnel
kerosene
pilot flame
supersonic combustor
点火实验
碳氢燃料
超燃冲压发动机
超音速燃烧室
风洞实验
impulse wind tunnel
supersonic combustor
ignition
kerosene
pilot flame
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ISSN1000-9361
2588-9230
DOI10.1016/S1000-9361(11)60216-1

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Summary:The direct-connected supersonic combust or experiment is finished for kerosene fuel ignition in H2/O2 preheated impulse facility. The entrance parameter of combustor corresponds to scram jet flight Mach number 3.5. Kerosene ignition is realized by using hydrogen as pilot flame. Wall pressure distributions of combustion are measured and flame photographs of ultraviolet ray are got. Experiment indicates that it is very difficult for kerosene fuel to realize self-ignition at low entrance temperature (below 900K) in supersonic combustor. Hydrogen pilot flame is one of the efficient methods for realizing kerosene ignition.
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ISSN:1000-9361
2588-9230
DOI:10.1016/S1000-9361(11)60216-1