| Item type |
学術雑誌論文 / Journal Article(1) |
| 公開日 |
2016-06-21 |
| タイトル |
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タイトル |
Effects of thermally cracked component of n-dodecane on supersonic combustion behaviors in a scramjet model combustor |
|
言語 |
en |
| 言語 |
|
|
言語 |
eng |
| キーワード |
|
|
言語 |
en |
|
主題Scheme |
Other |
|
主題 |
Supersonic combustion |
| キーワード |
|
|
言語 |
en |
|
主題Scheme |
Other |
|
主題 |
Hydrocarbon fuels |
| キーワード |
|
|
言語 |
en |
|
主題Scheme |
Other |
|
主題 |
Thermal cracking |
| キーワード |
|
|
言語 |
en |
|
主題Scheme |
Other |
|
主題 |
Scramjet |
| 資源タイプ |
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資源タイプ識別子 |
http://purl.org/coar/resource_type/c_6501 |
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資源タイプ |
journal article |
| アクセス権 |
|
|
アクセス権 |
metadata only access |
|
アクセス権URI |
http://purl.org/coar/access_right/c_14cb |
| 著者 |
中谷, 辰爾
津江, 光洋
河野, 通方
今村, 宰
富岡, 定毅
Nakaya, Shinji
Tsue, Mitsuhiro
Kono, Michikata
Imamura, Osamu
Tomioka, Sadatake
|
| 著者所属 |
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東京大学 |
| 著者所属 |
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東京大学 |
| 著者所属 |
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東京大学 |
| 著者所属 |
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日本大学 |
| 著者所属 |
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宇宙航空研究開発機構角田宇宙センター(JAXA)(KSPC) |
| 著者所属（英） |
|
|
|
en |
|
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The University of Tokyo |
| 著者所属（英） |
|
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|
en |
|
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The University of Tokyo |
| 著者所属（英） |
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|
en |
|
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The University of Tokyo |
| 著者所属（英） |
|
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|
en |
|
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Nihon University |
| 著者所属（英） |
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|
en |
|
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Kakuda Space Center, Japan Aerospace Exploration Agency (JAXA)(KSPC) |
| 出版者（英） |
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出版者 |
Elsevier |
| 書誌情報 |
en : Combustion and Flame
巻 162,
号 10,
p. 3847-3853,
発行日 2015-10
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| 抄録（英） |
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内容記述タイプ |
Other |
|
内容記述 |
Supersonic combustion ramjet technology using liquid hydrocarbon fuels is invaluable due to great benefits of the energy density per unit volume and handling. This study carried out experiments to investigate the effects of the components in thermally cracked n-dodecane on ignition and supersonic combustion behavior at supersonic speeds (Mach 2.0) and at stagnation temperatures between 1800 K and 2400 K in a supersonic model combustor with a cavity flame holder. Components of the thermally cracked n-dodecane at 1.0 MPa in a flow reactor were experimentally measured by using a gas chromatograph. Based on the measured components, surrogate fuels consisting of main components of cracked n-dodecane, hydrogen, methane, ethane and ethylene were defined, and fractions of the component was varied at less than 10%. Ignition and supersonic combustion behaviors were tested for single component and surrogate fuels. In all cases where supersonic combustions were achieved, ignitions were firstly observed in the boundary layer at the expanding cross section zone. The flames, then, propagated upstream and were held at the cavity. Two combustion modes, jet wake stabilized and cavity stabilized flames were observed based on the distribution of rise in pressure and OH chemiluminescence. In cases of pure fuel injections, ignitions for ethylene injections could be observed at a stagnation temperature of 1800 K. On the other hand, ignitions for methane and ethane injections could be observed above a stagnation temperature of 2200 K. Ignitions for surrogate fuel injections were also investigated. These ignition limits were also validated by a simple estimation of chemical reaction and residence times. It was also found that an increase in fuel temperature improved the ignition limits although the effect of the dynamic pressure ratio between the fuel injection and the main flow was rather limited in the present study. |
| 内容記述 |
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内容記述タイプ |
Other |
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内容記述 |
形態: カラー図版あり |
| 内容記述（英） |
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内容記述タイプ |
Other |
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内容記述 |
Physical characteristics: Original contains color illustrations |
| ISSN |
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収録物識別子タイプ |
ISSN |
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収録物識別子 |
0010-2180 |
| 書誌レコードID |
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収録物識別子タイプ |
NCID |
|
収録物識別子 |
AA00610787 |
| DOI |
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識別子タイプ |
DOI |
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関連識別子 |
http://dx.doi.org/10.1016/j.combustflame.2015.07.021 |
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関連名称 |
info:doi/10.1016/j.combustflame.2015.07.021 |
| 資料番号 |
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内容記述タイプ |
Other |
|
内容記述 |
資料番号: PA1610082000 |
