| タイトル |
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en
Advantage of ethanol fuel for gas generator cycle air turbo ramjet engine
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| 作成者 |
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en
MINATO, Ryojiro
ja
湊, 亮二郎
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| アクセス権 |
open access |
| 権利情報 |
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en
© 2016. This manuscript version is made available under the CC-BY-NC-ND 4.0 license http://creativecommons.org/licenses/by-nc-nd/4.0/
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| 主題 |
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NDC
538.3
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Other
en
Air turbo ramjet engine
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Other
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Supersonic UAV
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Other
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Gas generator
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Other
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Ethanol
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| 内容注記 |
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Other
application/pdf
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Abstract
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Performance analyses of Gas Generator cycle Air Turbo Ramjet (GG-ATR) engine are conducted to investigate the feasibility of ethanol fuel, as comparing Liquefied Hydrogen (LH2), Liquefied Natural Gas (LNG), and n-C12H26. Liquefied Oxygen (LOX) is considered as an oxidizer. Gas generator combustion temperature and compressor pressure ratio are selected as the analytical parameters, which are varied from 900 to 1700 K and from 2.0 to 4.0, respectively. In general, specific impulses of light molecule weight fuels, such as LH2 and LNG, are higher than those of large molecule weight fuel. For storable fuel, Isp of ethanol is larger than that of n-C12H26 when gas generator temperature is less than 1300 K, although specific heat release of ethanol is only two thirds of n-C12H26 heat release. The main chemical species of n-C12H26 gas generator (GG) combustion gas are CH4 and CO. On the other hand, ethanol GG combustion gas is mainly composed of H2 and CO, resulting in smaller molecular weight than n-C12H26. These characteristics contribute to larger Isp of ethanol than n-C12H26 and indicate the feasibility of ethanol for GG-ATR engine fuel.
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Other
ja
本アーカイブに掲載したPDFは校正前の原稿である。
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| 出版者 |
en
Elsevier
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| 日付 |
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| 言語 |
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| 資源タイプ |
journal article |
| 出版タイプ |
AM |
| 資源識別子 |
HDL
http://hdl.handle.net/10258/00008626
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URI
https://muroran-it.repo.nii.ac.jp/records/8637
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| 関連 |
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isVersionOf
DOI
https://doi.org/10.1016/j.ast.2015.12.026
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| 収録誌情報 |
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PISSN
1270-9638
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PISSN
0034-1223
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NCID
AA11136713
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NCID
AA11522422
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en
Aerospace Science and Technology
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巻50
開始ページ161
終了ページ172
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| ファイル |
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| コンテンツ更新日時 |
2023-10-13 |
