| Item type |
テクニカルレポート / Technical Report(1) |
| 公開日 |
2015-03-26 |
| タイトル |
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タイトル |
Combustion Characteristics of Oxygen/Hydrogen High Pressure Preburners for Staged Combustion Cycle Rocket Engine |
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言語 |
en |
| 言語 |
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言語 |
eng |
| 資源タイプ |
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資源タイプ識別子 |
http://purl.org/coar/resource_type/c_18gh |
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資源タイプ |
technical report |
| その他のタイトル |
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その他のタイトル |
酸素-水素・高圧プリバーナの燃焼特性 |
| 著者 |
小野, 文衛
田村, 洋
坂本, 博
佐々木, 正樹
ONO, Fumiei
TAMURA, Hiroshi
SAKAMOTO, Hiroshi
SASAKI, Masaki
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| 著者所属 |
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航空宇宙技術研究所角田支所 |
| 著者所属 |
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航空宇宙技術研究所角田支所 |
| 著者所属 |
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航空宇宙技術研究所角田支所 |
| 著者所属 |
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航空宇宙技術研究所角田支所 |
| 著者所属（英） |
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en |
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Kakuda Branch Office, National Aerospace Laboratory(NAL) |
| 著者所属（英） |
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en |
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Kakuda Branch Office, National Aerospace Laboratory(NAL) |
| 著者所属（英） |
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|
en |
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Kakuda Branch Office, National Aerospace Laboratory(NAL) |
| 著者所属（英） |
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en |
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Kakuda Branch Office, National Aerospace Laboratory(NAL) |
| 出版者 |
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出版者 |
航空宇宙技術研究所 |
| 出版者（英） |
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出版者 |
National Aerospace Laboratory(NAL) |
| 書誌情報 |
航空宇宙技術研究所報告
en : Technical Report of National Aerospace Laboratory TR-1044
巻 1044,
p. 27,
発行日 1989-11
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| 抄録（英） |
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内容記述タイプ |
Other |
|
内容記述 |
The influence of preburner design and operating conditions on the combustion characteristics of high pressure fuel rich preburners with oxygen/hydrogen propellant was experimentally evaluated using small scale hardware. Seven different types of preburners whose injectors consisted of one to six coaxial type injection elements were tested. Gaseous oxygen at room temperature and liquid oxygen were used as oxidizer, and gaseous hydrogen at room temperature and such hydrogen at low(83-117K) were used as fuel. Testing also covered a combustion pressure range of 5.0 to 15.1 MPa, an oxidizer to fuel ratio range from 0.22 to 0.83 and an injection element propellant flow rate range from 0.026 to 0.238 kg/sec. Combustion performance and gas temperature uniformity data are presented for each preburner. Measured combustion performances were nearly 100％ for all preburners over the tested range. Measured temperature uniformity was correlated by an empirical correlation parameter which accounts for the effects of oxidizer to fuel ratio, shear force due to oxygen and hydrogen injection velocity difference, and combustion gas residence time. Abnormal combustion phenomena which were characterized by abnormally low combustion performance and low combustion gas temperature were observed. The phenomena were interpreted as meaning that the propellant injected from some coaxial elements did not burn due to misignition. |
| 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 |
0389-4010 |
| 資料番号 |
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内容記述タイプ |
Other |
|
内容記述 |
資料番号: NALTR1044000 |
| レポート番号 |
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内容記述タイプ |
Other |
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内容記述 |
レポート番号: NAL TR-1044 |
naltr01044.pdf (2.4 MB)
