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Studies of High Frequency Combustion Oscillations in a Gaseous Propellant Rocket Motor
https://jaxa.repo.nii.ac.jp/records/34638
https://jaxa.repo.nii.ac.jp/records/34638c9cdbcbe-64a1-47ad-9063-087b64a52b30
| 名前 / ファイル | ライセンス | アクション |
|---|---|---|
SA2404947.pdf (1.9 MB)
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| Item type | 紀要論文 / Departmental Bulletin Paper(1) | |||||||||
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| 公開日 | 2015-03-26 | |||||||||
| タイトル | ||||||||||
| タイトル | Studies of High Frequency Combustion Oscillations in a Gaseous Propellant Rocket Motor | |||||||||
| 言語 | en | |||||||||
| 言語 | ||||||||||
| 言語 | eng | |||||||||
| 資源タイプ | ||||||||||
| 資源タイプ識別子 | http://purl.org/coar/resource_type/c_6501 | |||||||||
| 資源タイプ | departmental bulletin paper | |||||||||
| 著者 |
TSUJI, Hiroshi
× TSUJI, Hiroshi
× TAKENO, tadao
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| 出版者 | ||||||||||
| 出版者 | 東京大学航空研究所 | |||||||||
| 出版者（英） | ||||||||||
| 出版者 | Aeronautical Research Institute, University of Tokyo | |||||||||
| 書誌情報 |
東京大學航空研究所報告 en : Report/Aeronautical Research Institute, University of Tokyo 巻 29, 号 13, p. 191-218, 発行日 1964-03 |
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| 抄録（英） | ||||||||||
| 内容記述タイプ | Other | |||||||||
| 内容記述 | The experimental studies were conducted in a research rocket motor burning premixed gases as propellants for investigating the effects of several variables upon the high frequency combustion oscillations in a rocket motor in detail and making clear the driving mechanism of these oscillations. The effects of the combustion chamber length, the propellant equivalence ratio, the mean chamber pressure and the shape of the nozzle upon the longitudinal-mode pressure oscillations were examined. The research rocket motor had a rectangular combustion chamber of 5cm×8cm cross section and the propellants used were the premixed city gas and air. Three modes of the longitudinal pressure oscillations, namely, the fundamental-, the second harmonic- and the third harmonic-mode oscillations were observed in the combustion chamber and the measured periods of each mode oscillation were found to satisfy the relation of acoustic-mode oscillations. Therefore the high frequency combustion pressure oscillations may be treated essentially as the standing waves of the longitudinal mode, though the propagating shock-type pressure waves appeared as the feed energy to the oscillation was increased. The fundamental and the higher harmonic-mode pressure oscillations occurred only for certain conditions of the chamber length, the propellant equivalence ratio and the chamber pressure. With increasing the chamber length and the chamber pressure, the instability regions of each mode oscillation were increased. It was confirmed from the experimental results of the instability regions that the combustion oscillations are initiated and sustained only when the period of the oscillation is larger than some combustion time lag determined by the chamber pressure, the fuel compositions, the mixture ratio, the injection velocity of propellant, etc. | |||||||||
| ISSN | ||||||||||
| 収録物識別子タイプ | ISSN | |||||||||
| 収録物識別子 | 0376-1061 | |||||||||
| 書誌レコードID | ||||||||||
| 収録物識別子タイプ | NCID | |||||||||
| 収録物識別子 | AA00514444 | |||||||||
| 資料番号 | ||||||||||
| 内容記述タイプ | Other | |||||||||
| 内容記述 | 資料番号: SA2404947000 | |||||||||
