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気液同軸型噴射要素による噴霧流の実験及び解析(3)(液酸・液水ロケット燃焼性能予測計算への応用)
https://jaxa.repo.nii.ac.jp/records/45027
https://jaxa.repo.nii.ac.jp/records/450276f4017d9-a324-4469-ba44-0cc86697b421
| 名前 / ファイル | ライセンス | アクション |
|---|---|---|
naltr00769.pdf (2.7 MB)
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| Item type | テクニカルレポート / Technical Report(1) | |||||||||
|---|---|---|---|---|---|---|---|---|---|---|
| 公開日 | 2015-03-26 | |||||||||
| タイトル | ||||||||||
| タイトル | 気液同軸型噴射要素による噴霧流の実験及び解析(3)(液酸・液水ロケット燃焼性能予測計算への応用) | |||||||||
| 言語 | ||||||||||
| 言語 | jpn | |||||||||
| 資源タイプ | ||||||||||
| 資源タイプ識別子 | http://purl.org/coar/resource_type/c_18gh | |||||||||
| 資源タイプ | technical report | |||||||||
| その他のタイトル（英） | ||||||||||
| その他のタイトル | An Experimental and Analytical Study on Spray Flow Field by Liquid/Gas Coaxial Injector Elements (3)Application for the Combustion Performance Prediction Model of LO2/LH2 rocket Combustors | |||||||||
| 著者 |
八柳, 信之
× 八柳, 信之
× YATSUYANAGI, Nobuyuki
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| 著者所属 | ||||||||||
| 航空宇宙技術研究所角田支所 | ||||||||||
| 著者所属（英） | ||||||||||
| en | ||||||||||
| Kakuda Branch Office, National Aerospace Laboratory(NAL) | ||||||||||
| 出版者 | ||||||||||
| 出版者 | 航空宇宙技術研究所 | |||||||||
| 出版者（英） | ||||||||||
| 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-769 巻 769, p. 30, 発行日 1983-07 |
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| 抄録（英） | ||||||||||
| 内容記述タイプ | Other | |||||||||
| 内容記述 | An analytical computing model for performing LO2/LH2 rocket combustor performance analysis was derived by using the results of former studies of spray flow field characteristics of Liquid/Gas coaxial injector elements. The each process of liquid atomization, mixing of liquid phase to gas phase and vaporization of liquid droplets are the combustion controlling model. In formulating the analytical combustion model, the combustion zone was subdivided into a series of two discrete zones along the axis of the combustion chamber. At the region immediately adjacent to the propellant injector, the flow is characterized by the behavior of the spray jet from the injector elements. And after each spray jet interactes with each other, the flow is assumed almost one dimensional expect for the mass flux distribution of liquid droplets. For the first region, spray flow field characteristics which were obtained in former studies by the author were applied in modifing the confined spray jet characteristics. By this analytical model, the calculation of combustion gas parameters and liquid droplets histories along the chamber axis, the prediction of C efficiencies and the calculation of heat flux distribution were performed for sub-scaled combustors and actual rocket engines such as the RL-10, LE-5 and HM-7. The predicted C efficiencies were almost within ±2％, compared to the values obtained from experiments. The calculated heat flux values were also in close agreement with values obtained from experiments. | |||||||||
| ISSN | ||||||||||
| 収録物識別子タイプ | ISSN | |||||||||
| 収録物識別子 | 0389-4010 | |||||||||
| 資料番号 | ||||||||||
| 内容記述タイプ | Other | |||||||||
| 内容記述 | 資料番号: NALTR0769000 | |||||||||
| レポート番号 | ||||||||||
| 内容記述タイプ | Other | |||||||||
| 内容記述 | レポート番号: NAL TR-769 | |||||||||
