| Item type |
会議発表論文 / Conference Paper(1) |
| 公開日 |
2015-08-12 |
| タイトル |
|
|
タイトル |
Numerical estimation of the thrust performance on a rotating detonation engine for a hydrogen-oxygen mixture |
|
言語 |
en |
| 言語 |
|
|
言語 |
eng |
| キーワード |
|
|
言語 |
en |
|
主題Scheme |
Other |
|
主題 |
Rotating detonation engine |
| キーワード |
|
|
言語 |
en |
|
主題Scheme |
Other |
|
主題 |
Thrust performance |
| キーワード |
|
|
言語 |
en |
|
主題Scheme |
Other |
|
主題 |
Three-dimensional effects |
| 資源タイプ |
|
|
資源タイプ識別子 |
http://purl.org/coar/resource_type/c_5794 |
|
資源タイプ |
conference paper |
| 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 |
坪井, 伸幸
渡辺, 裕介
小島, 孝之
林, 光一
Tsuboi, Nobuyuki
Watanabe, Yusuke
Kojima, Takayuki
Hayashi, A. Koichi
|
| 著者所属 |
|
|
|
九州工業大学 |
| 著者所属 |
|
|
|
九州工業大学 |
| 著者所属 |
|
|
|
宇宙航空研究開発機構研究開発本部(JAXA) |
| 著者所属 |
|
|
|
青山学院大学 |
| 著者所属（英） |
|
|
|
en |
|
|
Kyushu Institute of Technology |
| 著者所属（英） |
|
|
|
en |
|
|
Kyushu Institute of Technology |
| 著者所属（英） |
|
|
|
en |
|
|
Aerospace Research and Development Directorate, Japan Aerospace Exploration Agency (JAXA) |
| 著者所属（英） |
|
|
|
en |
|
|
Aoyama Gakuin University |
| 出版者（英） |
|
|
出版者 |
Elsevier |
| 書誌情報 |
en : Proceedings of the Combustion Institute
巻 35,
号 2,
p. 2005-2013,
発行日 2015
|
| 抄録（英） |
|
|
内容記述タイプ |
Other |
|
内容記述 |
The numerical simulations of 2D and 3D rotating detonation engines for a hydrogen-oxygen mixture are performed using a detailed chemistry model. The comparison of 2D/3D flow fields for the same injection conditions indicates that the overall flow structures are in agreement for the two simulations and that both rotating velocities are approximately 96% of the CJ value. However, Isp for the 2D RDE is approximately 10 s larger than Isp for the 3D RDE. The grid resolution study indicates that the higher grid resolution produces detonation cellular structure; however, its effects on Isp are approximately a few seconds. Although Isp in the 2D smallest scale for higher mass flow is approximately 10 s larger than that of the other large scales, Isp for low mass flow is not affected by the scale. However, 3D scale effects are important because the radius of curvature along the circumferential direction changes, which affects the propagation of the rotating detonation. Because Isp and thrust are governed by the stagnation pressure and the micro-nozzle area ratio, the mass flow rate from the injector also depends on these parameters. Isp and thrust for RDE are found to be correlated with the mass flow rate, similar to the case of a conventional rocket engine. This result indicates that the two important parameters, A*/A and P0, can be replaced by one parameter, i.e., the mass flow rate. |
| ISSN |
|
|
収録物識別子タイプ |
ISSN |
|
収録物識別子 |
1540-7489 |
| 書誌レコードID |
|
|
収録物識別子タイプ |
NCID |
|
収録物識別子 |
AA11552208 |
| DOI |
|
|
|
識別子タイプ |
DOI |
|
|
関連識別子 |
http://dx.doi.org/10.1016/j.proci.2014.09.010 |
|
|
関連名称 |
info:doi/10.1016/j.proci.2014.09.010 |
| 資料番号 |
|
|
内容記述タイプ |
Other |
|
内容記述 |
資料番号: PA1520030000 |
