| Item type |
会議発表論文 / Conference Paper(1) |
| 公開日 |
2015-03-26 |
| タイトル |
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|
タイトル |
Physical Insight into Hypermixer Injector Design for Fuel/Air Mixing Enhancement in Scramjet Engines via Parametric Numerical Simulations and Surrogate-Assisted Sensitivity Analysis |
|
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_5794 |
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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 |
Ogawa, Hideaki
小寺, 正敏
Boyce, Russell R.
Ogawa, Hideaki
Kodera, Masatoshi
Boyce, Russell R.
|
| 著者所属 |
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ロイヤルメルボルン工科大学 |
| 著者所属 |
|
|
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宇宙航空研究開発機構(JAXA) |
| 著者所属 |
|
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クイーンズランド大学 |
| 著者所属（英） |
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|
en |
|
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Royal Melbourne Institute of Technology |
| 著者所属（英） |
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en |
|
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Japan Aerospace Exploration Agency(JAXA) |
| 著者所属（英） |
|
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|
en |
|
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The University of Queensland |
| 出版者（英） |
|
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出版者 |
American Institute of Aeronautics and Astronautics(AIAA) |
| 書誌情報 |
発行日 2013-09
|
| 会議概要（会議名, 開催地, 会期, 主催者等）（英） |
|
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内容記述タイプ |
Other |
|
内容記述 |
The 21st International Symposium on Air breathing Engines (ISABE 2013) (September 9-13, 2013.), Busan, Korea. |
| 抄録（英） |
|
|
内容記述タイプ |
Other |
|
内容記述 |
Hypersonic airbreathing propulsion offers the great potential for reliable, reusable and economical systems for access-to-space and high-speed atmospheric cruise for both civilian and strategic purposes. Scramjet (supersonic combustion ramjet) propulsion, in particular, is a promising technology that can enable efficient and flexible transport systems by removing the need to carry oxidizers and other limitations of conventional rocket engines. A scramjet engine typically consists of an inlet, combustor, and nozzle. It operates in a sequential process comprising flow compression, combustion and expansion. Fuel/air mixing plays a crucial role in the scramjet combustion process (fuel injection, mixing, ignition and combustion), which must occur within an extremely short residence time in hyper-velocity flowfields. Hypermixers using alternating wedge struts (Figure 1) are capable of generating streamwise vortices to enhance fuel/air mixing in the core flow, incurring minimum influence of fluid compressibility.Extensive research has been conducted at JAXA Kakuda Space Center in order to investigate the effects of streamwise vortices introduced by hypermixers on fuel mixing enhancement. A parametric numerical study is conducted in the presentresearch in order to examine the flowfields with various combinations of the primary hypermixer design parameters, namely the spanwise spacing, ramp angle of the wedges, and fuel/air equivalence ratio (Figure 2 displays the fuel distributions downstream of a baseline hypermixer configuration). Their influence on the mixing performance is evaluated with respect to various performance parameters including the mixing efficiency, total pressure loss, fuel propagation height, and streamwise circulation by applying sensitivity analysis based on prediction from surrogate models. The sensitivity indices obtained as a result are plotted in Figure 3. Narrow spanwise intervals and large fuel/air equivalence ratios have been found to be beneficial for effective mixing, while higher total pressure recovery is associated with shallower ramp angles and lower fuel/air equivalence ratios. Higher fuel propagation is achieved with steeper ramp angles and lower fuel/air equivalence ratios, and greater streamwise circulation is yielded with wider spanwise spacing and steeper ramp angles in laminar non-reacting flow assumptions. |
| 資料番号 |
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内容記述タイプ |
Other |
|
内容記述 |
資料番号: AC1400053000 |
| レポート番号 |
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内容記述タイプ |
Other |
|
内容記述 |
レポート番号: ISABE-2013-1624 |
