| Project/Area Number |
19760572
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| Research Category |
Grant-in-Aid for Young Scientists (B)
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| Allocation Type | Single-year Grants |
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| Research Field |
Aerospace engineering
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| Research Institution | The University of Tokyo |
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Principal Investigator |
SHIMIZU Kazuya The University of Tokyo, 大学院・工学系研究科, 特任助教 (80373447)
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| Project Period (FY) |
2007 – 2009
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| Project Status |
Completed (Fiscal Year 2009)
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| Budget Amount *help |
¥2,760,000 (Direct Cost: ¥2,400,000、Indirect Cost: ¥360,000)
Fiscal Year 2009: ¥780,000 (Direct Cost: ¥600,000、Indirect Cost: ¥180,000)
Fiscal Year 2008: ¥780,000 (Direct Cost: ¥600,000、Indirect Cost: ¥180,000)
Fiscal Year 2007: ¥1,200,000 (Direct Cost: ¥1,200,000)
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| Keywords | 航空宇宙流体・推進 / 数値流体力学 / 燃焼 / 気液二相流 / ロケットエンジン / 水素 / 酸素 / 数値解析 / 微粒化 / 超臨界 / 実在流体 / 非保存型スキーム |
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| Research Abstract |
In a liquid rocket engine, mixing process affects on the stability of combustion, and the process is strongly depends on pressure in a combustion chamber. In this research, I have studied development of numerical method to investigate combustion phenomena in a rocket engine coaxial injector flow. The final target of this activity is to include vaporization of liquid oxygen in a numerical treatment. A detailed chemical kinetic model in hydrogen/oxygen system applicable to rocket engine combustion is proposed, and a stable time integration method of the detailed kinetic mechanism in a flow analysis is also proposed. The deformation of an oxygen droplet in a hydrogen stream and its mixing behavior is numerically studied. Numerical results showed that flow field and mixing process is divided into two patterns, depending on Reynolds number. When an ambient pressure becomes high, the deformation of the droplet becomes rapid and the separation behind the droplet developed significantly.
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