| Project/Area Number |
12450075
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| Research Category |
Grant-in-Aid for Scientific Research (B)
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| Allocation Type | Single-year Grants |
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| Section | 一般 |
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| Research Field |
Fluid engineering
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| Research Institution | Osaka University |
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Principal Investigator |
TSUJIMOTO Yoshinobu Osaka University, Graduate School of Engineering Science, Professor, 基礎工学研究科, 教授 (50112024)
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| Co-Investigator(Kenkyū-buntansha) |
YOKOTA Kazuhiko Nagoya Institute of Technology, Mechanical Engineering, Associate Professor, 機械工学部, 助教授 (70260635)
SAKAZUME Norio National Space Development Agency of Japan, Office of Space Transportation Systems, Senior Engineer, 宇宙輸送システム本部, 主任開発部員
YOSHIDA Yoshiki Osaka University, Graduate School of Engineering Science, Associate Professor, 基礎工学研究科, 助教授 (80240836)
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| Project Period (FY) |
2000 – 2001
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| Project Status |
Completed (Fiscal Year 2001)
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| Budget Amount *help |
¥7,100,000 (Direct Cost: ¥7,100,000)
Fiscal Year 2001: ¥1,600,000 (Direct Cost: ¥1,600,000)
Fiscal Year 2000: ¥5,500,000 (Direct Cost: ¥5,500,000)
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| Keywords | Mach Disk / Cap Shock / Free Shock Separation / Restricted Shock Separation / Trapped Vortex / Small step for film cooling / CTP nozzle / Three dimensional CFD / 2次元ノズル / 数値シミュレーション / 超音速風洞実験 / 流体振動 / 横推力 / キャップショック / FSS / RSS |
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| Research Abstract |
Recently, the large side loads is observed in the latest rocket nozzles during start-up and shutdown transient. The objective of this study is to clarify the mechanisms of producing the side loads. In this study, both experimental and numerical studies are performed. In the numerical studies, both the three-dimensional and two-dimensional simulations are performed. The results of three-dimensional simulations show that the simultaneous occurrence of the Free Shock Separation (FSS) and the Restricted Shock Separation (RSS) produces the large side load. In the two-dimensional simulations, the flow field is replaced with a two-dimensional planer field so that it is possible to observe the asymmetric flow patterns. The results show that the small step for film cooling gives great effect on the side load. At the steps, the separation points are trapped in the certain range of pressure ratio, and rapidly shifts to the nozzle exit at the certa(in press)ure ratio. This shift occurs asymmetrically and it produces the large side load. The experimental studies are performed by using the two-dimensional supersonic nozzles. The results show that the asymmetric flow patterns are produced by the instability of shear layer in the downstream of shock wave. But in two-dimensional nozzles, the flow is separated from sides of the test section, and the affects the separation pattern on the nozzle wall.
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