1998 Fiscal Year Final Research Report Summary
Catalytic Combustion in Low Temperature Supersonic Mixing Layer on Scramjet Engine Model
| Project/Area Number |
09651006
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| Research Category |
Grant-in-Aid for Scientific Research (C)
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| Allocation Type | Single-year Grants |
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| Section | 一般 |
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| Research Field |
Aerospace engineering
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| Research Institution | MURORAN INSTITUTE OF TECHNOLOGY |
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Principal Investigator |
ARAI Takakge Muroran Institute of Technology, Machanical System Engineering, Associate Professor, 工学部, 助教授 (10175945)
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| Co-Investigator(Kenkyū-buntansha) |
NAGATA Harunori Hokkaido University, Faculty of Engineering, Associate Professor, 大学院・工学研究科, 助教授 (40281787)
SUGUIYAMA Hiromu Muroran Institute of Technology, Machanical System Engineering, Professor, 工学部, 教授 (70002938)
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| Project Period (FY) |
1997 – 1998
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| Keywords | Scramjet Engine / Supersonic Combustion / Supersonic Mixing / Catalytic Combustion / Turbulent Mixing / Measurement |
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| Research Abstract |
It is important for scramjet engine study to understand the mixing process in supersonic mixing layer. So far, many experimental and numerical studies have been conducted to clarify the mixing process in supersonic mixing layer. Most of experimental studies have focused in the velocity distributions concerned with mixing layer, and also evaluated the flow visualization results. Meanwhile, with CPD developing, numerical results have been able to give the spatial data of equivalence ratio of H_2 (distribution of H_2 concentration). There is less data of distribution of equivalence ratio in mixing layer as reason for the difficulty of measuring it. This study proposes a new evaluation technique for the mixing condition of H_2 in hydrogen-air supersonic flow. We have reported the new technique for the evaluation of turbulent supersonic mixing layer using catalytic reaction on constant high temperature Pt wire. This technique has been developed and is applied to measure H_2 concentration in
… More
supersonic mixing flow produced by inclined hydrogen injection into a Supersonic flow.
Hydrogen was injected normally to a Mach 1.8 cold air stream with a backward-facing step to investigate mixing flow field in a scramjet combustor. Catalytic reaction on constant temperature Pt wire was used to measure the mixing condition of H_2 and O_2. It was new technique to investigate H_2 mixing condition. The amount of heat release due to the catalytic reaction, which corresponds to the concentration of H_2 and/or O_2 on the surface of the catalyst, was measured spatially so that the local mixing condition of H_2 and O_2 was cleared. The results showed that there were two core regions. which would have good mixing condition for supersonic combustion, in the mixing layer. The development of core regions along flow direction was also clarified It was also clarified that the new teclmique proposed in the present study was very useful and easy to evaluate the hydrogen concentration in supersonic mixing flow field. Less
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