| Project/Area Number |
02452089
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| Research Category |
Grant-in-Aid for General Scientific Research (B)
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| Allocation Type | Single-year Grants |
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| Research Field |
Aerospace engineering
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| Research Institution | Univ. of Tokyo |
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Principal Investigator |
NAGASHIMA Toshio Univ. of Tokyo・Engineering・Professor, 工学部, 教授 (70114593)
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| Co-Investigator(Kenkyū-buntansha) |
ITOH Hiroshi Univ. of Tokyo・Engineering・Assistant, 工学部, 助手 (20211055)
KONO Michikata Unin. of Tokyo・Engineering・Professor, 工学部, 教授 (60011194)
TANIDA Yoshimichi Univ. of Tokyo・RCAST・Professor, 先端研, 教授 (50013628)
HIRATA Masaru Univ. of Tokyo・Engineering・Professor, 工学部, 教授 (70010775)
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| Project Period (FY) |
1990 – 1991
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| Project Status |
Completed (Fiscal Year 1991)
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| Budget Amount *help |
¥5,900,000 (Direct Cost: ¥5,900,000)
Fiscal Year 1991: ¥1,900,000 (Direct Cost: ¥1,900,000)
Fiscal Year 1990: ¥4,000,000 (Direct Cost: ¥4,000,000)
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| Keywords | Fuel Injection / Supersonic Flows / Shock waves / Hydrogen / Optimization / Ignition / Flame / 混合拡散 / 垂直噴射 / 衝撃波境界層干渉 / マッハディスク |
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| Research Abstract |
Fuel gas injection into Mach 2 air flows between parallel walls has been investigated in order to achieve optimum fuel injection conditions that satisfy reliable ignition and flaming, shorter combustion length and less totalpressure loss. Hydrogen gas has been transversely injected through circular holes which are mounted flush to the walls and act as sonic nozzles.
Experimental results show the occurrence of strong bow shock wave and the associated shock wave boundary layer interaction as well as the turbulent mixing of the hydrogen into the main flow. When the total temperature of air was raised above 1000ﾟC, the self-ignition flame was observed at the test section. In case of a single, injector the flow separation distance ahead of the injector increased linearly with the injection pressure and the barrel shock wave structure within the hydrogen jet was enlarged accordingly. The hydrogen plume kept similar profile as it was convected downstream. The case of two injectors arrayed in tandem, on the other hand, revealed an interesting interference zone between the two injectors that yielded little static pressure variation and high hydrogen concentration. The total pressure loss measured at the test section exit showed a minimum as the injection pressure ratio between the two injectors was varied. Those results indicated the possible optimization of the fuel injection by the control of the injector array patterns.
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