A Study on Flame-Holding and Ignition of Hydrocarbon Fuel in Supersonic Flow
| Project/Area Number |
15560685
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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 | Gifu University |
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Principal Investigator |
WAKAI Kazunori (2005) Gifu University, Faculty of Engineering, Professor, 工学部, 教授 (50021621)
高橋 周平 (2003-2004) 岐阜大学, 工学部, 助教授 (40293542)
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| Co-Investigator(Kenkyū-buntansha) |
IHARA Tadayoshi Gifu University, Faculty of Engineering, Research Associate, 工学部, 助手 (30377684)
若井 和憲 岐阜大学, 工学部, 教授 (50021621)
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| Project Period (FY) |
2003 – 2005
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| Project Status |
Completed (Fiscal Year 2005)
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| Budget Amount *help |
¥3,500,000 (Direct Cost: ¥3,500,000)
Fiscal Year 2005: ¥700,000 (Direct Cost: ¥700,000)
Fiscal Year 2004: ¥1,500,000 (Direct Cost: ¥1,500,000)
Fiscal Year 2003: ¥1,300,000 (Direct Cost: ¥1,300,000)
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| Keywords | Supersonic flow / Combustion / Kerosene / Ignition / Flame-holding / Scramjet / Temperature measurement / Two-band emission method / 微粒化 / キャビティー / 着火 / 保炎 / 噴霧化 / 予蒸発 |
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| Research Abstract |
Hydrocarbon fuel is attractive for scramjet engine because of its high energy density. However, its low reactivity is pointed out as a large demerit. In order to use hydrocarbon fuel for a scramjet combustor, it is important to ensure ignition and flame-holding in a supersonic airflow. In this research, we use kerosene as a fuel and inject it into a scramjet combustor with a cavity, which is L in length and D in depth. The Mach number is 2 and the total temperature is 1800K-2400K. We also conduct numerical simulations as well as wind tunnel experiments. From the experimental result, it is found that there is a certain combination of L and D that leads to the maximum improvement of flame-holding performance. The numerical result shows that in a such case, large and complex vortex structure is generated in the cavity and prolong the residence time of the fuel in the combustor. On the other hand, it is predicted that the temperature in the cavity increases due to the decrease of the incoming flow. However, it is difficult to measure the temperature with intrusive method, such as a thermocouple. Hence, we adopt the two-band emission method instead with H2O as a target particle. We can measure the temperature in the cavity without disturbing the flow filed. The measured temperature was compared with the predicted one and they agree well. It is found that the well-designed cavity has good performance for flame-holding of hydrocarbon fuel in supersonic flow by prolonging the residence time and increasing the temperature.
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Report
(4 results)
Research Products
(6 results)
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[Journal Article] Characteristics of Flame-holding in a Scramjet Combustor with a Cavity2004
Author(s)
Tanaka, H., Takahashi, S., Uriuda, Y., Wakai, K., Tsue, M., Kono, M., Ujiie, Y.
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Journal Title
Proceedings of Asian Joint Conference on Propulsion and Power (CD-ROM)
Description
「研究成果報告書概要(和文)」より
Related Report
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[Journal Article] Characteristics of Flame-holding in a Scramjet Combustor with a Cavity2004
Author(s)
Tanaka, H., Takahashi, S., Uriuda, Y., Wakai, K., Tsue, M., Kono, M., Ujiie, Y.
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Journal Title
Proceedings of Asian Joint Conference on Propulsion and Power, Seoul (CD-ROM)
Description
「研究成果報告書概要(欧文)」より
Related Report
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[Publications] Tanaka, H., Takahashi, S., Uriuda, Y., Wakai, K., Tsue, M., Kono, M., Ujiie, Y.: "Characteristics of Flame-holding in a Scramjet Combustor with a Cavity"Proceedings of Asian Joint Conference on Propulsion and Power. (CD-ROM). (2004)
