Fundamental research on micro hydrogen combustor for MEMS gas turbine engine
| Project/Area Number |
17560047
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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 |
Applied physics, general
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| Research Institution | Ritsumeikan University |
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Principal Investigator |
TORIYAMA Toshiyuki Ritsumeikan University, Micro system technology, Professor, 理工学部, 教授 (30227681)
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| Project Period (FY) |
2005 – 2006
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| Project Status |
Completed (Fiscal Year 2006)
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| Budget Amount *help |
¥3,400,000 (Direct Cost: ¥3,400,000)
Fiscal Year 2006: ¥700,000 (Direct Cost: ¥700,000)
Fiscal Year 2005: ¥2,700,000 (Direct Cost: ¥2,700,000)
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| Keywords | Micromachine / Aerospace engineering |
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| Research Abstract |
Aerothermal and structural designs for a micro combustor applied to MEMS turbo machinery are considered. The aero thermal performance of the micro combustor is analyzed based on the assumption that it is composed of two chemical reactors. Theses are aft-wake behind flame folder and flame propagation regions, and modeled as well stirred and plug flow reactors, respectively. The combustion loading parameter, residence time and reaction rate are calculated based on the above mentioned reactor models in order to determine stable combustion limit, chamber volume, optimum equivalent ratio and adiabatic flame temperature. The micro combustor is composed of 8 stacked silicon wafers. These are aligned and bonded together to construct the complete structure. The micro combustor has flame folder, liner cooling jacket and spark ignition plug. FE analysis is performed in order to evaluate the heat conduction and thermal deformation of the micro combustor. The designed micro combustor has following specification. Mass flow rate:0.2g/sec, Inlet temperature:444K, Inlet stagnation pressure:237kPa, Outlet temperature:1300K, Volume:10^<-7>m^3. Brayton cycle states that MEMS gas turbine engine having thrust power of 0.1N and power to weight ratio of 0.5 is feasible by using the proposed micro combustor. Bulk micromachining based on the Deep-RIE and direct bonding is adopted to fabricate the micro combustor. Pressure loss and hydrogen combustion are confirmed to demonstrate validity of the proposed concept by preliminary experiment.
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Report
(3 results)
Research Products
(4 results)
