| Budget Amount *help |
¥5,330,000 (Direct Cost: ¥4,100,000、Indirect Cost: ¥1,230,000)
Fiscal Year 2014: ¥780,000 (Direct Cost: ¥600,000、Indirect Cost: ¥180,000)
Fiscal Year 2013: ¥1,950,000 (Direct Cost: ¥1,500,000、Indirect Cost: ¥450,000)
Fiscal Year 2012: ¥2,600,000 (Direct Cost: ¥2,000,000、Indirect Cost: ¥600,000)
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| Outline of Final Research Achievements |
The pre-cooled turbojet engine is a candidate using hydrogen for hypersonic propulsion system. The propulsion system operates from Mach 0 to Mach 6. At the wide operation range, it is required to understand the combustion in engines to realize high thermal efficiency and low emission index of NOx. In the present study, we conducted measurements of hydrogen combustion in the model ram combustor connected to the exit of a high enthalpy wind tunnel. Besides, we conducted a computational fluid dynamics using detailed reaction models of hydrogen combustion and NOx production. As results, injection configurations of hydrogen are clarified to achieve high efficiency combustion. Mechanism of NOx production is clarified especially for rich hydrogen combustions. In additions, a two color pyrometry was suggested by seeding particles in hydrogen. The experimental results showed this method was very useful to measure temperature distributions of hydrogen combustions.
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