Mchanism of hydrogen combustion and NOx production in ram combustor of pre-cooled turbo jet

2014 Fiscal Year Final Research Report

• Project/Area Number: 24560971
• Research Category: Grant-in-Aid for Scientific Research (C)
• Allocation Type: Multi-year Fund
• Section: 一般
• Research Field: Aerospace engineering
• Research Institution: The University of Tokyo
• Principal Investigator: TSUE Mitsuhiro 東京大学, 工学(系)研究科(研究院), 教授 (50227360)
• Co-Investigator(Renkei-kenkyūsha): SHINJI Nakaya 東京大学, 工学系研究科, 准教授 (00382234)
• Project Period (FY): 2012-04-01 – 2015-03-31
• Keywords: 推進機関 / エンジン / 水素 / 予冷ターボジェット / 極超音速

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.

Free Research Field

航空宇宙推進