A study on supersonic mixing by circular nozzle with various injection angle for air breathing engine
- Paper number
IAC-06-C4.5.06
- Author
Mr. Kei Inoue, Kyushu University, Japan
- Coauthor
Mr. Kohei Yamaguchi, Kyushu University, Japan
- Coauthor
Prof. Shigeru Aso, Kyushu University, Japan
- Coauthor
Dr. Yasuhiro Tani, Kyushu University, Japan
- Year
2006
- Abstract
SCRAM-jet engine is considered one the useful system propulsion for super/hyper sonic transportation vehicle and various researches were made to develop the engine. However, these are a lot of problems to be solved to develop it and one of them is the problem of supersonic mixing. In the SCRAM-jet engine combustor, main airflow is supersonic and residence time of the air is very short (about 1ms). Hence rapid mixing of air and fuel is necessary. However, usually it is quite difficult to mix fuel with air in very short distance. Also total pressure loss occurs by flow interaction the air and fuel. Total pressure loss is not preferable because it causes the thrust loss. Therefore, supersonic mixing with very rapid mixing and lower total pressure loss is highly requested. In order to develop the supersonic mixing, it is very important to understanding the effect of injection angle. In present study, we investigate the effect of injection angle with circular sonic nozzle by changing the injection angle. Experimental and computational studies on supersonic mixing phenomena of two-dimensional slot injector with various injection angle were conducted. Supersonic wind tunnel was used for the experiments. The free stream Mach number is 3.8, total pressure is 1.1MPa and total temperature is 287K on average. As a secondary gas, Helium gas was injected at sonic speed from the circular nozzle. The injection angle is 30deg, 60deg and 90deg. Its total pressure is 0.4MPa and total temperature is 287K on average. The same flow field was also simulated by solving three-dimensional full Navier-Stokes equation with AUSM-DV scheme (Wada et al.(1994)) for convective terms and full implicit LU-ADI factorization method (Obayashi et al.(1986)) for time integration. Central difference was used for viscous terms and k-ω two-equation turbulence model (Wilcox, D.C.(1988)) was also employed. 30,90 and 150deg injection angle cases have been calcurated. In the experiments, stream line on the wall surface was revealed by the oil flow picture and the flow field was visualized by the Shlieren photograph. The wall static pressure profile along the flow was obtained by the wall pressure measurements. Also volume fraction distribution measurements were conducted. Each one of those showed good agreement with computational ones. From the thorough investigation of the flow field by experiments and computations, various characteristics of the supersonic mixing with circular nozzle have been revealed.
- Abstract document
- Manuscript document
IAC-06-C4.5.06.pdf (🔒 authorized access only).
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