Influence of Injection Angle on the Mixing Efficiency in Supersonic Flow with A Transverse Sonic Jet
In order to develop an injection method for effective air-fuel mixing and little total pressure loss in scramjet combustion, the influence of injection angle in supersonic flow with a sonic jet is numerically studied. At first, 2-D numerical simulation of a supersonic flowfield with a vertical sonic jet of helium is performed using AUSMDV scheme and k-ω SST turbulence model with Wilcox compressibility correction, and good agreements between numerical results and experimental data validate the reliability of the numerical method. Whereafter, flowfields with a sonic jet of hydrogen are simulated in five injection angles-30°, 60°, 90°, 120° and 150°. Two parameters, averaged total pressure and mixing rate, are defined to evaluate the performance of different injection angles. It is found that injection angle of 30° and 60° induce little loss of total pressure but much smaller air-fuel mixing rates. Comparing with injection angle of 90° and 150°, the injection angle of 120° induces a much larger air-fuel mixing rate, while only a bit larger loss of total pressure. Therefore, it is concluded that injection angle of 120° is the optimum choice for fuel injection.
scramjet engine supersonic combustion turbulent mixing numerical simulation mixing efficiency
Gao Zhenxun Lee Chunhian
School of Aeronautical Science and Engineering,Beihang University, Beijing 100191,China School of Aeronautical Science and Engineering,Beihang University,Beijing 100191, China
国际会议
2010 Asia-Pacific International Symposium on Aerospace Technology(2010 亚太航空航天技术研讨会 APISAT 2010)
西安
英文
296-300
2010-09-01（万方平台首次上网日期，不代表论文的发表时间）