Aviation Kerosene Supersonic Combustion in Dual-Mode Scramjet
With the software numerical analysis of the aviation kerosene spray supersonic combustion was carried out in the dual-mode scramjet combustor. At Mach number 5 flight conditions, the numerical results were gotten with the discrete droplet model, the equilibrium reaction kinetics model, the κ-ω turbulence model and the probability density function turbulence combustion model. The wall static pressure distributions derived with the CFD agreed with the experimental results, and the numerical total pressure loss coefficient 0.703, is lower than the experimental value 0.707. The numerical results show the strut and cavities improve the mixture and combustion, and the combustion efficiency of the combustor exit is 0.62, which is less than the experimental combustion efficiency 0.696. This dual- mode combustion system operates in ramjet mode.
scramjet engine dual-mode subsonic combustion supersonic combustion
LIU Ouzi ZOU Jianfeng ZHENG Yao CAI Yuanhu HU Yuli
School of Aeronautics and Astronautics, Zhejiang University, Hangzhou 310027, Zhejiang, China School of Power and Energy, Northwestern Polytechnical University, Xian 710072, Shaanxi, China School of Marine, Northwestern Polytechnical University, Xian 710072, Shaanxi, China
国际会议
西安
英文
487-491
2007-10-23（万方平台首次上网日期，不代表论文的发表时间）