Experimental Study on Measurement and Calculation of Heat Flux in Supersonic Combustor of Scramjet  

作　　者：ZHANG Cong YAO Zhanli QIN Jiang BAO Wen 

机构地区：[1]Harbin Institute of Technology

出　　处：《Journal of Thermal Science》2015年第3期254-259,共6页热科学学报（英文版）

摘　　要：An experimental measurement and calculation method which consist of thermal response model, convergence criteria and control algorithms, is proposed in this paper for the determination of heat flux in a scramjet combus- tot. Numerical simulations are done to evaluate the effectiveness of the proposed method, and experiments are made in the direct-connect hydrocarbon fueled scramjet combustor of Mach-6 flight for different equivalence ra- tios. The distribution of heat flux along the axial and circumferential directions can be obtained using the pro- posed method. The distribution of heat flux is uneven which is caused by the aerodynamic heating, combustion heat release and changes of section area, and the peak heat flux can be more than 2MW/m^2 during the experi- ments. Heat flux increases with the increase in equivalence ratio for the same Mach number. And axial distribu- tion of heat flux is uniform for different equivalence ratios. In addition, the combustion heat release area of the combustion chamber can therefore be concluded which is useful for guiding the structural design of the thermal protection system.

关 键 词：SCRAMJET Heat flux Thermal response model Thermal protection 

分 类 号：V235.21[航空宇航科学与技术—航空宇航推进理论与工程] O6-3[理学—化学]