Numerical Study on Coupled Heat Transfer Between Cooling Channel and Combustor of Scramjet

In order to further analyse the coupled heat transfer process of the regenerative cooling channel and the combustion chamber, and to explore the characteristics of coupled heat transfer in active cooling under multiple factors, a numerical simulation study of supersonic combustion and flow cracking coupled heat transfer processes was performed. The effects of cracking reaction, cooling mass flow and equivalent ratio on coupled heat transfer were analysed. The results show that the disturbance caused by fuel injection and combustion will destroy the wave system and transmit to the isolation section, and the combustion intensity becomes more intense as the combustion equivalent ratio increases. Under the same conditions, the heat transfer generated by cracking cannot be ignored when the cooling mass flow rate is small, and the increase of the cooling flow rate will shift the cracking position backward and the cracking degree will be weakened. When the cooling flow rate is 4g/s, the n-decane is completely cracked, and the cracking rate is less than 10% when it increases to 8g/s. Equivalent ratio has no significant effect on coupled heat transfer, when the equivalence ratio increases from 0.67 to 0.84, the cooling channel outlet temperature increases by about 5K, and the inner wall temperature in the combustion chamber increases by only 30K. © 2022, Editorial Department of Journal of Propulsion Technology. All right reserved.