抄録
In order to design a combustion chamber of rocket engine, it is very important to predict wall temperature and wall heat flux. In this research, numerical simulation for non-adiabatic turbulent combustion flow was conducted to validate combustion model. Conserved scalar model based on flamelet approach was expanded and applied to predict wall heat flux. To calculate turbulence, conserved scalar model was coupled with Large Eddy Simulation. As a result, typical structure of non-premixed flame was predicted by numerical simulation. In addition, thermal boundary layer was also predicted in the region near the non-adiabatic wall. The prediction of wall heat flux showed qualitative agreement with experimental result. It suggests that expanded conserved scalar approach coupled with LES has possibility to predict wall heat flux correctly.
