Modelling of a 7-elements gox/gch4 combustion chamber using rans with edc combustion model

This paper summarized the computational work conducted by the the group from Harbin Institute of Technology and Prof. Haidn for the SFB-TRR40 2017 summer program. A 7-element rocket combustion chamber using GOX/GCH4 as propellant has been modelled and simulated to get a more comprehensive knowledge for combustion and heat transfer process. All the computational cases in our investigation used the EDC combustion model for detailed chemistry and two-equations RANS model for turbulence closure. The simulation results show that our model agrees well with experimental data in terms of wall pressure but it overpredicts the heat flux a little in the combustor and underestimate it at the throat. Changing the turbulence model will have great influence on the combustion field and thus the heat transfer conditions. While changing the Prandtl number will change the heat transfer condition without changing the combustion field too much when using RANS model. It has been also found that the reaction mechanism will have great influence on the combustion and heat transfer through having effects on thermophysical properties of the combustion products.