Comparison on the effect of regenerative and film cooling in the heat transfer characteristics of semi cryogenic thrust chamber having rectangular cooling channels by using cfd and numerical analysis

In this paper, Computational Fluid Dynamics and Numerical Analysis is used to investigate the rocket thrust chamber cooling characteristics. The scope of the investigation involves the study of effect of regenerative and film cooling on the heat transfer characteristics of coolant channel. Steady state pressure based analysis is carried out in this work. The temperature distributions of coolant along the rectangular cooling channel, temperature distributions of copper and stainless steel walls are the main focus of the study. In this study the, the coolant (kerosene), which is the fuel) enters at the aft end of the thrust chamber and passes through the rectangular cooling channels before it is fed to the injectors.