Numerical Investigation on the Thermal Behaviour of a LOx/LCH4 Demonstrator Cooling System

Reliability of liquid rocket engines is strictly connected with the successful operation cooling jackets, able to sustain impressive operative conditions in terms huge thermal and mechanical loads, generated thrust chambers. Cryogenic fuels, like methane or hydrogen, are often used as coolants they may behave transcritical fluids flowing jackets: after injection a state, phase pseudo-change occurs along chamber because heat released by combustion gases exiting vapour. Thus, development such subsystems, important issues focused on numerical methodologies adopted simulate fluid behaviour inside design procedures well manufacturing technological process topics. The present paper includes analyses regarding jacket belonging oxygen/liquid demonstrator, realized framework HYPROB (HYdrocarbon PROpulsion test Bench) program. Numerical results considering nominal operating jackets methane-fuelled mode water-fed one included case application electrodeposition for manufacturing. A comparison similar jacket, through conventional brazing process, addressed underline benefits technology.