The customer approached MSI during the design phase of their project for assistance with understanding and improving the heat transfer in the full assembly for their liquid rocket engine.
The main assembly consisted of 60 solid parts comprising all major components of the liquid cooled rocket engine nozzle. The model resolves a fully coupled conjugate heat transfer analysis with the flow of the cryogenic fuel through the channels acting as cooling for the nozzle assembly until it reaches the injector into the combustion chamber. The hot combustion gas flow through the engine at maximum thrust was modeled with all modes of heat transfer considered. The analysis was carried out in Siemens Simcenter STAR-CCM+ using advanced meshing techniques such as the surface wrapper to extract the cooling channel flow volume throughout the assembly.
If you'd like MSI to help you solve design problems with your rocket engine using our advanced analysis tools and techniques, while relying on our decades of experience, Contact Us.