Investigation of RANS turbulence models for cryogenic rocket combustion chambers

Abstract

The accurate numerical simulation of high-pressure rocket combustion chambers is a key element for the design of future space transportation vehicles. The main challenges include the consistent approximation of thermodynamic effec ts within a broad temperature range. Another open question is which are the additional physical processes that have to be modeled for Reynolds Averaged Navier-Stokes (RANS) based approaches. To this open question we contribute with a detailed study of RANS turbulence models and their influence onto the flame shape for a simplified academic test case and a subscale rocket combustion chamber at supercritical pressure.