Numerical simulation of hot-gas side heat transfer enhancement in thrust chambers by wall ribs

High performance liquid rocket engines environment is characterized by high temperature and high heat fluxes. Heat transfer accurate prediction is one of the key features for the development of these engines, especially in the case of expander cycle feed system. In the present study, hot-gas side heat transfer enhancement due to ribbed walls in an expander cycle engine thrust chamber is analyzed by means of a Reynolds-Averaged Navier-Stokes (RANS) equations solver. As a validation of the solver, a ribbed wall experimental test case is reproduced to assess the capability of the solver to properly capture thermal boundary layer and heat transfer enhancement. In this test case, heat enhancement is quantified by measuring water coolant temperature increase along the duct. Then a simplified coupling procedure is adopted to compare numerical simulation against experimental data. Finally an expander cycle engine thrust chamber is studied focusing on heat transfer enhancement due to ribbed walls, compared to the smooth wall case. In this study the capability of the solver to be employed as a design tool for wall ribbed thrust chambers is shown. © 2011 by the American Institute of Aeronautics and Astronautics, Inc.