Numerical Investigations of Heat Transfer Enhancement in a Thrust Chamber with Hot Gas Side Wall Ribs

Heat transfer enhancement due to hot gas side wall ribs in a thrust chamber is discussed in this paper. Three-dimensional Favre-averaged Navier-Stokes simulations conjugating heat conduction simulation were performed for LOX/GH2 calorimeter chambers considering the finite rate chemical reactions. Atomization process of a LOX jet was modeled as LOX droplets by Discrete Phase Model. The computed results reveal the threedimensional combustion flow mechanism inside the chambers, and predict heat transfer enhancement due to hot gas side wall ribs. The computed heat flux agreed well with the experimental values, although some discrepancies were observed. Maximum heat flux and temperature on the hot gas side ribbed cylinder as well as the throat section were predicted.