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Influence of recessing nozzle extent on a process of heat exchange in the combustion chamber of a solid fuel rocket engine

This paper considers issues of numerical simulation of the spatial gas dynamics and heat transfer in the pre-nozzle volume of the combustion chamber of a large solid-fuel rocket engine. It is investigated the effect of the degree of recessing of the nozzle specifying the ratio of flow rates of a gas through the channel and the supra-nozzle gap of the processes in the pre-nozzle volume. An analysis of a topology of the flow structure and thermophysical processes near inlet surface of the recessing nozzle was performed. The distribution of the heat transfer coefficient equation on the inlet surface of the recessed nozzle and a criterial for the estimation of heat transfer depending on topological features on the surface of the recessed nozzle are obtained.