Simulation and Analysis of Convective Heat Transfer and Non-Steady-State
Temperature Distribution in the Wall of the Liquid-Propellant Rocket Engine
One of the options of the cooling of the wall of Liquid Propellant Rocket Engine (LPRE) thrust
chamber and nozzle is “accumulative” cooling, when the heat transferred by the convection from the
combustion chamber is accumulated in the wall and transferred from the wall into the ambient
medium. This technique of the cooling is applicable to the engines which have relatively short
operation time and relatively small thrust. Because of small operation time, the heat transfer through
the wall should be treated as a non-steady state heat transfer.
Compute the non-steady-state temperature distribution in the 6-mm wall as shown in the figure 1,
using explicit method. The engine operation time is 20 seconds and the initial temperature of the
wall is of 310?K.

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