Transfer of an analytical transpiration cooling model to the cooling analysis of rocket combustion chambers made of ceramic matrix composites

Kurzfassung

Analytical models to describe transpiration cooling are assessed for combustion chamber conditions. The models describe the temperature profile and the pressure loss over the chamber wall. The results of the models are compared to recent tests of a transpiration cooled CMC chamber developed at DLR. While temperature measurements at distinct points cannot be directly compared to the models due to uncertainties in measurement and model, the pressure loss under heat load, as an volume averaged, easily measured parameter is promising. Only when taking the heating of the coolant into account, the pressure loss is comparable to the experiments.