Numerical and Experimental Characterizations of the SiFRP Ablator for the Combustion Chamber Heat Shields of Liquid Rocket Engines

抄録

To design the LOX/LNG ablative combustor, it is indispensable to build up the mathematical ablation model. In this paper, the mathematical model of SiFRP has been developed, which successfully predicts the penetration depth of both charred and decomposed zones and also the temperature profiles in the various kinds of experimental results which have been conducted to verify the model. Using this model, the peripheral-zone temperature profiles in the combustor, that is to say, combustor wall heat flux profiles, are estimated to reproduce the char penetration depth which has encountered in the ground firing tests, and the model has been successfully applied to design a LOX/LNG combustor.