Mathematical Modeling of Transpiration Cooling in Cylindrical Domain

ABSTRACT: This research is conducted to develop numerical schemes modeling one-dimensional steady-state non-equilibrium transpiration cooling in Si-C porous materials. The transpiration cooling process is assumed to be used to protect the thrust chamber of a liquid rocket engine by blocking the enormous heat transfer towards its walls. The flow modeling within the porous media is performed through applying numerical schemes to the compressible flow of the coolant in cylindrical coordinates. The results of this modeling are validated by the experimental results obtained from a study in the University of Stuttgart. Also, a numerical method is developed to solve the equations of hot gases which are flowing through the nozzle in order to provide the hot boundary condition of the porous segment. The flow equations within the porous medium are solved separately, to analyze the important parameters affecting the transpiration cooling process. The effect of coolant mass flow rate, hot face boundary condition type, gas type, and sample length are observed as well. Moreover, the internal convective heat transfer between solid structure and the coolant flow is studied. The porous solver code is then coupled with the gas solver code so that the cooling process can be studied in a more realistic area. The results show the variation of gas properties through the nozzle the effect of transpiration cooling on them. Also, a sample method of controlling the nozzle wall temperature is demonstrated. Keywords: Transpiration cooling, cylindrical, porous media, thrust chamber. …………………………………………………………………………………………………………………………