Method of computing temperature field in regeneratively-cooled thrust chamber

To quickly and accurately obtain temperature distribution in regeneratively-cooled thrust chamber, a method of computing temperature field in thrust chamber was developed. One-dimensional cooling model of axial symmetrical thrust chamber was formulated and empirical formulas were used. Temperature of gas wall along thrust chamber axis was obtained. Two-dimensional conductive model of cooling jacket was set up and numerical simulation was carried out using one-dimensional results. Temperature field in cooling jacket was computed. Using this method, the influences of gas wall material, gas wall thickness and flow rate of coolant on regenerative cooling of thrust chamber were investigated. In terms of computing time and accuracy of results, this method could provide a reference for optimization design and performance estimation.