To quickly and accurately obtain temperature distribution in regeneratively-cooled thrust chamber

a method of computing temperature field in thrust chamber was developed.Firstly

one dimensional cooling model of axi-symmetric thrust chamber was formulated and empirical formulas were used.Temperature of gas wall along thrust chamber axis was obtained.Secondly

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.Then using this method

influence of gas wall material

gas wall thickness and flow rate of coolant on regenerative cooling of thrust chamber was investigaed.The results were satisfactory.In terms of computing time and accuracy of results

this method could provide a reference for optimization design and performance estimation.