A Coupled Heat Transfer Calculation Strategy for Composite Cooling Liquid Rocket Engine

To better understand the characteristics of coupled heat transfer in liquid rocket engines, a calculation scheme is proposed this paper. This can simulate processes, including combustion and flow thrust chamber, radiation transfer, conduction wall, coolant cooling channel, gas film chamber wall. The numerical method used each physical area, data between computing module, strategy on coupling interface, process, convergence criterion are all introduced detail. was verified by analyzing water-cooled nozzle. Then, carried out for engine using propellant composed unsymmetrical dimethylhydrazine dinitrogen tetroxide. Two working conditions were analyzed: whether performed or not. results showed that algorithm successfully indicated protective effect wall surface, reasonable. It played guiding role composite method.