Numerical optimization simulation on heat transfer in cooling channel of H₂/O₂ liquid rocket engine thrust chamber

Turbulent fluid flow and heat transfer in a regenerative-cooling channel of H₂/O₂ liquid rocket engine were numerically investigated by solving three-dimensional elliptical Navier-Stokes equations and the standard k-e turbulent model was adopted. The coolant was hydrogen, whose thermal properties such as thermal conductivity, density, dynamical viscidity, etc were varied with both temperature and pressure. Two optimized calculation schemes were applied so as to find the best design for rocket combustion chamber. The first scheme was that keeping thickness and height of rib constant, changing the cooling channel number so as to change the aspect ratio of cooling channels. The second one was that keeping the channel number and mass flow rate constant, changing the height of channel so as to change the aspect ratio of cooling channels. The simulation result shows that exist an optimal number of cooling channel which optimize the heat transfer effect of rocket combustion chamber. Heat transfer of rocket chamber will be enhanced when height of cooling channel is reduced, while the pressure drop will increase at the same time.