Numerical study on coupled heat transfer of thrust chamber with regenerative cooling

Numerical study on coupled heat transfer of the hot gas, chamber wall and coolant was performed. The two-dimensional Navier-Stokes equations were adopted to describe the hot gas flow, while a reduced one-dimensional model was employed for the coolant flow and heat transfer, and one dimensional heat transfer model was used to calculate the coupling heat transfer through the wall. The N-S equations were discretized by the finite volume method in body-fitted coordinates and the coupling of pressure and velocity was implemented with the compressible form of SIMPLE algorithm. The compressible form of the standard k-ε turbulence model was adopted to simulate the hot gas flow. Radiation of gas stream was also considered and simulated with the FLUX model. Results show that the method adopted in this paper can simulate two dimensional gas flow field well. Moreover, the method can calculate the heat flux through the wall, wall temperature and the temperature increase of coolant quickly. The numerical results are expected to be helpful for the design, especially for cooling scheme design of rocket engines.