Numerical Simulation Of High-speed Rotating Inner Flow Field Of Solid Rocket Motors

To calculate the united flow filed in a rocket motor in the condition of different rotate speed,the RNG k-ε turbulent model was adopted to calculate the3D united flow filed in a rocket motor with inner-burning tube solid propellant. The user defined function (UDF) was adopted to offer the condition of mass flow inlet. The calculational results show that the united flow field in combustion chamber and nozzle of high-speed spinning SRM is complex.The tangential velocity distribution of the flow closed by front blockage in the chamber is similar to Rankine combination swirl, and in nozzle it is similar to the forced vortex. The tangential velocity reached to two extremums in combustion chamber and the throat of nozzle. The tangential velocity changed rapidly, and reached to two extremums., the negative value of axial velocity was appeared near axis.Secondly the two-dimensional unsteady nozzle wall of fluid-solid heat coupling model is established to calculatethe heated state, heat flux and other parameters of nozzle. Calculation results show that as a continuation of the engine work time, total heat transfer wall heat flux density gradually reduced in the nozzle, it reach the most in the front of engine nozzle throat, and the heat transfer is the strongest.High-speed rotating impact on engine wall heat transfer is the total trend with the increase of rotating overload. Engine gas tangential velocity increased significantly, and the number of gas molecules per unit time through the wall increased, it make the convective heat transfer coefficient increases, led to increasing convective heat transfer. Both in the region of the combustion chamber and nozzle, the gas vortex is produced. In the vortex of the gas kinetic energy dissipation into heat energy, can make the wall heat transfer enhanced.It leads to a seriously affect to the structural strength and thermal protection of the former head of combustion chamber and nozzle thoart.