Numerical Simulation of Transpiration Cooling for Sintered Metal Porous Strut of the Scramjet Combustion Chamber

The strut structure in a scramjet combustion chamber is used to inject fuel into the main stream. The environment surrounding the strut in the scramjet chamber is supersonic flow at very high temperatures. Thus, the leading edge of the strut is easily ablated due to aerodynamic heating. This study analyzes the effect of a transpiration cooling scheme using a sintered metal porous media surface to protect the strut from ablation. Numerical simulations are used to study the transpiration cooling for different strut structures and coolant conditions. The influences of these parameters on the transpiration cooling of the strut are analyzed for a main stream Mach number of 2.5 and a total temperature of 1700 K. The surface temperature can be reduced to a safe temperature with a coolant mass flow rate through the porous media of 27.5 kg/ m²-s. The coolant flow near the leading edge is most important, with less flow needed downstream.