Discussion of the design method for porosity driven by pressure differences during transpiration cooling

Optimizing active cooling strategies has become an essential topic in thermal protection due to the increasing structural thermal protection requirements for hypersonic aircraft with higher Mach numbers. This paper proposes a design method for the transpiration cooling structure, taking the isothermal wall as the design target and the pressure difference between the inside and outside of the transpiration matrix and the porosity of the porous medium as the design parameters. The method can achieve the reverse design of the porosity of the transpiration matrix and homogenize the temperature gradient of the surface of porous media. The numerical analysis shows that the porosity design method for pressure difference-controlled transpiration cooling proposed in this research can be used to optimize the porosity design of porous media and achieve maximum utilization of the coolant flow.