Amadeus Trübsbach  , Andreas Schwab , Christian Kromer , Markus Selzer

DOI Number XXX-YYY-ZZZ

Conference Number HiSST 2018_167084

Transpiration cooling is a promising active cooling technique for high-temperature aerospace applications such as rocket combustion chambers or reentry vehicles. It combines a cooling effect inside the material and a cooling film that protects the structure from high heat fluxes. Along the cooled wall, heat flux and pressure vary and consequently, the cooling mass flow needs to be adjusted regarding these changing conditions. In this paper a numerical approach is developed where the cooling mass flow through four porous carbon reinforced carbon (C/C) samples is coupled with a turbulent hot gas channel flow. The results show that the blowing ratio is the most influential parameter for the transpiration cooling system. An increase of the blowing ratio results in a significant reduction of the wall temperature. Besides, the thermal conductivity of the C/C-samples and the Mach number of the hot gas channel flow affect the hot side wall temperature. Furthermore, one of the porous C/C samples is replaced by a copper sample for a comparison with the regenerative cooling method. The result shows that transpiration cooling is more effective than regenerative cooling even for relatively low blowing ratios.

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In Categories: HiSST 2018, Thermal & Environmental Control Systems, Thermal and Energy Management Systems, Thermal Protection Systems, Thermal Protection Systems
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