Radiant heat transfer to an enclosure from two-phase flows.

Abstract

Radiant heat transfer from hot solid combustion products to the walls of a combustion chamber has been investigated analytically. For the typical rocket engine configuration considered, the radiation component of heat transfer from the combustion of aluminum in an oxygen containing atmosphere was of the same magnitude as the convective component. The analysis was accomplished using illuminating engineering practices modified to account for absorption and emission of radiation by the combustion products. Numerical techniques were used in a parametric investigation of the system. It was found that the radiant heat flux to the wall is a function of the location on the wall, the particle size, the chamber pressure, the wall reflectivity, and the particle mass fraction. The radiant heat flux was found to be independent of the temperature of the wall in the range of wall temperatures considered.