Abstract
Combined radiative and convective heat transfer is analyzed numerically in the combustion chamber of aeroengines by using the Monte Carlo method to obtain the heat-flux profiles onto the surface of turbine nozzle vanes. The combustion chamber and the nozzle-vane cascade are supposed to be three-dimensional. The following results are obtained from the analyses: (1) liner temperature has a strong effect on the radiative heat flux onto the nozzle vanes, which is shown only by using three -dimensional analysis; (2) Radiative heat flux onto the nozzle vanes is strongly affected by the absorption coefficient of the flame zone.
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