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 profiles of heatflux onto the surfaces of high-pressure turbine-cooled nozzle vanes and cooled rotor blade group. The following results are obtained from the parametric studies : (1)radiative heat flux onto the nozzle vanes is over l0% of the convective flux for the nozzle-inlet temperature of 1700 K, (2)the radiative heat flux onto the rotor blade group is about half of that onto the leading edge of the nozzle vanes and (3)the radiative heat flux onto the nozzle vanes is affected by the absorption coefficient of the flame zone rather than by the nozzle-inlet temperature.
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