With the continuous increase of turbine inlet temperature in modern aero-engines, radiative heat transfer plays an increasingly important role in the thermal loading of hot-end components such as turbine vanes. However, the radiation field exiting the combustor is typically highly non-uniform in space, whereas most current engineering analyses still approximate the vane inlet radiative boundary using a uniform temperature assumption due to the lack of practical acquisition methods. The objective of this study is to develop a physically based approach for resolving the non-uniform interfacial radiation field and to evaluate its influence on vane heat transfer prediction. A Monte Carlo–based interfacial radiation model is established and coupled with CFD flow–thermal solutions to directly compute the spatial distribution of radiative heat flux at the turbine vane inlet without relying on empirical reconstruction or analytical simplifications. The results show that the proposed method can capture localized radiative hotspots and strong directional effects that are completely smoothed out under the conventional uniform boundary treatment. Quantitative comparisons indicate that the approach achieves engineering-level accuracy with a maximum relative deviation of about 10% while maintaining reasonable computational cost. The model provides a more realistic non-uniform radiation boundary condition for conjugate heat transfer simulations of turbine vanes and can be applied to improve thermal load assessment and cooling structure design in high-temperature turbine components.
Xian-long et al. (Fri,) studied this question.