A rapid one-dimensional wall temperature calculation method for an integrated afterburner central cone film cooling structure

The cooling of thermal-end components is a critical research focus within the field of aero-engine technology. This research performs a numerical analysis of the film-cooling structure of the central cone under real operating conditions of aircraft engines. Three critical structural parameters influencing the wall temperature profile are selected. A genetic algorithm is introduced to solve the proposed adiabatic film-cooling efficiency correlation, and the convective heat transfer coefficients on both sides of the conical surface are investigated, taking into account the segmented and gradually tapered features of the central cone. A rapid one-dimensional wall temperature calculation method based on numerical computation, film-cooling theory, and genetic algorithm is proposed. The analysis reveals that when the blowing ratio is 0.8, the total average relative error between the one-dimensional wall temperature calculation method and the traditional CFD calculation for the overall film-cooling efficiency along the path is 6.75%. As the blowing ratio increases, the accuracy of the one-dimensional wall temperature calculation method improves, with an overall average relative error of only 4.27% at a blowing ratio of 2.0. Within the study range, the overall average error of the one-dimensional wall temperature calculation method remains below 5.4%. Additionally, the stochastic models are introduced to validate the one-dimensional wall temperature calculation method, confirming its applicability and accuracy. This method can achieve rapid calculations of the one-dimensional wall temperature for the central cone film-cooling structure under different structural parameters a range of and blowing ratios. It provides an approach and framework for quickly calculating wall temperatures in complex models, which is valuable for engineering applications.