Numerical study on the cooling characteristic of a novel laminated cooling configuration with chained beam turbulator in an afterburner heat shield

The next-generation aircraft engine requires the development of high-efficiency laminate cooling configurations to protect afterburners. This paper proposes a novel laminated cooling configuration featuring a chained beam turbulator with annular holes. The film cooling effectiveness and the overall cooling effectiveness of the chained beam turbulator are calculated and compared with existing configurations. The effect of different parameters and temperature uniformity on the film cooling effectiveness of the chained beam turbulator is systematically researched. The results demonstrate that the novel laminated cooling configuration exhibits a higher cooling advantage. Compared to the cylindrical spoiler laminate, the surface-averaged film cooling effectiveness of the chained beam turbulator has increased by 7.0 %, while that of the existing cellular partition laminate increased by 7.1 %. The overall cooling effectiveness of the chained beam turbulator is 8.7 % higher than that of the cylindrical spoiler laminate, demonstrating the highest comprehensive cooling performance compared to other configurations. At a high momentum ratio of 0.16 (representing high-power engine operation), the uneven factor of temperature distribution of the new type laminate decreases by 2.1 %, whereas that of the cellular partition laminate reduces by 1.4 %. The average relative standard deviation of the chained beam turbulator is the lowest, which indicates that it has more superior temperature uniformity in three type laminates. Additionally, increases in the momentum ratio, distance between holes, and the end diameter of spoiler column all contribute to enhancing the heat insulating performance of the heat shield composed of the new type laminate.