Hybrid film cooling geometry analysis with OpenFOAM

Abstract

This paper presents a numerical investigation of the film cooling performance of a new hybrid film cooling geometry. The new hybrid concept was created to enhance the film cooling performance of gas turbine blade. The scheme consists of a converging slot hole or console with a cylindrical hole featuring a branching cylindrical hole. An analysis of the cooling performance of the advanced hybrid film cooling model was carried out across blowing ratios of (B = 0.37, 0.60, and 0.87) at a density ratio of DR=1. A numerical simulation was performed using open-source CFD software OpenFOAM. The validity of the current numerical model was evaluated for the console case, revealing excellent agreement between the numerical results and the experimental data. In this study, two distinct forms, F1 and F2, are represented with the same position variation; the SST K − \({\omega }\) turbulence model was selected as the turbulence model for the analysis. The results show that the hybrid concepts, including auxiliary jets, enhance film cooling efficiency by effectively dispersing coolant across downstream surfaces and reducing the impact of the counter-rotating vortex pair by improving mixing with the mainstream flow. Furthermore, the supplementary jet ensures the primary coolant jet moves beside the test surface, which results in higher effectiveness, especially at high blowing ratios.