This study employs numerical simulation and particle swarm optimization with a constriction factor to explore film-cooling effectiveness on a turbine blade featuring a single row of converging slot holes. Operating under a Reynolds number of \(1.74\times {10}^{4}\) , the investigation spans a blowing ratio range of 0.1–2.5 and an injection angle range of 20°–45°. The optimal parameter set determined was (M, α) = (1.3, 37°), showing a 5% improvement in target value over the baseline case. The study also delves into the impact of crucial factors like the blowing ratio and injection angle on heat transfer and aerodynamic performance. A notable observation is an 11.8% increase in film-cooling effectiveness when the blowing ratio is elevated from 0.8 to 2.0. Conversely, a rise in the injection angle from 30° to 45° results in a 4.8% reduction in cooling effectiveness. Additionally, the converging slot hole configuration demonstrates promising attributes, including lateral diffusion of coolant and stronger adherence to the cooling surface, which are conducive to elevating cooling efficiency in turbine blade film-cooling scenarios.
