The Influence of Geometric Parameters on the Cooling Performance of a Turbine Rotor

With the continuous pursuit of improved aero-engine performance in recent years, turbine inlet temperatures have steadily increased, placing stringent demands on the thermal strength of turbine blades. Owing to material limitations, a variety of innovative cooling structures have been proposed and implemented. This study systematically investigates the influence of geometric design parameters—including film-cooling holes, impingement holes, rib turbulators, and pin fins—on cooling performance. The most influential parameters were analyzed in greater detail. Optimization applied to an actual engineering turbine blade indicates that the diameter of film-cooling holes and the expansion angle of fan-shaped holes exert the most significant influence on blade temperature. The best cooling performance was achieved by increasing the hole diameter by 0.05 mm and the expansion angle by 6°. These findings provide valuable guidance for subsequent geometric optimization and offer practical insights into addressing turbine blade cooling challenges in engineering applications.