Numerical investigation of oscillating jet film cooling on a flat plate for enhanced thermal management in high-temperature turbine applications

Abstract

Jet film cooling is essential for ensuring the thermal integrity of turbine blades in high-temperature environments. Previous research highlights the need for optimized cooling methods to enhance turbine component performance and longevity. This study examines the use of a fluidic oscillator in the cooling process, addressing the increasing demand for efficient and durable turbine designs. The focus is on evaluating the effectiveness of jet film cooling on high-temperature hydrogen turbine blades and understanding how factors such as cooling air velocities, hot gas compositions, and wet air cooling influence temperature distribution and flow behavior. Utilizing the Eulerian-Lagrangian method, the study presents quantitative findings based on varying cooling inlet velocities. At a cooling inlet velocity of 30 m/s, maximum blade temperatures near the cooling entrance reach 1217 K, while temperatures decrease to 866 K at the outlet. Increasing the inlet velocity to 40 m/s results in a maximum temperature rise to 1222 K, accompanied by increased turbulence. At 50 m/s, temperatures reach their peak at 1250 K due to vortex formation, with vortex areas showing a decrease in temperature to 820 K. Notably, the research indicates that variations in hot gas composition have minimal impact on the cooling process, while wet air cooling effectively lowers temperatures in the mixing area, leading to a more uniform film on the hot surface. Overall, the findings confirm that oscillating jet film cooling serves as an efficient approach for enhancing thermal management in turbine blade applications, paving the way for practical implementations in cooling systems.