Prediction and Optimization of Turbine Blade Cooling Hole Configuration for Advanced Power Generation Gas Turbine Using Response Surface Methodology

Advanced gas turbines play a crucial role in power generation, operating at turbine inlet temperatures exceeding 1200°C to maximize efficiency and output. While nickel‐based superalloys provide structural integrity, their performance is limited at temperatures above 1250°C, necessitating the use of advanced cooling strategies. This study employs response surface methodology (RSM) to systematically analyze and optimize cooling hole configurations, enhancing thermal management in high‐temperature environments. Existing configurations prove inadequate for next‐generation gas turbines operating at 1400°C with cooling air at 400°C. Through predictive modeling, an optimal configuration is identified, characterized by a blade height of 300 mm, 45 holes with a diameter of 2.0 mm, and a spacing of 4.75 mm, which effectively reduces metal temperatures to below 1250°C. This optimized design significantly improves cooling efficiency and mitigates thermal hotspots, offering a viable solution for high‐temperature turbine applications. The findings from this study offer a practical and scalable solution for thermal management in high‐performance gas turbines, supporting the advancement of turbine technology capable of operating under more demanding thermal conditions.