Design and Experimental Study of Turbine Blade Cooling Structure for an Engine

To address issues such as leading-edge and trailing-edge ablation and cracking of turbine blades during operation in an engine, this study integrates the characteristics of additive manufacturing technology and utilizes a comprehensive simulation and design platform for turbine cooled blades to design three schemes of film cooling structures. Numerical simulations were employed to optimize the blade cooling configurations, resulting in a finalized cooling structure scheme, which was then subjected to experimental evaluation of its cooling performance. An experimental platform for turbine blade cooling effectiveness was established, capable of simulating actual engine operating parameters. Based on this platform, experimental studies were conducted to investigate the effects of key parameters—including pressure ratio(β), temperature ratio(K), and flow ratio(B)—on the cooling effectiveness and the dimensionless temperature distribution on the blade surface. Experimental results show that within the studied operating conditions, the β has a greater impact on the cooling effectiveness of the blade compared to variations in B and K. When the β = 1.2, the cooling effectiveness of the blade surface is 0.130, and when β = 1.6, the effectiveness increases to 0.176, representing a 35.38% improvement. Within the tested range, variations in flow ratio resulted in a 19.12% increase in cooling effectiveness, while changes in temperature ratio led to a 26.62% improvement.