CFD Analysis of Gas Turbine Blade Cooling with Staggered Holes

Abstract

The role of turbine inlet temperature plays a pivotal role in determining overall turbine performance. As the temperature at the turbine inlet increases, it leads to an enhancement in the turbine's average efficiency. Gas turbines operate under extremely elevated temperatures, reaching levels of 1200°C to 1500°C. This extreme heat poses the risk of turbine blade melting and potential failure. Consequently, the need arises for a sophisticated cooling mechanism for the turbine blades. Optimally increasing the inlet temperature of the turbine blades can certainly elevate the turbine's overall efficiency. However, it's important to recognize that this increase in temperature directly impacts the durability of the turbine blades. To address this challenge, various innovative cooling technologies have been devised, including the implementation of distinct blade cooling hole configurations. These methodologies aim to ameliorate blade temperatures and consequently enhance turbine performance.Turbine blades are engineered using superalloys, renowned for their ability to withstand high thermal stress. Advanced software tools are harnessed to assess their performance under extreme temperatures. Computational Fluid Dynamics (CFD) software is commonly employed for analyzing turbine blades. A prevailing approach for blade temperature reduction entails employing diverse cooling systems, often utilizing air as a cooling agent. This directed airflow over the blades significantly curtails their temperatures. In this context, blade design featuring staggered hole layouts is applied, and both STATIC and CFD simulations, grounded in defined boundary conditions, are executed, yielding commensurate outcomes. Comparative analysis demonstrates that staggered hole configurations provide superior temperature distribution uniformity across blade surfaces, effectively reducing peak temperatures in contrast to blade configurations devoid of cooling holes..