NUMERICAL STUDY OF TURBINE BLADE FILM COOLING TECHNOLOGY

Abstract

In order to increase thermal efficiency of a gas turbine, higher turbine inlet temperature (TIT) is needed. However, higher TIT increases thermal loading to its hot-section components and reducing their life. Therefore, one of the very complicated cooling technology such as film cooling and internal cooling is required especially for HP turbine blades. In film cooling, relatively cool air is injected onto the turbine blade surface to form a protective layer between the surface and hot mainstream gas. The highest thermal load usually occurs at the leading edge of the airfoil, and failure is probably to happen in this region. Film cooling is typically applied to the leading edge through an array of hole rows called showerhead. In this work firstly prediction of blowing ratio is done on a flat plate for film cooling then to get the idea of flow physics analysis is extended over the actual turbine blade using ANSYS Workbench.