Conjugate Heat Transfer Analysis for 1.5 Stage High-Pressure Turbine

Abstract

The evaluation of cooling performance in the hot sections of gas turbines plays a critical role in the gas turbine development. Specifically, accurate prediction of cooling performance in the high-pressure turbine, which involves complex interactions between internal cooling and film cooling mechanisms, poses a significant technical challenge. Several methodologies have been devised to predict the cooling performance in the high-pressure turbine, to address this technical challenge. Among these approaches, the conjugate heat transfer analysis method can predict the turbine blade surface temperatures by simulating both solid and fluid domains without any empirical formulations. In this study, a conjugate heat transfer analysis on a 1.5-stage high-pressure turbine within a 1,000 shp class gas turbine has been conducted, with the objective of assessing the cooling performance of both external and internal cooling methods and their impacts on the main flow within the turbine flow path. The overall cooling effectiveness analysis demonstrated that blade