Session: 12-05 Conjugate heat transfer investigations

Paper Number: 125672

125672 - Conjugate Heat Transfer Simulation of High-Pressure Cooling Blade Under Rotational Conditions in a Gas Turbine 

In a gas turbine, the first-stage blade is the most significant component, operating in an extreme environment with high temperatures, pressure, and rotational speed. Affected by blade row interaction and wake flow from vanes, the rotor flow field exhibits significant unsteady characteristics. These factors are the main reason causing the crack on the blade. In this study, steady and unsteady conjugate heat transfer simulations were performed to investigate the heat transfer and aerodynamics of the first stage of the W501F cooling blade. Factors such as internal cooling structure, hot streaks, and rotation were considered. The vane was treated as an empty domain with a film cooling hole inlet on the vane surface. The effects of flow characteristics on the blade's heat transfer have been discussed in detail. Specifically, the results reveal that the formation of a vortex around the blade strongly affects the distribution of film cooling on the blade. In some cases, the vortex interacts with the wall surface, causing a reduction in film cooling performance on the blade surface. Consequently, overheating occurs in regions such as the leading edge (LE), rim squealer tip, and platform. The maximum temperature at these critical regions could be reached 1250K, close to the blade's melting temperature. The prediction of the overheating position shows good agreement with a crack position on blade patterns from the power plant company. Furthermore, by understanding the heat transfer characteristics of the blade, we can apply advanced treatments to improve the blade's cooling performance.

Presenting Author: DUY TAN VO Chung Ang University

Presenting Author Biography: Duy-Tan Vo received his Ph.D. from Chung-Ang University in Korea and is currently serving as a Postdoctoral Researcher at Korea University. He specializes in mechanical engineering, with a keen interest in the aerodynamics and heat transfer of gas turbine blades and combustors, as well as expertise in multiphase systems and heat pipe technology.

Authors:

DUY TAN VO Chung Ang University
Yoonhyeong Jeong Korea University
Jaiyoung Ryu School of Mechanical Engineering, Korea University