Simulation of Film Cooling in the Leading Edge Region of a Turbine Blade Using ANSYS CFX

M. R. Pairan; N. Asmuin; H. Salleh

Authors

M. R. Pairan Centre for Energy and Environmental Study (CEIES), Faculty of Mechanical and Manufacturing Engineering, Universiti Tun Hussein Onn Malaysia (UTHM), Locked Bag 101, Parit Raja, 86400 Batu Pahat, Johor Darul Ta’zim, Malaysia
N. Asmuin Centre for Energy and Environmental Study (CEIES), Faculty of Mechanical and Manufacturing Engineering, Universiti Tun Hussein Onn Malaysia (UTHM), Locked Bag 101, Parit Raja, 86400 Batu Pahat, Johor Darul Ta’zim
H. Salleh Centre for Energy and Environmental Study (CEIES), Faculty of Mechanical and Manufacturing Engineering, Universiti Tun Hussein Onn Malaysia (UTHM), Locked Bag 101, Parit Raja, 86400 Batu Pahat, Johor Darul Ta’zim

Keywords:

Trench effect, Film cooling, turbine blade

Abstract

Film cooling is one from the many of cooling techniques applied to turbine blade. Gas turbine uses film cooling technique to protect turbine blade from direct exposure to hot gas to avoid wear and defects of the blade. The focus of this investigation is to investigate the effect of embedding three different depths of trench at coolant holes geometry. Comparisons are made at three different blowing ratios, which are 1.0, 1.25 and 1.5. Three configurations of leading edge with different depths, which are Case A (0.0125D), Case B (0.0350D) and Case C (0.0713D), were compared to leading edge without trench. The result shows that as blowing ratio increased from 1.0 to 1.2, the film cooling effectiveness increased for leading edge without trench and also for all cases. However, when the blowing ratio increased to 1.5, the film cooling effectiveness decreased for all cases. Overall, Case B with blowing ratio of 1.25 has the best film cooling effectiveness with a significant improvement compared to leading edge without trench and with trench for Case A and Case C.