PREDICTION OF ADIABATIC FILM COOLING EFFECTIVENESS OVER FLAT PLATE WITH CYLINDRICAL AND SHAPED FILM HOLES

Dhulesh Mirje, Batchu Suresh, HR Purushothama

Abstract: Increasing the creep life of gas turbine blades can be achieved by cooling the blades effectively. Film cooling is an effective method of cooling the blade surface. To improve the cooling effectiveness, recent attention has been given to contour the film hole shape. Film cooling holes with diffuser-shaped and expanded exits will improve the film-cooling performance on a gas turbine blade. The present study aims at estimating the adiabatic film cooling effectiveness downstream of cylindrical and laid back fan shaped holes on a flat plate using Fluent CFD software. Analysis is carried out to identify the suitable turbulence model for predicting the film cooling effectiveness on a flat plate. The effect of blowing ratio and turbulence intensity on film cooling effectiveness is brought out in this study. The advantage of adopting laidback fan shaped film hole over cylindrical film hole is highlighted

Keywords: Film Cooling Effectiveness, Blowing Ratio, Cylindrical Hole Model (CHM), Laidback Fan Shaped Hole Model (LBFSHM)

DOI: https://doi.org/10.15623/ijret.2016.0525012