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.
Sign-in/Register to access full text options 
Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Schedule a callMore From: International Journal of Research in Engineering and Technology
Disclaimer: All third-party content on this website/platform is and will remain the property of their respective owners and is provided on "as is" basis without any warranties, express or implied. Use of third-party content does not indicate any affiliation, sponsorship with or endorsement by them. Any references to third-party content is to identify the corresponding services and shall be considered fair use under The CopyrightLaw.
