• Dhirajkumar Mahajan
• Kalpesh Lambe
• Yash Lahane
• Abhijeet Nandan
• M. J. Naidu

Gas turbine has become the most proficient device for aircraft propulsion and in land-based power generation or industrial applications. The importance of effective cooling of the vane has extensively increased along with the demand of increasing the power output and thermal efficiency. The technique used for this effective cooling is known as Film cooling. In this paper film cooling performances for Cylindrical hole configuration and Branched hole configuration are enlisted by varying their blowing ratios respectively. Static analysis on three vanes from stator ring has been considered for results. Meshing of the model is done using automatic platforms of ANSYS software. Also results are obtained on the basis of average temperature (vane wall temperature) at different blowing ratios of both hole configurations (cylindrical and branched). The focus of the analysis in this study was about the film coverage over the pressure side of vane. The study shows significant improvement of cooling effectiveness using branched hole configuration than cylindrical hole configuration.

"Study of Film Cooling Performance for a Gas Turbine Test Vane by Varying Blowing Ratio and Hole Configuration", International Journal of Emerging Technologies and Innovative Research (www.jetir.org), ISSN:2349-5162, Vol.6, Issue 4, page no.186-192, April-2019, Available :http://www.jetir.org/papers/JETIRBB06040.pdf

"Study of Film Cooling Performance for a Gas Turbine Test Vane by Varying Blowing Ratio and Hole Configuration", International Journal of Emerging Technologies and Innovative Research (www.jetir.org | UGC and issn Approved), ISSN:2349-5162, Vol.6, Issue 4, page no. pp186-192, April-2019, Available at : http://www.jetir.org/papers/JETIRBB06040.pdf