Author : P.Venkata Vara Prasad, Surisetty Naga Kishore and T.Venkateswara Rao

Film cooling is the method used to protect the surface exposed to high temperature flows such as those that exist in gas turbines. It involves the injection of secondary fluid that covers the surface to be protected. In this study, film cooling effectiveness was investigated numerically on a cylindrical hole with a stream wise angle of 300,600 and 900 in a flat plate test facility with a zero pressure gradient. The short but engine representative hole length (L/D=4) is constant for all thee geometries. The blowing ratio ranges from 0.33 to 1.67. The current results are compared with the experimental results obtained by Yuen and Martinez-Botas and the effects of variations in injection angle are described.

Keywords: Blowing ratio (M), Injection Angle, Velocity, Temperature, Fluent, Heat transfer coefficient

Article published in International Journal of Current  Engineering  and Technology, Vol.4,No.2 (April- 2014)