Article Information
Computational Study of Film Cooling Effectiveness for a Comparison of Cylindrical, Square and Triangular Holes of Equal Cross-Sectional Area

Keywords: CFD, Film Cooling Effectiveness, Heat Transfer, Fluid Flow, Turbine Blade Cooling.

Mehran University Research Journal of Engineering & Technology

Volume 29 ,  Issue 4

Fayyaz  Hassan  Asghar,Muhammad  Javed  Hyder


Film cooling effectiveness is studied computationally for a comparison of circular, square and two types of equilateral triangular holes with an inclination of 30o with streamwise direction. Reynolds number based on the freestream velocity and hole diameter is 10364. Length to diameter ratio of circular hole is 4, which is representative of gas turbine engines. The coolant to mainstream density ratio is 0.92. Main flow is supplied at the temperature of 293.15K and coolant is supplied at 318.15K. Centerline and laterally averaged effectiveness are presented for film cooling measurements. Current computational results for circular hole are compared with experimental results. Computational results are well in agreement with the experimental results even for high blowing ratios. Blowing ratios ranging from 0.33-2.0 have been investigated. It is observed that triangular hole having lateral straight edge on leeward side shows much higher effectiveness values than circular film cooling hole case in the near hole region and almost similar coolant jet height as that in case of circular film cooling. Also it is observed that triangular hole having lateral straight edge on windward side and converging corner on leeward side shows lesser coolant jet height and higher film cooling effectiveness in the region x/D>10, especially at blowing ratios greater than 1.0.