Film Cooling Effectiveness using Cylindrical and Compound Cooling Holes at the End Wall of Combustor Simulator

S. Salimi; A.Fazeli; E. Kianpour

Film Cooling Effectiveness using Cylindrical and Compound Cooling Holes at the End Wall of Combustor Simulator

Authors

S. Salimi Faculty of Mechanical Engineering, Universiti Teknologi Malaysia, 81310 Skudai, Johor, Malaysia
A.Fazeli Faculty of Mechanical Engineering, Universiti Teknologi Malaysia, 81310 Skudai, Johor, Malaysia
E. Kianpour Faculty of engineering, Islamic Azad University of Najaf Abad, Najaf abad, Esfahan, Iran

Keywords:

Compound Hole, Cylindrical Hole, Gas Turbine , Film Cooling Effectiveness

Abstract

A numerical 3-D simulation has been performed to investigate fluid flow and heat transfer characteristics of a film cooling injected through cylindrical and compound angle oriented holes with alignment angle of 30 degree adjacent to the end wall surface for a Pratt and Whitney gas turbine engine by ANSYS FLUENT 14.0. The results indicate that employing compound angle cooling holes injection gives much better protection to the components rather that obtained when simple angle cooling holes were used.

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Published

2014-09-15

How to Cite

S. Salimi, A.Fazeli, & E. Kianpour. (2014). Film Cooling Effectiveness using Cylindrical and Compound Cooling Holes at the End Wall of Combustor Simulator. Journal of Advanced Research in Fluid Mechanics and Thermal Sciences, 1(1), 28–33. Retrieved from http://semarakilmu.com.my/journals/index.php/fluid_mechanics_thermal_sciences/article/view/2518