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
Volume 1, No. 1, September 2014, Pages 28-33

S. Salimi1,*, A.Fazeli1, E. Kianpour2
1Faculty of Mechanical Engineering, Universiti Teknologi Malaysia, 81310 Skudai, Johor, Malaysia
2Faculty of engineering, Islamic Azad University of Najaf Abad, Najaf abad, Esfahan, Iran
*Corresponding author: shahin.salimi84@gmail.com

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.

CITE THIS ARTICLE

MLA
Salimi, S., et al. “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 (2014): 28-33.

APA
Salimi, S., Fazeli, A., & Kianpour, E. (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.

Chicago
Salimi, S., Fazeli, A., and Kianpour, E. “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, no. 1 (2014): 28-33.

Harvard
Salimi, S., Fazeli, A. and Kianpour, E., 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), pp.28-33.

Vancouver
Salimi, S, Fazeli, A, Kianpour, E. 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. 2014;1(1):28-33.

REFERENCES

[1] S.S. Vakil, K.A. Thole, Flow and thermal field measurements in a combustor simulator relevant to a gas turbine aeroengine, Journal of Enineering for Gas Turbines and Power 127 (2005) 257-267.
[2] E. Kianpour, N.A.C. Sidik, A.S.M. Bozorg, Dynamic analysis of flow field at the end of combustor simulator, Jurnal Teknologi 58 (2012) 5.
[3] A. Azzi, B.A. Jubran, Influence of leading-edge lateral injection angles on the film cooling effectiveness of a gas turbine blade, Journal of Heat Mass Transfer 40 (2004) 501–508.
[4] A. Rozati, K. Danesh Tafti, Effect of coolant–mainstream blowing ratio on leading edge film cooling flow and heat transfer-LES investigation, International Journal of Heat and Fluid Flow 29 (2008) 857–873.
[5] S. Stitzel, K.A. Thole, Flow field computations of combustor-turbine relevant to a gas turbine engine, Journal of Turbomachinery 126 (2004) 122-129.