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Hole Configuration Effect on Turbine Blade Cooling

Authors: M. Farhadi, A.Hasanpour, H.R. Ashorynejad


In this paper a numerical technique is used to predict the metal temperature of a gas turbine vane. The Rising combustor exit temperatures in gas turbine engines necessitate active cooling for the downstream turbine section to avoid thermal failure. This study is performed the solution of external flow, internal convection, and conduction within the metal vane. Also the trade-off between the cooling performances in four different hole shapes and configurations is performed. At first one of the commonly used cooling hole geometry is investigated; cylindrical holes and then two other configurations are simulated. The average temperature magnitude in mid-plan section of each configuration is obtained and finally the lower temperature value is selected such as best arrangement.

Keywords: forced convection, gas turbine blade, Hole Configuration

Digital Object Identifier (DOI):

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[1] B.Dennis, I.Egorov, G.Dulikravich, S.Yoshimura, Optimisation of a Large Number Coolant Passages Located Close to the Surface of a Turbine Blade, ASMEPaperGT2003-38051, 2003.
[2] Zhihong Gao, DigantaP.Narzary, Je-ChinHan,2008, Film cooling on a gas turbine blade pressure side or suction side with axial shaped holes, International Journal of Heat and Mass Transfer 51,2139-2152
[3] Grzegorz Nowak, Wlodzimierz Wroblewski, 2009, Cooling system optimization of turbine guide vane: 567-572, Applied Thermal Engineering 29
[4] Kercher, D.M., 2003. Film-cooling bibliography: 1940-2002, Private publication.
[5] Kercher, D.M., 2005. Film-cooling bibliography addendum: 1999-2004, Private publication
[6] Bogard, D.G., Thole, K.A., 2006. Gas turbine film cooling. AIAA J. Prop. Pow. 22, 249-270.
[7] Sieverding, C.H., Wilputte, P., 1981. Influence of mach number and endwall cooling on secondary flows in a straight nozzle cascade ASME J. Eng. Gas Turb. Pow. 103, 257-264.
[8] Friedrichs, S., Hodson, H.P., Dawes, W.N., 1995. Distribution of filmcooling effectiveness on a turbine endwall measured using the ammonia and diazo technique. ASME J. Turbo. 118, 613-621.
[9] Kost, F., Nicklas, M., 2001. Film-cooled turbine endwall in a transonic flow field: Part I - Aerodynamic measurements, ASME 2001-GT-0145.
[10] Barigozzi, G., Benzoni, G., Franchini, G., Perdichizzi, A., 2005. Fanshaped hole effects on the aero-thermal performance of a film cooled endwall, ASME GT2005-68544.
[11] Friedrichs, S., Hodson, H.P., Dawes, W.N., 1997. Aerodynamic aspects of endwall film-cooling. ASME J. Turbo. 119, 786-793.
[12] Colban, W., Thole, K.A., Haendler, M., 2006a. A comparison of cylindrical and fan-shaped film-cooling holes on a vane endwall at low and high freestream turbulence levels, ASME GT2006-90021.
[13] Hylton, Milhec, Turner, Nealy and York.(1983) "Analytical and Experimental Evaluation of the Heat Transfer Distribution Over the Surface of Turbine Vanes". NASA CR 168015.
[14] Jatin Gupta, B.Tech ,(2009,"Applicarion Of Conjugate Heat Transfer Methodology For Computation Of Heat Transfer On A Turbine Blade", ), A Thesis Presented in Partial Fulfillment of the Requirements for the Degree Master of Science in the Graduate School of The Ohio State University
[15] Goldsmith, Waterman and Hirschhorn. (1961) "Handbook of Thermophysical Properties of Solid Materials - Volume II: Alloys". The Macmillan Company, New York, USA.
[16] York, D. W., and Leylek, J. H.,( 2003),"Three-Dimensional Conjugate Heat Transfer Simulation of an Internally-Cooled Gas Turbine Vane", ASME Paper No. GT2003-38551,.
[17] Launder and Spalding. (1972) "Lectures in Mathematical Models of Turbulence". Academic Press, London, England.
[18] Shih, Liou, Shabbir and Zhu. (1995) "A New k-╬Á Eddy-Viscosity Model for High Reynolds
[19] Number Turbulent Flows: Model Development and Validation. Computers and Fluids". v. 24, no. 3, pp. 227-238.
[20] Walters and Leylek. (2000) "Impact of Film-Cooling Jets on Turbine Aerodynamic Losses". ASME Journal of Turbo-machinery, v.122, pp. 537-545.
[21] Wolfstein. (1969) "The Velocity and Temperature Distribution of One- Dimensional Flow With Turbulence Augmentation and Pres-sure Gradient," International Journal of Heat and Mass Transfer. v. 12, pp. 301-318.
[22] Kwak and Han. (2002) "Heat Transfer Coefficient and Film Cooling Effectiveness on a Gas
[23] Turbine Blade Tip". GT -2002-30194.
[24] Kwak and Han. (2002) "Heat Transfer Coefficient and Film Cooling Effectiveness on the
[25] Squealer Tip of A Gas Turbine Blade". GT-2002-30555.
[26] Uwe kruger ,karsten kusterer,Gernot Lang, Hauke Rosch, 2000,Analysis of the influence of cooling steam conditions on the cooling efficiency of a steam cooled vane using, conjugate calculation technique, Private publication-D-52070 Aachen-Germany, vol .5, pp.87-96.