Hole Configuration Effect on Turbine Blade Cooling
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.
[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.
[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.
@article{"International Journal of Mechanical, Industrial and Aerospace Sciences:58557", author = "A.Hasanpour and M. Farhadi and H.R. Ashorynejad", title = "Hole Configuration Effect on Turbine Blade Cooling", abstract = "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", volume = "5", number = "1", pages = "169-5", }
