Cooling Turbine Blades using Exciting Boundary Layer
The present study is concerned with the effect of
exciting boundary layer on cooling process in a gas-turbine blades.
The cooling process is numerically investigated. Observations show
cooling the first row of moving or stable blades leads to increase
their life-time. Results show that minimum temperature in cooling
line with exciting boundary layer is lower than without exciting.
Using block in cooling line of turbines' blade causes flow pattern and
stability in boundary layer changed that causes increase in heat
transfer coefficient. Results show at the location of block,
temperature of turbines' blade is significantly decreased. The k-ε
turbulence model is used.
[1] Perry L. Young, Surface roughness effects on heat transfer in micro
scale single phase, Proceedings of the Sixth International ASME
Conference on Nano channels, Micro channels and Mini channels,
ICNMM2008, June 23-25, 2008, Darmstadt, Germany
[2] Y. Suzue, K. Morimoto, N. Shikazono, Y. Suzuki and N. Kasagi, High
performance heat exchanger with oblique wave walls, 13th International
Heat Transfer Conference, Sydney, Australia, 13-18 August 2006..
[3] A. M. Jacobi, Y. Park, Y. Zhong, G. Michna, and Y. Xia, High
performance heat exchangers for air-conditioning and refrigeration
applications (non-circular tubes), Report No. ARTI-21CR/605-20021-
01, July 2005, University of Illinois.
[4] K. Inakova, J.Yamamoto, K.Suzuki, Dissimilarity Between Heat
Transfer and Momentum Transfer in a Disturbed Boundary Layer with
Insertion of a Rod - Modeling and Numerical Simulation, International
Journal of Heat and Fluid Flow, 20(1999) 290-301.
[5] K.Teraguchi, K.Katoh, T. Azuma, Dissimilarity between Turbulent
Momentum and Heat Transfer by Excitation of Transverse Vortex,
Journal of the Japan Society of Mechanical Engineers, 2005 (80).
[6] D.L. Schmidt, B. Sen, D.G. Bogard, Film cooling with compound angle
holes: adiabatic effectiveness, ASME Paper No. 94-GT-312, 1994.
[7] J. Dittmar, A. Schulz, S. Wittig, Assessment of various film cooling
configurations including shaped and compound angle holes based on
large scale experiments, ASME Paper No. GT-2002-30176, 2002.
[8] S. Mhetras, D. Narzary, Z. Gao, J.C. Han, Effect of a cutback squealer
and cavity depth on film-cooling effectiveness on a gas turbine blade tip,
AIAA Paper No. AIAA 2006-3404, 2006.
[9] B. E. Launder, D. B. Spalding. Lectures in Mathematical Models of
Turbulence. Academic Press, London, England, 1972.
[10] T.B Gatski, M.Y.Hussaini, J.L. Lumley, Simulation and Modeling of
Turbulent flows, Oxford University Press, New York, 1996.
[11] Fluent User-s Guide, Version 4.3, vols, 1-4, Fluent Incorporated,
Lebanon, NH, 1995.
[12] S. V. Patankar, Numerical Heat Transfer and Fluid Flow, McGraw-Hill,
1980.
[1] Perry L. Young, Surface roughness effects on heat transfer in micro
scale single phase, Proceedings of the Sixth International ASME
Conference on Nano channels, Micro channels and Mini channels,
ICNMM2008, June 23-25, 2008, Darmstadt, Germany
[2] Y. Suzue, K. Morimoto, N. Shikazono, Y. Suzuki and N. Kasagi, High
performance heat exchanger with oblique wave walls, 13th International
Heat Transfer Conference, Sydney, Australia, 13-18 August 2006..
[3] A. M. Jacobi, Y. Park, Y. Zhong, G. Michna, and Y. Xia, High
performance heat exchangers for air-conditioning and refrigeration
applications (non-circular tubes), Report No. ARTI-21CR/605-20021-
01, July 2005, University of Illinois.
[4] K. Inakova, J.Yamamoto, K.Suzuki, Dissimilarity Between Heat
Transfer and Momentum Transfer in a Disturbed Boundary Layer with
Insertion of a Rod - Modeling and Numerical Simulation, International
Journal of Heat and Fluid Flow, 20(1999) 290-301.
[5] K.Teraguchi, K.Katoh, T. Azuma, Dissimilarity between Turbulent
Momentum and Heat Transfer by Excitation of Transverse Vortex,
Journal of the Japan Society of Mechanical Engineers, 2005 (80).
[6] D.L. Schmidt, B. Sen, D.G. Bogard, Film cooling with compound angle
holes: adiabatic effectiveness, ASME Paper No. 94-GT-312, 1994.
[7] J. Dittmar, A. Schulz, S. Wittig, Assessment of various film cooling
configurations including shaped and compound angle holes based on
large scale experiments, ASME Paper No. GT-2002-30176, 2002.
[8] S. Mhetras, D. Narzary, Z. Gao, J.C. Han, Effect of a cutback squealer
and cavity depth on film-cooling effectiveness on a gas turbine blade tip,
AIAA Paper No. AIAA 2006-3404, 2006.
[9] B. E. Launder, D. B. Spalding. Lectures in Mathematical Models of
Turbulence. Academic Press, London, England, 1972.
[10] T.B Gatski, M.Y.Hussaini, J.L. Lumley, Simulation and Modeling of
Turbulent flows, Oxford University Press, New York, 1996.
[11] Fluent User-s Guide, Version 4.3, vols, 1-4, Fluent Incorporated,
Lebanon, NH, 1995.
[12] S. V. Patankar, Numerical Heat Transfer and Fluid Flow, McGraw-Hill,
1980.
@article{"International Journal of Mechanical, Industrial and Aerospace Sciences:52747", author = "Ali Ghobadi and Seyed Mohammad Javadi and Behnam Rahimi", title = "Cooling Turbine Blades using Exciting Boundary Layer", abstract = "The present study is concerned with the effect of
exciting boundary layer on cooling process in a gas-turbine blades.
The cooling process is numerically investigated. Observations show
cooling the first row of moving or stable blades leads to increase
their life-time. Results show that minimum temperature in cooling
line with exciting boundary layer is lower than without exciting.
Using block in cooling line of turbines' blade causes flow pattern and
stability in boundary layer changed that causes increase in heat
transfer coefficient. Results show at the location of block,
temperature of turbines' blade is significantly decreased. The k-ε
turbulence model is used.", keywords = "Cooling, Exciting Boundary Layer, Heat Transfer,Turbine Blade.", volume = "4", number = "2", pages = "162-4", }
