Cooling Turbine Blades using Exciting Boundary Layer

Authors: Ali Ghobadi, Seyed Mohammad Javadi, Behnam Rahimi

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.

Digital Object Identifier (DOI): doi.org/10.5281/zenodo.1330673

References:

[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.