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http://dx.doi.org/10.5293/kfma.2012.15.2.041

A Numerical Study on the Film-Cooling Characteristics of Gas Turbine Blade using CO2  

Kim, Sang-Gwon (성균관대학교 대학원 기계공학과)
Lee, Jong-Chul (강릉원주대학교 기계자동차공학부)
Kim, Youn-Jea (성균관대학교 기계공학부)
Publication Information
The KSFM Journal of Fluid Machinery / v.15, no.2, 2012 , pp. 41-44 More about this Journal
Abstract
In order to cool the turbine blade under high temperature operating conditions, the film-cooling method is generally applied. In this study, $CO_2$ was used as working fluid and it helped the operating system to prevent the loss of compressed air. The trapezoidal diffuser shape was adopted at the cross section of hole and the characteristics of heat flow with various working fluids were numerically studied. In particular, the different mixture ratios of $CO_2$, such as various density ratios of 0.2, 0.8, and 1.0, respectively, were considered. Numerical results are graphically depicted with various conditions.
Keywords
Film-Cooling; Gas Turbine; CFD;
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  • Reference
1 Ekkad, S. V., Han, J. C. and Du, H., 1998, "Detailed Film Cooling Measurements on a Cylindrical Leading Edge Model: Effect of Free-Stream Turbulence and Coolant Density," Journal of Turbomachinery, Vol. 120, pp. 799-807.   DOI
2 Ekkad, S. V., Zapata, D. and Han, J. C., 1997, "Film Effectiveness over a Flat Surface with Air and $CO_2$ Injection through Compound Angle Holes Using a Transient Liquid Crystal Image Method," Journal of Turbomachinery, Vol. 119, pp. 587-593.   DOI
3 Silieti, M., Kassab, A. J. and Divo, E., 2009, "Film Cooling Effectiveness: Comparison of Adiabatic and Conjugate Heat Transfer CFD Models," International Journal of Thermal Sciences, Vol. 48, pp. 2237-2248.   DOI
4 Lee, K. D. and Kim, K. Y., 2010, "Shape Optimization of a Fan-Shaped Hole to Enhance Film-Cooling Effectiveness," International Journal of Heat and Mass Transfer, Vol. 53, pp. 2996-3005.   DOI
5 Gibbins, J. and Chalmers H., 2008, "Carbon Capture Storage," Energy Policy, Vol. 36, pp. 4317-4322.   DOI
6 Gritsch, M., Schulz, A. and Wittig, S., 1998, "Adiabatic Wall Effectiveness Measurements of Film-Cooling Holes with Expanded Exits," ASME Journal of Turbomachinery, Vol. 120, pp. 549-556.   DOI
7 Menter, F. R., Kuntz, M. and Langtry, R., 2003, "Ten Years of Industrial Experience with the SST Turbulence Model," Proceedings of the 4th International Symposium on Turbulence, pp. 652-632.
8 CFX-13.0 Solver Theory Guide, ANSYS Inc., 2010.
9 Cohen, H., Rogers, G. F. C. and Saravanamuttoo, H. I. H., 1979, Gas Turbine Theory, Longman Group, 2nd Edition, pp. 232-240.
10 Han, J. C. and Ekkad, S., 2001, "Recent Development in Turbine Blade Film Cooling," International Journal of Rotating Machinery, Vol. 7, No. 1, pp. 21-40.   DOI
11 Salcudean, M., Gartshore, I., Zhang, K. and Barnea, Y., 1994, "Leading Edge Film Cooling of a Turbine Blade Model Through Single and Double Row Injection: Effects of Coolant Density," ASME, No. 94-GT-2.
12 Kim, Y. J. and Kim, S. M., 2004, "Influence of Shaped Injection Holes on Turbine Blade Leading Edge Film Cooling," International Journal of Heat and Mass Transfer, Vol. 47, pp. 245-256   DOI