Vol. 7, No. 4 (November 1994) 215-224   

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E. Esmaeilzadeh

Department of Mechanical Engineering
University of Tabriz
Tabriz, Iran


Abstract    An experimental study of hydrodynamics of film cooling is performed by using a single longitudinal slot on a cylindrical model simulated to the leading edge of the gas turbine blade. The model is set up into the test section of an open-circuit induced flow wind tunnel which provides the main flow. The injected air, as a secondary film flow, produced from a high pressure compressor is considered so that, the cooling factor always remained between 0.1 and 3.9. The first separation region of the boundary layer over the cylinder caused by the presence of injected flow was determined. The separation region extends up to 20 degrees after injection point with different conditions used in this experiment.


Keywords    Gas Turbine Blade, Leading Edge, Film Cooling, Slot Film Cooling, Cooling Factor, Effectiveness of Film Cooling



1. Wakil, M. M. El., "Power Plant Technology", McGraw-Hill, N. Y., (1988).
2. Barry, B., "The Aerodynamic Penalties Associated with Blade Cooling. In Turbine Blade Cooling", VKILS 83 (1976).
3. Goldstein, R. J., "Film Cooling Advanced in Heat Transfer", Academic Press, N. Y. and London., (1971), 321-379.
4. Bring, R. P. "Experimental Investigation of Film Cooling on Turbine Rotor Blade"; J. Egg. For Power., ASME, Vol. 100, (July-1978).
5. Bring, R. P., "Film Cooling of a Gas Turbine Blade"; J. Egg. for Power., ASME, Vol. 102, No. 1, (Jan-1980), 81-87.
6. Von Karman Institute for Fluid Dynamic, "Film Cooling and Turibine Heat Transfer", Lecture Series; Vol. 1 and Vol. 2, (1982).
7. Takers, K., "Experimental Study of Heat Transfer and Film Cooling on Low Aspect Ratio Turbines Nozzles"; J. Turbomach., Vol. 112, No. 2, (Jul-1990), 448-496.
8. Fitt A. D.,  "Aerodynamics of Slot Film Cooling” Theory and Experimental"; J. Fluid Mech., Vol. 160, (1985), 15-57.
9. Schewarz, S. G., "Influence of Curveture on Film Cooling Performance"; J. Turbomach, Vol. 113, No. 3, (Jul-1991), 472-478.
10. Teekaran, A. J. H., "Film Cooling in the Presence of Mainstream Pressure Gradients"; Int. Gas Turbine and Aeroengine Congress; Brussel, Belgium, (Jun-1990).
11. Kasagi, N., "Effects of the Wall Curvature on the Full-Converage Film Cooling Effectiveness", First int. Sym. On Transport Phenomena, Honolulu, USA, (May-1985).
12. Schlichting, H., "Boundry Layer Theory", McGraw-Hill, N. Y., (1979).
13. Yavuzkurt, S. "Full Coverage Film Cooling: 2-Prediction of the Recovery Region Hydrodynamics" ; J. Fluid Mech., Vol. 13, No. 101, (1980), 159-178.
14. Shembharkar, T. R., "Prediction of Film Cooling with a Liquid Coolant"; Int. J. Heat Mass Transfer. Vol. 29, No. 6, (Jun-1986), 899-908.
15. Gartshore, I., "Film Cooling Effectiveness; Trans. Can. Soc. Mech. Eng., Vol. 15, No. 1, (1991), 43-56.
16. Cole, J. D. and Aroesty, J., "The Blowhard Problem Inviscid Flows with Surface Injection" ; Int. J. Heat Mass Transfer, Vol. 11 (1968), 1167-1183.

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