Numerical Study Of Heat Transfer In Cooling Passages Of Turbine Blade
محتوى المقالة الرئيسي
الملخص
As the temperature of combustion gases is higher than the melting temperature of the turbine materials, cooling of turbine parts in a gas turbine engine is necessary for safe operation. Cooling methods investigated in this computational study included cooling flow losses. Film-cooling is one typically used cooling method whereby coolant is supplied through holes passage, in present study the holes placed along the camber line of the blade. The subject of this paper is to evaluate the heat transfer that occur on the holes of blade through different
blowing coolant rates. The cases of this study were performed in a low speed wind tunnel with two tip gap at small and large (0.03 and 0.09cm) and multiple coolant flow rates through the film-cooling holes. The
blowing ratios was studied whereby coolant was injected from holes placed along the tip of a large scale blade model with Reynolds number (2.1 x 105 ) of the engine was matched. Results showed that baseline
Nusselt numbers on the holes were reduced along the holes passage, and heat transfer coefficient is high values at iterance region. Overall, the cooling by holes appears to be a feasible method for prolonging blade life.
تفاصيل المقالة
كيفية الاقتباس
تواريخ المنشور
المراجع
Acharya, S., Yonk, H., Prakash, C. and Bunker, R., "Numerical Study of Flow and Heat Transfer on a Blade tip with Different Leakage Reduction Strategies'', ASME paper No. GT-2003-38617, 2003.
Allen, H. W. and. Kofskey, M.G, "Visualization Study of Secondary Flows in Turbine Rotor Tip Regions", NACA Technical Note 3519, 1955.
Arnal, M.P., "A General computer program for two-dimensional, turbulent, re-circulating flows", Report No.Fm-83-2, 1983.
Bunker, R. S., "Cooling Design Analysis", AIAA Journal of Propulsion and Power, 2002.
Christophel, J. R., Couch, E., Thole, K. A. and Cunha, F. J., "Measured Adiabatic Effectiveness and Heat Transfer for Blowing from the Tip of a Turbine Blade", ASME paper No. GT2004- 53250, 2004.
Cohen H., Rogers G.F.C., and Saravanamutto H.I.H., "Gas turbine theory", 3rd edition, Longman scientific and technical, 1987.
Couch, E., "Measurement of Cooling Effectiveness along the Tip of a Turbine Blade", Master's Thesis, Virginia Polytechnic Institute and State University, Blacksburg, VA, 2003.
Fluent Inc., Fluent User’s Guide, Version 6.3.26, 2009.
Hohlfeld, E. M., "Film Cooling Predictions Alone the Tip and Platform of a Turbine Blade", Master's Thesis, Virginia Polytechnic Institute and State University, Blacksburg, VA, 2003.
Ideriah, F. J. K., "Review of equation solved in TEACH", private communication, 1975
Jonas, B., "Internal cooling of gas turbine blades", PhD, Chalmers university of Technology Goterborg, Sweden, 2002.
Karki, K., and Patankar, S., "Pressure Based Calculation Procedure for Viscous Flows at All Speeds in Arbitrary Configurations", ALAa Journal, Vol. 27, PP. 1167-1174, 1989.
Launder, B.E. and Spalding, D.B.," Mathematical models of turbulence", Academic press, London, 1972.
Nasir H. S., Ekkad, V., Divad M. K., Bunker, R. S. and Prakash C., "Effect of Tip Gap and Squealer Geometry on Measured Heat Transfer Over a HPT Rotor Blade Tip", J. of Turbomachinery, 125, pp. 221-228, 2003.
Verestage, H. K., and Malalasekera, W., "An Introduction to Computational Fluid DynamicThe Finite volume Method", Longman Group Ltd, 1995.
Yang, H., Chen, H-C and Han, J-C, "Numerical Prediction of Film Cooling and Heat Transfer With Different Hole Arrangements on the plane and Squealer Tip of a Gas Turbine Blade", ASME Paper No. GT2004-53199, 2004.