This paper describes a method that allows the effect of film cooling on the capacity of a turbine to be computed. The model is based on fundamental cooling performance parameters and is applicable to situations in which a mainstream flow is displaced by a partially mixed film cooling layer. The purpose is to quantify the error that is incurred in the engine situation when common—but simplified—assumptions are made regarding the flow, and where necessary, to provide a means of correcting the capacity for the effect of the film cooling flow.
Issue Section:
Gas Turbines: Heat Transfer
1.
Afanasiev
, I. V.
, Granovski
, A. V.
, Karelin
, A. M.
, and Kostege
, M. K.
, “Effect of 3D Vane Shape on the Flow Capacity
,” ASME Paper No. GT2004-53095.2.
Fielding
, L.
, 1981, “Effect of Irreversibility on the Capacity of a Turbine Blade Row
,” Proc. Inst. Mech. Eng.
0020-3483, 195
, pp. 127
–37
.3.
Hoheisel
, H.
, Kiock
, R.
, Lichtfuss
, H. J.
, and Fottner
, L.
, 1987, “Influence of Free-Stream Turbulence and Blade Pressure Gradient on Boundary Layer and Loss Behaviour of Turbine Cascades
,” ASME J. Turbomach.
0889-504X, 109
(2
), pp. 210
–219
.4.
Hartsel
, J. E.
, 1972, “Prediction of Effects of Mass-Transfer Cooling on the Blade-Row Efficiency of Turbine Airfoils
,” AIAA Tenth Aerospace Sciences Meeting
, CA, Jan. 17
–19
, AIAA Paper No. 72-11.5.
Kollen
, O.
, and Koschel
, W.
, 1985, “Effect of Film Cooling on the Aerodynamic Performance of a Turbine Cascade
,” Paper No. AGARD CP-390.6.
Eckert
, E. R. G.
, and Drake
, R. M.
, 1972, Analysis of Heat and Mass Transfer
, McGraw-Hill
, New York
, pp. 453
–466
.Copyright © 2010
by American Society of Mechanical Engineers
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