Heat Transfer From a Shrouded Disk System With a Radial Outflow of Coolant

[+] Author and Article Information
C. M. Haynes, J. M. Owen

School of Applied Sciences, University of Sussex, England

J. Eng. Power 97(1), 28-35 (Jan 01, 1975) (8 pages) doi:10.1115/1.3445907 History: Received November 13, 1973; Online July 14, 2010


This paper describes a combined theoretical and experimental study of the heat transfer from an air-cooled gas turbine disk using the model of a plane disk rotating close to a shrouded stator. Numerical solutions of the boundary layer equations are obtained by assuming a modified system geometry, and it is shown that this technique yields adequate estimates of moment coefficients and mean Nusselt numbers for the air-cooled disk. Experimental results show the effect of rotational speeds up to 4000 rev/min, coolant flow rates up to 2 lb/s, stator clearances and shroud clearances up to 2.7 in., on the mean Nusselt numbers for a 30-in-dia disk and its stator.

Copyright © 1975 by ASME
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