Heat Transfer in Thermal Barrier Coated Rods With Circumferential and Radial Temperature Gradients

[+] Author and Article Information
B. T. F. Chung, M. M. Kermani, M. J. Braun, J. Padovan

Department of Mechanical Engineering, The University of Akron, Akron, Ohio 44325

R. C. Hendricks

NASA Lewis Research Center, Cleveland, Ohio 44135

J. Eng. Gas Turbines Power 107(1), 135-141 (Jan 01, 1985) (7 pages) doi:10.1115/1.3239673 History: Received January 12, 1984; Online October 15, 2009


To study the heat transfer in ceramic coatings applied to the heated side of internally cooled hot section components of the gas turbine engine, a mathematical model is developed for the thermal response of plasma-sprayed ZrO2 -Y2 O3 ceramic materials with a Ni-Cr-AL-Y bond coat on a Rene 41 rod substrate subject to thermal cycling. This multilayered cylinder with temperature dependent thermal properties is heated in a cross-flow by a high veloctiy flame and then cooled by ambient air. Due to high temperature and high velocity of the flame, both gas radiation and forced convection are taken into consideration. Furthermore, the local turbulent heat transfer coefficient is employed which varies with angular position as well as the surface temperature. The transient two-dimensional (heat transfer along axial direction is neglected) temperature distribution of the composite cylinder is determined numerically.

Copyright © 1985 by ASME
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