A Study of the Effects of Thermal Barrier Coating Surface Roughness on the Boundary Layer Characteristics of Gas Turbine Aerofoils

[+] Author and Article Information
R. M. Watt, J. L. Allen

Department of Engineering Science, University of Oxford, Oxford, OX1 3PJ, United Kingdom

N. C. Baines

Department of Mechanical Engineering, Imperial College, London, SW7 2BX, United Kingdom

J. P. Simons, M. George

Rolls-Royce Ltd., Filton, Bristol, BS12 7QE, United Kingdom

J. Turbomach 110(1), 88-93 (Jan 01, 1988) (6 pages) doi:10.1115/1.3262172 History: Received February 19, 1987; Online November 09, 2009


The effect of thermal barrier coating surface roughness on the aerodynamic performance of gas turbine aerofoils has been investigated for the case of a profile typical of current first-stage nozzle guide vane design. Cascade tests indicate a potential for significant extra loss, depending on Reynolds number, due to thermal barrier coating in its “as-sprayed” state. In this situation polishing coated vanes is shown to be largely effective in restoring their performance. The measurements also suggest a critical low Reynolds number below which the range of roughness tested has no effect on cascade efficiency. Transition detection involved a novel use of thin-film anemometers painted and fired onto the TBC surfaces.

Copyright © 1988 by ASME
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