Numerical Study of Steady State Heat Transfer in Gas Turbine Blades
by
Hamid Fazeli
Department of Aerospace Engineering, K.N.Toosi University of Technology, Tehran, Iran
Coauthors: I. Firoozpour, A. Ashrafizadeh, N. Rostamy

As gas turbine entry temperature (TET) increases, thermal loading on first stage blades increases. So a variety of cooling techniques and thermal barrier coatings (TBC) are used. In this work, steady state heat transfer is studied numerically in uncoated blade as well as the ceramic-coated ones. Convection and radiation to the external surface of blades are also modeled for a super alloy blade with and without TBC. In order to obtain the temperature distribution, heat flux vectors, nodal temperature and radiation effects on the blades, the finite volume method is used in the present work. The temperature distribution and heat flux on the blade with TBC are less than those of blade without TBC. There is a good agreement between these results and other experimental results due to the comparison between them.

Date received: April 18, 2008

Copyright © 2008 by the author(s). The author(s) of this document and the organizers of the conference have granted their consent to include this abstract in Atlas Conferences Inc. Document # caxc-51.