Film Cooling Research on the Endwall of a Turbine Nozzle Guide Vane in a Short Duration Annular Cascade: Part 2—Analysis and Correlation of Results

[+] Author and Article Information
S. P. Harasgama, C. D. Burton

Royal Aerospace Establishment, Propulsion Department, Pyestock, Farnborough, Hampshire, GU14 OLS, United Kingdom

J. Turbomach 114(4), 741-746 (Oct 01, 1992) (6 pages) doi:10.1115/1.2928027 History: Received March 04, 1991; Online June 09, 2008


Results have been presented on the heat transfer characteristics of the film cooled endwall (platform) of a turbine nozzle guide vane in an annular cascade at engine representative conditions in a companion paper by Harasgama and Burton (1992). The present paper reports on the analysis of these measurements. The experimental results are well represented by the superposition theory of film cooling. It is shown that high cooling effectiveness can be achieved when the data are corrected for axial pressure gradients. The data are correlated against both the slot-wall jet parameter and the discrete hole injection function for flat-plate, zero pressure gradient cases. The pressure gradient correction brings the present data to within ± 11 percent of the discrete hole correlation. Preliminary predictions of heat transfer reduction have been carried out using the STANCOOL program. These indicate that the code can predict the magnitude of heat transfer reduction correctly, although the absolute values are not in good agreement. This is attributed to the three-dimensional nature of the flow at the endwall.

Copyright © 1992 by The American Society of Mechanical Engineers
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