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A comparative study of the film cooling hole configurationeffects on the leading edge of asymmetrical turbine blade

Published online by Cambridge University Press:  14 March 2011

Mustapha Benabed
Mustapha Benabed*
Affiliation:
Laboratoire de Mécanique Appliquée, Faculté de Génie-Mécanique, Université des Sciences et de la Technologie d’Oran, BP 1505 El-Mnouar, Oran, Algeria
*
a Corresponding author: bennabed@yahoo.fr
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Abstract

The focus of this comparative-numerical study is to investigate the effects of advancedcooling hole geometries on film cooling effectiveness. Computational results are presentedfor a row of coolant injection holes on each side of an asymmetrical turbine blade modelnear the leading edge. Six film cooling configurations are considered in the presentstudy, namely: (1) a cylindrical film hole, (2) a shaped film hole, (3) a uniform filmslot, (4) a convergent film slot, (5) a crescent film hole, and (6) a trenched film hole.All simulations are conducted for the same density ratio of 1.0 and the same inlet plenumpressure. A new parameter, Rc, is defined to measure the rate of bladecoverage by the film cooling. Results show that, at the suction side, except for thetrenched case, all configurations provide an increase of film effectiveness, specially thecrescent slot case which provides the highest increase over the baseline case. On pressureside, the five configurations produce better quality of cooling and an enhancement whichreaches 60% for the crescent hole case. The best blade coverage by the film cooling isallotted to the two cases: uniform and converge slot configurations.

Keywords

Film cooling effectivenesscoverage ratioSST turbulence modelhole configuration
Type
Research Article
Information
Mechanics & Industry , Volume 12 , Issue 1 , 2011 , pp. 25 - 36
Copyright
© AFM, EDP Sciences 2011

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