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A detailed study of effects of row trenched holes at the combustor exit on film cooling effectiveness

Kianpour, Ehsan and Che Sidik, Nor Azwadi (2017) A detailed study of effects of row trenched holes at the combustor exit on film cooling effectiveness. Journal of the Serbian Society for Computational Mechanics, 11 (1). pp. 59-68. ISSN 1820-6530

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Official URL: http://dx.doi.org/10.24874/jsscm.2017.11.01.06

Abstract

The current research was performed in order to analyze the effects of cylindrical and row trench cooling holes with the alignment angle of 90 degrees on the film-cooling effectiveness near the combustor endwall surface at the blowing ratio of BR=3.18. The three-dimensional representation of a Pratt and Whitney gas turbine engine was simulated and analyzed with the commercial finite volume package, FLUENT 6.2.26. in order to find the most effective row trenched cooling holes. The analysis was done with Reynolds averaged Navier-Stokes turbulence model (RANS) on internal cooling passages. This combustor simulator was combined with the interaction of two rows of dilution jets, which were staggered in the stream-wise direction and aligned in the spanwise direction. In comparison with the baseline case of cooling holes, using a row trenched hole near the endwall surface increased the film-cooling effectiveness by 44% in average.

Item Type:Article
Uncontrolled Keywords:Gas turbine engine, film-cooling, trench hole, dilution hole
Subjects:T Technology > TC Hydraulic engineering. Ocean engineering
Divisions:Mechanical Engineering
ID Code:77483
Deposited By: Yanti Mohd Shah
Deposited On:30 Nov 2018 15:09
Last Modified:30 Nov 2018 15:09

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