Computational Investigation of Film Cooling from Cylindrical and Row Trenched Cooling Holes near the Combustor End Wall

Abstract:

This study was accomplished in order to investigate the effects of cylindrical and row trenched cooling holes with alignment angle of 0 degree and 90 degree at blowing ratio, BR = 3.18 on the film cooling performance adjacent to the endwall surface of a combustor simulator. In this research a three dimensional representation of Pratt and Whitney gas turbine engine was simulated and analyzed with a commercial finite volume package FLUENT 6.2. The current study has been performed with Reynolds-averaged Navier-Stokes turbulence model (RANS) on internal cooling passages. This combustor simulator combined the interaction of two rows of dilution jets, which were staggered in the stream wise direction and aligned in the span wise direction, with that of film cooling along the combustor liner walls. The findings of the study declared that with using the row trenched holes near the endwall surface, film cooling effectiveness is doubled compared to the cooling performance of baseline case.

• Periodical: Applied Mechanics and Materials (Volume 554)
• Pages: 225-229
• DOI: https://doi.org/10.4028/www.scientific.net/AMM.554.225
• Online since: June 2014
• Authors: Nor Azwadi Che Sidik*, Kianpour Ehsan
• Keywords: Cylindrical Hole, Dilution Hole, Film-Cooling, Gas Turbine, Trenched Hole

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