Analyzes of Film Cooling from Cylindrical and Row Trenched Holes with Alignment Angle of 90 Degrees at Low Blowing Ratio

Abstract:

The current study was conducted to analyze the effects of cylindrical and row trenched cooling holes with alignment angle of 90 degrees at blowing ratio, BR = 1.25 on the film cooling effectiveness near the end wall surface of a combustor simulator. In the current research a three dimensional representation of Pratt and Whitney gas turbine engine was simulated and analyzed with a commercial finite volume package FLUENT 6.2.26. This 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 arrangement, 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 end wall surface, film cooling effectiveness is increased three times compared to the cooling performance of baseline case.

• Periodical: Applied Mechanics and Materials (Volume 695)
• Pages: 376-379
• DOI: https://doi.org/10.4028/www.scientific.net/AMM.695.376
• Online since: November 2014
• Authors: Kianpour Ehsan*, Nor Azwadi Che Sidik
• Keywords: Blowing Ratio, Cylindrical Hole, Film Cooling, Gas Turbine, Trenched Hole

References

[1] S. Stitzel, K.A. Thole, Flow Field Computations of Combustor-Turbine Relevant to a Gas Turbine Engine, J. Turbomach. 126 (2004) 122-129.

DOI: 10.1115/1.1625691

[2] S.S. Vakil, K.A. Thole, Flow and Thermal Field Measurements in a Combustor Simulator Relevant to a Gas Turbine Aeroengine, J. Eng. Gas Turbines Power. 127 (2005) 257-267.

DOI: 10.1115/1.1806455

[3] E. Kianpour, N.A.C. Sidik, A.S.M. Bozorg, Dynamic Analysis of Flow Field at the End of Combustor Simulator, Jurnal Teknologi. 58 (2012) 5.

DOI: 10.11113/jt.v58.1540

[4] A. Azzi, B.A. Jubran, Influence of leading-edge lateral injection angles on the film cooling effectiveness of a gas turbine blade, J. Heat Mass Transfer. 40 (2004) 501–508.

DOI: 10.1007/s00231-003-0457-5

[5] A. Rozati, K. Danesh Tafti, Eeffect of coolant–mainstream blowing ratio on leading edge film cooling flow and heat transfer–LES investigation, Int J Heat Fluid Fl. 29 (2008) 857–873.

DOI: 10.1016/j.ijheatfluidflow.2008.02.007