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Pressure loss and wall heat transfer characteristics in blade trailing-edge cooling passage

DOI: 10.1615/ICHMT.2012.ProcSevIntSympTurbHeatTransfPal.560
pages 506-517

M. Effendy
Department of Mechnical Engineering, Muhammadiyah University of Surakarta, J1. A. Yani Surakarta, Indonesia 57102; School of Aerospace & Aircraft Engineering, Kingston University, Roehampton Vale, Friars Avenue, London SW15 3DW, UK

Yufeng Yao
School of Aerospace & Aircraft Engineering, Kingston University, Roehampton Vale, Friars Avenue, London SW15 3DW, UK

Jun Yao
School of Engineering, Isaac Newton Building, University of Lincoln, Brayford Pool, Lincoln LN6 7TS, UK

Sinopsis

This paper presents a numerical study of flow and heat transfer inside an internal cooling passage of industrial turbine blade trailing-edge. Five configurations with staggered elliptical or circular pin-fins are investigated using RANS-based CFD modelling. Validation study of total pressure loss over the passage gives 2% and 4% discrepancies respectively for two baseline configurations in comparison with available experimental data. Further studies focused on wall heat transfer coefficient (HTC), and it was found that CFD predicted pin-fin wall HTC are generally in good agreement with test data for the streamwise staggered elliptic pin-fin model, but not the spanwise staggered elliptic pin-fin model in which some discrepancies occur. A ratio of averaged pin-fin and end wall HTC is estimated 1.3 - 1.5, close to that of a circular pin-fin configuration that gives 1.8 - 2.1. Further study should focus on the improvement of the end wall HTC predictions, probably through a conjugate heat transfer model including heat conduction in the solid region.

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