A Converging Slot-Hole Film-Cooling Geometry—Part 1: Low-Speed Flat-Plate Heat Transfer and Loss
Author:
Sargison J. E.1, Guo S. M.2, Oldfield M. L. G.2, Lock G. D.3, Rawlinson A. J.4
Affiliation:
1. School of Engineering, University of Tasmania, Hobart, Tasmania 7001, Australia 2. Department of Engineering Science, University of Oxford, Oxford OX1 3PJ, UK 3. Department of Mechanical Engineering, University of Bath, Bath BA2 7AY, UK 4. Rolls Royce plc, Derby DE24 8BJ, UK
Abstract
This paper presents experimental measurements of the performance of a new film-cooling hole geometry—the con¯vergings¯lot-hole¯ or console. This novel, patented geometry has been designed to improve the heat transfer and aerodynamic loss performance of turbine vane and rotor blade cooling systems. The physical principles embodied in the new hole design are described, and a typical example of the console geometry is presented. The cooling performance of a single row of consoles was compared experimentally with that of typical 35-deg cylindrical and fan-shaped holes and a slot, on a large-scale, flat-plate model at engine representative Reynolds numbers in a low-speed tunnel with ambient temperature main flow. The hole throat area per unit width is matched for all four hole geometries. By independently varying the temperature of the heated coolant and the heat flux from an electrically heated, thermally insulated, constant heat flux surface, both the heat transfer coefficient and the adiabatic cooling effectiveness were deduced from digital photographs of the color play of narrow-band thermochromic liquid crystals on the model surface. A comparative measurement of the aerodynamic losses associated with each of the four film-cooling geometries was made by traversing the boundary layer at the downstream end of the flat plate. The promising heat transfer and aerodynamic performance of the console geometry have justified further experiments on an engine representative nozzle guide vane in a transonic annular cascade presented in Part 2 of this paper.
Publisher
ASME International
Subject
Mechanical Engineering
Reference17 articles.
1. Sargison, J. E., Guo, S. M., Oldfield, M. L. G., Lock, G. D., and Rawlinson, A. J., 2002, “A Converging Slot-Hole Film-Cooling Geometry—Part 2: Transonic Guide Vane Heat Transfer and Loss,” ASME Paper No. 2001-GT-127, ASME J. Turbomach., 124, pp. 461–471. 2. Denton, J. D.
, 1993, “Loss Mechanisms in Turbomachines,” ASME J. Turbomach., 115, pp. 621–656. 3. Eckert, E. R. G., and Drake, R. M., 1972, Analysis of Heat and Mass Transfer, McGraw Hill, New York, NY, pp. 453–466. 4. Farmer, J. P., Seager, D. J., and Liburdy, J. A. 1997 “The Effect of Shaping Inclined Slots on Film Cooling Effectiveness and Heat Transfer Coefficient,” ASME Paper No. 97-GT-399. 5. Ligrani, P., Ciriello, S., and Bishop, D. T., 1992 “Heat Transfer, Adiabatic Effectiveness and Injectant Distributions Downstream of a Single Row and Two Staggered Rows of Compound Angle Film-Cooling Holes,” ASME J. Turbomach., 114, pp. 687–700.
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