TECHNICAL PAPERS: Gas Turbines: Heat Transfer

Gas Turbine Engine Durability Impacts of High Fuel-Air Ratio Combustors—Part II: Near-Wall Reaction Effects on Film-Cooled Heat Transfer

[+] Author and Article Information
D. R. Kirk, G. R. Guenette, S. P. Lukachko, I. A. Waitz

Gas Turbine Laboratory, Department of Aeronautics and Astronautics, Massachusetts Institute of Technology, Cambridge, MA 02139

J. Eng. Gas Turbines Power 125(3), 751-759 (Aug 15, 2003) (9 pages) doi:10.1115/1.1606473 History: Received November 27, 2001; Online August 15, 2003
Copyright © 2003 by ASME
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Lukachko, S. P., et al., “Turbine Durability Impacts of High Fuel-Air Ratio Combustors, Part 1: Potential For Intra-Turbine Oxidation of Partially-Reacted Fuel,” ASME GT-2002-30077.
Kercher, D. M., “Short Duration Heat Transfer Studies at High Free-Stream Temperatures,” ASME 82-GT-129.
Kirk, D. R., 1999, “Aeroacoustic Measurement and Analysis of Transient Hot Supersonic Nozzle Flows,” Master’s thesis, Massachusetts Institute of Technology.
Keyes, W. M., and Crawford, M. E., 1980, Convective Heat and Mass Transfer, McGraw-Hill Book Company, New York. NY.
White, F. M., 1991, Viscous Fluid Flow, McGraw-Hill Book Company, Boston, NA.
Schultz, D. L., and Jones, T. V., 1973, “Heat-Transfer Measurements in Short-Duration Hypersonic Facilities,” AGARD No. 165.
Handbook of Heat Transfer Applications, 1985, 2nd Ed., McGraw-Hill, New York, NY.
Walters,  D. K., and Leylek,  J. H., 2000, “A Detailed Analysis of Film-Cooling Physics: Part 1—Streamwise Injection With Cylindrical Holes,” ASME J. Turbomach., 122 , Jan.
Walters,  D. K., and Leylek,  J. H., 1997, “A Systematic Computational Methodology Applied to a Three-Dimensional, Film-Cooling Flowfield,” ASME J. Turbomach., 119, Oct., pp. 777–785.
Eammons,  H. W., 1956, “The Film Combustion of Liquid Fuel,” Z. Angew. Math. Mech., 36:1–2, pp. 60–71.


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Sample pressure, wall temperature, and wall heat flux traces, T=2000 K
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Wall temperature distributions (ζ=0.0) for three wall heat flux distributions
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Flat plate heat transfer results
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Test section and flat plate details
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Maximum change, B=1.0,H*=0.005–0.8
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Comparison of B=0.5 versus 2.0, H*=0.18, Da=24
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Numerical study results for adiabatic wall cases
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Scaled data set for B=1.0,H*=0.05–0.8
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Scaled data set for H*=0.18–0.8
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Decay in film effectiveness due to local reactions, H*=0.54, Da=25
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Sample of film-cooling test result
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Augmented heat flux due to local reaction, B=1.0,H*=0.18, Da=20




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