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TECHNICAL PAPERS

A Method for Correlating the Influence of External Crossflow on the Discharge Coefficients of Film Cooling Holes

[+] Author and Article Information
D. A. Rowbury

Rolls-Royce plc, Bristol, UK

M. L. G. Oldfield

Department of Engineering Science, University of Oxford, Oxford, UK

G. D. Lock

Department of Mechanical Engineering, University of Bath, Bath, UK

J. Turbomach 123(2), 258-265 (Feb 01, 2000) (8 pages) doi:10.1115/1.1354137 History: Received February 01, 2000
Copyright © 2001 by ASME
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References

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Sasaki,  M., Takahara,  K., Sakata,  K., and Kumagai,  T., 1976, “Study on Film Cooling of Turbine Blades: Experiments on Film Cooling With Injection Through Holes Near the Leading Edge,” Bull. JSME, 19, No. 137, pp. 1344–1352.
Foster,  N. W., and Lampard,  D., 1980, “The Flow and Film Cooling Effectiveness Following Injection Through a Row of Holes,” ASME J. Eng. Power, 102, No. 3, pp. 584–588.
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Martinez-Botas, R. F., Main, A. J., Lock, G. D., and Jones, T. V., 1993, “A Cold Heat Transfer Tunnel for Gas Turbine Research on an Annular Cascade,” ASME Paper No. 93-GT-248, International Gas Turbine and Aero-Engine Congress and Exposition, Cincinnati, Ohio, May 1993.
Rowbury, D. A., Oldfield, M. L. G., Lock, G. D., and Dancer, S. N., 1998, “Scaling of Film Cooling Discharge Coefficient Measurements to Engine Conditions,” ASME Paper No. 98-GT-79, International Gas Turbine and Aero-Engine Congress & Exhibition, Stockholm, Sweden, June 1998.
Rowbury, D. A., Oldfield, M. L. G., and Lock, G. D., 1997, “Engine-Representative Discharge Coefficients Measured in an Annular Nozzle Guide Vane Cascade,” ASME Paper No. 97-GT-99, International Gas Turbine and Aero-Engine Congress & Exhibition, Orlando, Florida, June 1997.
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Rowbury, D. A., Oldfield, M. L. G., and Lock, G. D., 2000, “Large-Scale Testing to Validate the Influence of External Crossflow on the Discharge Coefficients of Film Cooling Holes,” ASME Paper No. 2000-GT-0293, International Gas Turbine and Aero-Engine Congress & Exhibition, Munich, Germany, May 2000.
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Hay, N., Lampard, D., and Khaldi, A., 1994, “The Coefficient of Discharge of 30° Inclined Film Cooling Holes With Rounded Entries or Exits,” ASME Paper No. 94-GT-180, International Gas Turbine and Aero-Engine Congress and Exposition, The Hague, Netherlands, June 1994.
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Burd,  S. W., and Simon,  T. W., 1999, “Measurements of Discharge Coefficients in Film Cooling,” ASME J. Turbomach., 121, No. 2, pp. 243–248.
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Figures

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Schematic diagram of the CHTT
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Vane cross-section, illustrating the “regions” referred to in the declaration of coefficients for the “δout=Akout,⊥−B−C” relationships (Table 2)
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Definition of film cooling hole angles
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δout vs. kout for CHTT row 1 as cylindrical holes
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Comparison between with-crossflow measurements and additive loss coefficient predictions for CHTT row 1 as cylindrical film cooling holes
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Rig measurements and “generalized” predictions for row 1 as cylindrical film cooling holes
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Rig measurements and “generalized” predictions for row 10 (cylindrical film cooling holes)
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Rig measurements and “generalized” predictions for row 14 as fan-shaped film cooling holes
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Comparison between Karlsruhe experimental data for an inclined 30 deg cylindrical film cooling hole and predictions using the proposed methodology

Tables

Errata

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