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TECHNICAL PAPERS

Leading-Edge Film-Cooling Physics—Part III: Diffused Hole Effectiveness

[+] Author and Article Information
William D. York, James H. Leylek

Department of Mechanical Engineering, Clemson University, Clemson, SC 29634

J. Turbomach 125(2), 252-259 (Apr 23, 2003) (8 pages) doi:10.1115/1.1559899 History: Received October 10, 2001; Online April 23, 2003
Copyright © 2003 by ASME
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References

York, W. D., and Leylek, J. H., 2002, “Leading-Edge Film-Cooling Physics: Part I—Adiabatic Effectiveness,” ASME Paper No. GT-2002-30166.
Mick,  W. J., and Mayle,  R. E., 1988, “Stagnation Film Cooling and Heat Transfer, Including Its Effect Within the Hole Pattern,” ASME J. Turbomach., 110, pp. 66–72.
Mehendale,  A. B., and Han,  J. C., 1992, “Influence of High Main-stream Turbulence on Leading Edge Film Cooling Heat Transfer,” ASME J. Turbo-mach., 114, pp. 707–715.
Ekkad, S. V., Han, J. C., and Du, H., 1997, “Detailed Film Cooling Measurements on a Cylindrical Leading Edge Model: Effect of Free-Stream Turbulence and Coolant Density,” ASME Paper No. 97-GT-181.
Salcudean,  M., Gartshore,  I., Zhang,  K., and McLean,  I., 1994, “An Experimental Study of Film Cooling Effectiveness Near the Leading Edge of a Turbine Blade,” ASME J. Turbomach., 116, pp. 71–79.
Cruse, M. W., 1997, “A Study of Film Cooling Adiabatic Effectiveness for Turbine Blade Leading Edges,” M.S. thesis, University of Texas at Austin.
Reiss, H., and Bölcs, A., 1999, “Experimental Study of Showerhead Cooling on a Cylinder Comparing Several Configurations Using Cylindrical and Shaped Holes,” ASME Paper No. 99-GT-123.
Chernobrovkin, A., and Lakshminarayana, B., 1998, “Numerical Simulation and Aerothermal Physics of Leading Edge Film Cooling,” ASME Paper No. 98-GT-504.
Lin, Y.-L., Stephens, M. A., and Shih, T.I.-P., 1997, “Computation of Leading-Edge Film Cooling with Injection Through Rows of Compound-Angle Holes,” ASME Paper No. 97-GT-298.
Martin, C. A., and Thole, K. A., 1997, “A CFD Benchmark Study: Leading Edge Film-Cooling With Compound Angle Injection,” ASME Paper No. 97-GT-297.
Thakur, S., Wright, J., and Shyy, W., 1997, “Computation of Leading-Edge Film Cooling Flow Over an Experimental Geometry,” ASME Paper No. 97-GT-381.
Shih,  T.-H., Liou,  W. W., Shabbir,  A., and Zhu,  J., 1995, “A New k-ε Eddy-Viscosity Model for High Reynolds Number Turbulent Flows: Model Development and Validation,” Comput. Fluids, 24(3), pp. 227–238.
McGrath,  E. L., and Leylek,  J. H., 1999, “Physics of Hot Crossflow Ingestion in Film Cooling,” ASME J. Turbomach., 121, pp. 532–541.

Figures

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View of the computational domain with dimensions in film-hole diameters (D=6.32 mm). The transparent side boundaries are periodic planes.
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Schematic of (a) the cylindrical (REF) film-hole, and (b) the conical diffuser (CDIFF) hole in the three orthogonal planes
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View of the film-hole and leading edge surface mesh at the Row2 hole breakout. The extremely dense grid in this region was necessary to achieve a y+ of unity or less along the walls while maintaining high quality cells.
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Contours of adiabatic effectiveness on the leading edge with CDIFF holes for (a) M=1.0, and (b) M=2.0
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Plots of predicted laterally averaged effectiveness for the CD, FF, and REF geometries of blowing ratios of (a) M=1.0, (b) M=1.5, (c) M=2.0, and (d) M=2.5
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Contours of Vy on the FHEP of the Row1 conical diffuser hole at M=2.0 show a fairly low, uniform coolant flow
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Lines of constant θ on three planes of constant z-coordinate between Row1 hole centerlines at the blowing ratio M=2.0. Note the extremely low trajectory of the coolant jet.
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Contours of Vy on a plane through the centerline of the Row2 film hole (from upstream to downstream edge) at M=2.0 shows the development of a jetting region
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Lines of constant Vy on the Row2 FHEP for (a) M=1.0, and (b) M=2.0 show the highly nonuniform velocity field at the diffuser exit
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Contours of θ on three planes of constant x-coordinate aft of the Row2 film hole for the blowing ratio M=2.0. The dashed lines mark the extent of the region on the surface in which θ≤0.3.
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Velocity vectors sized by in-plane velocity magnitude on the x/D=4.5 plane (just aft of the Row2 hole) at M=2.0 showing a relatively strong secondary flow. The gray line marks the θ=0.5 isotherm.
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Pathlines of the coolant from Row1 and Row2 for the case of M=2.0 show the strong interaction between rows
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Paths of massless particles released in the crossflow boundary layer just upstream of Row2 for M=2.0 show the vortex that brings crossflow below the FHEP
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Contours of θ on the FHEP of the Row2 conical diffuser hole for the cases of (a) M=1.0, and (b) M=2.0
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Lines of constant θ on the film-hole walls inside the Row2 CDIFF hole at blowing ratios of (a) M=1.0, and (b) M=2.0 reveal the severe heating of the metal surface near the TE

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