0
TECHNICAL PAPERS: Forced Convection

Film Cooling of a Cylindrical Leading Edge With Injection Through Rows of Compound-Angle Holes

[+] Author and Article Information
Y.-L. Lin, T. I.-P. Shih

Department of Mechanical Engineering, Michigan State University, East Lansing, MI 48824-1226

J. Heat Transfer 123(4), 645-654 (Jan 09, 2001) (10 pages) doi:10.1115/1.1370513 History: Received April 28, 1999; Revised January 09, 2001
Copyright © 2001 by ASME
Your Session has timed out. Please sign back in to continue.

References

Simoneau,  R. J., and Simon,  F. F., 1993, “Progress Towards Understanding and Predicting Heat Transfer in the Turbine Gas Path,” Int. J. Heat Fluid Flow, 14, No. 2, pp. 106–128.
Hanus,  G. J., and L’Ecuyer,  M. R., 1977, “Leading Edge Injection for Film Cooling of Turbine Vanes,” J. Energy, 1, pp. 44–49.
Karni,  J., and Goldstein,  R. J., 1990, “Surface Injection Effect on Mass Transfer from a Cylinder in Cross Flow,” ASME J. Turbomach., 112, pp. 477–487.
Camci,  C., and Arts,  T., 1991, “Effect of Incidence on Wall Heating Rates and Aerodynamics on a Film-Cooled Transonic Turbine Blade,” ASME J. Turbomach., 113, pp. 493–501.
Mayle,  R. E., and Anderson,  A., 1991, “Velocity and Temperature Profiles for Stagnation Film Cooling,” ASME J. Turbomach., 113, pp. 457–463.
Ou,  S., and Han,  J. C., 1992, “Influence of Mainstream Turbulence on Leading Edge Film Cooling Heat Transfer Through Two Rows of Inclined Film Slots,” ASME J. Turbomach., 114, pp. 724–733.
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., Yuki, U. M., and Bogard, D. G., 1997, “Investigation of Various Parametric Influences on Leading Edge Film Cooling,” ASME Paper 97-GT-296.
Ames,  F. E., 1998, “Aspects of Vane Film Cooling with High Turbulence: Part I—Heat Transfer,” ASME J. Turbomach., 120, pp. 768–776.
Ames,  F. E., 1998, “Aspects of Vane Film Cooling with High Turbulence: Part II—Adiabatic Effectiveness,” ASME J. Turbomach., 120, pp. 777–784.
Garg,  V. K., and Gaugler,  R. E., 1996, “Leading Edge Film Cooling Effects on Turbine Blade Heat Transfer,” Numer. Heat Transfer, Part A, 30, pp. 165–187.
Heidmann, J., Rigby, D. L., and Ameri, A. A., “A Three-Dimensional Coupled Internal/External Simulation of a Film-Cooled Turbine Vane,” ASME Paper 99-GT-186.
Bohn, D. E., Becker, V. J., Kusterer, K. A., and Rungen, A. U., 1998, “Experimental and Numerical Conjugate Investigation of the Blowing Ratio Influence on the Showerhead Cooling Efficiency,” ASME Paper 98-GT-85.
Kercher,  D. M., 2000, “Turbine Airfoil Leading Edge Film Cooling Bibliography: 1972–1998,” Int. J. Rotating Mach., 6, No. 5, pp. 313–319.
Chernobrovkin, A., and Lakshminarayana, B., 1998, “Numerical Simulation and Aerothermal Physics of Leading Edge Film Cooling,” ASME Paper 98-GT-504.
Lin, Y.-L., Stephens, M. A., and Shih, T. I.-P., 1987, “Computations of Leading-Edge Film Cooling With Injection Through Rows of Compound Angle Holes,” ASME Paper 97-GT-298.
Martin, C. A., and Thole, K. A., 1997, “A CFD Benchmark Study: Leading-Edge Film Cooling with Compound Angle Injection,” ASME 97-GT-297.
Thakur, S., Wright, J., and Shyy, W., 1997, “Computation of a Leading-Edge Film Cooling Flow over an Experimental Geometry,” ASME Paper 97-GT-381.
Menter, F. R., 1993, “Zonal Two-Equation k-ω Turbulence Models for Aerodynamic Flows,” AIAA Paper 93-2906.
Wilcox, D. C., 1993, Turbulence Modeling for CFD, DCW Industries, La Canada, California.
Kandula, M., and Wilcox, D. C., 1995, “An Examination of k-ω Turbulence Model for Boundary Layers, Free Shear Layers, and Separated Flows,” AIAA Paper 95-2317.
Bardina, J. E., Huang, P. G., and Coakley, T. J., 1997, “Turbulence Modeling Validation, Testing, and Development,” NASA TM 110446.
Shih, T. I.-P., and Sultanian, B., 2001, “Computations of Internal and Film Cooling,” Heat Transfer in Gas Turbine Systems, B. Suden and M. Faghri, eds., WIT Press, Ashurst, Southhampton.
Thomas,  J. L., Krist,  S. T., and Anderson,  W. K., 1990, “Navier-Stokes Computations of Vortical Flows Over Low-Aspect-Ratio Wings,” AIAA J., 28, No. 2, pp. 205–212.
Rumsey, C. L., and Vatsa, V. N., 1993, “A Comparison of the Predictive Capabilities of Several Turbulence Models Using Upwind and Central-Difference Computer Codes,” AIAA Paper 93-0192.
Roe,  P. L., 1981, “Approximate Riemann Solvers, Parameter Vector and Difference Schemes,” J. Comput. Phys., 43, pp. 357–372.
Roe,  P. L., 1986, “Characteristic Based Schemes for the Euler Equations,” Annu. Rev. Fluid Mech., 18, pp. 337–365.
Pulliam,  W. R., and Chaussee,  D. S., 1981, “A Diagonal Form of an Implicit Approximate Factorization Algorithm,” J. Comput. Phys., 39, pp. 347–363.
Ni, R.-H., 1981, “A Multiple Grid Scheme for Solving the Euler Equations,” AIAA Paper 81-1025.
Anderson,  W. K., Thomas,  J. L., and Whitfield,  D. L., 1988, “Multigrid Acceleration of the Flux-Split Euler Equations,” AIAA J., 26, No. 6, pp. 649–654.
Stephens, M. A., Chyu, M. K., Shih, T. I-P., and Civinskas, K. C., 1996, “Calculations and Measurements of Heat Transfer in a Square Duct with Inclined Ribs,” AIAA Paper 96-3163.
Leylek,  J. H., and Zerkle,  R. D., 1994, “Discrete-Jet Film Cooling: A Comparison of Computational Results with Experiments,” ASME J. Turbomach., 116, pp. 358–368.

Figures

Grahic Jump Location
Schematic of experimental setup 7
Grahic Jump Location
Schematic of computational model
Grahic Jump Location
Grid system used: overall grid and grid about film-cooling holes
Grahic Jump Location
Coarsest grid used for grid-independence study
Grahic Jump Location
Computed and measured normalized temperature Θ as a function of Z/D and Y/D at three X/D locations
Grahic Jump Location
Adiabatic effectiveness η: (a) computed; (b) computed, averaged over 0.43D×0.43D; and (c) measured with resolution of 0.43D×0.43D7.
Grahic Jump Location
Adiabatic effectiveness, local and laterally averaged
Grahic Jump Location
Velocity-vector field about the middle of a symmetry-plane hole and the middle of a second-row hole in two x-y planes
Grahic Jump Location
Pressure contours on the cylindrical surface (X-Z plane at Y=0) and two Y-Z planes (P1:X/D=0,P3:X/D=3.50; see Fig. 10)
Grahic Jump Location
Projected streamlines at selected Y-Z and X-Y planes. P1, [[ellipsis]], P6 correspond to X/D=0, 1.84, 3.50, 5.47, 8.47, and 12.72, respectively. S1, [[ellipsis]], S6 correspond to Z/D=1.10, 2.24, 3.37, 4.27, 5.73, and 7.64, respectively.
Grahic Jump Location
Normalized temperature Θ at the symmetry plane and the leading-edge surface

Tables

Errata

Discussions

Some tools below are only available to our subscribers or users with an online account.

Related Content

Customize your page view by dragging and repositioning the boxes below.

Related Journal Articles
Related eBook Content
Topic Collections

Sorry! You do not have access to this content. For assistance or to subscribe, please contact us:

  • TELEPHONE: 1-800-843-2763 (Toll-free in the USA)
  • EMAIL: asmedigitalcollection@asme.org
Sign In