0
TECHNICAL PAPERS

Flow Field Simulations of a Gas Turbine Combustor

[+] Author and Article Information
M. D. Barringer, O. T. Richard, J. P. Walter, S. M. Stitzel, K. A. Thole

Mechanical Engineering Department, Virginia Polytechnic Institute and State University, Blacksburg, VA 24061

J. Turbomach 124(3), 508-516 (Jul 10, 2002) (9 pages) doi:10.1115/1.1475742 History: Received November 01, 2000; Revised March 01, 2001; Online July 10, 2002
Copyright © 2002 by ASME
Your Session has timed out. Please sign back in to continue.

References

Langston,  L. S., 1980, “Crossflows in a Turbine Cascade Passage,” ASME J. Eng. Power, 102, p. 866.
Kang,  M., and Thole,  K. A., 2000, “Flowfield Measurements in the Endwall Region of a Stator Vane,” ASME J. Turbomach., 122, pp. 458–466.
Munk, M., and Prim, R. C., 1947, “On the Multiplicity of Steady Gas Flows Having the Same Streamline Pattern,” Proc. National Academy of Sciences, 33 .
Shang,  T., and Epstein,  A. H., 1997, “Analysis of Hot Streak Effects on Turbine Rotor Heat Load,” ASME J. Turbomach., 119, pp. 544–553.
Hermanson,  K., and Thole,  K. A., 2000, “Effect of Inlet Profiles on Endwall Secondary Flows,” J. Propul. Power, 16, pp. 286–296.
Butler,  T. L., Sharma,  O. P., Joslyn,  H. D., and Dring,  R. P., 1989, “Redistribution of an Inlet Temperature Distortion in an Axial Flow Turbine Stage,” J. Propul. Power, 5, pp. 64–71.
Shang, T., Guenette, G. R., Epstein, A. H., and Saxer, A. P., 1995, “The Influence of Inlet Temperature Distortion on Rotor Heat Transfer in a Transonic Turbine,” AIAA Paper No. 95- 36318.
Stabe, R. G., Whitney, W. J., and Moffitt, T. P., 1984, “Performance of a High-Work Low Aspect Ratio Turbine Tested with a Realistic Inlet Radial Temperature Profile,” NASA Technical Memorandum 83655, AIAA Paper No. 84-1161.
Burd, S., and Simon, T., 2000, “Effects of Slot Bleed Injection Over a Contoured Endwall on Nozzle Guide Vane Cooling Performance: Part I—Flow Field Measurements,” ASME Paper No. 2000-GT-199.
Burd, S., Satterness, C., and Simon, T., 2000 “Effects of Slot Bleed Injection Over a Contoured Endwall on Nozzle Guide Vane Cooling Performance: Part II—Thermal Measurements,” ASME Paper No. 2000-GT-200.
Soechting, F. O., and Cheung, A., 1999, private communication at Pratt & Whitney.
Kang,  M., Kohli,  A., and Thole,  K. A., 1999, “Heat Transfer and Flowfield Measurements in the Leading Edge Region of a Stator Vane Endwall,” ASME J. Turbomach., 121, pp. 558–568.
Radomsky,  R., and Thole,  K. A., 2000, “Highly Turbulent Flowfield Measurements Around a Stator Vane,” ASME J. Turbomach., 122, pp. 255–262.
Radomsky,  R., and Thole,  K. A., 2000, “High Freestream Turbulence Effects in the Endwall Leading Edge Region,” ASME J. Turbomach. (2000-GT-202), 122, pp. 699–708.
Lefebvre, A. H., 1998, Gas Turbine Combustors, Taylor and Francis, New York, NY.
Walsh, P. P., and Fletcher, Pl, 1998, Gas Turbine Performance, Blackwell Science LTD, NJ.
Burd,  S., and Simon,  T., 1999, “Measurements of Discharge Coefficients in Film Cooling,” ASME J. Turbomach., 121, pp. 243–248.
Moffat,  R. J., 1988, “Describing the Uncertainties in Experimental Results,” Electronics, 1, pp. 3–17.
Zimmerman, D. R., 1979, “Laser Anemometer Measurements at the Exit of a T63-C20 Combustor,” National Aeronautics and Space Administration, NASA Lewis Research Center, Contract NAS 3-21267.
Moss, R. W., 1992, “The Effects of Turbulence Length Scale on Heat Transfer,” University of Oxford, Department of Engineering Science, Report No. OUEL 1924, Ph.D. dissertation.
Zess,  G. A., and Thole,  K. A., 2002, “Computational Design and Experimental Evaluation of a Leading Edge Fillet on a Gas Turbine Vane,” ASME J. Turbomach. (2001-GT-404), 124, pp. 167–175.

Figures

Grahic Jump Location
Illustration of the low speed wind tunnel facility with the combustor simulator section
Grahic Jump Location
Illustration of the supply channels for each of the combustor liner and dilution flows (a), and geometric details of the primary flow path (b).
Grahic Jump Location
Film-cooling hole pattern for each liner panel
Grahic Jump Location
Schematic illustrating the combustor liner exit slot
Grahic Jump Location
Measured discharge coefficients of the film-cooling hole arrays
Grahic Jump Location
Measured velocity profiles downstream of the first panel at three different spanwise positions
Grahic Jump Location
Mean velocity profiles measured at the exit of the simulator in the span (a) and pitch (b) with, and without the dilution jets
Grahic Jump Location
Turbulence profiles measured at the exit of the combustor simulator in the span (a) and pitch (b), and streamwise velocity energy spectra (c)
Grahic Jump Location
Contours of normalized streamwise velocity (a) and turbulence levels upstream of the slot exit (b) for the dilution flow case
Grahic Jump Location
The nonuniform total pressure profile across the pin-finned exit slot. Below the plot is an indication of where the pin fins and slot feeder holes are located.
Grahic Jump Location
Nondimensional total pressure profiles of the exit slot for the no dilution (a) and dilution cases (b)
Grahic Jump Location
Spatially averaged nondimensional total pressure profiles downstream of the combustor liner slot for the no dilution and dilution cases compared to a turbulent boundary layer 21
Grahic Jump Location
Nondimensional thermal field contours after the exit slot for no dilution (a) and dilution (b)
Grahic Jump Location
Adiabatic effectiveness contours (a) and downstream levels (b) on the endwall for the case with dilution jets

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