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TECHNICAL PAPERS: Gas Turbines: Combustion and Fuels

Optimization of Wall Cooling in Gas Turbine Combustor Through Three-Dimensional Numerical Simulation

[+] Author and Article Information
R. Gordon, Y. Levy

Faculty of Aerospace Engineering, Technion—Israel Institute of Technology, Haifa 32000, Israel

J. Eng. Gas Turbines Power 127(4), 704-723 (Sep 20, 2005) (20 pages) doi:10.1115/1.1808432 History: Received April 28, 2003; Revised May 05, 2004; Online September 20, 2005
Copyright © 2005 by ASME
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References

Danis,  A. M., Burrus,  D. L., and Mongia,  H. C., 1997, “Anchored CCD for Gas Turbine Combustor Design and Data Correlation,” ASME J. Eng. Gas Turbines Power, 119, pp. 535–545.
Lawson, R. J., 1993, “Computational Modeling of an Aircraft Engine Combustor to Achieve Target Exit Temperature Profiles,” ASME Paper-93GT-164.
Fuller, E. J., and Smith, C. E., 1993, “Integrated CFD Modeling of Gas Turbine Combustors,” AIAA paper 93-2196.
Tolpadi,  A. K., Burrus,  D. L., and Lawson,  R. J., 1995, “Numerical Computation and Validations of Two-Phase Flow Downstream of a Gas Turbine Combustor Dome Swirl Cup,” ASME J. Eng. Gas Turbines Power, 117, pp. 704–712.
Gulati,  A., Tolpadi,  A. K., VanDeusen,  G., and Burrus,  D. L., 1995, “Effect of Dilution Air on Scalar Flowfield at Combustor Sector Exit,” J. Propul. Power, 11, pp. 1162–1169.
Lai, M. K., 1997, “CFD Analysis of Liquid Spray Combustion in a Gas Turbine Combustor,” ASME Paper 97-GT-309.
Gosselin, P., DeChamplain, S., Kalla, and Kretschmer, D., 2000, “Three-Dimensional CFD Analysis of a Gas Turbine Combustor,” AIAA-2000-3466 paper, 36th AIAA/ASME/SAE/ASEE Joint Propulsion Conf. and Exhibit, 16–19 July, 2000, Huntsville, Alabama.
Mongia, H. C., and Brands, D. J., 1982, “Design Documentation Report Counter Flow Film-Cooled Combustor Program,” NASA CR-167922 June 1982.
Rizk,  N. K., and Mongia,  H. C., 1991, “Three-Dimensional Analysis of Gas Turbine Combustors,” J. Propul. Power, 7, No. 3, pp. 603–611.
Mongia, H. C., 1998, “Aero-thermal Design and Analysis of Gas Turbine Combustion Systems: Current Status and Future Direction,” AIAA Paper 1998-3982.
Kumar, G. N., and Mongia, H. C., 2000, “Validation of Near-wall Turbulence Models for Film Cooling Applications in Combustors,” AIAA Paper 2000-0480.
Kumar, G. N., Duncan, B. S., and Mongia, H. C., 2000, “Results of a DOE on Film Cooling Effectiveness of a Modern Combustor With Machined Ring,” AIAA Paper 2000-3354, 36th AIAA/ASME/SAE/ ASEE Joint Propulsion Conf. and Exhibit, 16–19 July, 2000, Huntsville, Alabama.
Mongia, H. C., 2001, “Gas Turbine Combustor Liner Wall Temperature Calculation Methodology,” AIAA Paper 2001-3267, 36th AIAA/ASME/SAE/ ASEE Joint Propulsion Conference and Exhibit, 16–19 July, 2000, Huntsville, Alabama.
Crocker,  D. S., Nickolaus,  D., and Smith,  C. E., 1999, “CFD Modeling of a Gas Turbine Combustor From Compressor Exit to Turbine Inlet,” ASME J. Eng. Gas Turbines Power, 121, pp. 89–95.
Lefebvre, A. H., 1980, Gas Turbine Combustion, Taylor & Francis, London, Chap. 8: Heat Transfer.
Methodology—STAR-CD Version 3.15, Computational Dynamics Ltd., 2001.
Richardson, J. M., Howard, H. C., Jr., and Smith, R. W., 1953, “The Relation Between Sampling Tube Measurements and Concentration Fluctuations in a Turbulent Gas Jet,” 4th Symp. On Combustion, pp. 814–817.
Magnussen, B. F., and Hjertager, B. W., 1981, “On the Structure of Turbulence and a Generalized Eddy Dissipation Concept for Chemical Reaction in Turbulent Flow,” 19th AIAA Aerospace Meeting, St. Louis, MO.
Gordon, R., and Levy, Y., 2000, “Evaluation of Results of CFD Calculations Applied to Combustion Chambers,” Report No. 27645985-01, Technion-IIT Haifa, Israel, Sept. 2000.

Figures

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A 36 deg sector of the YT-175 combustion chamber
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The YT-175 combustor liner
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Cold flow velocity vector field along a longitudinal cross section
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Calculated results using a fine grid, MARS scheme and COMTIME model. (a) Velocity vector field along a longitudinal cross section. (b) Temperature field along a longitudinal cross section. (c) Temperature field at the combustor exit cross section. (d) Temperature field along the vaporizer cross section. (e) Velocity vector field along the vaporizer cross section. (f) CO concentration field at the combustor exit cross section.
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Comparison of the calculated and measured airflow through the combustor. (a) Velocity field along a longitudinal cross section. (b) Photo image of the flow.
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Calculated results for the fine grid, MARS scheme and COMTIME model. (a) Liner wall temperatures. (b) Liner hot gas heat transfer coefficients.
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Calculated results using a coarse grid, MARS scheme and COMTIME model. (a) Velocity vector field along a longitudinal cross section. (b) Temperature field along a longitudinal cross section. (c) Temperature field at the combustor exit cross section. (d) Temperature field along the vaporizer cross section.
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Liner wall temperatures calculated with a coarse grid, MARS scheme and COMTIME model
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Calculated results using a coarse grid, UW scheme and COMTIME model. (a) Velocity vector field along a longitudinal cross section. (b) Temperature field along a longitudinal cross section. (c) Temperature field at the combustor exit cross section. (d) Temperature field along the vaporizer cross section.
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Liner wall temperatures calculated with a coarse grid, UW scheme and COMTIME model
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Calculated results using a fine grid, MARS scheme and PPDF model. (a) Velocity vector field along a longitudinal cross section. (b) Temperature field along a longitudinal cross section. (c) Temperature field at the combustor exit cross section. (d) Temperature field along the vaporizer cross section. (e) Velocity vector field along the vaporizer cross section. (f) CO concentration field at the combustor exit cross section.
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Liner wall temperatures calculated with a fine grid, MARS scheme and PPDF model
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Comparison of the radial exit plane temperature profiles of the various case studies. (a) Circumferentially averaged temperature. (b) Maximum temperature.
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Alternative I configuration geometry along a longitudinal cross section
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Alternative II configuration geometry along a longitudinal cross section
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Calculated results of alternative I using a fine grid, MARS scheme and COMTIME model. (a) Velocity vector field along a longitudinal cross section. (b) Temperature field along a longitudinal cross section. (c) Temperature field at the combustor exit cross section.
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Liner wall temperatures of alternative I using a fine grid, MARS scheme and COMTIME model
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Calculated results of alternative II using a fine grid, MARS scheme and COMTIME model. (a) Velocity vector field along a longitudinal cross section. (b) Temperature field along a longitudinal cross section. (c) Temperature field at the combustor exit cross section.
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Line wall temperatures of alternative II using a fine grid, MARS scheme and COMTIME model
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Comparison of the radial exit plane temperature profiles of the original and modified configurations. (a) Circumferentially averaged temperature profiles. (b) Maximal temperature profiles.

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