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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

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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