IMPROVEMENT OF THE COOLING PERFORMANCE OF GAS TURBINE COMBUSTOR COOLING TECHNIQUES

Date

2026-9-23

Author

Gülenç, Gamze

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This thesis presents the development, validation, and application of numerical methodology to investigate the cooling performance of gas turbine combustor cooling techniques under non-reacting conditions. To isolate the effects of key cooling parameters from the complex swirling and reacting flow environment of practical combustors and enable a systematic parametric assessment, the combustor liner was represented by a simplified flat-plate configuration. A three-dimensional conjugate heat transfer (CHT) framework was developed to predict coolant-mainstream interaction and cooling effectiveness distributions in effusion-cooled liners. The methodology was validated against experimental data from the literature for both pure effusion and combined impingement-effusion cooling configurations. The effects of hole orientation, inclination angle, and blowing ratio were systematically investigated by comparing forward and backward injection configurations. Multi-row CHT simulations revealed a strong dependence of backward injection behavior on inclination angle. For 160° backward holes, kidney vortices progressively weakened downstream, whereas they persisted for the 120° configuration. Backward injection also generated horizontal recirculation zones near the hole exits, producing localized low-temperature regions. Blowing ratio significantly affected cooling effectiveness, vorticity magnitude, and turbulent kinetic energy. The effects of key thermal and geometric parameters, including Biot number, wall thermal conductivity, wall thickness, and mainstream heat transfer coefficient, were also evaluated. In addition, combined cooling configurations were assessed, with slot-effusion cooling improving cooling effectiveness for both forward and backward injection. Overall, the findings clarify the relationships among injection configuration, vortex behavior, thermal parameters, and cooling performance, providing guidance for advanced combustor liner cooling design.

Subject Keywords

Gas Turbine, Effusion Cooling, Combustion Chamber, Conjugate Heat Transfer

URI

https://hdl.handle.net/11511/120953

Collections

Graduate School of Natural and Applied Sciences, Thesis