Thermodynamic and Sensitivity Analysis of Internal Convection Blade Cooled Gas Turbine Cycle: Effect of Radiative Heat Transfer on Blade Coolant Requirements
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Abstract
This article presents a thermodynamic investigation of a gas turbine cycle using internally convection-cooled turbine
blades. Three existing blade cooling models and one proposed model were analysed to predict blade coolant mass fraction when compressor-bled air is used for cooling. The proposed model uniquely incorporates radiative heat transfer along with internal convection, leading to the highest coolant requirement among all models. Comparative analysis showed close agreement between the models. Thermodynamic evaluation of the proposed cooled gas turbine cycle indicated a maximum specific-work of 341.1 kJ/kg at a pressure ratio of 20 and turbine inlet temperature of 1550 K. Maximum cycle efficiency of about 40.19% occurred at a pressure ratio of 28 and turbine inlet temperature of 1400 K. Exergy analysis identified the combustor as the major source of exergy destruction. Sensitivity analysis revealed that blade material technology, represented by maximum permissible blade temperature, has the greatest influence on gas turbine performance.