Abstract
In recent years improved gas turbine performance throughdevelopments in high temperature materials and blade cooling methodshas made a positive impact on the combined cycle performance.Transpiration cooling technique has emerged as the most promisingtechnique to improve the gas turbine cycle performance by allowinghigher turbine inlet temperatures. This paper concentrates on improvingthe combined cycle performance by allowing higher turbine inlettemperatures (TIT) using transpiration cooling of gas turbine blades. Afour-stage advanced gas turbine coupled with the dual pressure steambottoming cycle is considered for the performance of combined cycle.Realistic input parameters used in current industrial practice havebeen considered for this study. The effects of variation of TIT on theperformances of topping, bottoming and combined cycle are presentedand discussed. For the combined cycle with transpiration cooled gasturbine an increase in TIT from 1600 K to 1800 K exhibits the combinedcycle efficiency increase by 2.37 percent and the combined specific workincreases by 185.42 kJ/kg. The results indicate that at a TIT of 1800 K theachievable efficiency of combined cycle with transpiration cooled gasturbine is 59.97 percent.
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