Abstract
The maximum temperature at the gas turbine inlet gets restricted due to metallurgical constraints, which can be increased using blade cooling. Among different techniques for cooling blades in the gas turbine, the transpiration cooling of blades permits quite a high temperature at the turbine inlet. The objective of this study is to analyse the sensitivity of transpiration cooled gas turbine cycle performance for cooling parameterssuch as allowable blade material temperature, film cooling effectiveness, and internal cooling efficiency, so that the most important cooling parameters may be focused upon for the improvement of gas turbine cycle performance. In this study, it is found that the cycle efficiency is more sensitive to allowable blade material temperature followed by film cooling effectiveness and to internal cooling efficiency only a little bit. This study shows that with the use of cooling, for an increase in allowable blade temperature by 50 K, the gas turbine cycle efficiency increases by 0.15% . Also, the increase in film cooling effectiveness from 0.4 to 0.5 increases the cycle efficiency by 0.13% . Furthermore, with an increase in cooling efficiency from 0.7 to –0.8 the cycle efficiency increases by 0.03% only.
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