Abstract
AbstractGas turbine cycles are extensively used in view of their capability of offering high specific work output with high thermal efficiency compared to steam turbine cycles. Studies are being carried out worldwide to further improve the gas turbine cycle performance. Among different options for improving cycle performance, the use of high turbine inlet temperature (TIT) along with efficient means and methods of turbine blade cooling is an attractive option. Studies show that transpiration cooling technique uses the coolant more effectively than the film and convection cooling techniques.The present study investigates the effects of varying coolant hole diameter, hole pitch/diameter ratio and coolant injection angles on the transpiration cooled (full coverage film cooled) gas turbine cycle performance. The results have been taken for a TIT of 1700 K and a cycle pressure ratio of 23, as used in the advanced ‘H’ class gas turbines. It is found that the coolant requirement increases with the increasing coo...
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