Publication

Abstract : The work aims at analyzing the blade tip modification effects in a gas turbine flow. The high losses associated with turbine flows will drastically influence the performance parameters of gas turbines. A small amount of loss reduction will bring about greater efficiency and higher cost reduction in gas turbine industries. In the present work, tip modifications in the form of plane tip, double side squealer tip and pressure side squealer tip were numerically analyzed. The analysis was done using the commercial software ANSYS 14. Three tip clearance cases was analysed and compared in the present study. The results showed that tip modifications reduced the aerodynamic losses considerably. The modified blade geometries can be considered as a potential candidate in gas turbine industry which can bring about greater loss reduction in blade tip areas.