Leading edge of the gas turbine blades is subjected to highest temperature. Jet impingement cooling is an efficient technique for leading edge blade cooling. In this present study, a single baseline cylindrical hole and the proposed converging conical hole is numerically investigated for convective heat transfer using CFD code, STAR CCM+. The converging angle of the conical hole is 20°and the ratio of diameter is equal to two. The hole diameter is 2.15 cm and the study is carried out at

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... number ranging from 11000 to 50000 for a jet impinging length of R/2. The target surface is maintained at constant heat flux of 10000 W/m 2 .Steady-state simulations are performed using Reynolds Averaged Navier Stokes equation along with kω-SST turbulence model for closure. Based on the Nusselt number and temperature distribution, converging conical hole is observed to give a better heat transfer thereby cooling the blades effectively. Around 186 % increase in Nu and 13% decrease in surface temperature of the concave surface is observed at jet impingement point for Re = 23000.