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COMPUTATIONAL STUDY OF LEADING EDGE JET IMPINGEMENT COOLING WITH A CONICAL CONVERGING HOLE FOR BLADE COOLING
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 atfatcat:6doojeflxfe7fbqkxmoq4i6evy