Indian Journal of Science and Technology
Year: 2016, Volume: 9, Issue: 6, Pages: 1-6
Chandrakant R. Kini1 , Sai Sharan Yalamarty1 , Royston Marlon Mendonca1 , N. Yagnesh Sharma1 and B. Satish Shenoy2*
1Department of Mechanical and Manufacturing Engineering, Manipal Institute of Technology, Manipal University, India; [email protected], nys[email protected], [email protected], [email protected] 2Department of Aeronautical and Automobile Engineering, Manipal Institute of Technology, Manipal University, India; [email protected]
*Author for Correspondence
B. Satish Shenoy
Department of Aeronautical and Automobile Engineering, Manipal Institute of Technology, Manipal University, India; [email protected]
Gas turbines play a vital role in the today’s industrialized society, and as the demands for power increase, the power output and thermal efficiency of gas turbines must also increase. Modern high-speed aero-engines operate at elevated temperatures about 2000 K to achieve better cycle efficiencies. The internal cooling techniques of the gas turbine blade includes: jet impingement, rib turbulated cooling, and pin-fin cooling which have been developed to maintain the metal temperature of turbine blades within acceptable limits. Cooling passages having fins are incorporated into the trailing edge regions which are modelled and analysed to achieve maximum thermal performance in terms of cooling. It is seen that fins provide an augmented convective area for better heat dissipation. The shape and orientation of fins plays a major role in air flow patterns and greatly affects the heat dissipation rate.
Keywords: CHT Analysis, Fins, HP Stage Turbine, Trailing Edge Cooling
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