Indian Journal of Science and Technology
DOI: 10.17485/ijst/2016/v9i31/95795
Year: 2016, Volume: 9, Issue: 31, Pages: 1-6
Original Article
Chandrakant R. Kini1 , Harishkumar Kamat1 and B . Satish Shenoy2*
1 Department of Mechanical and Manufacturing Engineering, [email protected]
[email protected]
2 Department of Aeronautical and Automobile Engineering, Manipal Institute of Technology, Manipal University, [email protected]
*Author for correspondence
Satish Shenoy
Department of Aeronautical and Automobile Engineering, Manipal Institute of Technology, Manipal University,
Email:[email protected]
Objectives: In gas turbine blades, heat transmission can be improved by using twisted tape inserts. In the present paper, cooling effect of a gas turbine blade can be improved by using suitable twisted tape configurations. Methods/Statistical Analysis: It was found from validation test that the twisted tape is a favourable technique for heat transfer augmentation. It was also found that heat transfer can be enhanced in the cases with suitable width ratio of twisted tapes. CFD Results show that the results are satisfactory when compared with the reference journal paper. Simulations are carried out for different width ratios of twisted tape inserts. Findings: Computation results showed that by employing twisted tape inserts of width ratio (W) = 0.3 provides better cooling effect compared to the others. The blade temperature is decreased by 34% at the leading edge. Application/Improvements: All these established that influence of cooling over gas turbine blade particularly at the leading edge can be enhanced with suitable twisted tape insert configurations.
Keywords: Leading Edge, Numerical Analysis, Turbine Blade Cooling, Twisted Tape Insert
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