Indian Journal of Science and Technology

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Numerical Simulation of Internal Cooling Effect of Gas Turbine Blades using Twisted Tape Inserts


Affiliations
1 Department of Mechanical and Manufacturing Engineering, Manipal Institute of Technology, Manipal University, Manipal – 576104, Karnataka, India
2 Department of Aeronautical and Automobile Engineering, Manipal Institute of Technology, Manipal University, Manipal – 576104, Karnataka, India
 

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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  • Numerical Simulation of Internal Cooling Effect of Gas Turbine Blades using Twisted Tape Inserts

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Authors

Chandrakant R. Kini
Department of Mechanical and Manufacturing Engineering, Manipal Institute of Technology, Manipal University, Manipal – 576104, Karnataka, India
Harishkumar Kamat
Department of Mechanical and Manufacturing Engineering, Manipal Institute of Technology, Manipal University, Manipal – 576104, Karnataka, India
B. Satish Shenoy
Department of Aeronautical and Automobile Engineering, Manipal Institute of Technology, Manipal University, Manipal – 576104, Karnataka, India

Abstract


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.



DOI: https://doi.org/10.17485/ijst%2F2016%2Fv9i31%2F130970