Indian Journal of Science and Technology

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Effect of Twisted Tape Inserts and Stacks on Internal Cooling of Gas Turbine Blades


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 transfer can be enhanced by using twisted tape inserts and stacks. In the present paper, we proposed cooling effect of a gas turbine blade can be improved by using suitable twisted tape inserts and stack configurations. A Comparative study between this type and the twisted tape without stack configurations was performed. Methods/Statistical Analysis: Simulations are carried out for different width ratios of twisted tape with and without using stack configurations. Computation results showed that by using twisted tape inserts of width ratio (W) = 0.3 with stack configurations, provides better cooling effect compared to the others. Findings: Without using the stack Configurations, blade temperature is decreased by 34% at the leading edge and 21.2% at the trailing edge for W = 0.3. By using stack configurations, the blade temperature is decreased by 50.7% at the leading edge and 48% at the trailing edge for W = 0.3. Application/Improvements: All these demonstrated that cooling effect of gas turbine blade especially at the trailing edge can be enhanced with suitable twisted tape and insert and stack configurations.

Keywords

Leading Edge, Numerical Analysis, Stacks, Trailing Edge, Turbine Blade Cooling, Twisted Tape Inserts.
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  • Effect of Twisted Tape Inserts and Stacks on Internal Cooling of Gas Turbine Blades

Abstract Views: 128  |  PDF Views: 0

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 transfer can be enhanced by using twisted tape inserts and stacks. In the present paper, we proposed cooling effect of a gas turbine blade can be improved by using suitable twisted tape inserts and stack configurations. A Comparative study between this type and the twisted tape without stack configurations was performed. Methods/Statistical Analysis: Simulations are carried out for different width ratios of twisted tape with and without using stack configurations. Computation results showed that by using twisted tape inserts of width ratio (W) = 0.3 with stack configurations, provides better cooling effect compared to the others. Findings: Without using the stack Configurations, blade temperature is decreased by 34% at the leading edge and 21.2% at the trailing edge for W = 0.3. By using stack configurations, the blade temperature is decreased by 50.7% at the leading edge and 48% at the trailing edge for W = 0.3. Application/Improvements: All these demonstrated that cooling effect of gas turbine blade especially at the trailing edge can be enhanced with suitable twisted tape and insert and stack configurations.

Keywords


Leading Edge, Numerical Analysis, Stacks, Trailing Edge, Turbine Blade Cooling, Twisted Tape Inserts.



DOI: https://doi.org/10.17485/ijst%2F2016%2Fv9i31%2F131204