Indian Journal of Science and Technology
DOI: 10.17485/ijst/2016/v9i31/95978
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, Manipal Institute of Technology, Manipal University, [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
Email:[email protected]
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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