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.
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