Numerical simulation of internal cooling effect of gas turbine blades using twisted tape inserts

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5 Citations (Scopus)

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.

Original languageEnglish
Article number95795
JournalIndian Journal of Science and Technology
Volume9
Issue number31
DOIs
Publication statusPublished - 01-01-2016

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Die casting inserts
Tapes
Turbomachine blades
Gas turbines
Cooling
Computer simulation
Heat transfer
Statistical methods
Computational fluid dynamics

All Science Journal Classification (ASJC) codes

  • General

Cite this

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title = "Numerical simulation of internal cooling effect of gas turbine blades using twisted tape inserts",
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.",
author = "Kini, {Chandrakant R.} and Harishkumar Kamat and {Satish Shenoy}, B.",
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AU - Kini, Chandrakant R.

AU - Kamat, Harishkumar

AU - Satish Shenoy, B.

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N2 - 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.

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