CHT analysis of trailing edge region cooling in HP stage turbine blade

Chandrakant R. Kini, Sai Sharan Yalamarty, Royston Marlon Mendonca, N. Yagnesh Sharma, B. Satish Shenoy

Research output: Contribution to journalArticlepeer-review

6 Citations (Scopus)

Abstract

Gas turbines play a vital role in the today's industrialized society, and as the demands for power increase, the power output and thermal efficiency of gas turbines must also increase. Modern high-speed aero-engines operate at elevated temperatures about 2000 K to achieve better cycle efficiencies. The internal cooling techniques of the gas turbine blade includes: Jet impingement, rib turbulated cooling, and pin-fin cooling which have been developed to maintain the metal temperature of turbine blades within acceptable limits. Cooling passages having fins are incorporated into the trailing edge regions which are modelled and analysed to achieve maximum thermal performance in terms of cooling. It is seen that fins provide an augmented convective area for better heat dissipation. The shape and orientation of fins plays a major role in air flow patterns and greatly affects the heat dissipation rate.

Original languageEnglish
JournalIndian Journal of Science and Technology
Volume9
Issue number6
DOIs
Publication statusPublished - 2016

All Science Journal Classification (ASJC) codes

  • General

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