A Review of Cooling Studies on Gas Turbine Rotor Blades with Rotation

Shyy Woei Chang, Pey Shey Wu, Ting Yu Wan, Wei Ling Cai

研究成果: Review article同行評審

3 引文 斯高帕斯(Scopus)

摘要

Increases in power density and thermal efficiency of a highly efficient gas turbine engine motivate an ever-mounting turbine entry temperature. The combined metallurgical and cooling advancements ensure the structural integrity of a gas turbine rotor blade that spins at high rotor speeds in a gas stream with temperatures above the melting point of the blade material. The cooling performances promoted by a variety of heat transfer enhancement methods typical of the coolant channels of the leading edge, the mid-chord region, and the trailing edge of a gas turbine rotor blade are reviewed. The manifested rotational effects on the aerothermal performances of impinging jets and swirl chambers for leading-edge cooling, multi-pass ribbed, dimpled, and/or wavy channels over the mid-chord region, as well as pin fin and latticework narrow ducts in the trailing edge of a gas turbine rotor blade, are summarized and cross-examined. Research orientations for future cooling studies aimed at preventing the development of hot spots in a gas turbine rotor blade are recommended.

原文English
文章編號21
期刊Inventions
8
發行號1
DOIs
出版狀態Published - 2023 2月

All Science Journal Classification (ASJC) codes

  • 一般工程

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