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

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