RT Journal Article ID 7fe6aca4092bd9dc A1 Huh, Michael A1 Han, Je-Chin T1 Recent Studies in Turbine Blade Internal Cooling JF Heat Transfer Research JO HTR YR 2010 FD 2011-02-11 VO 41 IS 8 SP 803 OP 828 K1 gas turbines K1 blade cooling K1 totating effect AB Gas turbines are used extensively for aircraft propulsion, land-based power generation, and industrial applications. The turbine inlet temperatures are far above the permissible metal temperatures. Therefore, there is a need to cool the blades for safe operation. Modern developments in turbine cooling technology play a critical role in increasing the thermal efficiency and power output of advanced gas turbine designs. Turbine blades and vanes are cooled internally and externally. This paper focuses on turbine blade internal cooling. Internal cooling is typically achieved by passing the coolant through several rib-enhanced serpentine passages inside the blades. Impinging jets and pin fins are also used for internal cooling. In the past 10 years there has been considerable progress in turbine blade internal cooling research and this paper is limited to reviewing a few selected publications to reflect recent developments in this area. In particular, this paper focuses on the effects of channel inlet geometry, sharp 180° turning, and channel cross-section aspect ratio on the coolant passages heat transfer at high rotation number conditions. Rotation effects on the blade leading-edge triangular-shaped channel and trailing-edge wedge-shaped channel with coolant ejection are included. PB Begell House LK https://www.dl.begellhouse.com/journals/46784ef93dddff27,734f68c856e85bfc,7fe6aca4092bd9dc.html