... Transfer Augmentation Technologies for Internal Cooling of Turbine Components of Gas Turbine Engines ,” Int. J. Rotating Mach. , 2013 , pp. 1 – 32 . 10.1155/2013/275653 [2] Yeranee , K. , and Rao , Y. , 2021 , “ A Review of Recent Studies on Rotating Internal Cooling for Gas...

...Bai-Tao An; Jian-Jun Liu; Si-Jing Zhou Multirow film cooling is widely used in gas turbine airfoils cooling to cope with extremely high inlet temperature. The film cooling effectiveness of diffusion slot holes was measured in multirow arrays at a flat plate experimental facility using the pressure...

.... Furthermore, we proposed a method to evaluate a correction factor corresponding to the thermal resistance of the airfoil heat exchanger. Nusselt number supercritical carbon dioxide gas turbine airfoil heat exchanger intercooler recuperator Intercooled, recuperated aviation gas turbines (IR...

... speed was controlled and monitored by the servomotor driver. The diameter of the rod ( d ) was 5 mm, which considered the trailing edge thickness of a real gas turbine vane. The pitch of the rods ( P rod ) was 80 mm, which was the same as the pitch of the blades. The distance between the rods...

... gas turbine density ratio compound shaped hole axial shaped hole PSP (1) Overall, the compound angle provides wider film coverage and higher effectiveness level than the axial angle. (2) Film effectiveness on the suction side increases proportionally with density ratio...

... and boundary layer unsteadiness. 18 09 2011 04 03 2012 09 07 2012 09 07 2012 thin film gauges gas turbine convective heat transfer The thermal design, evaluation, and management of turbomachinery components require invariant descriptors of the heat transfer process...

... induced secondary flow on the heat transfer coefficient was not as significant as that for the smooth channel case. 24 01 2011 11 11 2011 30 04 2012 02 05 2012 References 1 Han , J. C. , Dutta , S. , and Ekkad , S. V. , 2000 , Gas Turbine Heat Transfer...

... factors increased with rotation number due to the increased Sherwood number ratios and decreased friction factor ratios. 30 08 2010 12 08 2011 27 10 2011 27 10 2011 channel flow gas turbines heat transfer mass transfer rotational flow swirling flow turbulence gas...

... transfer in the stagnation region. 12 10 2009 07 07 2010 13 08 2010 13 08 2010 blades cooling jets mass transfer rotational flow stagnation flow turbines impingement/effusion cooling gas turbine heat transfer Coriolis force rotation Recent increase...

..., the heat/mass transfer analogy factor is applied and shows a good agreement between heat transfer and mass transfer results on the endwall with the fillets from the leading edge to the trailing edge. 29 06 2007 08 05 2008 14 10 2008 blades boundary layers gas turbines heat...

...Jaeyong Ahn; M. T. Schobeiri; Je-Chin Han; Hee-Koo Moon Detailed film cooling effectiveness distributions are measured on the leading edge of a rotating gas turbine blade with two rows (pressure-side row and suction-side row from the stagnation line) of holes aligned to the radial axis using...