... and Technology Innovation Commission (Grant No. JCYJ20170306155153048). National 111 Project, Chinese Ministry of Education (Grant No. B18041). 25 05 2022 09 09 2022 09 12 2022 multi-objective optimization gas turbine cooling surrogate model nondominated sorting genetic...

...). • National Science and Technology Major Project (Grant No. 2017-III-0009-0035). e-mail:  yurao@sjtu.edu.cn e-mail:  guozhongqiu@sjtu.edu.cn e-mail:  wangdeqiang@alumni.sjtu.edu.cn gas turbine cooling multipass serpentine channel W-shaped ribs heat transfer Pressure loss...

... of the distribution of the velocity and turbulence level in the flow, which revealed the underlying mechanisms for the pressure loss and heat transfer characteristics in the pin fin-dimple channels of different configurations. gas turbine cooling pin fin dimple flow heat transfer enhancement Short...

... of the airfoil. 30 04 2010 09 08 2011 11 04 2012 13 04 2012 turbine disk turbine blade gas turbine cooling rotating heat pipe In order to increase thermodynamic efficiency, improve the thrust/weight ratio, or reduce the specific air consumption of a gas turbine...

... internal cooling gas turbine cooling heat transfer enhancement Rib turbulated internal cooling passages are used in gas turbine blades to remove heat, letting the engine operate at a higher firing temperature—and therefore at a higher efficiency. Aviation gas turbine blade designers use...

... 30 12 2009 30 12 2009 channel flow convection cooling engines gas turbines tip wall pin fins enhancement computation gas turbine cooling It is a well-known fact that one way to increase the power output and thermodynamic efficiency of a gas turbine engine...

... in the synthetic fuels for next generation turbines, the increased flame temperature and flame speed from those of natural gas combustion will make gas turbine cooling more difficult and more important. Therefore, development of new cooling techniques is essential for surpassing current limits. One potential new...