Release:2018, Vol. 4. №4
About the authors:Igor N. Baybuzenko, Postgraduate Student, Department “Gas Turbine and Renewable Power Plants”, Bauman Moscow State Technical University; email@example.com
This article illustrates the design of modern cooling systems for heavy-duty gas turbines hot path parts. The authors show blade and vanes cooling require serpentine internal cooling channels, and that heat transfer enhancement employ periodic ribs at the walls. Transient liquid crystal (TLC) method is one of the advanced modern approaches for heat transfer measurements of gas turbine cooling features.
The authors describe the test rig and post-processing. They summarize the results of heat transfer and pressure tests for ribbed cooling channels for Reynolds number in the range of Re = 100,000...180,000, which fits the level of parameters of modern power gas turbines. Heat transfer data is based on the local distribution of heat transfer coefficient for midrib surfaces. That allows defining the optimal ribs configuration and more reliable thermal state calculation of turbine blade.
In addition, the authors highlight the results of numerical modeling of flow and heat transfer in ribbed channel, considering the flow features.