Gas Turbine Blade internal Rib cooling
 

Hi all, I have chosen to do some research with regards to gas turbine blade cooling. In this research I would like to use porous material to enhance heat transfer in gas turbine blade internal channels. However, my professor says that I must validate my research methods by replicating past data and simulating it on ANSYS.

I have chosen J C Han's paper because he provides all the necessary information for me to properly replicate his data. He gives me uniform heat flux to the walls, all rib dimensions, channel dimensions and so on. I am quite new to this so I have some beginner questions. I have attached

1. the Geometry I wish to validate in ANSYS
2. The mesh for my geometry.

How should I apply the uniform heat flux? Once I go into setup, I believe ANSYS automatically detects a "WALL" boundary condition. What is this exactly? Should I just click on all the surfaces that are not ribbed and call them the wall where I apply my uniform heat flux?

The data he collects via thermocouples and converts them into normalized Nusselt data. My other questions is, should I take his data and convert it into Temperature for comparison? Or does ANSYS have a feature where it can show nusselt number distribution?

Thank you!