Turbine blade thermal analysis
 

Hello

I have a simulation for turbine blade surface temperature analysis. The blade has a complex internal cooling. Available parts consist of vane geometry and muscle and domain geometry to determine the surface of the hot gas hitting the vane.
For simulation, I first subtracted the complex geometry of the cooler from the vane with the Boolean tool, and then the vane from the main domain, but there was a problem in meshing.
What should I do to make the geometry so that meshing does not become a problem?
In the attachment, I uploaded the blade and cooling geometry