[Josh]

Hello all -

Problem:

I have searched up and down this forum and online for a tutorial on how to create an H-O-H-grid for a turbomachinery problem. I have completed most of the tutorials on the portal (2D pipe, 3D pipe...), but none of them seem to cover my specific problem. I noticed people mentioning a stator tutorial, which could be useful, but I could not find it. I did find the .zip files of ICEM PowerPoint lectures somebody posted. They were somewhat useful, but still didn't answer my problem. I will be importing the mesh into CFX. Here is the geometry:

[img=http://img101.imageshack.us/img101/7696/icemt106ageom.th.jpg]

The first square inlet region is the first H-grid section. I then want an O-grid around the airfoils (the top section is the pressure surface, the bottom is the suction surface), followed by a transition to another H-grid in the rectangular outlet.

Method:

I blocked the domain like this:

[img=http://img694.imageshack.us/img694/7884/icemblocking1.th.jpg]

With the associations shown:

[img=http://img706.imageshack.us/img706/5061/icemblocking2.th.jpg]

The thought process here is that I want the first and last blocks to be simple, structured H-grids. The airfoil block has an O-grid split (the blue square). The diagonal block after the airfoils will be a transition region between the O- and H-grids. I'd like the O-grid to be orthogonal to the airfoil, and refined for proper boundary layer capturing.

I know how to make the entire domain unstructured prisms. I know how to create a fully structured H-mesh with specified nodes. I don't know how to implement both in the same simulation.

Any help would be much appreciated, whether it's simple advice, tutorials, or (bonus) instructions.