Summary
I would like to request improved support for multi-block structured CGNS meshes generated by turbomachinery mesh generators such as AutoGrid
The practical use case is a compressor or turbine mesh where each blade row is composed of multiple structured blocks in CGNS
For SU2 turbomachinery simulations, a natural workflow would be to treat each blade row as one computational zone, while the internal block interfaces inside the same blade row should become internal mesh connectivity, not external boundary markers or separate SU2 zones
Current limitation
Based on the current documentation, SU2 supports multi-zone computations, but a single multi-zone mesh file currently works only with the native SU2 mesh format using NZONE= and IZONE=
The CGNS input support appears to be limited mainly to unstructured single-zone CGNS files
This makes it difficult to directly use standard turbomachinery meshes generated by AutoGrid or similar tools, because these meshes are usually exported as structured multi-block CGNS files
Why this matters
Many compressor and turbine grids are generated as multi-block structured meshes
A single blade row may contain many blocks, such as passage blocks, O/H/C topology blocks, tip-clearance blocks, hub/shroud blocks, and periodic-interface blocks
For SU2, these blocks should usually be merged or interpreted as one blade-row computational zone
At present, users have to rely on external conversion workflows, for example Pointwise, Gmsh, custom CGNS scripts, or conversion to a native SU2 mesh
This adds a fragile preprocessing step and makes SU2 harder to use for realistic turbomachinery cases
Expected behavior
SU2 should ideally support one of the following workflows
-
Read a structured multi-block CGNS file and correctly assemble connected blocks within the same blade row
-
Convert a structured multi-block CGNS file into a native SU2 mesh while preserving physical boundary markers
-
Allow users to specify how CGNS zones or blocks should be grouped into SU2 computational zones
-
Treat internal block interfaces inside the same blade-row group as internal connectivity
-
Preserve physical boundaries such as inlet, outlet, blade, hub, shroud, periodic boundaries, and mixing-plane interfaces
Actual behavior
At present, a multi-block structured CGNS mesh generated by AutoGrid cannot be used directly in the expected blade-row based way
The user must first convert or reconstruct the mesh externally before SU2 can run the case
This is especially inconvenient for multi-row compressor and turbine calculations
Example workflow that would be useful
AutoGrid structured multi-block CGNS mesh
Blade row 1:
block_001
block_002
block_003
...
Blade row 2:
block_101
block_102
block_103
...
Desired SU2 interpretation:
SU2 zone 0 = all blocks belonging to blade row 1
SU2 zone 1 = all blocks belonging to blade row 2
Interfaces inside each blade row = internal connectivity
Interfaces between blade rows = SU2 zone interfaces or mixing-plane interfaces
Possible implementation direction
A useful option could be a CGNS zone grouping mechanism, for example through CGNS FamilyName, zone names, or a user-provided grouping map
For example:
CGNS_BLOCK_GROUPING= FAMILY
CGNS_GROUP_TO_SU2_ZONE= YES
or a mapping file such as:
row_0: block_001, block_002, block_003
row_1: block_101, block_102, block_103
The grouped blocks would then be converted internally into SU2-style unstructured connectivity for each computational zone
Context
This issue is motivated by compressor meshes generated by AutoGrid
The mesh is multi-block structured and organized by blade row
The target solver workflow is SU2 turbomachinery simulation with blade-row level zones and mixing-plane or zone interfaces
Question
Is support for structured multi-block CGNS turbomachinery meshes planned
If not, would the SU2 team consider accepting an enhancement for CGNS multi-block import and conversion into native SU2 multizone format
Summary
I would like to request improved support for multi-block structured CGNS meshes generated by turbomachinery mesh generators such as AutoGrid
The practical use case is a compressor or turbine mesh where each blade row is composed of multiple structured blocks in CGNS
For SU2 turbomachinery simulations, a natural workflow would be to treat each blade row as one computational zone, while the internal block interfaces inside the same blade row should become internal mesh connectivity, not external boundary markers or separate SU2 zones
Current limitation
Based on the current documentation, SU2 supports multi-zone computations, but a single multi-zone mesh file currently works only with the native SU2 mesh format using
NZONE=andIZONE=The CGNS input support appears to be limited mainly to unstructured single-zone CGNS files
This makes it difficult to directly use standard turbomachinery meshes generated by AutoGrid or similar tools, because these meshes are usually exported as structured multi-block CGNS files
Why this matters
Many compressor and turbine grids are generated as multi-block structured meshes
A single blade row may contain many blocks, such as passage blocks, O/H/C topology blocks, tip-clearance blocks, hub/shroud blocks, and periodic-interface blocks
For SU2, these blocks should usually be merged or interpreted as one blade-row computational zone
At present, users have to rely on external conversion workflows, for example Pointwise, Gmsh, custom CGNS scripts, or conversion to a native SU2 mesh
This adds a fragile preprocessing step and makes SU2 harder to use for realistic turbomachinery cases
Expected behavior
SU2 should ideally support one of the following workflows
Read a structured multi-block CGNS file and correctly assemble connected blocks within the same blade row
Convert a structured multi-block CGNS file into a native SU2 mesh while preserving physical boundary markers
Allow users to specify how CGNS zones or blocks should be grouped into SU2 computational zones
Treat internal block interfaces inside the same blade-row group as internal connectivity
Preserve physical boundaries such as inlet, outlet, blade, hub, shroud, periodic boundaries, and mixing-plane interfaces
Actual behavior
At present, a multi-block structured CGNS mesh generated by AutoGrid cannot be used directly in the expected blade-row based way
The user must first convert or reconstruct the mesh externally before SU2 can run the case
This is especially inconvenient for multi-row compressor and turbine calculations
Example workflow that would be useful
AutoGrid structured multi-block CGNS mesh
Blade row 1:
block_001
block_002
block_003
...
Blade row 2:
block_101
block_102
block_103
...
Desired SU2 interpretation:
SU2 zone 0 = all blocks belonging to blade row 1
SU2 zone 1 = all blocks belonging to blade row 2
Interfaces inside each blade row = internal connectivity
Interfaces between blade rows = SU2 zone interfaces or mixing-plane interfaces
Possible implementation direction
A useful option could be a CGNS zone grouping mechanism, for example through CGNS FamilyName, zone names, or a user-provided grouping map
For example:
CGNS_BLOCK_GROUPING= FAMILY
CGNS_GROUP_TO_SU2_ZONE= YES
or a mapping file such as:
row_0: block_001, block_002, block_003
row_1: block_101, block_102, block_103
The grouped blocks would then be converted internally into SU2-style unstructured connectivity for each computational zone
Context
This issue is motivated by compressor meshes generated by AutoGrid
The mesh is multi-block structured and organized by blade row
The target solver workflow is SU2 turbomachinery simulation with blade-row level zones and mixing-plane or zone interfaces
Question
Is support for structured multi-block CGNS turbomachinery meshes planned
If not, would the SU2 team consider accepting an enhancement for CGNS multi-block import and conversion into native SU2 multizone format