(> NAX is currently under development for v1.0 - to be released soon !!! )
For further details/ issues / latest capabilities please directly contact :: email Sandeep Kumar : kumarsp@mail.uc.edu )
#--------------- Non-AXisymmetric 3D blade design system ---------------------------------------------------------#
NAX was first developed to design distortion tolerant propulsion systems for Boundary Layer Ingestion or Turbo-Electic propulsion configuarations as mentioned in NASA N+3 category.
To cite this code:
Kumar, Sandeep, Turner, Mark G., Siddappaji, Kiran, and Celestina, Mark. "Aerodynamic Design System for Non-Axisymmetric Boundary Layer Ingestion Fans." Proceedings of the ASME Turbo Expo 2018: Turbomachinery Technical Conference and Exposition. Volume 2C: Turbomachinery. Oslo, Norway. June 11–15, 2018. V02CT42A048. ASME. https://doi.org/10.1115/GT2018-77042
or see website : http://gtsl.ase.uc.edu/NAX/
Known Applications
- NAX has been already used in design of 1.5 stage transonic BLI thruster design ( as in NASA N+3 configuration).
- NAX is also being used for design of 1 stage Outlet Guide Vanes to reduce effect of couple effect on rotor.
#-------------------------------------------------------------------------------------#
**How to run **
-
Use the executables specific to your OS.
-
Make sure you have permissions on your machine. Else for Unix\Linux user: in "executables" directory -
chmod 777 .\tblade3 ( PRESS RETURN)
chmod 777 .\geomTurbo ( PRESS RETURN)
- Make any "design-case" directory your working directory and run wrapper script from here -
..\ .\ naxdesign.sh ( PRESS RETURN)
In case of any issue: Please check the files in "inputs" directory for correctness and "scripts\geomTurbo_v0.3.py" for "n" blade row case.
#--------------------------------------------------------------------------------------#
NAX provides a unique design capability for development of multi-row Axisymmetric and/or non-axisymmetric turbomachinery 3D blade design and development.
It uses harmonics content (Discrete Fourier Transforms) based design space to represent blade parameters in (R, THETA) space . Following blade parameters f(theta), can be used to create non-axisymmetry in 3D blade designs -
*1. Inlet /exit blade metal angles,
*2. Lean,
*3. Sweep,
*4. thickness,
*5. chord length *
All these blade parameters can exhibit non-axisymmetry in R , or (R,THETA ) direction for blade design. This non-axisymmetry can be assigned at used defined span location with magnitude, phase values for designing.
NAX is highly paramteric and completely automated in nature and can easily be integrated to Analysis(CFD) or/and Optimization process.
The package comes with complete documentation and system requires Python v3x and Shell ( Unix environmemt). Windows OS users can use Cygwin.
The definition of non-axisymmetry is shown here using NAX-input file
