A 3D Analysis Code for Turbomachinery CFD

  • The TRAF code is one of the most widely employed turbomachinery specific CFD solvers.
  • Full intergration with TURBOdesign1 software.
  • Suitable for incompressible and compressible flows, single blade row and multiple stages (up to 3)
  • Automatic mesh generation and quick case setup.
  • Three different turbulence models are available including Baldwin-Lomax model, One Equation Spalart-Allmaras model and Two Equation k-omege Wilcox’s model.
  • Parallel and automatic computation of characteristic curves (multiple cases) in batch mode.
  • Detailed visualization and powerful investigation of the flow field in the post-processing window

TURBOdesign CFD Pre-Processor

The process of setting up a case in TURBOdesign CFD consists of 5 main steps:

Step 1 – Input the blade geometry

TURBOdesign1 geometry (.geo) file can be directly imported into TURBOdesign CFD. The blade geometry can be visualized in 2D and 3D.

Step 2 – Grid generation

Automatic and robust body fitted structured mesh generation function allows users to control extension to up/downstream boundaries, grid dimensions, grid flaring and hub/shroud clearance. Automatic elliptic smoothing can also be applied to provide high quality mesh for highly staggered geometries.

Fig. 1 Grid Generation Window

Step 3 – Specification

The Specification window allows users to select turbomachine type and define flow compressibility, flow properties, turbulence model and rotational speed of blade rows.

Step 4 – Boundary conditions

The Boundary conditions window allows users to define turbulence parameters, wall conditions, inlet and outlet boundary conditions with constant values or a distribution from input files.

Step 5 – Convergence & Advanced settings

Number of iterations and initialization of solver can be used to control the solving process. Advanced parameters are also available to tune the solver convergence.

TURBOdesign CFD Post-Processor

A detailed performance summary file which contains the most important flow information including pressure, temperature, density, Mach number, efficiency/head and broadband noise (for fans) is generated automatically at the end of TURBOdesign CFD calculation.

The post-processor allows easy visualization of turbomachinery flow field in 3D and 2D views on meridional, blade to blade and pitchwise planes.

Fig. 2 Pressure contour and line plot on 3D and 2D blade to blade view

Contours and vector plots are available for all 2D views. Blade surface data can also be plotted using line plot.

Fig. 3 Velocity vector plot

Related content

  • Chorin, A. J., 1967, “A Numerical Method for Solving Incompressible Viscous Flow Problems”. J. Comput. Phys., 2, pp. 12–26.
  • Baldwin, B. S. and Lomax, H., 1978, “Thin Layer Approximation and Algebraic Model for Separated Turbulent Flows”. AIAA paper 78–257, 16th Aerospace Sciences Meeting, January 16–18, Huntsville, AL, USA.
  • Spalart, P. R. and Allmaras, S. R., 1994, “A One–equation Turbulence Model for Aerodynamic Flows”. La Recherche Aérospatiale, 1, pp. 5–21.
  • Arnone, A., 1994, “Viscous Analysis of Three–Dimensional Rotor Flow Using a Multigrid Method”. ASME Journal of Turbomachinery, 116 (3), pp. 435–445.
  • Durbin, P. A., 1996, “On the k–ε Stagnation Point Anomaly”. International Journal of Heat and Fluid Flow, 17, pp. 89–90.
  • Wilcox, D. C., 1998, Turbulence Modeling for CFD, 2nd ed., DCW Industries Inc., La Cañada, CA, USA, ISBN 1-928729-10-X.
Green (TURBODesign CFD)

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